NASA Contractor Report 198472
Heat Transfer Experiments in the InternalCooling Passages of a Cooled RadialTurbine Rotor
B.V. Johnson and J.H. Wagner
United Technologies Research Center
East HarO_ord, Connecticut
May 1996
Prepared forLewis Research Center
Under Contract NAS3-25952
f
National Aeronautics and
Space Administration
https://ntrs.nasa.gov/search.jsp?R=19960035825 2020-06-23T05:51:00+00:00Z
FOREWORD
This report covers work performed under NASA Contract NAS-25952 to investigate heat
transfer characteristics of rotating coolant passages of a cooled radial turbine rotor. The NASA Program
Manager is Kestutis Civinskas, NASA Lewis Research Center. Seyf Tanrikut served as the Technical
Program Manager at Pratt & Whitney. Acknowledgments are given to S. Orr, J. Nycz, and the assistance
of colleagues at Pratt & Whitney and UTRC for their contributions to the program.
iii
HEAT TRANSFER EXPERIMENTS
IN THE INTERNAL COOLING PASSAGES
OF A COOLED RADIAL TURBINE ROTOR
TABLE OF CONTENTS
3.0
4.0
5.0
6.0
7.0
8.0
9.0
Summary 1
Introduction 2
2.1 Background 2
2.2 Objectives 3
Description of Apparatus and Experiment3.1 Heat Transfer Model
3.2 Model Instrumentation
3.3 Rotating Heat Transfer Facility
3.4 Experimental Procedures
Experimental Parameters and Test Matrix4. l Flow Parameters
4.2 Geometric Parameters
4.3 Test Conditions
4.4 Outline for Presentation of Results
Heat Transfer Results from Thermocouples5.1 Data and Results for Medium Coolant Flow Rate
5.2 Effects of Rotation on Local Heat Transfer
5.3 Summary of Results from Thermocouple Measurements
Heat Transfer Results from Liquid Crystals
6.1 Results for Stationary Tests
6.2 Results for Rotating Tests
Comparison with Previous AnalysisReferences
Appendix
9.1 Nomenclature
6
6
7
11
16
27
27
28
28
31
32
32
47
58
59
59
64
73
74
79
80
9.2
9.3
9.4
Tablesof Flow Conditions for Full Scale NASA
Radial Turbine and 1.15 Scale Model Coolant Passage
Sample Data Table for Stationary Test Condition and
Medium Flowrate (Test # 6.2, TC 2)
Adjusted Thermocouple Results
ea_ggg
81
93
97
vi
LIST OF TABLES
Table
Table 3-1
Table 4-1Locations of Wall Thermocouples in ModelFlow Conditions for Transient Heat Transfer Tests
14
29
Figure 2-1
Figure 3-1
Figure 3-2
Figure 3-3
Figure 3-4
Figure 3-5
Figure 3-6
Figure 3-7
Figure 3-8
Figure 3-9
Figure 3-10
Figure 3-11
Figure 3-12
Figure 4-1
Figure 5-1
Figure 5-2
LIST OF FIGURES
Sketch of Internal Coolant Passage for NASA LeRC
Cooled High Temperature Radial Turbine Program 5
Internal Passages of NASA LeRC Cooled RadialTurbine Rotor 8
Nomenclature for Internal Passages of NASA LeRCCooled Turbine Rotor 9
Photograph of Leading and Trailing Surfaces
of Coolant Passage Before Assembly 10
Thermocouple Instrumentation for Internal Passagesof NASA LeRC Cooled Turbine Rotor 13
Photograph of Model Mounted in Rotating
Heat Transfer Facility (with cover removed) 15
Schematic of Rotating Heat Transfer Facility 15
Optics Arrangement for Rotating Heat Transfer
Measurements With Liquid Crystals 20
Optical Test Section With Previous Four Pass ModelInstalled 20
Frame of Video Recording Before Startof Transient Heat Transfer Test 21
Frame of Video Recording During TransientHeat Transfer Test 22
Processed Frame of Video Data From Transient
Heat Transfer Test 23
Uncertainty Analysis Results 26
Comparison of Test Matrix With NASA LeRC
Full Scale Operating Conditions 30
Thermocouple Data for Liquid Crystal Test on Leading
Surface with f_ = 0 RPM 33
Results From Thermocouple Data for Liquid Crystal Test
on Leading Surface with I'_ = 0 RIM 34
vii
Figure
Figure
Figure
Figure
Figure
Figure
Figure
Figure
Figure
Figure
Figure
Figure
Figure
Figure
Figure
Figure
Figure
Figure
Figure
Figure
Figure
Figure
Figure
5-3
5-4
5-5
5-6
5-7
5-8
5-9
5-10
5-11
5-12
5-13
5-14
5-15
5-16
5-17
5-18
5-19
6-1
6-2
6-3
6-4
6-5
6-6
Thermocouple Data for Liquid Crystal Test on TrailingSurface with _ = 0 RPM
Results From Thermocouple Data for Liquid Crystal Test
on Trailing Surface With _ = 0 RPM
Thermocouple Data for Liquid Crystal Test on Leading
Surface with _ = 450 RPM
Results From Thermocouple Data for Liquid Crystal Test
on Leading Surface with _ = 450 RPM
Thermocouple Data for Liquid Crystal Test on Trailing
Surface with f2 = 450 RPM
Results From Thermocouple Data for Liquid Crystal Test
on Trailing Surface With f2 = 450 RPM
Thermocouple Data for Liquid Crystal Test on LeadingSurface with f2 = 750 RPM
Results From Thermocouple Data for Liquid Crystal Test
on Leading Surface with f2 = 750 RPM
Thermocouple Data for Liquid Crystal Test on TrailingSurface with _ = 750 RPM
Results From Thermocouple Data for Liquid Crystal Test
on Trailing Surface With D = 750 RPMDimensional and Dimensionless Heat Transfer Results
From Thermocouple Data for Region 1
Dimensional Heat Transfer Results From Thermocouple
Data for Region 2 and Re = 13,000
Dimensionless Heat Transfer Results From Thermocouple
Data for Region 2
Dimensional Heat Transfer Results From Thermocouple
Data for Region 3 and Re = 13,000
Dimensionless Heat Transfer Results From Thermocouple
Data for Region 3
Dimensional Heat Transfer Results From Thermocouple
Data for Region 4 and Re = 13,000
Dimensionless Heat Transfer Results From Thermocouple
Data for Region 4
Video Records of Liquid Crystal Isotherms for Test 8.1
Video Records of Liquid Crystal Isotherms for Test 6.2
Nomograph for Evaluating Liquid Crystal Data for
Re = 13,000 and _ = 0 RPM
Heat Transfer Coefficients From Liquid Crystal Isotherms
for Re = 13,000 and D = 0 RPM
Video Records of Liquid Crystal Isotherms for Test 16.3
Video Records of Liquid Crystal Isotherms for Test 10.2
35
36
39
40
41
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46
48
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66
viii
Figure 6-7
Figure 6-8
Figure 6-9
Figure 6-10
Figure 6-11
Figure 6-12
Figure 9.4-1
Figure 9.4-2
Figure 9.4-3
Figure 9.4-4
Figure 9.4-5
Figure 9.4-6
Figure 9.4-7
Figure 9.4-8
Figure 9.4-9
Figure 9.4-10
Figure 9.4-11
Figure 9.4-12
Nomograph for Evaluating Liquid Crystal Data for
Re = 13,000 and f2 = 450 RPM 67
Heat Transfer Coefficients From Liquid Crystal Isotherms
for Re = 13,000 and f_ = 450 RIM 68
Video Records of Liquid Crystal Isotherms for Test 16.4 69
Video Records of Liquid Crystal Isotherms for Test 12.2 70
Nomograph for Evaluating Liquid Crystal Data for
Re = 13,000 and _ = 750 RPM 71
Heat Transfer Coefficients From Liquid Crystal Isotherms
for Re = 13,000 and f2 = 750 RPM 72
Thermocouple Data for Liquid Crystal Test on Leading
Surface with f2 = 0 RPM 98
Results From Thermocouple Data for Liquid Crystal Test
on Leading Surface with f2 = 0 RIM 99
Thermocouple Data for Liquid Crystal Test on TrailingSurface with f2 = 0 RPM 100
Results From Thermocouple Data for Liquid Crystal Test
on Trailing Surface With f2 = 0 RPM 101
Thermocouple Data for Liquid Crystal Test on LeadingSurface with _ = 450 RPM 102
Results From Thermocouple Data for Liquid Crystal Test
on Leading Surface with f_ = 450 RIM 103
Thermocouple Data for Liquid Crystal Test on Trailing
Surface with D = 450 RPM 104
Results From Thermocouple Data for Liquid Crystal Test
on Trailing Surface With f2 = 450 RPM 105
Thermocouple Data for Liquid Crystal Test on LeadingSurface with f2 = 750 RPM 106
Results From Thermocouple Data for Liquid Crystal Test
on Leading Surface with f2 = 750 RPM 107
Thermocouple Data for Liquid Crystal Test on TrailingSurface with f2 = 750 RPM 108
Results From Thermocouple Data for Liquid Crystal Test
on Trailing Surface With f_ = 750 RPM 109
ix
1.0 SUMMARY
An experimental study was conducted (1) to experimentally measure, assess and analyze the heat
transfer within the internal cooling configuration of a radial turbine rotor blade and (2) to obtairt heat
transfer data to evaluate and improve CFD procedures and turbulent transport models of internal coolant
flows. A 1.15 times scale model of the coolant passages within the NASA LeRC High Temperature
Radial Turbine was designed, fabricated of Lucite and instrumented for transient heat transfer tests using
thin film surface thermocouples and liquid crystals to indicate temperatures. Transient heat transfer tests
were conducted for Reynolds numbers of one-fourth, one-half, and equal to the operating Reynolds
number for the NASA Turbine. Tests were conducted for stationary and rotating conditions with
rotation numbers in the range occurring in the NASA Turbine.
Results from the experiments showed the heat transfer characteristics within the coolant passage
were affected by rotation. In general, the heat transfer increased and decreased on the sides of the
straight radial passages with rotation as previously reported from NASA-HOST-sponsored experiments.
The heat transfer in the tri-passage axial flow region adjacent to the blade exit was relatively unaffected
by rotation. However, the heat transfer on one surface, in the transitional region between the radial
inflow passage and axial, constant radius passages, decreased to approximately 20 percent of the values
without rotation. Comparisons with previous 3-D numerical studies indicated regions where the heat
transfer characteristics agreed and disagreed with the present experiment.
2.0 INTRODUCTION
NASA Lewis Research Center (LeRC), the US Army and US gas turbine manufacturers have
been developing light weight, radial gas turbines for over 20 years. NASA LeRC and the US ,Army
Aviation Systems Command, in conjunction with gas turbine contractors, have a Cooled High-
Temperature Radial Turbine Program with a cooled turbine designed and manufactured by the Allison
Gas Turbine Division (Snyder, 1992), an analytical and experimental program at the LeRC, and analytical
efforts at ADAPCO and Carnegie Mellon University. The present study supports the NASA LeRC
program by experimentally determining the heat transfer characteristics in the coolant passages of a
model similar to the LeRC rotor (Snyder, 1992).
2.1 Background
Axial Flow Turbines - Heat transfer in rotating radial internal coolant passages, typical of turbine
airfoils of large gas turbine aircraft engines, has been investigated experimentally and analytically for the
past ten to fifteen years. The experimental studies have been sponsored by national and private
laboratories (e.g. USA/NASA, USSR, UK/RAE, France, Germany/DLR, Japan, Taiwan, USA/DOE, and
USA/EPRI) and the large gas turbine manufacturers (e.g. PW, GE, and RR). The pioneering studies
were reported by Morris, 1981.. More recent studies up to 1991, with a wider range of flow and
geometric parameters, are reported in the authors' previous papers by Wagner et al., 1991, and Johnson
et al., 1992, and in NASA contractors reports, Hajek et al., 1991, and Johnson et al., 1993. Other recent
references include Han et al., 1992, E1-Husayni et al., 1992, and Mochizuki et al., 1992, and contain most
references from the studies sponsored by GE, EPRI, and RAE. The results from these studies are
bringing an understanding to the turbine blade durability designer of the effects of many parameters on
heat transfer in rotating radial coolant passages including such flow parameters as Reynolds number,
rotation number, wall-to-bulk density ratio, and buoyancy in addition to such geometric parameters as
trip geometry, passage aspect ratio, and flow direction. The understanding developed by the authors in
their previous studies of heat transfer in rotating internal coolant passages will be used to interpret the
results of the present study.
Radial Flow Turbines - Internal cooling of radial turbines is more complex than that for axial
turbines because of the large surface area of the coolant passages, the large variations in coolant passage
cross-sectional area from inlet to exit, and the changes in flow direction, axially and azimuthally, as the
blade contour varies. A summary of work to 1992 (Roelke, 1992) describes the previous cooled radial
turbine efforts at Garrett (Vershure et al., 1980), Pratt and Whitney (Calvert et al., 1971), and Solar
2
(Hammeret al., 1986). The previous heat transfer studies have been primarily analytic or have measured
the overall performance of the turbine.
The analytical heat transfers studies to date have been conducted with one and three dimensional
analyses. The one dimensional analyses have used heat transfer relationships and a flow network analysis
for multi-path flows. The three dimensional analyses have used 3-D Navier Stokes codes and have been
focused on the configuration used in the NASA LeRC Cooled High Temperature Radial Turbine
Program. The 3-D studies include those by Ippolito, 1991, at ADAPCO using the STAR-CD code,
Dawes, 1992, using a code with an unstructured grid, Steinthorsson et al., 1993, and Stephens et al.,
1993. Results from the analytical studies vary, however, all studies show regions with low convective
velocities which can be expected to produce low heat transfer rates and low heat transfer coefficients.
2.2 Objectives
The principal objectives of this project are (1) to experimentally measure, assess, and analyze the
heat transfer within the internal cooling passage of a radial turbine rotor blade and (2) to obtain heat
transfer data to evaluate and improve CFD procedures and turbulent transport models in internal coolant
flows.
The model used for the experiments was a 1.15 times scale of the coolant passages in the NASA
LeRC Cooled Radial Turbine(Figure 2-1). The model was constructed from a Lucite block and was
instrumented for transient heat transfer experiments with surface and air temperature thermocouples and
liquid crystal paints. Based on (1) UTC previous experience (e.g. Hajek et al., 1991, and Johnson et al.,
1993) in the NASA HOST and in corporate sponsored research programs on heat transfer in rotating
models for axial flow turbines and (2) the flowrates and operating conditions of the LeRC turbine, it is
•expected that the rotation number (Ro = c0d/V) and the coolant passage Reynolds numbers (Re = 9Vd/_t)
will be the principal parameters affecting heat transfer in the model. In addition, because of the
reasonably high Reynolds numbers, it is expected that the heat transfer will scale approximately as Re 0.8
The test matrix was developed using these assumptions.
The transient heat transfer data, which was obtained in this program and which will be used to
evaluate CFD codes, is difficult to present in report form because of its three-dimensional, time
dependent nature. In addition, the data was obtained on a model at flow conditions that were not
identical to those used to predict the performance of the NASA rotor. Therefore, an approximate heat
transfer coefficient was deduced from the results based on the time dependent heat flux from the wail, the
time dependent inlet temperature, and the local wall temperature. This coefficient will be used to
evaluatethe effects of rotation and to make qualitativecomparisonswith the availablenumerical
predictions.
The transient heat transfer results obtained from the surface thermocouple data will be discussed
first. These data obtained at approximately one second intervals for the 150 second tests, are smoothed
and used to produce more accurate results than the liquid crystal data. The liquid crystal data will be
subsequently discussed and used, in conjunction with the surface thermocouple data, to determine
isotherms (at specific times) and iso-heat transfer coefficient contours. These results will be qualitatively
compared with 3-D Navier Stokes calculations.
Figure 2-1. Sketch of Internal Coolant Passage for NASA LeRC Cooled High
Temperature Radial Turbine Program.
3.0 DESCRIPTION OF APPARATUS AND EXPERIMENT
3.1 Heat Transfer Model
A Lucite model of the coolant passages in the NASA LeRC High-Temperature, Cooled, Radial
Turbine was constructed for the experiments. The model was 1.15 times the actual scale and was
constructed using surface coordinates obtained from the LeRC (Roelke, 1991) and drawings from the
Allison Division, General Motors (Anon, 1989).
The views of the coolant passage with the coordinate grid, the flow dividers, and pedestals are
shown in Figure 3-1. The coolant inlet passage of the full-scale rotor was simulated in the 1.15 scale
Lucite model. The coolant exit geometry was modified to account for the relatively small radial pressure
gradient at the model exit plenum due to the larger radial location of the model compared to the full scale
model. The exit plane of the coolant passage was selected to be the streamwise location where the
coolant passage is faired into the trailing edge on the pressure side of the blade (Figure 3-2). Based on
flow estimate information from the LeRC, a discharge flow-control plate with selected orifices was used
at the model exit plane to approximate the exit flow distribution. Twelve orifices were used to regulate
the distribution of trailing edge flow. Six were located at the exit of the inner trailing edge passage and
three were located at each exit of the middle and outer trailing edge passages. The orifices were evenly
spaced in the radial direction in patterns of three. The inner passage required the pattern to be staggered
to obtain a more uniform discharge area distribution. The discharge areas of the inner exit passage was
twice that of the middle and outer exit passages (see Figure 3-2 and table below). Consequently, the
configuration is expected to have 50 percent of the total coolant flow in the inner exit passage and 25
percent of the total coolant flow in each of the middle and outer exit passages.
Inner passage
Middle passage
Outer passage
Exit Plane Orifices
No. Used Diameter, mm(in.)
6 1.5 (0.059)
3 1.5 (0.059)
3 1.5 (0.059)
The leading and trailing surfaces of the coolant passages were machined in blocks of Lucite as
shown in Figure 3-3. The coolant passage was oriented 32.7 degrees from the plane of the test section.
This required that the test section with the model be rotated that amount to conduct the experiment with
the same relative orientation (i.e. axial alignment) as the full scale rotor.
6
The design and fabrication of the model were accomplished using Computer Aided Design and
Computer Aided Machining Technology. The assembly drawing for the model and installation is UTRC
Drawing 1896-30.
3.2 Model Instrumentation
The coolant passage model was instrumented with thermocouples and liquid crystal temperature
indicating paints as discussed in the following paragraphs.
Thermocouple Instrumentation - Chromel-Alumel, thin-film surface thermocouples were installed
on the leading and trailing test surfaces at selected locations as shown in Figure 3-4. The thin-film
thermocouples used were 13 microns (0.0005 in.) thick which resulted in minimal disturbance to the
coolant flow. These surface thermocouples provide an on-board calibration for the liquid crystals and are
also used to obtain local heat transfer rates with numerous time-temperature data points. The locations
of the wall thermocouples are presented in Table 3.1. Fine-wire (36 gage) thermocouples with small
beads were used to measure the inlet air temperature and the exit air temperatures. Four thermocouples
were installed in the inlet duct by suspending the thermocouple from the sides of the duct. A
thermocouple was also suspended in the air stream downstream of a central orifice used to control the
relative tlowrate through each of the three Region 4 channels. Inspection of all the air thermocouples
after the experiments indicated that all the thermocouple junctions were in the same position as at the
onset of the experiments.
Liquid Crystal - Mixtures of encapsulated, chiral-nematic paints for color changes at 47C(116F),
43C(110F), 38C(100F), 32C(90F), and 27C(80F) were sprayed on the test surfaces after the surface
thermocouples were installed. A layer approximately 13 microns (0.0005 in.) thick was used for these
tests. A second layer, approximately 13 microns thick, of black, water-based paint was sprayed over the
liquid crystal to provide optical separation between the leading and trailing surfaces. These thicknesses
provide adequate liquid crystal signals (i.e. color change) and do not require a large correction in the data
analysis due to the temperature drop across the liquid crystal and black paints.
a) Y-Z View
Y
b) Y-X View
X
c) Perspective View
Figure 3-1. Internal Passages of NASA LeRC Cooled Radial Turbine Rotor.
Location C
W c = 5.79 cm2.28 in.
Coolant exit
Outer
Location B
W b = 2.41 cm
I/
Location A
Wa= 0.719 cm0.283 in.
Coolant inlet
location
Middle
Inner
/ [______Region__Orifice / Lir_ 4 ILocations
Exit
Plane
Region1
Figure 3-2. Nomenclature for Internal Passages of NASA LeRC
Cooled Turbine Rotor.
UTRCDrawing 1896-30-66913TrailingSurface
UTRCDrawing 1896-30-66912
Leading Surface
Figure 3-3. Photograph of Leading and Trailing Surfaces of Coolant Passage Before Assembly.
3.3. Rotating Heat Transfer Facility
Rotating Components - The Rotating Heat Transfer Facility (RHTF) (Figures 3-5 and 3-6)
consists of the containment vessel with the integral arm assembly and motor with associated controller.
The containment vessel is 1.83 m (6.0 ft) in diameter and was designed to withstand a destructive failure
of the rotating assembly. The vessel was designed for operation at a pressure of 5 to 13 mm of Hg
absolute to reduce the power required to rotate the arm. The rotating arm assembly is driven by a 11
KW (15 Hp) DC motor via a toothed belt. Shaft RPM is controlled by an adjustable feedback electronic
controller. Maximum shaft speed is approximately 3,500 RPM producing body forces on the model of
approximately 14,000 g's at the tip of the model and approximately 10,000 g's at the root. However, the
flash lamps used to illuminate the model were found to not work properly when the pressure was below
atmospheric. Therefore, the vessel was operated at near atmospheric pressure and the maximum shaft
speed for the present program was 750 RPM. A safety shutdown interlock circuit is used to turn off the
drive motor and model heater power supplies, turn on a magnetic brake and open the containment vessel
vacuum chamber vent. The safety shutdown system prevents damage to the model or the facility in the
event of a leak in the model or an imbalance in the rotating assembly.
The shaft assembly comprises a main outer shaft with two shorter inner shafts. This shaft
arrangement was designed for dual fluid paths from each rotary union mounted on the ends of the shaft to
the rotating assembly. For the present program, a single fluid path was utilized to provide coolant air to
and from the heat transfer model. Grooves located on the exterior surface of the outer shaft allow
instrumentation and power leads to extend from the rotating arm to the rotating portion of the
instrumentation slipring. Two slipring assemblies (a 40 channel unit located on the upper end of the shaft
and a 200 channel unit located on the lower end of the shaft) are used to transfer heater power and
instrumentation leads between the stationary and rotating frames of reference.
Thermocouple Data Acquisition System - The data acquisition system contains two major
components; the computer and the data acquisition control unit. The computer consisted of a DEC PDP
11/03 processor unit with 128k memory, two 20 cm (8 in) floppy disk drives, and a DECWRITER III
terminal. The Hewlett Packard 3497A data acquisition system can be controlled from the front panel or
through the interface connected to the computer. Upon completion of the acquisition of voltage data
through the acquisition control unit and the computer, results are calculated and printed in engineering
units. Flow parameter and raw data are stored on disk for future reduction.
Heater Power Sources - A variable DC power supply was used to provide current to the model
inlet heater assembly. The air inlet, electrical-resistance-type, heater assembly consisted of a thin-wall
11
tube bundle connected in series. Model inlet coolant air flowed through the tubes which were aligned in
the flow direction. The model air was heated to the initial temperature for each experiment by passing
current through the tubes. The thin-wall tubes were subsequently heated by the tube resistance and
provided an efficient method of heating the inlet air. The thin-wall tubes also provided a relatively'short
time constant response due to low total mass of the system. The current from the power supply was
switched on and offby a computer controlled, high current capacity relay. Additional low power supplies
were used to heat resistance film heaters mounted to the model pressure containment shell. These
auxiliary heaters were used to help provide isothermal initial test conditions.
Flow Supply System - Model coolant air is supplied continuously by the UTRC 27 arm (400 psig)
air system which is regulated to approximately 10 arm (150 psig) at the RHTF. The air flowrate to the
model is measured with variable area flow meters. The model coolant return air flows through an
additional flow meter to determine a mass flow balance on the system. Model pressure is controlled by
back pressuring the model air flow system with a return air control valve. The maximum mass flowrate
available is dependent on the model operating pressure and the total pressure loss of the system including
the heat transfer model. For typical models, the maximum air flowrate is approximately 0.02 kg/sec
(0.044 lbm/sec).
The model air is cooled to approximately -12°C(10°F) before flowing to the shaft rotary union
with a chilled-liquid/air heat exchanger. Heat pickup in the shaft and air supply lines on the rotating arm
increase the model air temperature to approximately 10°C(50°F) at the location just before entering the
model inlet heater system.
12
+ Air TC
• Wall TCo Exit orifice locations
a) Leading side viewed fromoutside model
b) Trailing side viewed fromoutside model
e8
o •7o o
0 0 0 00
6•o
o
e32A 4A
17 • oo o
oo o o
o o
°_ 16 _/o 23
O
1 °÷2_?
• 14_o_b
for scaled model
Figure 3-4. Thermocouple Instrumentation for Internal Passages of NASA LeRC
Cooled Turbine Rotor. (Note: model centerline was moved 22.85 inches
from the center of rotation of the test facility.)
13
TABLE 3-t LOCATIONS OF WALL THERMOCOUPLES IN MODEL
NASA LeRC Radial Turbine RotorThermocouple Locations reference to UTRC Drawings Nos. 1896-30-66913 & 66912Note: Axial reference point is the upstream tip of the coolant passage(See Figures 3-1 and 3-4 for coordinate systems)
1.15 Scale Model 1.15 Scale Model
In facility coordinates In rotorcoordinatesx R e x r
Location TC# (in.) (in.) (deg.) (in.) (in.)
Full Scale NASA LeRC Model
LeadingLeadingLeadingLeadingLeadingLeading
_- Leading4==
1 0.125 * 30.145 * -0.530 * 0.125 * 7.300 * -0.5305 0,520 30.160 -0.530 0.520 7.315 -0.530 -0.068 6.361 0.4522 1.169 27.328 -1.010 1.169 3.383 -1.010 -0.079 3.899 1.0177 2.293 27.845 4.370 2.293 5.012 4.370 0.381 4.358 1.9943 2.375 26.369 4.120 2.375 3.532 4.120 0.254 3.071 2.0658 3.380 28.323 19.360 3.380 4.699 19.360 1.558 4.086 2.9394 3.242 25.830 16.120 3.242 3.092 16.120 0.858 2.689 2.819
Trailing 11 0.125 * 30.045 * .57" 0.125 * 7.200 *Trailing 15 0.492 30.077 0.570 0.492 7.232Trailing 12 1.144 27.190 1.550 1.144 4.346Trailing 17 2.340 27.901 6.390 2.340 5.082Trailing 13 2.419 26.016 8.550 2.419 3.202Trailing 18 3.380 27.127 20.710 3.380 4.527Trailing 14 3.278 25.704 19.830 3.278 3.018
0.5700.570 0.072 6.289 0.4281.550 0.118 3.779 0.9956.390 0.566 4.419 2.0458.550 0.476 2.784 2.103
20.710 1.601 3.937 2.93919.830 1.024 2.624 2.850
* = Approximate locationx = axial distance relative tor = radial distance relative to the scaled rotorcenterline before mountingin the rotating facilityR = radialdistance relative to model centedine of rotation after mounted in the rotatingfacility
e = angular location relative to theX,Y,Z = cartesian coordinates for the fullscale NASA LeRC Model
0 X Y Z(deg.) (in.) (in.) (in.)
Dual path _-.2!rotalion union
for airtransfer
Upper slip
ring location
Figure 3-5. Photograph of a Model Mounted in Rotating Heat Transfer Facility.
(Rotating heat transfer facility with cover removed).
E
1.83 m (6 ft) f "Model air in "[Counter- r_ _ . _ I
_ Z_ _ I_ Pressure shell
i ,li 2; 11nstrumen at-ion
slipring assembly _ Motor drive I[
.____ j assembly IIModel air out
Figure 3-6. Schematic of Rotating Heat Transfer Facility.
15
3.4 Experimental Procedures
Thermocouple Data Acquisition - The EMF for each thermocouple was measured and recorded
using laboratory computers and the HP3497A data acquisition system. The data acquisition system was
configured to repeatedly measure the EMF from a sequence of thermocouples in the model. The data
was stored in a memory buffer in the HP3497 and transferred to a data file for the specific test number.
Some unsteadiness was noted for some thermocouples. Typical time variations of measured
temperature are presented in Section 5. The time variations of temperature indicate an approximately +/-
0.5°C(I°F) random noise component added to the expected temperature variation. The probable sources
for this unsteadiness were (1) rotating instrumentation leads through magnetic flux lines generated by the
DC motor, (2) motor power controller noise, and (3) lead, slipring, and instrumentation contact
irregularities. The temperature data were smoothed by performing a second order, least squares fit to the
closest seven data points around each time point of interest. This technique effectively removed the
random noise component but allowed the fit temperature to follow the experimental transient.
Thermocouple Data Reduction - Transient heat transfer measurement techniques are well
documented (e.g., Schultz, et al., 1973, Clifford, et al., 1983, Metzger and Larson, 1986, Saabas et al.,
1987, and Metzger et al., 1989). A typical approach to obtaining transient heat transfer data involves
solving the one-dimensional transient heat conduction equation subject to a semi-infinite wall boundary
condition with a uniform initial wall temperature and a step change in a convection boundary condition on
the surface exposed to the coolant flow (e.g., Kreith, 1973, Metzger and Larsort, 1986, Metzger et al.,
1989). A single, time-temperature pair (typically from phase change paints, wall mounted thermocouples
or liquid-crystal paints) is then used to determine the heat transfer coefficient for each separate point on
the test surface. Different points on a test surface will have differing time-temperature histories. Implicit
in this solution is that the heat transfer coefficient is a constant with time. However, when heat transfer
coefficient is known to be a function of the temperature difference, such as in rotating coolant passages,
this technique may not be appropriate (see Wagner et al., 1989, for more discussion of the combined
effects of Coriolis and buoyancy forces on heat transfer in rotating passages).
The one-dimensional, time dependent heat conduction equation was solved to obtain a time
dependent heat flux and a time dependent heat transfer coefficient. The formulation for time dependent
heat transfer coefficients is required because of the variations in the heat transfer coefficient during the
transient test due to changing buoyancy effects as the wall-to-bulk temperature difference decreases. 2-D
effects of lateral conduction have been studied and reported by Metzger et al., 1989; Metzger and
Larson, 1986, and Saabas et al., 1987, and will not be discussed here. In general, the 1-D assumption has
16
been shown tO be valid for a judicious choice of test surface material and test times. Following is a
description of the UTRC data analysis procedure from Blair et al., 1991, solved to obtain a relationship
for the heat flux from the prescribed surface temperature boundary condition at a particular point in the
coolant passage. The 1-D transient heat conduction equation subject to a semi-infinite wall boundary
condition and a time dependent prescribed surface temperature is shown below.
52T(x, t) 1 6T(x, t)
(_2 a t_t
with boundary and initial conditions:
r(x,0) = m*x +/;,
o¢'T(oo, t)-m
5x
T(0, t) = experimentally determined
Solution:
T(_(O,t- r) at_ m, k
47
An analysis showed that the first temporal derivative of the wall temperature is a continuous
function, therefore, the evaluation of the integral was accomplished by assuming an average derivative,
T' (0, t-x), for a given time increment. This reduced the integral to a series of summations for equally
spaced time increments which were evaluated as shown below.
J
Q(t)= _[_-= _], [T_ (j + 2-i)- T'.(j + 1-i)]
17
A term was included in the solution to allow for an initial temperature gradient in the model wall
due to the difficulty of obtaining a perfect isothermal initial condition during the warm-up phase of the
experiment. For the case of an isothermal wall initial condition, this term is zero.#
These tests had heaters in the space between the model and the Lucite windows which formed the
transparent walls of the Optical Test Section (Figures 3-7 and 3-8). The heaters were used to bring the
average temperature on the outer wall of the model to the same temperature as the inlet air temperature
at the start of the test. In general, isothermal conditions (i.e. inlet flow and model surface temperature
within +/- I°C(2°F)) were obtained for the stationary test conditions. However, test conditions with
rotation had larger temperature variations (i.e. on the order of +/- 3°C(6°F)) especially on the trailing
surface and at the model coolant air exit plane. The procedure to obtain isothermal conditions consisted
of flowing heated air through the model coolant passages with the external auxiliary heaters on for
approximately two hours prior to the initiation of the transient portion of the test. It is likely that the
combination of rotating the model and the thicker model walls on the trailing side resulted in a need for
an increase in the thermal soak time which was not recognized at the time of the test. With limited
external surface instrumentation (3 external thermocouples on each side) and a fairly complex 3-D
thermal initial condition an acceptable initial temperature gradient could not be determined. Therefore,
no initial temperature gradient term was used for the analysis of the data in this study. A discussion of
the effect of initial wall temperature gradient is included in subsequent paragraphs where experimental
uncertainties of the data are presented.
Video Data Acquisition - The typical pre-test procedure consisted of heating the air flowing
through the rotating model coolant passages until the acrylic heat transfer model walls reached
approximately isothermal conditions. Note, the experimental methods described by Metzger and Larson,
1986, and Saabas et al., 1987, utilized an initially cold model wall subject to a suddenly heated
• mainstream flow. However, for the rotating heat transfer problem, the model walls must be hot with a
cold coolant flow in order to give the proper sense to the rotation-induced buoyancy force effects (see
Clifford, 1985, and Wagner et al., 1989). The test was then initiated by switching off the power to the
coolant passage inlet heater. A video imaging system was utilized to record the changing liquid crystal
paint on the coolant passage surface. Concurrently, the inlet and exit coolant temperatures and surface
temperatures were recorded as described in the thermocouple data acquisition section.
The video data was acquired using the optics arrangement shown in Figure 3-7. The video was
recorded on 3/4 inch magnetic tape. The time reference was superimposed on each frame using a
time/date generator. The start of each transient test (Time = 0.0 see) occurred when the heater power
was shut off. Typical test times recorded were 5 seconds prior to the start of the test and 150 to 200
18
seconds after the start. The camera and lighting system were timed by a 1/REV signal such that the
model was recorded in approximately the same position each revolution. (i.e. +/- 1 degree of rotation).
Video Data Analysis - Video imaging processing equipment was used to analyze selected'video
frames. The image processing equipment can display, edit, enhance, analyze, print, and animate images.
The video analysis system supports many standard image processing functions, including histogram
equalization, contrast enhancement, density profiling, smoothing, sharpening, edge detection, median
filtering, and spatial convolution with user defined kernels up to 63x63.
Typical test and data analysis frames are shown in Figures 3-9, 3-10 and 3-11. The video
recording obtained before the start of the test is shown in Figure 3-9. Only the portions of the video
showing a surface of the model are shown. This frame provides a reference that includes shadows and
reflections from the two layers of Lucite. A frame of the video during the test is shown in Figure 3-10.
Although there are differences between Figures 3-9 and 3-10, the liquid crystal contours cannot be readily
discerned from the viewing of one video frame. However, the contours are easier to discern when
viewing the video during playback and the viewer's eye and mind can discern the small changes in video
frames.
A processed video data frame is shown in Figure 3-11. The processing included subtracting the
Figure 3-9 frame from the Figure 3-10 frame, adjusting the location of the pixels to account for small
shifts in the model location, and contrast enhancement. This video frame process enhancement eliminates
extraneous light reflections by "zeroing" portions of the image not associated with the model coolant
passage and enhances the intensity of the liquid crystal isotherms. The processed frame shows a small
liquid crystal contour in Region 1, (see Figure 3-2 for definitions of Regions) two contours in Region 2
with flow radially inward, and contours in Regions 3 and 4 at the entrances to the Inner and Middle
portions of Region 4. Each contour on the frame was identified as to temperature and the time after the
start of the test. See Figure 6-2 for the identifications of video frames used on this video test for the
trailing surface.
Corrections were made to the coolant path wall surface temperature to account for the transient
energy storage in the liquid-crystal paint and temperature gradients through the paint. The transient
energy storage corrections were obtained by estimating the temperature at the paint/air interface based on
the calculated heat flux and the measured temperature at the paint/acrylic interface. The average internal
paint temperature was then calculated for each time step. Differences in the temporal response of the
average paint temperature and the paint/acrylic interface temperature (measured with the liquid-crystal
19
. Counterweigh_
Flash '/ w_,,,,_ II \\
1/rev signal }
_ Xybion B/W _"_u_'__ _ iii I
| m_ed -1 ,_ "11 __ Rotating optical
|._l__r-_J ..:...._..__.. _-- Lucite model
]P°y_m_gabt_r] _'_ C°°NN_-Lucite window lant Passage
Time/date L__ Vide° ___ Monitor Igenerator [_ recorder I I
Figure 3-7. Optics Arrangement for Rotating Heat Transfer Measurements
With Liquid Crystals.
UTRC Drawing 1896-20
Figure 3-8. Rotating Optical Test Section With Previous Four PassModel Installed.
2o
Superimposed on NASA LeRC cooled turbine rotor outline
;!::!ii':!ii::iii::i!!!ili::!i_::!
:::::::::::::::::::::
:::::::::::::::::::::::::::::::::::::::: :::::::::::::::::::::::
" ........................._:i:_:i:i:!:_:i:i:i:i:i:i:!:i:i:!:i:i:i:iiii_::.':':::: .... .
_!_::i:J::!iiiiiiii!iiiiiiiiiiii::::::::::;
Figure 3-9. Frame of Video Recording Before Start of Transient Heat Transfer Test.
21
Superimposed on NASA LeRC cooled turbine rotor outline
.... :::i_!!!iiii_:i!iiiii!_
.::i!i!iiiii_i_iiii_::.... "
Figure 3o10. Frame of Video Recording During Transient Heat Transfer Test.
22
Superimposed on NASA LeRC cooled turbine rotor outline
Figure 3-11. Processed Frame of Video Data From Transient Heat Transfer Test
23
paint) were associated with the transient energy storage in the paint. The corrections associated with the
energy storage and temperature gradient in the paint were typically on the order of 3 to 5 percent aider 10
seconds.
A rotation induced calibration shift was also observed in this series of experiments. Comparison
of the surface temperatures obtained with the liquid crystal paints with the thin film thermocouples
showed that a calibration correction was necessary when the model was rotating. The temperatures
measured with the liquid crystals on the stationary model were in good agreement, i.e. +/- 0.5°C (I°F),
with the thermocouple measurement for stationary test conditions. The temperature calibration of the
liquid crystals changed considerably during rotation. The liquid crystals are known to be sensitive to
shear stresses which will occur due to the centrifugal force on the liquid crystals due to its own weight
and that of the black overcoat on the liquid crystal paint. The experimental results showed a 2 to 7°C(4
to 14°F) difference between the liquid-crystal surface and thin film thermocouples mounted on the test
surface at the 450 and 750 RPM test conditions. This calibration shift is attributed to stresses in the paint
under conditions of rotation which are not present when stationary. The surface thermocouples provide
an on board calibration required to resolve these variations.
Heat transfer coefficients at specific locations were calculated by dividing the instantaneous heat
flux with the wall-to-coolant inlet temperature difference for a given test time.
Accuracy of Results - A number of factors can affect the accuracy of the reduced heat transfer
coefficient data. Typically, uncertainties in absolute and relative temperature differences are the largest
contributors to uncertainties in calculated heat transfer coefficients. In this section the effect of
temperature measurement error, noise in the temperature data, time resolution error, initial wall
temperature gradient, paint thickness, and material property errors are presented.
A baseline test condition (Run 6.2) at a midpassage location (TC02) was used for the uncertainty
analysis. The baseline wall temperature data was perturbed as noted and reduced to evaluate the effects
listed. The temperature measurement error was simulated by adding I°C(2°F) to the raw data. Noise in
the data was simulated by applying a random function ranging +/-I°C(2°F) to the smoothed data. The
effect of time resolution was simulated by adding 1 second to the raw data. The effect of an initial wall
temperature gradient was determined by assuming the outside of the model was approximately 6°C(10°F)
lower than the coolant passage surface at the start of the test. The effect of uncertainty of the Lucite
model material properties was determined by adjusting the thermal conductivity 10 percent. The
perturbations were applied to the measured data set and reduced to obtain heat flux and heat transfer
coefficient results.
24
The inlet coolant temperature, wall temperature, heat flux, and heat transfer coefficient records
are shown in Figure 3-12. The results show that random noise on the wall temperature data causes
significant fluctuations in the resulting heat flux and heat transfer coefficient histories (Figure 3-12_ and
d) and that fluctuations in the heat transfer results are more likely related to less-than-ideal smoothing
rather than flow-induced oscillations. Aside from the application of random offsets to the wall
temperature data, the perturbation analysis indicates that the results are fairly insensitive to the effects
studied. The percent change in heat transfer coefficient at Time = 50 seconds is listed below. As
previously noted, the uncertainty in measuring temperature results in the largest contribution to the
uncertainty in the heat transfer coefficient results although the temperature offset had a minimal effect on
the heat flux distribution.
Percent Change in Heat Transfer Coefficient
Percent Change
Twall + I°C(2°F)
Twan +/- (random) I°C(2°F)
Time + 1 second
With initial gradient
Without paint corrections
10 percent increase in model conductivity
-8
NA
+1
-3
-3
+5
25
a) T_.
140 1
120_
R06T02 Data
eeeee Baseline_.se Tw w/ offset
Tw w'/ randomTime + 1 secondw/. gradient
w'/o paint_v 1.1 * K
100
°_E__80-
60.
4O o ......... s'o........ i66 ....... i5oTime, see
140
120
100
80
60'
4O0
b) T_.
RO6T02 Data
eeeee Baselineseeee Tw w/ offset
Tw w/ random(HHH_ Time + 1 second
w/ gradientw/o paint
........bb........i6o.......isoTime, sec
1000
c)Qw
R06T02 Data
5
i000 50 100
Time, sec
i000
2
100
1
lO
5"
Z
150
d) nr
R06T02 Data
oeeee Baseline_eeee Tw w/ offset
Tw w/ randomTime + i secondw/. gradient
w/o paint_1.1 *K
0 50 I00 150Time, sec
Figure 3-12. Uncertainty Analysis Results (Run 6.2, TC02)
26
4.0 EXPERIMENTAL PARAMETERS AND TEST MATRIX
The present study of heat transfer from a 1.15 times scale model was conducted at several
dimensionless flow parameters in or near the range of the NASA LeRC rotor. Following is discussion of
the flow and geometric parameter test conditions, and an outline of the presentation of results.
4.1 Flow Parameters
A dimensional analysis study performed at UTRC (Section 10 ofHajek et al., 1991, similar to that
of Guidez, 1989), showed that the flow patterns and convective heat transfer in rotating radial passages
would be influenced by four dimensionless flow parameters and several geometric parameters. The
dimensionless flow parameters are as follows:
Reynolds number (Re) pVd/_t
Rotation Number (Ro) c0d/V or oH/V
Density Ratio (Ap/p) (Pb - Pw)/Pb = (Tw - Tb)/Tw
Buoyancy Parameter (BUOY) [(Pb - pw)/Pb](c0R/V)(od/V)
For flow in rotating radial coolant passages, Coriolis forces, represented by the dimensionless
parameter, c0d/V, and the dimensionless streamwise velocity gradients, produce secondary flows in the
plane perpendicular to the radial direction. These secondary flows are produced by the viscous
force/Coriolis force interaction. Buoyancy also produces secondary flows in the radial direction. For
flow in rotating radial coolant passages with walls hotter than the bulk fluid, the buoyancy effects drive
the heated flow inward. Thus, the buoyancy flow direction is opposite the mean velocity direction for
flow radially outward and is in the same direction for flow radially inward. From previous studies, both
the Coriolis and buoyancy forces can be expected to produce significant changes to the coolant passage
flowfield and heat transfer. Rotating constant-temperature flow studies by Johnston, et al., 1972, have
shown that the Coriolis forces can dampen turbulent fluctuations and laminarize flow in portions of a
channel. Combined free and forced convection studies in stationary systems have shown that the
turbulent shear structure and heat transfer is significantly altered with co-flowing or counter-flowing
buoyancy effects ( e.g., Eckert et al., 1953).
27
4.2 Geometric Parameters
The flow and heat transfer in stationary coolant passages are also strong functions of the
geometric parameters (e.g., Johnson et al., 1993). All parameters except the radial location of the model
are identical to the NASA LeRC rotor.
4.3 Test Conditions
The test conditions for the heat transfer experiments are listed in Table 4-1. The variations of
Reynolds number and rotation numbers are shown in Figure 4-1. Tests were conducted for three
flowrates (Reynolds numbers indicated in the figure) and three nominal rotation rates (0, 450, and 750
RPM). Tests were conducted at the Reynolds number range and approximately one-half and one-fourth
the Reynolds number of the Full Scale Rotor. Due to the Reynolds number variation in the coolant
passage for a given flowrate, subsequent references to flowrate will be as low, medium, and high flowrate
test conditions. A tabulation of the test conditions for which thermocouple and liquid crystal data were
obtained and the Full Scale NASA LeRC Radial (Full Scale) Turbine operating conditions are presented
in Section 9.2. The characteristic dimensions used for the representation of the Reynolds and rotation
numbers are shown in Figure 3-2. The channel width dimensions, W, were determined from the model
drawings. The channel depth dimensions, H, at each location indicated on Figure 3-2 were obtained
from the tabulated coolant passage coordinates supplied by the LeRC. Because of the flow distribution
uncertainty, the average results anticipated for Regions 3 and 4 are represented by the single Location C.
Results are presented for all of the available locations. The Nusselt and Reynolds numbers
(nominal values noted in the figures where appropriate) were calculated based on the geometry of
Location B (see Appendix 9.2 and Figure 3-2). The viscosity and thermal conductivity of the coolant
were based on the film properties where the coolant temperature was assumed to be the lowest
temperature obtained for a given test condition (Tc, Appendix 9.2) and the wall temperature was
assumed to be the initial temperature of the coolant (i.e. the ideal initial wall temperature, Tw in
Appendix 9.2). Flow properties, velocity and Reynolds number, were based on the coolant temperature
described above. Whereas the Nusselt and Reynolds numbers used the hydraulic diameter of the passage
for a characteristic dimension, the separation distance, H, was used for the calculation of Rotation
number. Local Rotation, Reynolds, and Nusselt numbers at a given location can be obtained using the
local geometry and applying adjustments to the parameters presented based on ratios of the local and
Location B dimensions. Normalizing the data in this manner (i.e. using a common representative model
location) resulted in plots with similar scales so that results could be compared more easily. Note that the
location designations in the figures refer to thermocouple (TC) locations shown in Figure 3-4.
28
Table 4-1
Flow Conditions for Transient Heat Transfer Tests
Test Flow Video
No. Date Rate RPM Surface Comments
5.1 4/13/92 H 0 Trailing (11)
5.2 4/13/92 H 0 Trailing (11)
6.1 4/13/92 M 0 Trailing (11)
6.2 4/13/92 M 0 Trailing
7.1 4/14/93 H 0 Leading (11)
8.1 4/14/93 M 0 Leading (11)
9.1 6/1/93 H 453 Trailing
9.2 6/1/93 M 453 Trailing
10.1 6/2/93 H 450 Trailing
10.2 6/2/93 M 450 Trailing
11.1 6/3/93 H 756 Trailing
12.1 6/24/93 H 749 Trailing
12.2 6/24/93 M 751 Trailing
12.3 6/24/93 L 749 Trailing
Low Quality Video
Low Quality Video
14.1 6/26/93 H 750 Trailing No Video
14.2 6/26/93 H 750 Trailing Low Quality Video
14.3 6/26/93 M 750 Trailing Low Quality Video
14.4 6/26/93 L 750 Trailing Low Quality Video
15.1 8/12/93 H 753 Leading (1,8,11)
16.1 8/13/93 H 450 Leading (1,11)
16.2 8/13/93 H 753 Leading (1,8)
16.3 8/13/93 M 750 Leading (1,8)
16.4 8/13/93 M 450 Leading (1)
16.5 8/13/93 L 452 Leading (1,11)
16.6 8/13/93 L 751 Leading (1)
Data
TC
Y
Y
Y
Y
Y
Y
Y
Y
Y
Y
N
Y
Y
Y
Y
Y
Y
N
Y
Y
Y
Y
Y
Y
Y
ReducedVideo
N
Y
N
Y
Y
Y
N
N
Y
Y
N
Y
Y
Y
N
N
N
N
N
Y
Y
Y
Y
Y
Y
Note: Numbers in ( ) indicate thermocouple locations where data is not available.
29
o
0
c_
o
0.08
a) Location A
0 Full scaleX Test point
0.04 --
0.00
0.20
0
X OX
X
20000 40000 60000 80000
b) Location B
Re d
0.15 --
0.i0--
0.05--
0.00
1.00
X
X
0
X<
i l>_<t
0 i0000 20000 30000
Re d
c) Location C
0.80 --
0.60 --
0.40--
0.20-
0.00
X
X
X
>X<
0 4000 8000 12000
Re d
Figure 4-I. Comparison of Test Matrix With NASA LeRC Ful!
Scale Operating Conditions.3o
The combinations of Re and Ro for the tests and for the Full Scale turbine are shown in Figure 4-
1 for Locations A, B, and C. The figure shows the maximum rotation numbers obtained during this series '
of tests with the scaled UTRC model for Locations A and B (see Figure 3-2) near the entrance of the
airfoil coolant passage were approximately half that of the Full Scale model at the design Reynolds
number. The low test rotation numbers for these locations were due to facility limitations. However, the
design rotation numbers for these locations were obtained at Reynolds numbers half the Full Scale
operating conditions.
Design rotation numbers were obtained for Location C as a result of the large pressure drop
through the Full Scale model coolant passage (1.66 to 0.82 atmospheres) and the relatively small pressure
drop through the UTRC model (11.0 to 10.9 atmospheres). The large pressure drop in the Full Scale
model results in a significant increase in coolant velocity and a commensurate decrease in Full Scale
rotation numbers compared to little pressure drop in the UTRC model. Therefore, due to the relatively
low pressure drop in the coolant passage of the scaled UTRC model the same relative decrease in the
rotation number which occurs in the Full Scale model with streamwise distance does not occur in the
UTRC model.
4.4 Outline for Presentation of Results
A total of twenty-five tests were conducted with models as shown in Table 4-1 (repeat runs were
obtained under different test numbers). These tests consisted of eight different combinations of coolant
flowrate and rotation rate as noted. Repeat runs and runs where one portion of the data system was
unsatisfactory are also noted. In order to make the presentation of the principle results for this program
tractable and discernible to the reader, the heat transfer data is presented in several stages.
The local heat transfer results obtained from the thermocouple data are presented in Section 5.0
These results show the range of heat flux and heat transfer coefficients based on the inlet air temperature,
the local wall temperature, and the local wall heat flux for three sets of rotating conditions and the
medium flowrate. The results for each thermocouple location at this flowrate are compared to show the
effects of rotation. To summarize the effects of flow and rotation, the heat transfer ratio, Nu/Re 0.8,
versus rotation number, Ro, is used to compare all of the data acquired.
Liquid crystal data and regions of constant heat flux will be presented in Section 6.0.
31
5.0 HEAT TRANSFER RESULTS FROM THERMOCOUPLES
Six sets of thermocouple data are presented in detail to identify the range of wall temperature
responses, heat fluxes, and heat transfer coefficients based on measured inlet coolant temperatureS. All
six cases were at the same approximate coolant flowrate, 3.4 gm/sec (0.0075 Ibm/see) and the same
model pressure, approximately eleven atmospheres. These data were obtained during transient heat
transfer tests at 0, 450, and 750 RPM with concurrent video recording of the leading or trailing coolant
passage surfaces (one side per test). These thermocouple data facilitate the interpretation of the results
from the video records of the liquid crystal color changes. Data and results are available on computer
disk. A sample table is provided in Appendix 9.3.
5.1 Data and Results for Medium Coolant Fiowrate
Measured temperature, heat flux, and heat transfer coefficient results are presented. The
temperature records shown in the figures are not smoothed. Note that not all of the temperature records
were available for analysis. During the testing it was speculated that the thin film thermocouples were
intermittently failing. However, the test-to-test variations in the quality and availability of the
thermocouple data suggest that lead and switch contact irregularities may have been contributing factors.
The temperature data was smoothed with a "running" second order fit of the nearest seven data points.
The smoothed data was used to obtain heat flux and heat transfer coefficient results. Using more points
resulted in smoother heat flux and heat transfer coefficient plots but was not deemed necessary. The
major purpose of the smoothing was to reduce the large variations which tended to obscure the general
trends (see discussion of uncertainty in Section 3). It is the authors' recommendation that using the
relative smoothness of the heat flux and heat transfer coefficient data to contemplate the unsteadiness of
the coolant flow should be done with much care.
Stationary Tests - The data and results for the two medium flow, stationary tests are presented in
Figures 5-1 through 5-4. The leading and trailing wall temperature histories (Figure 5-1c and d) are used
to determine their respective wall heat flux histories (e.g., Figure 5-2a and b)as described in Section 3.4.
The inlet air temperature histories (e.g., Figure 5-1a), the wall temperature histories, and the heat flux
histories are used to determine a heat transfer coefficient, Hr, (e.g., Figure 5-2c and d) based on the
difference between the local wall temperature and the inlet temperature. Note that the calculated heat
transfer coefficients are essentially independent of time aider 10 seconds of test time for these stationary
tests.
32
140
120
100
8O
60
40-50
a) Tin
Re = 13,000
140'R08T01 Data oOOOOTC02
_TC03_TC010_0_TC04
II IIIIIlllll,l,llllll,llt,ll,llllllllll
0 50 100 150Time, see
120
i00
60-
b) Tou t
40-50
R08T01 Data eeeeeTC21_TC22_TC23----- Tout. avg
IIt111,111 II, I,1111|1,1,111tlIII1,11111
0 50 100 150Time, sec
E-_
140
120
I00
c) Leading Surface
8O
60
R08T01 Data eeeeeTC01meBe_TC02a_TC03_TC04_TC05B-B-B_TC07
0 I I I, ,I l ,1 Illll II tI111 II III I-I1 II IIIII III
-50 0 50 100 150Time, sec
d) Trailing Surface140
R08T01 Data
120
100
_e_s.eTC12_a_,a-,aTC13v'_w-vTCl4
_a.,_TCl5_9-9-_TC17
60
4°-5_ ....... 6........ g_ ....... i66....... i5oTime, see
Figure 5-1. Thermocouple Data for Liquid Crystal Test on Leading Surface
With fi = 0 rpm.
33
Re = 13,000
a) Leading Surface b) Trailing Surface ,
looo I/'_ .o_.o,oa_a _G%' I 1000I ..- .o,_o,D_,o/ / \ _ TC12 [
I U _ a-a-a-6-a TC03 I 1 ] _ _ TC18 II I _ _ TC04 I "_ I _ _ TCl4 III _ _TC05 I |1 N-A _TCl5 I
II _-_-._ % _ =o_ i - I _ _ _ TC17 I
I00 100__
0 50 100 150 0 50 100 150Time, sec Time, sec
1000c) Leading Surface
R08T01 Data
1000
2
O
"6 .00
o ......... 5'o........ i66 ....... i50Time, see
2
10
d) Trailing Surface
R08T01 Data
eeseeTCl2_TCI3w_TCl4
_TC15_TCI7
_TCI8
,4Lill*-,,li*ll,tillllll,lli'I
50 100 150Time, see
Figure 5-2. Results From Thermocouple Data for Liquid Crystal Test on
Leading Surface With f2 = 0 rpm
34
140"
120"
100'
._ 80
6O
a) Tin
Re = 13,000
140
40--50
R06T02 Data eeeeeTC02eeeeeTC03
a_TC01_TC04
.... Tin, avg
,11111,111111111111 IIIIIIIIIIIIIIIIIIII
0 50 i00 150Time, sec
P
120
i00
8O
b) Tou t
60
40-50
RO6T02 Data
eeOeeTC21eeee_TC22_TC23
------ j
I,t,nnl,,I II,ll,n, I1,1 II_ll ,,I ,,I,II, II
0 50 I00 150Time, sec
140'
120
I00
c) Leading Surface
RO6T02 DataeeeeeTC01eememTC02
a._a.a_TC03_TC04
_k ,_-_TC05
l_ t_-_-DTC07
8O
6O
40 ......... t ......... t ......... _ .........-50 0 50 I00 150
Time, sec
140d) Trailing Surface
120
I00
=_ 80'
6O
R06T02 Dataeeeee TCIIeeeem TCI2ac_ec_m TCI3
_ TCI4TCI5TCI7
4°-5'd ....... 6........ b'd ....... {6b ....... {50Time, sec
Figure 5-3. Thermocouple Data for Liquid Crystal Test on Trailing Surface
With f2 = 0 rpm.
35
Re = 13,000
a) Leading Surface b) Trailing Surface '
1000 1 _ ROeT02 Data oeeeozc01 "I 1000 _ . R0eT0Z Data oooooTC11i a "_ _Booe TC02 [ | _ _TC12III Tco3 11 Tcls• " _ _ TC04 -I / -_ _ TCI4
5
i00 z 100
0 50 i00 150 0 50 100 150Time, sec Time, sec
c) Leading Surface d) Trailing Surface
i000 _ i 1 RO6T02Data eeeeeTCllRo6r02 Data eeeee TC01 [ 000
5-[ Dos_o TC02 _ _. _ TCI2"I _ TC03 [ _ TCI3TCI4J _ TC04 [ _ _ TC15t _ TC05 I -
o I00 _ tOO
_ -
i0[_ i0 '_2
1 10 50 I00 150
Time, see
_i,is,lJlii_,lililillt,i,lltl
0 50 i00 150Time, sec
Figure 5-4. Results From Thermocouple Data for Liquid Crystal Test on
Trailing Surface With f2 = 0 rpm.
36
The data indicate a quick decrease in inlet flow temperature when power to the inlet heater is
switched off at Time=0 (Figures 5-1a and 5-3a). For this medium flowrate the time constant of the inlet
heater system is approximately 5 seconds. The outlet temperature response (Figure 5-1b) is much slower
due to the heat transfer to the coolant from the model walls. The dashed lines in the figures are the
smoothed average of the measured inlet and exit flow temperature data. The average coolant
temperature records were used for determination of the heat transfer coefficients. The wall temperature
records by definition are slower responding than the inlet flow temperature due to the heat capacity of the
model walls and the finite heat transfer coefficient. Note that the wall temperature records are not bound
by the limits of the outlet coolant temperature. In general, as the shape of a wall temperature trace
approaches that of the inlet coolant temperature trace the heat transfer coefficients become large (i.e.
towards infinity in the limiting case). Conversely, as the model wall temperature records approach a flat
distribution (i.e. constant wall temperature) the heat transfer decreases to zero,
The wall temperature records represent a wide range of time temperature responses indicating
various levels of heat flux and, therefore, heat transfer coefficient. The heat flux records (Figure 5-2a and
b and Figure 5-4a and b) are characterized by a large increase in heat flux near the start of the test
(Time=0) and a general decline as the model wall temperatures approach the coolant temperature.
The heat flux histories are somewhat sensitive to the smoothness of the temperature records. For
example, the temperature record for TC08 in figure 5-1c results in heat flux and heat transfer coefficient
records which are not as smooth as the other records associated with this test. The unsteadiness of this
thermocouple trace is attributed to lead, slip ring, and switch contact irregularities. The unsteadiness was
intermittent and was not restricted to specific channels (note TC08 in Figure 5-1 c and TC07 in Figure 5-
3c). Smoothing of the raw data reduced the effects of the unsteadiness as discussed in Section 3.
The results for the stationary tests show a 10 fold variation in heat transfer in the model
depending on the relative location from the inlet. Heat transfer is highest near the two inlet locations
(TC01, TC05, TC11, and TC15) and lowest near the exit in the outer passage of Region 4. The large
variations noted are due to large differences in local Reynolds numbers and redistribution of flow near the
exit of the model passage.
Rotating Tests - The data and results for two rotation rates (450 and 750 RPM) are presented in
Figures 5-5 through 5-12 in the same format as the results from the stationary tests. Several differences
between the operating condition of the stationary and rotating tests should be noted.
37
It is clear from the thermocouple data for times less than zero (i.e. the initial conditions before the
start of the transient portion of the test) that the model did not attain the same level of temperature
uniformity for the rotating tests as for the stationary tests. Whereas the initial inlet temperature
uniformity was good for all tests, the range of exit temperatures increased from +/- I°C(2°F) for the
stationary tests to approximately +/- 3°C(6°F) for rotating test conditions. The variations noted for the
exit flow temperatures are representative of the level at which isothermal conditions were attained in the
model prior to the start of the test. This was also indicated in the plots showing the wall temperature
data.
Rotation decreased the range of the inlet flow temperature variation alter the inlet heater was
switched off. The inlet temperature varied from 52 to 27°C(125F to 80°F) in the rotating tests and from
52 to 13°C(125 to 55°F) in the stationary tests. The decrease in range is due to increased heat pick up in
the rotating air supply system to the model. The combination of rotation and a fixed attainable minimum
coolant supply temperature resulted in reduced temperature differences and, consequently, lower values
of buoyancy parameter.
The temperature records for the tests with rotation were used to calculate the heat flux histories
at each thermocouple location as outlined above. The results shown in Figures 5-5 through 5-12 show
that heat transfer was significantly affected by rotation. The most notable effect is the reduction in heat
flux from locations in Regions 3 and 4 on the leading surface, (e.g. TC07, see Figures 3-2 and 3-4). The
outer portion of Region 3 was especially slow in thermal response which resulted in very low heat flux
and heat transfer coefficient.
Some heat transfer coefficient results from tests with rotation show some uncharacteristic
behavior, principally, a sharp increase in heat transfer coefficient as time increases from the start of the
test (TC01 and TC 11) even though the heat flux traces for these locations are consistent compared to the
other traces associated with a given test. This characteristic is typically associated with the outer
locations of Regions 1 and 2 (i.e. near the inlet of the passage). The sharp increases in the heat transfer
coefficient traces are attributed to nonisothermal initial test conditions combined with high heat transfer
rates. The wall temperatures for locations in the model with high heat transfer decrease rapidly from the
onset of the transient portion of the test. This results in small temperature differences between the wall
and the inlet coolant which increases heat transfer coefficients. Additionally, the measured wall
temperatures were corrected for conduction and heat storage effects associated with the liquid crystal
paint which also contributed to smaller temperature differences. Therefore, results where the temperature
difference is greater are expected to be more useful for analyzing the effects of rotation.
38
140
120
100
P
__ 80
Re = 13,000
a) Tin140
60
RI6T03 Data EM_eeeTC02_TC03a_-_TC01
_TCO4
405'6 ....... 8........ '5_....... f Sb....... i5oTime, sec
120
i00
p_
b) Tou t
RI6T03 Data e_eeeTC21sseesTC22_._TC23
Tout, avg
60'
4°-s_ ....... 6 ........ 5'd ....... ido ....... i50Time, see
140
120
100
-_ 8o
c) Leading Surface
RI6T03 DataTC02TC03
TC04
60
4°--5i_ ....... 6........ '_iJ....... i db....... i aoTime, see
140
d) Trailing Surface
120
100
P
60 ¸
RI6T03 Data eeeee TCIIe_se_TCl2
_TCI3w_,_TC14
TCI8
4°-5'd....... 6 ........ 5'd....... fbb....... fsoTime, sec
Figure 5-5. Thermocouple Data for Liquid Crystal Test on Leading Surface
With f2 = 450 rpm.39
Re= 13,000
a) Leading Surface
i000 I RI6T03 Data moses TC02
TC03_ TC04
/ ",, rco5
d
1000 50 100
Time, sec
b) Trailing Surface
I000 I R16T03 Data eeeee TCll
TC12TCI3
vvv_v TC14_ TC15
5 _ TC18
100150 0 50 100 150
Time, sec
i000
._0
loo8
10
10
c) Leading Surface
TC02 RI6T03 Data . [A/ITC04 . ! '_ ,
a_ad_ad TC05 t-_ _ "
i.l i i i s i I i I i i _ i _ i i i i 1 4 i J _ i i i i i
5O
1000
100 150Time, sec
=
100_Do
_D
=
d) Trailing Surface
8-
10
2
10
TCI3v'_q_TCl4
_TCI5_9_9_TC17
_TCI8
i_l,IIJ,,l,lli,lt0111111111J_
50 I00 150Time, see
Figure 5-6. Results From Thermocouple Data for Liquid Crystal Test on
Leading Surface With f2 = 450 rpm.
40
Re= 13,000
a) LeadingSurfacemR1000
]//_ R10T02 Data eeeee TC01'I If \_t _ TC024 II x__\ _ TC08II1 _ _ TC0411 A \"_ _Tco_J I of" _ _x^ _ TC07
lOOZ_
0 50 100Time, see
b) Trailing Surface1000
T RIOT02 Data c_eee TCI 1j Qeeee 'l'C 12
_ _ TC13-_ _ _ TC14
[ I _ _ TC15-I! _ _ TClV
O' z
10050 0 50 i00 150
Time. sec
c) Leading Surface
- eeeeeTC01 R10T02 Data / _[ 1000TC02 A /k/ U
6-- _ TC03 I _ I "
TCO5 ._ ../ _. / _,/ :_
2 _ TC07 _ / _ pv ,v-e-
d) Trailing Surface
_I000 sI 1 _.BeeeTCII_BBee_Tc15Tc14Tcz3TC12R10T02 Data//_j_j_ l_J'":_ |illj'
? /
_ lo_C,_-_- _ lO"_ t_ -_ " " " I_
i i , i i i i i l '_ i i i i _ _ i i i L _ D i iI o 5o ioo 15o o 5'o' 166 i50Time, see Time, see
Figure 5-8. Results From Thermocouple Data for Liquid Crystal Test on
Trailing Surface With _ = 450 rpm.
42
Re = 13,000
a) Leading Surface b) Trailing Surface ,
"__ R10TO_Data _ TC01'] 1000 7 Rlcroa D_ _ Ten1000
• BBBOB TC02 | J _ TC12_f/ _ _*_ =03i _ -- _ =_34U "_ _ Tco4 ! _ [ "_ _ Tc14If _ \_s. _ TCO5 | | | _ _ TC15
I _f" _ _ _TC07 | "1 I _ _TC17
d
i002 10021 ......................
o so loo 15o o 'sb' i66 i5oTime, see Time, see
c) Leading Surface d) Trailing Surface
1000 bl--_j_ oeeeeTC01_ Tc03TC02TC04R 10T02 Data t!_\ d!/_l-vl_L/_[ ]G_j_/]I _:_ 1000 5_ °_eee TC111_ Tc14Tc13TC12 R 10T02 Dat_^ ,_Y-_//_J'a _ //|t_'_ -I _ TC05 / _ I _ / i _ TC15 /x,._. |
_ lOO _ loo _
_ _o_f_ • _ _o_'_
='_ i_Id-_ .... 1_ [I1 I ......... J, ........ _ ......... '
0 50 100 150 0 50 100 150Time, see Time, see
Figure 5-8. Results From Thermocouple Data for Liquid Crystal Test on
Trailing Surface With f) = 450 rpm.
42
Re = 13,000
o
140
120
100
80
a) Tin
60 ¸
40-50
R16T04 Data _TC02meemmTC03_TC01_TC04
i i,ii,lllllllllll,lll,,lllll_lllllll*ll
0 50 i00 150Time, sec
140
120
i00
8o.
b) Tou t
60
40-50
R16T04 Data_TC21mmmmmTC22
Tout, avg
ill tii Sill i illllllil I,II,IL iii iII1_11,1
0 50 100 150Time, sec
140
120
100.
c) Leading Surface
80 ¸
60-
40 :-50
R16T04 Data_TC02_,_-_TC03_TC04
_ TC05
'-,4_,.__. _ TC07
illltlll[lllll II,lll,l**''al'lllll III[I
0 50 100 150Time, sec
140
120
IO0
60
d) Trailing Surface
40-50
RI6T04 Data eeee_TCll
eeeeeTCl2
_TCI3
v_v_TCi4
,_TC15_-_-_TC17_TCI8
IILiIIIl III IllllllIllllll lllalllllll'll
0 50 100 150Time, sec
Figure 5-9. Thermocouple Data for Liquid Crystal Test on Leading Surface
With f2 = 750 rpm.
43
Rc = 13,000
a) Leading Surface b) Trailing Surface ,
1000 _ R16T04 Data _ TO02 4 _ TC12 |
] r.. _,co, I looo I RI,,_D._ ____,, ]- " _ TCO3 • _ TCI3 l
. , R _4444 TC05 {[ _ _ TC07 I ] Y X"_x a.a-,ma-a TC15 |/ I "x.',_ _ TCl"t /
100 1000 50 100 150 0 50 100 150
Time, see Time, see
c) Leading Surfacei000
i00
1o
2
i
.o
ssseeTC02
_TC03v_wTC04
_TC05_TC07
_TC08
0
d) Trailing Surface
_J sesse TC12TC13TCI4TCI5
21 _ TCl7._o__ _ TC18
lO
1......... 5b........ i 66 ....... i 50 o 50 1oo 15oTime, sec Time, see
Figure 5-10. Results From Thermocouple Data for Liquid Crystal Test on
Leading Surface With f_ = 750 rpm.
44
Re--- 13,000
a) Tin140
120
100
__ 80E-.,
60
R12T02 Data eoeeoTC02BBBB_TC03_TCOI
_T904
405'0 ....... 6 ........ '5_ ....... /66 ....... ,50Time, sec
140
120
i00
P
_ eoE-_
60
b) Tou t
RI2T02 Data eeeeeTC21_TC22_TC23
------ Tout, avg
"X
4o5'6 ....... 6 ........ _'6 ....... f66 ....... %0Time, see
o_
E-_
140
120
100
BO
c) Leading Surface
R12T02 Data eeeeeTCOl_BBe_TC02_TC03
_-,_TC05_-_-_TC07
60
405'6 ....... 6 ........ i'd ....... 1'66 ....... i50
Time, see
140
120
_100
80
60
d) Trailing Surface
RI2T02 Data _TC11_TC12_TCI3_TC14
_-_TC15
_TCI7_TCI8
405'6 ....... 6 ........ 5'd ....... 1'66 ....... ]'50
Time, see
Figure 5-11. Thermocouple Data for Liquid Crystal Test on Trailing Surface
With £2 = 750 rpm.
45
Re = 13,000
a) Leading Surface b) Trailing Surface '
•1ooo _ R12zo2 Dat_ o_oTC01"l 1000 _ RIaZ02Data _ZCn ]• eeeee TC02 4 eeeee TCI8 ["_ _TC03 [ • _TC13 [
I _ _ zco4 I 4 _ Tc,4 IJ" "" _ TC05 I / _ _ TCI5 I
I00 I000 50 i00 150 0 50 I00 150
Time, sec Time, sec
c) Leading Surface d) Trailing Surface
RI2T02 Data eeeee TCll
seeee TCI2TCI3TC14TC15TC17TC18
0 50 1oo 1_o o ......... 5'o........ i 66 ....... isoTime, sec Time, see
Figure 5-12. Results From Thermocouple Data for Liquid Crystal Test on
Trailing Surface With f2 = 750 rpm.
46
An adjustment was applied to the measured temperature data. Offsets were applied to normalize
the thermocouple results with rotation to the same initial temperature variation as shown for the
stationary tests. Temperature offsets from mean model surface and flow temperatures for each
thermocouple were calculated from the tests with stationary conditions. These offsets were subsequently
applied to the mean model surface and flow temperatures determined for tests with rotation. The
corrected results are presented in Appendix 9.4. Note that the heat flux records were essentially
unaffected by the temperature offset adjustments.
The adjusted heat transfer coefficient results shown in the appendix are less affected by the small
temperature differences associated with the high heat transfer areas as evidenced by the flatter heat
transfer coefficient records for TC01, TC05, TC11, and TC15. The effects of rotation on heat transfer
are shown in the figures. In general, lesser increases in heat transfer coefficient as a result of rotation are
shown in the adjusted results compared to the nonadjusted results. However, the large decrease in heat
transfer in certain model areas with rotation are still predicted for the low heat transfer areas (i.e. TC07).
The effects of rotation on heat transfer are more clearly shown in the following section for two elapsed
times atter the beginning of the transient portion of the test.
5.2 Effects of Rotation on Local Heat Transfer
The adjusted heat transfer coefficient records for the medium (0.0075 lbm/sec) coolant flowrates
for all rotation rates are presented in Figures 5-13 through 5-18. Additionally, the heat transfer ratio,
Nu/Re 0.8, at 10 and 30 seconds from the start of the test are compared as a function of rotation number
for the three coolant flowrates and the three rotational rates, i.e. stationary, 450 RPM, and 750 RPM.
Adjusted results, as described above, are presented in this section and subsequent sections.
Region 1 - Tip Section - The adjusted heat transfer coefficients for Location 1 (Figure 5-13a,
leading surface) with medium flow and RPM = 0 are essentially identical, indicating repeatability for this
flow condition. The heat transfer coefficients for the two tests with medium flow and rotation are
approximately 60 to 100 percent greater than those for RPM = 0. The effect of rotation on heat transfer
ratio is shown in Figure 5-13c. These results show an increase in heat transfer (consistent with the
medium flow heat transfer coefficient results, Figure 5-13a) at moderate values of rotation number (i.e.
Ro less than 0.1) and then a subsequent decrease for larger Rotation numbers. The increase in heat
transfer coefficient is not consistent with the previous results from Guidez, 1989, or Wagner et al., 1991,
where the heat transfer on the leading surface of coolant passages with flow outward decreased with
rotation. It is likely that the increase in heat transfer at the moderate to high flowrates results from
secondary flows in the inlet duct and the continuation of these secondary flows in the coolant passage.
47
a) Location 1, Tip Region,Leading Surface
i lO00 i_
100
9
10
s-
Q Runeeeee 0 0602eeeee 0 0801
+450 1002+750 1202
Surface
TrailingLeading
TrailingTrailing
11o"'3'o"'5b'"vb'"9'o"''"_d'k5o,10
_[le, see
b) Location 11, Tip Region,Trailing Surface
I000
ool16'
10
1I0
D Run Surface
oeeee 0 . 0602 Trailing+450 1002 Trailing
+750 1202 Trailing
I'l'II'il'H'HIlil'l'iIII"l'I""'"l''lll'lill"''''lq''''"H30 50 70 90 110 130 150
T'h'n e, sec
0.1
0.01
c) Location 1, Tip Region,
Leading Surface
• 08'
$
0 0
Re
ooooo 6,000ooooo 13,00000000 27,000
Solid symbol - 10 secOpen symbol 30 see
o.OOlo.od.....o'._.....o'.d_.....o'A_.....o'.15Ro (B)
0.1
_. 0.01
Z
d) Location 11, Tip Region,Trailing Surface
00
0 =$ $$ B •
0 O0
Solid symbol - 10 secOpen symbol 30 sec
Re
ooooo 6,000
oDooo 13,000o0oo0 27,000
ii i=1_ ill= i_l°'°°lo.od" 'o'.6_ ......o.o8 o.12'" '0.16go (B)
Figure 5-13. Dimensional and Dimensionless Heat Transfer Results From
Thermocouple Data for Region 1.
48
1000
.__ 100o
c.)
s
I0
a) Location 5,Tip Region,
Leading Surface
Run Surface
o_ee.e 0 0602 Trailingv_eee 0 0801 Leading
_-_+4501002_a'._+450 1604
+750 1202 Trailing+750 1403 Trailing+750 1603 Leading
IIl|lll,l|ll,ll,l,ll,llllllllllll'lll'ltlnllllll|llllll'll|''''l'll|
10 30 50 70 90 110 130 150
TiII1e, sec
b) Location 15, Tip Region,
Trailing Surface
1000 ol
._ I00 /o
0
10 Q Run Surface
eeeee 0 0602 Trailing0 0801 Leading
+450 1002 Trailing+450 1604 Leading+750 1202 Trailing+750 1403 Trailing+750 1603 Leading
I IIIIIII II,lln,I, IIII IIIIIIIII1,,11 IIII1,, I,II Illllll IIII III III1,11,
I0 30 50 70 90 110 130 150
Time. sec
1000
c) Location 2, Root Region,
Leading Surface1000
=_ 100 o 100
_ I0'
I0 4
:1 0 0802 =_ aveee 0 0801 Leading-1 _ +450 1002 Trailing
_ +450 1604 Leading.J _ +750 1202 Trailing-| _ +750 1403 TraiLing
_ +750 1603 Leading1 I,,,,,,,,,,,,,,,,,,,.,,,,,,,,,,,,,,,,,,.,,,,,,,,.,,,,,",."'"'" 110 30 50 70 90 II0 130 150
TilIle, sec
d) Location 12, Root Region,Trailing Surface
eeeee 0 0602 Trailing
aeeev 0 0801 Leading+450 1002 Trailing
+450 1604 Leadingv_v_v +750 1202 Trailing
+750 1403 Trailing
+750 1603 Leading1,11, Ill, Ill I,I, Ill III, Ill ,,,1 Illl,llllll IIII II,.1|111111 |111111 IIIIII
I0 30 50 70 90 110 130 150
Tin'_ e, sec
Figure 5-14. Dimensional Heat Transfer Results From Thermocouple Data for
Region 2 and Re = 13,000.
49
0.1
0
0.01
Z
0.001
a) Location 5, Tip Region,Leading Surface
00
Solid symbol - 10 secOpen symbol - 30 sec
Re
ooooo 6,000
aaaao 13,000OOO00 27,000
o.od ..... 0..d_...... 0.._ .... '0..I_.... '0..16Ro (B)
0.1
0.01
Z
0.001
b) Location 15, Tip Region,
Trailing Surface
6-
0
gg
Solid symbol - i0 secOpen symbol 30 sec
Re
ooooo 6,000oaooo 13,00000000 27,000
,o6.....0..6,_......od_.....o'i_.....0:18Ro (B)
0.1
0.01
c) Location 2, Root Region,Leading Surface
00
• iP o
Solid symbol -- I0 sec
Open symbol 30 sec
Re
ooooo 6,000ooooo 13,00000000 27,000
o.ool 0.06 ...... o.o4'...... o'._ ..... o'._. ..... o'.16Ro (B)
0.I
._ 0.01
Z
0.001
d) Location 12, Root Region,
Trailing Surface
o O
## •
O
O@
Solid symbol - i0 sec
Open symbol 30 sec
• Re
ooooo 6,000ooooo 13,000
00000 27,000
0.06 ..... 0'.0'_ ..... 0'.()8..... 0..I_-..... 0.16
Ro (B)
Figure 5-15. Dimensionless Heat Transfer Results From Thermocouple Data
for Region 2.
5o
The results for Location 11 (Figure 5-13b and d, trailing surface, tip region) are generally similar
to previous studies (e.g., Hajek et al., 1991). Heat transfer coefficient and heat transfer ratio are shown
to increase, on the order of 50 percent, with increases in rotation number, especially for the low to
moderate flowrates.
The general conclusion from the analysis of the heat transfer results from Region 1 are that the
effect of rotation is consistent with earlier results where heat transfer decreases on the low pressure side
of the passage and increases on the high pressure side. However, this only appears to be consistently true
for the low flowrate. Note that the previous experience is generally limited to Reynolds numbers of
50,000 and below. The high flowrate case of the present program results in a local Reynolds number
significantly greater than previous experience (over 70,000). Considering that inlet flow effects may be
convecting into the coolant passage for the high flowrate cases, it is inappropriate to generalize the effect
ofrotation on the heat transfer results for Region 1.
Region 2 - Tip Section - The calculated heat transfer coefficient, Hr, for the medium flowrate
(Figure 5-14a) increased significantly with rotation for TC Location 5 (tip leading surface). The
calculated coefficients at 10 seconds were approximately 25 percent greater then the stationary values
and generally increased with time. Heat transfer on the trailing surface (TC Location 15, Figure 5-14b)
for the medium flowrate is much less affected by rotation. Heat transfer is shown to increase and
decrease with rotation compared to the stationary results. Additionally, the results are uncorrelated with
rotation rate. The effect of rotation number on heat transfer is shown in Figure 5-15a and b. Heat
transfer ratio is shown to increase with increases in rotation number on the leading and trailing surfaces.
Whereas the increase in heat transfer on the leading surface is pronounced at the low and moderate
rotation numbers, the effect of rotation on heat transfer on the trailing surface is minimal. In general,
heat transfer ratio for all flowrates increased or stayed the same with rotation. These results had high
heat transfer coefficients as expected from previous results. The local streamwise velocities are high and
a great deal of turbulence and vorticity downstream of the turn is expected. The conclusion from these
comparisons is that the vorticity in the channel is increased significantly due to rotation.
Region 2 - Root Section - The results from TC Location 2 at the root on the leading surface with
the medium flowrate and radially inward flow (Figure 5-14c) are compatible with Hajek et al., 1991.
Heat transfer coefficients increase on the leading surface approximately 50 percent with rotation. The
results for TC Location 12 at the root on the trailing surface appear anomalous (as discussed above for
51
the tip section) compared with the values for stationary conditions. Heat transfer coefficient is shown to
increase and decrease with rotation but is uncorrelated with the rotation rate. The effect of rotation
number on the heat transfer ratio is shown in Figure 5-15c and d for the root section of Region 2. The
results on the leading surface generally increase with rotation number for low to moderate valtles of
rotation number and then subsequently decrease to the same level of heat transfer ratio measured for the
stationary tests. The trend of the trailing surface results is opposite to that of the leading surface such
that heat transfer ratio generally decreases with rotation number for low to moderate values of rotation
and then subsequently increases to the same level of heat transfer ratio measured for the stationary tests.
The conclusion from the analysis of the heat transfer coefficient and heat transfer ratio results
from Region 2 is that heat transfer increased and decreased significantly with rotation on the leading and
trailing surfaces especially for the medium to high flowrate test conditions.
Region 3 - Tip Section - The tip, leading surface of Region 3 (TC Location 7, Figures 5-16a and
5-17a) was the only region that had consistently lower heat transfer with rotation. The heat transfer in
this region with rotation was as low as 10 to 30 percent of that with no rotation. Heat transfer on the
trailing surface (TC Location 17, Figures 5-16b and 5-17b) is less affected by rotation compared to the
leading surface. However, heat transfer is shown to increase slightly and then decrease with an increase
in the rotation number.
Region 3 - Root Section - The heat transfer in the root region of Region 3 (Figures 5-16c and d
and 5-17c and d) is shown to increase slightly and then decrease with rotation number on the leading and
trailing surfaces. These results are inconsistent with Coriolis driven secondary flows and are likely
affected by more complex rotation induced flow structures.
The general conclusion from the analysis of the heat transfer results obtained in Region 3 is that
the heat transfer is strongly affected by rotation especially in the tip section where heat transfer was
substantially reduced.
Region 4 - Tip section - The heat transfer on the leading and trailing surfaces in the tip region of
Region 4 (TC Location 8 and 18, Figures 5-18a and b and 5-19a and b) was relatively unaffected by
rotation. This relative insensitivity to rotation would be expected when the flow is axial and the stream
tubes do not change radius.
52
1000
.-_ 100o
a) Location 7, Tip Region,
Leading Surface
fl Run Surface
eeee-e 0 0602 Trailing
eeeee 0 0801 _a'._+450 1002+450 1604 Leading
+750 1202 Trailin E+750 1403 Trailing+750 1603 Leading
10 -
I
1 •
10 30 50 70 90 110 180 150
Ti.lIle, sec
1000
o 100
b) Location 17, Tip Region,Trailing Surface
fl Run Surface
e_e_e 0 0602 Trailing0 OflOl Lea.di'.ng
+450 1002 Trailing+450 1604 Leading
+750 1202 Trailing+750 1403 Trailing'"+750 1603 Leading
2
10 30 50 70 90 110 130 150
TiIne. sec
I000
100
10
c) Location 3, Root Region,
Leading Surface
0 Run Surface
eeeee 0 0602 _Le "aa_'_0 0801
+450 1002 Trailing+450 1604 Leading+750 1202 Trailing+750 1403 Trailing+750 1603 Leading
iHi,,,, lilll,, "*IIH'II''III|I*IIII'IHII' "lllilllill|'l|lli''i"
10 30 50 70 90 110 130 50
TiIne, sec
1000
8"
d) Location 13, Root Region,
Trailing Surface
0 Run Surface
0 0602 Trailingseeee 0 0801 Leading
+450 1002 Trailing+450 1604 Leading+750 1202 Trailing+750 1403 Trailing+750 1603 Leading.2 I00
o
8
:11 ii1||;111 ill i¢11111|1115IH|I|II|IIIII 1|1114¢¢H II;I HII II¢illlll|51
10 30 50 70 90 110 130 150
Time. sec
Figure 5-16. Dimensional Heat Transfer Data From Thermocouple Data for
Region 3 and Rc = 13,000.
53
0.01
0.001
Z
0.0001
a) LocationT, TipRegion,Leading Surface
SoLd symbol -- 10 seeOpen symbol - 30 sec
Re
ooooo 6,000ooooo 13,00000000 27,000
,.,o• •
0 o O
oo
oO
@
iL=l=tlt===ll i|=1 i===o.oo 0.04 '6.d_ 'd.i_ 'd.1.Ro (B)
0.01
0.001
z
5-
b) Location 17, Tip Region,
Trailing Surface
O
0 *t_' 8 o• _ eo
Solid symbol - 10 secOpen symbol - 30 sec
Re
ooooo 6,000Maoonn 13,00000000 27,000
o.ooo10.06.....o'.6_.....o'.d_.....o'.i_......o.16Ro (B)
0.1
0
_ 0.01
Z
0.001
c) Location3, RootRegion,LeadingSurface
Solid symbol - I0 seeOpen symbol -- 30 sec
Re
ooooo 6,000
ooooo 13,000OOOOO 27 000
o 0
• i o
• 0 0
i i i D i i s i i i _ e = i i i e i io.o6 'o'.d_..... o.os o.1_ 'o'.16Ro (B)
0.1
30.01
Z
d) Location 13, Root Region,
Trailing Surface
SoLd symbol - 10 secOpen symbol -- 30 sec
Re|-
)oooo 6,000ooooo 13,00000000 27,000
,! = oo
o.ool d......'......o'd_......'......o.o 0.o¢ . o.12 o.16Ro (B)
Figure 5-17. Dimensionless Heat Transfer Data From Thermocouple Data for
Region 3.
54
1000
"_ 1000
8
_ 1o
a) Location 8, Tip Region,
Leading Surface
0 Run Su_ace
oeoee 0 0602 TrailingVHaee_ 0 0801 Leading
+450 1002 Trailing+450 1604 Leading+750 1202 Trailing+750 1403 Trailing
+750 1603 Leading
llUlllUll[llllll,ll iiiiiii 1111111 iiii iiii iiii iiiiiiiiiiiiiiiii IIII III I
10 30 50 70 90 110 130 150
TiIne, Sec
1000
o 100
8cD
"_ 10
b) Location 18, Tip Region,
Trailing Surface
0 Run Surface
oeeee 0 0602 Trailing0 0801 Leading
+450 1002 Trailingee#-o-0 +450 1604 Leading
+750 1202 Trailing+750 1403 Trailing+750 1603 Leading
,.11,,,,|..1,, H, 1111.11|11, II.1.1| ,SIIH,,+I+II]+I+'I+IHI''''I+H '
10 30 50 70 90 110 130 150
Tinle, sec
I000
c) Location 4, Root Region,
Leading Surface
Run Su_ace
eeoeo 0 0602 Trailingeeeee 0 0801 Leading
+450 1002 TrailinE+450 1604 Leading+750 1202 Trailing+750 1403 Trailing+750 1603 Leading
.2 1000
8
_ 10 .
10 30 50 70 90 110 130 150
rilne, SeC
1000
o 100"3
8C.)
1o
d) Location 14, Root Region,
Trailing Surface
Q Run Surface
eeeee 0 0602 Trailingeeeee 0 0801 Leading
+450 1002 Trailing(H_H_ +450 1604 Leading
+750 1202 Trailing+750 1403 Trailing+750 1603 Leading
llll llllll I lllllll III IIII IIII IIIIIIIIIII IIII III IIII IIII III 1111 IIIII
10 30 50 70 90 110 130 150
TiIne, sec
Figure 5-18. Dimensional Heat Transfer Data From Thermocouple Data for
Region 4 and Re = 13,000.
55
0.1
0.01
2_
0.001
a) Location 8, Tip Region,Leading Surface
Solid symbol -- 10 secOpen symbol -- 30 sec
Re
)oooo 6,000ooooo 13,000
00000 27,000
O
13
• • 0
).0(_, , , , , , i , _ , , , , , , , , , , , , ,0.04 '0'.6fi '0'.I_. 0.16Ro (B)
0.1
0.01
Z
b) Location 18, Tip Region,
Trailing Surface
Solid symbol -- 10 secOpen symbol 30 sec
Re
ooooo 6,000ooooo 13,000
ooo00 27,000
IIk
@@
o.OOlo.o6..... o'.di..... o'.dg..... o'.i_..... o'.16Ro (B)
0.1
0.01
0.0010.00
c) Location 4, Root Region,
Leading Surface
Solid symbol - 10 seeOpen symbol -- 30 sec
Re
ooooo 6,000ooooo 13,00000000 27,000
00O o*! '_ I, .
I
i;i illll# t i llll 1111 ll;i ii1_ ii ii
0.04: 0.08 0.12 0.16
Ro (B)
0.1
0.01
Z
d) Location 14, Root Region,
Trailing Surface
Solid symbol - 10 secOpen symbol -- 30 sec
Re
ooooo 6,000iooooo 13,00000000 27,000
i °6
. $ 0 •
0
0
e
o.oo, 06.....o'd_......'.......'......o'O. . 0.08 0.12 .16
Ro (B)
Figure 5-19. Dimensionless Heat Transfer Data From Thermocouple Data for
Region 4.
56
Region 4 - Root Section - The heat transfer for TC Locations 4 and 14 (Figures 5-18c and d and
5-19c and d) are also relatively unaffected by rotation. One could conjecture that an increase in heat
transfer ratio occurred with an increase in rotation number at low rotation numbers on the leading
surface. However, the increased heat transfer ratio results are for the high flowrate case only which
might suggest a flow redistribution effect rather than a rotation induced flow phenomena.
The conclusion from the analysis of the heat transfer results from Region 4 is that rotation effects
are minimal when the flow is predominately axial. Any heat transfer differences with rotation are more
likely to be the result of a flow redistribution between the three exiting flow streams rather than by a
rotation induced secondary flow.
57
5.3 Summary of Results from Thermocouple Measurements
[] The heat transfer coefficients in the tip section of Regions 1 and 2 are at least twice as much as those
in other regions of the coolant passage.
[] Heat transfer in Regions 1 and 2 are significantly affected by rotation. The results are generally
consistent with previous studies where heat transfer increases on the high pressure side of a passage
and decreases on the low pressure side.
[] The affects of rotation are most pronounced on the leading surface of the tip section of Region 3.
Heat transfer decreased to a level of 10 to 30 percent of stationary levels when the model was
rotating. The consequence of this result is that this region of the airfoil is essentially uncooled. The
low heat transfer in this region is attributed to a redistribution of the coolant flow which results in a
large recirculating stall cell.
[] The heat transfer in Region 4 with axial flow was less affected by rotation than Regions 1, 2, or 3.
58
6.0 HEAT TRANSFER RESULTS FROM LIQUID CRYSTALS
The video records for fitteen combinations of model orientation and flow conditions of transient
heat transfer tests are available from the NASA LeRC. Used in conjunction with the thermocouple'data
for the same tests, such as that presented in Section 5, these video data might be used to evaluate codes
for predicting conjugate heat transfer in complex coolant passages. The results also show the shapes of
the constant heat flux contours and provide insight, through inference of the flow structure in the coolant
passages.
Because the transient heat flux and temperature distributions do not lend themselves to easy
interpretation, those data were used, along with the thermocouple data, to develop heat transfer
coefficient contours. Corresponding flow parameters for the selected tests for several locations in the
model coolant passage (Figure 3-2) are presented in Appendix 9.2.
The temperatures measured with the liquid crystals on the stationary model were in good
agreement, i.e. +/- 0.5C (IF), with the thermocouple measurement for stationary test conditions. The
temperature calibration of the liquid crystals changed considerably during rotation. The liquid crystals are
known to be sensitive to shear stresses which will occur due to the centrifugal force on the liquid crystals
due to its own weight and that of the black overcoat on the liquid crystal paint.
6.1 Results for Stationary Tests
The video records of liquid crystal isotherms for the leading and trailing surfaces of the model for
the middle flowrate are presented in Figures 6-1 and 6-2, respectively. The contours noted were drawn
from processed frames of video data like that shown in Figure 3-11. The identification system uses the
isotherms, 1 through 6, and the video times, 1 through 4, for test 8.1 (Figure 6-1).
Nomographs were constructed from surface thermocouple data, obtained concurrently, to aid in
the interpolation of each set of liquid crystal data (Figure 6-3). The heat transfer coefficients, determined
for each thermocouple, are plotted as a function of local wall temperature for selected times into the test.
The heat transfer coefficients at selected times after the start of the test (Times 1, 2, 3, and 4) for wall
temperatures (Isotherms 1 through 6) are determined by intersecting a vertical wall temperature isotherm
line with a selected test time shown as dashed lines in the nomograph figures. Heat transfer coefficients
greater and less than the range of data are obtained by extrapolation.
59
Isotherms
1 - 46.7 °C (116 °F)
2 - 43.3 °G (110 °F)
3 - 37.8 °C (100 °F)
4 - 32.2 °C ( 90 °F)
5 - 26.7°C ( 80 °F)
6 - 21.1 °C ( 70 °F)
Video Times ID System
1 - 5.8 sec
2- 9.2sec D [-7
3- 17.4sec I _---4 - 33.3 sec Time ,Isotherm
32
43
23, 34
12, 34
o o21
11,22,33,44
13
23 34 _ _-1224
22,33
11,44
Figure 6-1. Video Records of Liquid Crystal Isotherms for Test 8.1.
6O
Isotherms
1 - 46.7 °C (116 °F)
2 - 43.3 °C (110 °F)
3 - 37.8 °C (100 °F)
4 - 32.2 °C ( 90 °F)
5 - 26.7°C ( 80 °F)
6 - 21.1 °C( 70 °F)
Video Times
1 - 4.7 sec
2 - 7.8 sec
3 - 15.4 sec
4 - 29.4 sec
ID System
Time
Isotherm
23
13, 1234
23
23
13
Figure 6-2. Video Records of Liquid Crystal Isotherms for Test 6.2.
61
. "tuda 0 = ET pue 000'EI = o_I _oj _31eG IelS,(aD p!nb!l _u.q_nleA_ .mj qde:_otuo N "g-9 aang!tt
0_I 00I 09 09 0_I 00I 09
Og x_01, -H-H-Fgg _ \
08
o__'_..... \ \
iiI\ L_ a\ \_ f:l:t:t:_
\'\
'\ \, \ '\ _ "_ \'v
\ \ \atur.,L 1. \ _\ £ ___ IA___
-[-'_--_--_5--9"
su_saq_osI:
(:6 9_ ) Do _'_l_ = (pua) uT.I.
(90 0_I) Do 8"8_ = (]ae_s) m.L
_;'9 _,saLa_jsn S _[.n_s.I. (q
000!
O9
og x_Of,
gg P_Ogq_
/. ta..U.L_
_o N
"_N"., o\ _ _.",b"k\ \ N
N% •
"" ",, 'x 00I _
\ \\ \
,, \ \ \_
au_..I, I'x- gx- -_ k I, _-
stu:;aq]oslI 000I
_-5_ I_-5"s_.T_Iuaosj _G
(_To9_ ) Do _'_ = (pua) _L(_qo0_0 Do 9"9D= 0s_ s) _..L
178 %saL
a3ejsn s _pea'-I (e
Note: Dotted iso-coefficients
from TC data
O',
a) Leading SurfaceTest 8.1
II
/
b) Trailing SurfaceTest 6.2
3
Figure 6-4. Heat Transfer Coefficients From Liquid Crystal Isotherms for Re = 13,000 and f2 = 0 rpm.
The iso-heat-transfer coefficients at the intersections of the times and wall temperatures are
plotted on Figure 6-4. In Regions 1 and 2, the heat transfer coefficient contour shapes and levels on the
leading and trailing surfaces are similar. Variations in the results between the leading and trailing surfaces
(+/- 15 percent at the same location in the coolant passage) are indicative of the precision with whi6h the
heat flux and heat transfer coefficients can be determined using the liquid crystal and transient heat
transfer measurement system. The heat transfer on the leading and trailing surface in Region 4 are also
approximately the same on both sides of the channel, although the shapes of the contours in the middle
and root passages have significantly different shapes. The leading surface heat transfer contour shapes
indicate centerflowing coolant in the middle and root passages while the trailing surface contours suggest
the coolant flow is biased to the side of the passage. These differences are attributed to the curvature in
the coolant passage as the gas paths changes from radial (Region 1) to axial (Region 4).
6.2 Results from Rotating Tests
The apparent calibration of the liquid crystal paint changed appreciably due to rotation.
Consequently, an effort was made to evaluate isotherms which were adjacent to or passed over the
surface thermocouples. The isotherms selected are shown in Figures 6-5 and 6-6 for tests at 450 RPM
and in Figures 6-9 and 6-10 for tests at 750 RPM. Nomographs were constructed for the four data sets
required for the leading and trailing surfaces at 450 and 750 RPM (Figures 6-7 and 6-11). However,
comparison of the liquid crystal contours with thermocouple data indicated that the liquid crystal paint
calibration had shifted as much as 7.8°C (14°F) (e.g., in one instance the 46.6°C (116°F) liquid crystal
paint calibration had shifted to 38.9°C (102°F)). Consequently, the contours passing through the surface
thermocouple locations were used to characterize the heat transfer. Analysis of the liquid crystal and
thermocouple results suggested a constant shit_ in the paint calibrations was appropriate to compensate
for the effects of rotation. Therefore, a shi_ of 6°C(10°F) was applied to the liquid crystal paint
calibrations for tests with rotation (Figures 6-7 and 6-11) to help in the interpretation of the nomographs.
Iso-heat-transfer coefficient results for the medium flowrate at 450 and 750 RPM are presented in
Figures 6-8 and 6-12, respectively. As noted in the discussions of the thermocouple results, the largest
effects of rotation occurred on the leading surface in the tip section of Region 3 where the heat transfer
decreased by a factor of approximately 5 at the thermocouple location. The large decrease in heat
transfer is the result of a rotation induced flow redistribution in the exiting, Region 4, passages.
Comparing the contours of heat transfer coefficient with rotation (Figures 6-8 and 6-12) with those from
the stationary test (Figure 6-4) the flow structure is significantly different on the leading surface. The
flow structure in the outward passage of Region 4 is centerflowing when stationary and skewed when
rotating as a result of the blockage in the Region 3 tip section.
64
Isotherms
1 - 46.7 °C (116 °F)
2 - 43.3 °C (110 OF)
3 - 37.8 °C (100 OF)
4 - 32.2 °C ( 90 °F)
5 - 26.7 °C( 80 °F)
6 - 21.1 °C( 70 °F)
Video Times
1 - 18.9 sec2 - 30.9 sec
ID System_
Jl Time '
Isotherm
12
12
11
22
11
Figure 6-5. Video Records of Liquid Crystal Isotherms for Test 16.3.
65
Isotherms
1 - 46.7 °C (116 OF)
2 - 43.3 °C (110 OF)
3 - 37.8 oc (100 °F)4 - 32.2 °C ( 90 °F)
5 - 26.7 °C ( 80 °F)
6 - 21.1°C( 70 °F)
Video Times1 - 17.0 sec
2 - 26.0 sec
3 - 49.7 secTime
Isotherm
32
\
11, 22, 33
11, 22, 33
11, 22
3312
13
12
21
11, 22, 33
O
23
12, 23
12
23
13
Figure 6-6. Video Records of Liquid Crystal Isotherms for Test 10.2.
66
tO00
a) Leading SurfaceTest 16.3
Tin (start) = 51.7 °C (125 °F)
Tin (end) = 23.9 °C ( 75 °F)Data from Figs. 5-5 & 5-6
[-Iso erms I I [3 2--1
i000
b) Trailing SurfaceTest 10.2
Tin (start) = 52.8 °C (127 °F)
Tin (end) = 18.3 °C ( 65 °F)Data from Figs. 5-7 & 5-8
Isotherms - I [3 2--1
8
tO0
I0
160
2 1 Time100
\\\\'"'_ \ \ 8
\'_ x\\,\ , XX
t 0\\\ . \ \. _ _ F.)¢_..
\",Y ,%\ _111 s,o"<&\/111See _5
t3B_ 7 a_,_ I0
_ _o __ 25
25 ',_MI 8O884) 30
O'88"84) 30 _ _ _5
35 • -H-H-F 4040 >aa+x_ 50
50 I
80 tO0 t20 60
Twall, deg F
,..3--:2-1- Time
\ N,_ X
80 100
Twall, deg F
t20
Figure 6-7. Nomograph for Evaluating Liquid Crystal Data for Re = 13,000 and f) = 450 rpm.
Notes: Dotted iso-coefficients from TC data.
Iso-coefficients interpolated between values at TC locations
due to liquid crystal calibration shift with rotation.
O_
8
a) Leading SurfaceTest 16.3
O
V
b) Trailing SurfaceTest 10.2
® 10
7
9
5
10
Figure 6-8. Heat Transfer Coefficients From Liquid Crystal Isotherms for Re = 13,000 and f2 = 450 rpm.
Isotherms
1 - 46.7 °C (116 °F)
2 - 43.3 °C (110 °F)
3 - 37.8 °C (100 °F)
4 - 32.2 °C ( 90 °F)
5 - 26.7 °C ( 80 °F)
6 - 21.1 °C ( 70 °F)
Video Times
1 - 15.6 sec
2 - 23.8 sec3 - 43.9 sec4 - 58.0 sec
ID System
Time
Isotherm
2311
33
22
Figure 6-9. Video Records of Liquid Crystal Isotherms for Test 16.4.
69
Isotherms
1 - 46.7 °C (116 °F)
2 - 43.3 °C (110 °F)
3 - 37.8 °C (100 °F)
4 - 32.2 °C( 90 °F)
5 - 26.7°C( 80 °F)
6 - 21.1 °C ( 70 °F)
Video Times1 - 19.4 sec
2 - 32.9 sec
3 - 99.0 sec
ID System
Time _
Isotherm
32
11
22, 33
\
21
12
o
o
o o
o o
13
12, 23
1213
11, 22, 33
12
12
13
12
Figure 6-10. Video Records of Liquid Crystal Isotherms for Test 12.2.
7O
t000
a) Leading SurfaceTest 16.4
Tin (start) = 51.1 °C (124 °F)
Tin (end) = 22.8 °C ( 73 °F)Data from Figs. 5-9 & 5-10
b) Trailing SurfaceTest 12.2
Tin (start) = 51.1 °C (124 °F)
Tin (end) = 25.0 °C ( 77 °F)
Data from Figs. 5-11 & 5-12
I I000 I
Isotherms-- Isotherms--4._ 3 _ 2 --1 - -- 3 2--1
.,4
8
100
I0
t60
4_3 __2_1_ Time _ _. too 3:_2 -- 1--Time-
\\
G'K'% '
_ See' ,_\,X&\l [I _5Sec
'° \NI_ 25
25 _"Pa,k_ 08.0_0 30
30 l_ _ 35
35 _ 40
-H-'H-+ 40 _ 50
x-x-w.w-K50 I
80 100 120 60 80 tOOTwall, deg F Twall, deg F
,, \ XI_
120
Figure 6-11. Nomograph for Evaluating Liquid Crystal Data for Re = 13,000 and f_ ---750 rpm.
Notes: Dotted iso-coefficients from TC data.
Iso-coefficients interpolated between values at TC locations
due to liquid crystal calibration shift with rotation.
.,,abo
6
12
6
a) Leading Surface b) Trailing SurfaceTest 16.4 Test 12.2
I _
/50
\
10
®
Figure 6-12. Heat Transfer Coefficients From Liquid Crystal Isotherms for Re -- 13,000 and f2 = 750 rpm.
7.0 COMPARISON WITH PREVIOUS ANALYSIS
Only general heat transfer characteristics can be compared due to the differences in operating
conditions and the lack of velocity and pressure data within the model. The largest noticeable difference
in the flow fields and heat transfer between the four sets of calculations, Ippolito, 1991, Dawes, 1992,
Steinthorsson et al., 1991, and Stephens et al., 1993, occurs in Region 2 where the flow is radially
inward. The results of Ippolito, 1991, and Steinthorsson 1991, show higher velocities along the outer or
tip section of Region 2 and along the divider between Region 2 and Region 3. The results of Dawes,
1992, and Stephens, et al., 1993, show higher velocities in the center of the Region 2 passage. High heat
transfer accompanied the higher velocities in the preceding calculations. The results from both the
rotating and stationary heat transfer experiments show the highest heat flux in the center of the channel
with the characteristic predicted by Dawes, 1992, and Stephens et al., 1993. More recent work by
Steinthorsson, 1993, with a finer grid also produced (unpublished) results with the flow tending toward
the center of the Region 2 passage.
A second region in which general characteristics can be compared is the tip section of Region 3.
All the analyses showed low velocities and low heat transfers in this region. However, from the
numerical results presented, it does not appear that a significant difference was predicted by any of the
analyses in the heat transfer between the leading and trailing surface.
The heat transfer contours predicted by Ippolito, 1991, in the root section of Region 3 also
resemble the contours measured and have larger heat transfer coefficients on the leading surface than the
trailing surface. Recall that the experimental results from the leading and trailing surfaces of the root
section, Region 3, indicated increased levels of heat transfer with rotation for certain rotation numbers.
The shapes of the Region 4 heat transfer contours predicted by Ippolito, 1991, in the root, middle,
and tip passages resemble the contours measured.
Several of the heat transfer characteristics measured in the 1.15 scale model of the NASA LeRC
High Temperature Radial Turbine appear to be predicted by one or more of the numerical studies.
However, a more complete evaluation of the numerical procedures by direct comparison with the present
experiments requires that calculations be made using the boundary conditions of the experiment,
including possibly the conjugate heat transfer condition of the transient heat transfer experiment.
73
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Thermography in Rotating Turbomachinery Heat Transfer Research", ASME Preprint 91-GT-354.
Calvert, G.S., Beck, S.C., and Okapuu, E., 1971, "Design and Experimental Evaluation of a
High-Temperature Radial Turbine", USAAMRDL TR 71-20.
Clifford, R.J., Jones, T.V., and Dunne, S.T., 1983, "Techniques for Obtaining Detailed Heat
Transfer Coefficient Measurements Within Gas Turbine Blade and Vane Cooling Passages," ASME
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Clifford, R.J., 1985, "Rotating Heat Transfer Investigations on a Multipass Cooling Geometry",
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Dawes, W.N., 1992, "The Solution-Adaptive Numerical Simulation of the 3D Viscous Flow in
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EI-Husayini, H.A., Taslim, M.E. and Kercher, D.M., 1992, "Experimental Heat Transfer
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Hajek, T.J., Wagner, J.H., Johnson, B.V., Higgens, A.W., and Steuber, G.D., 1991, "Effects of
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74
Hammer, A.N., Aigret, G.G., Psichogios, T.P., and Rodger, C., 1986, "Fabrication of Cooled
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Han, J.C., Park, J.S. and Ibrahim, M.Y., 1986, "Measurement of Heat Transfer and Pressure
Drop in Rectangular Channels with Turbulence Promoters", NASA Contractors Report 4015.
Ippolito, J., 1991, "Three Dimensional Flow Analysis of the Internal Passage of a Cooled Radial
Rotor", Analysis and Design Application Company, LTD., Report Number 30-02-004, April 26, 1991.
Johnson, B.V., Wagner, J.H., Steuber, G.D. and Yeh, F.C., 1992, "Heat Transfer in Rotating
Serpentine Passages with Trips Skewed to the Flow", ASME Paper 92-GT-191.
Johnson, B.V., Wagner, J.H., and Steuber, G.D., 1993, "Effect of Rotation on Coolant Passage
Heat Transfer: Volume II - Coolant Passages with Trips Normal and Skew to the Flow", NASA
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Johnston, J.P., Halleen, R.M., and Lezius, D.K., 1972, "Effects of Spanwise Rotation of the
Structure of Two-Dimensional Fully Developed Turbulent Channel Flow", J. Fluid Mech., Vol 56, Part 3,
pp 533-557;
Kreith, F., 1973, "Principles of Heat Transfer" 3rd Edition, Intex Press, Inc., pp 177.
Kumar, G.N. and Deanna, R.G., 1998, "Development of a Thermal and Structural Analysis
Procedure for Cooled Radial Turbines", ASME Paper 88-GT-18.
Kumar, G.N, and Deanna, R.G, , 1989, "A Generalized One Dimensional Computer Code for
Turbomachinery Cooling Passage Flow Calculations", NASA Technical Memorandum 102079.
Metzger, D.E. and Larson D.E., 1986, "Use of Melting Point Surface Coatings for Local
Convective Heat Transfer Measurements in Rectangular Channel Flows with 90-deg Turns", ASME J.
Heat Transfer, Vol 108, pp 48.
75
Metzger, D.E., Bunker, R.S., and Bosch, G., 1989, "Transient Liquid Crystal Measurement of
Local Heat Transfer on a Rotating Disk with Jet Impingement", ASME Paper 89-GT-287.
Mochizuki, S., Takamura, J., Yamawaki, S., and Yang, W.J., 1992, "Heat Transfer in Serpentine
Flow Passages with Rotation", ASME Paper 92-GT-190
Morris, W.D., 1981, Heat Transfer and Fluid Flow in Rotating Coolant Channels, Research
Studies Press.
Roelke, R.J, 1991, Coordinates for Coolant Passage Core of NASA LeRC High-Temperature
Cooled Radial Turbine, Private Communication.
Saabas, J., Arora, S.C., and Abdel Messeh, W., 1987, "Application of the Transient Test
Technique to Measure Local Heat Transfer Coefficients Associated with Augmented Airfoil Cooling
Passages", ASME Paper 87-GT-212.
Schultz, D.L., Jones, T.V., Oldfield, M.L.G., and Daniels, L.C., 1973, "Heat Transfer
Measurements in Short-Duration Hypersonic Facilities", Agardograph 165.
Snyder, P.H., 1992, "Cooled High-Temperature Radial Turbine Program", NASA CR 189122,
USAACSCOM TR-92-C-010, Allison Report No. EDR 15982, May 1992.
Snyder, P.H. and Roelke, R.J., 1988, "The Design of an Air-Cooled Metallic High Temperature
Radial Turbine," Conference Preprint AIAA-88-2872.
Steinhorsson, E., Shih TI-P and Roelke R.J., 1991, "Computation of the Three-Dimensional Flow
and Heat Transfer Within a Coolant Passage of a Radial Flow Turbine", Conference Preprint AIAA-91-
2238. 1991.
Steinthorsson, E., Liou, M.S., and Povinelli, L.A., 1993, "Development of an Explicit
Multiblock/Multigrid Flow Solver for Viscous Flows in Complex Geometries", Conference Preprint
AIAA-93-2380.
Steinthorsson, E., 1993, "Private Communication", July.
76
Stephens, M.A.., Rimlinger, M.J., and Shih T.I-P, 1993, "Chimera Grids in the Simulation of
Three-Dimensional Flowfields in Turbine-Blade-Coolant Passages", Conference Preprim AIAA-93-2559.
Vershure, R.W., Large, G.D., Meyer, L.J., and Lane, J.M., 1980, "A Cooler Laminated Radial
Turbine Technology Demonstration", AIAA Paper 80-0300.
Wagner, J.H., Johnson, B.V., and Hajek, T.J., 1991, "Heat Transfer in Rotating Passages with
Smooth Walls and Radial Outward Flow", ASME Turbomachinery, Vol. 113 pp 42-51, January (ASME
Paper 89-GT-272).
77
78
9.0APPENDIX
79
9.1 Nomenclature
d
H
Hr
k
QwR
Re
Ro
t
T
V
W
x
(X
_t
£0
P
Hydraulic diameter, 2HW/(H+W)
Leading to trailing surface separation difference
Heat transfer coefficient, Btu/Ft2/hrFF
Thermal conductivity
Heat flux, Btu/Ft2/hr
Radial position
Reynolds number
Rotation number
Time
Temperature
Coolant velocity
Width of coolant passage
Distance into model wall
Thermal diffiasivity
Dynamic viscosity
Rotation rate rad/sec
Density
Subscripts:
b, c
w, wall
d
h
Bulk fluid property
Fluid property at the wall
Parameter based on hydraulic diameter
Parameter based on separation distance
80
9.2 Tables of Flow Conditions for Full Scale NASA Radial Turbine and 1.15 Scale Model
Coolant Passage
Note:
Model pressures noted are derived from an average of the measured pressures at the flowmeter locations
upstream and downstream of the rotating facility. Temperatures were measured in the model coolant
passage. For parametric analysis the wall temperature, Tw, was assumed to be the initial coolant
temperature prior to the transient portion of a test and the coolant temperature, To, was assumed to be
the inlet coolant temperature at 150 seconds. These two temperatures provided the ideal heat transfer
potential used for comparisons of the test results.
81
NASA RadialTurbine Full Scale
LocationFlowratcRadius
H
WPc
TcTwROh
REdBUOY
DensityVelocityRPM
Omegad
area
visc(mu)k
A0.0154
6.8
0.1100.246
24.5600
7500.02872949
0.00960.110742.6
215962261.5
0.1520.0001881.42E-05
0.0180
B
0.01546.8
0.1100.826
18.0650750
0.06427086
0.03330.075326.2
215962261.5
0.1940.0006311.46E-05
0.0186
C
0.01546.8
0.1701.983
12.0
700750
0.22611506
0.1356
0.046142.1
215962261.5
0.313
0.0023411.49E-05
0.0191
#1secin
inin
psiadeg R
degR
#/ft^3ft/sec
rad/secinin^2
lb/sec-ftBTU/ft-hr-F
82
1.15 Full Scale Model
Median Coolant Flow Rate
Stationary Model
Test # : 6.2 Date:
Location AFlowrate 0.0073
Radius 19.0H 0.127W 0.283
Pc 164.2Tc 514.5
Tw 579.9KOh 0.000REd 34676
BUOY 0.0000
Density 0.862Velocity 34.2RPM 0
Omega 0.0d 0.175area 0.000249
visc(mu) 1.24E-05k 0.0152
Test # : 8.1 Date:
Location A
Flowrate 0.0073Radius 19.0
H 0.127W 0.283
Pc 164.0Tc 514.9
Tw 580.7ROh 0.000
REd 34745
BUOY 0.0000
Density 0.861
Velocity 34.3RPM 0
Omega 0d 0.175
area 0.000249
visc(mu) 1.24E-05k 0.0152
B0.0073
19.00.127
0.950164.2514.5
579.90.000
131910.0000
0.86210.2
00.0
0.2230.0008351.24E-05
0.0152
B0.0073
19.00.1270.950
164.0
514.9580.70.000
13217
0.0000
0.86110.2
00
0.223
0.0008351.24E-05
0.0152
C0.0073
16.50.1962.280
164.2514.5
579.90.000
57360.0000
0.8622.7
00.0
0.3600.003095
1.24E-050.0152
C0.0073
16.5
0.1962.280
164.0514.9
580.7
0.0005748
0.00000.861
2.8
00
0.360
0.0030951.24E-05
0.0152
#/sec
ininin
psiadeg P.
deg R
#/ft^3ft/sec
rad/sec
inin^2
lb/sec-ftBTU/ft-hr-F
#/sec
in
in
in
psia
deg Rdeg R
#/ft^3ft/sec
rad/sec
inin^2
lb/sec-ftBTU/ft-hr-F
83
1.15 Full Scale Model
High Coolant Flow Rate
Stationary Model
Test # : 5.2 Date:
Location A
Flowrate 0.0151
Radius 19.0H 0.127W 0.283
Pc 161.0Tc 503.3
Tw 580.7ROh 0.000REd 72196
BUOY 0.0000
Density 0.864Velocity 70.5KPM 0
Omega 0.0d 0.175area 0.000249
visc(mu) 1.23E-05k 0.0151
Test # : 7.1 Date:
Location A
Flowrate 0.0149Radius 19.0
H 0.127W 0.283
Pc 160.2Tc 504.6
Tw 581.8ROh 0.0000REd 71033
BUOY 0:0000
Density 0.858
Velocity 69.98RPM 0
Omega 0.0d 0.175area 0.00025
visc(mu) 1.23E-05k 0.0151
B0.0151
19.00.1270.950
161.0503.3
580.70.00027463
0.0000
0.86421.0
0
0.00.223
0.0008351.23E-05
0.0151
B
0.014919.0
0.127
0.950160.2
504.6581.8
0.000027021
0.00000.858
20.850
0.00.223
0.00083
1.23E-050.0151
C
0.015116.5
0.1962.280161.0
503.3580.7
0.00011943
0.00000.864
5.70
0.0
0.3600.0030951.23E-05
0.0151
C
0.014916.5
0.1962.280
160.2504.6
581.80.0000
117500.0000
0.8585.62
00.0
0.3600.00310
1.23E-05
0.0151
#/sec
inin
in
psiadeg Rdeg R
#/fl^3
ft/sec
rad/secin
in^2lb/see-ft
BTU/ft-hr-F
#/see
inin
in
psia
deg Rdeg R
#/fl^3fl/sec
radlsecinin^2
lb/sec-ftBTU/ft-hr-F
84
1.15 Full Scale Model
Low Coolant Flow Rate
450 rpm
Test # : 16.5 Date:
Location AFlowrate 0.0038
Radius 19.0H 0.127
W 0.283Pc 165.3
Tc 536.8Tw 579.2
ROh 0.027REd 17642BUOY 0.0082
Density 0.832Velocity 18.2RPM 450
Omega 47.1d 0.175
area 0.000249
visc(mu) 1.25E-05k 0.0155
B
0.003819.0
0.1270.950
165.3536.8
579.20.0916711
0.09190.832
5.4450
47.10.223
0.000835
1.25E-050.0155
C0.0038
16.5
0.1962.280165.3
536.8579.2
0.5242918
1.69650.832
1.5
45047.1
0.3600.003095
1.25E-050.0155
#/sec
inin
in
psiadeg R
deg R
#/ft^3IVsec
racl/secin
in^2lb/sec-ft
BTU/ft-hr-F
85
1.15 Full Scale Model
Median Coolant Flow Rate
450 rpm
Test # : 10.2 Date:
Location A
Flowrate 0.0073Radius 19.0I-I 0.127
W 0.283Pc 164.2
Tc 518.9Tw 581.9ROh 0.014
REd 34650
BUOY 0.0034
Density 0.855
Velocity 34.6RPM 450
Omega 47.1d 0.175area 0.000249
visc(mu) 1.24E-05k 0.0153
Test # : 16.4 Date:
Location AFlowrate 0.0074
Radius 19.0
I-I 0.127W 0.283
Pc 164.4Tc 528.5Tw 580.3
ROh 0.014REd 34971
BUOY 0.0026
Density 0.840Velocity 35.7RPM 450
Omega 47.1d 0.175area 0.000249
visc(mu) 1.25E-05k 0.0154
B
0.007319.0
0.1270.950164.2
518.9581.9
0.04813181
0.03790.855
10.3450
47.10.223
0.0008351.24E-05
0.0153
C0.0073
16.5
0.1962.280164.2
518.9581.9
0.2775732
0.6991
0.8552.8450
47.10.360
0.0030951.24E-05
0.0153
B
0.007419.0
0.1270.950
164.4528.5
580.30.047
133030.0293
0.840
10.6450
47.10.223
0.000835
1.25E-050.0154
C
0.007416.5
0.1962.280
164.4528.5
580.30.268
57850.5415
0.840
2.9450
47.10.360
0.003095
1.25E-05
0.0154
#/secin
inin
psia
deg RdegR
#/ft^3ft/sec
rad/secin
in^2lb/sec-ft
BTU/ft-hr-F
#/secin
inin
psiadeg Rdeg R
#/ft^3
ft/sec
md/secin
in^2
lb/sec-ftBTU/t_-hr=F
86
1.15Full Scale Model
High Coolant Flow Rate
450 rpm
Test # : 10.1 Date:
Location A
Flowrate 0.0150
Radius 19.0H 0.127
W 0.283Pc 159.2
Tc 511.2Tw 579.3ROh 0.007
71036BUOY 0.0009
Density 0.841Velocity 71.5RPM 450
Omega 47.1d 0.175area 0.000249
visc(mu) 1.23E-05k "0.0152
Test # : 16.1 Date:
Location A
Flowrate 0.0151Radius 19.0
H 0.127
W 0.283Pc 161.7
Tc 512.7Tw 581.8
ROh 0.007REd 71417
BUOY 0.0009
Density 0.852Velocity 71.2RPM 450
Omega 47.1d 0.175area 0.000249
visc(mu) 1.24E-05k 0.0152
B
0.0150
19.00.127
0.950159.2
511.2579.3
0.02327022
0.00960.841
21.3
45047.1
0.2230.0008351.23E-05
0.0152
C
0.0150
16.50.196
2.280159.2
511.2579.3
0.13411751
0.17720.841
5.7
45047.1
0.3600.0030951.23E-05
0.0152
B
0.0151
19.00.127
0.950161.7
512.7581.8
0.02327167
0.0098
0.85221.2450
47.1
0.2230.0008351.24E-05
0.0152
C
0.0151
16.50.196
2.280161.7
512.7581.8
0.13411814
0.1808
0.8525.7450
47.1
0.3600.0030951.24E-05
0.0152
#/secin
in
in
psiadeg RdegR
#/ft^3ft/sec
rad/sec
inin^2lb/sec-ft
BTUIR-hr-F
#/secin
in
in
psiadeg R
deg tt
#/fl^3ft/sec
md/sec
inin^2
Ib/sec-ftBTU/ft-hr-F
87
1.15 Full Scale Model
Low Coolant Flow Rate
750 rpm
Test # : 12.3 Date:
Location AFlowrate 0.0039
Radius 19.0H 0.127W 0.283
Pc 164.3Tc 546.4
Tw 581.8ROb 0.043REd 18127
BUOY 0.0168
Density 0.812Velocity 19.3RPM 750
Omega 78.5d 0.175
area 0.000249
visc(mu) 1.26E-05k 0.0156
Test # : 16.6 Date:
Lo_tion A
Flowrate 0.0038
Radius 19.0H 0.127
W 0.283Pc 165.2
Tc 542.6Tw 581.6
ROh 0.045REd 17556BUOY 0.0203
Density 0.823
Velocity 18.5RPM 750
Omega 78.5d 0.175area 0.000249
visc(mu) 1.26E-05k 0.0155
B0.0039
19.00.127
0.950164.3
546.4581.80.144
68960.1888
0.8125.8
750
78.50.223
0.0008351.26E-05
0.0156
C
0.0039
16.50.196
2.280164.3546.4
581.80.8242999
3.4866
0.8121.6
750
78.50.360
0.0030951.26E-05
0.0156
B0.0038
19.00.127
0.950165.2
542.6581.6
0.1516678
0.2285
0.823
5.5750
78.5
0.223
0.0008351.26E-05
0.0155
C0.0038
16.50.196
2.280165.2
542.6581.6
0.8632904
4.2197
0.823
1.575078.5
0.3600.003095
1.26E-050.0155
#/sec
ininin
psia
deg Rdeg R
#/ft^3ft/sec
racl/secinin^2
lb/sec-ft
BTUlft-hr-F
#/sec
inin
in
psiadeg R
deg R
#/ft^3
ft/sec
rad/secin
in^2lb/sec-ft
BTU/fi-hr-F
88
1.15 Full Scale Model
Median Coolant Flow Rate
750 rpm
. Test#:
Location
FlowrateRadiusH
WPc
TcTw
ROhREd
BUOY
DensityVelocityRPM
Omegad
area
visc(mu)k
12.2 Date:
A B C0.0075 0.0075 0.0075
19.0 19.0 16.50.127 0.127 0.196
0.283 0.950 2.280164.1 164.1 164.1533.9 533.9 533.9
581.0 581.0 581.0
0.023 0.076 0.43835097 13351 58060.0063 0.0712 1.3146
0.830 0.830 0.83036.3 10.8 2.9
750 750 75078.5 78.5 78.5
0.175 0.223 0.3600.000249 0.000835 0.003095
1.25E-05 1.25E-05 1.25E-050.0154 0.0154 0.0154
Test # : 16.3 Date:
Location AFlowrate 0.0074
Radius 19.0H 0.127
W 0.283
Pc 164.1Tc 529.0
Tw 580.8ROh 0.023REd 34899
BUOY 0.0072
Density 0.838Velocity 35.7RPM 750
Omega 78.5d 0.175area 0.000249
visc(mu) 1.25E-05k 0.0154
B C
0.0074 0.007419.0 16.5
0.127 0.1960.950 2.280
164.1 164.1529.0 529.0
580.8 580.8
0.078 0.44613275 5773
0.0812 1.49910.838 0.838
10.6 2.9750 750
78.5 78.50.223 0.360
0.000835 0.0030951.25E-05 1.25E-05
0.0154 0.0154
#/secinin
in
psiadeg R
deg R
#/ft^3
ft/sec
rad/secinin^2
lb/sec-ftBTU/ft-hr-F
#/secin
inin
psia
deg Rdeg R
#/ft^3
ft/sec
rad/secin
in^2lb/sec-ft
BTU/ft-hr-F
89
1.15 Full Scale Model
Median Coolant Flow Rate
750 rpm
Test # : 14.3 Date:
Lo_tion A
Flowrate 0.0074Radius 19.0
H 0.127W 0.283Pc 164.4
Tc 542.0Tw 584.1
ROb 0.023REd 34376
BUOY 0.0056
Density 0.819
Velocity 36.3RPM 750
Omega 78.5d 0.175area 0.000249
visc(mu) 1.26E-05k 0.0156
B
0.007419.0
0.1270.950164.4542.0
584.10.077
130760.0634
0.81910.8750
78.50.223
0.0008351.26E-05
0.0156
C
0.007416.5
0.196
2.280164.4542.0
584.10.4395686
1.17080.819
2.9750
78.50.360
0.0030951.26E-05
0.0156
#/secin
inin
psiadeg R
degR
#/ft^3
ft/sec
rad/secinin^2
Ib/sec-ft
BTUfft-hr-F
9O
1.15 Full Scale Model
High Coolant Flow Rate
750 rpm
Test # : 12.1 Date:
Location AFlowrate 0.0150
Radius 19.0
H 0.127W 0.283Pc 163.6
Tc 522.4Tw 582.2
ROb 0.012REd 70633
BUOY 0.0021
Density 0.846Velocity 71.3RPM 750
Omega 78.5d 0.175area 0.000249
visc(mu) 1.24E-05k 0.0153
Test # : 16.2 Date:
Location A
Flowrate 0.0151
Radius 19.0H 0.127
W 0.283
Pc 161.7Tc 516.3Tw 581.3
ROh 0.012REd 71349
BUOY 0.0022
Density 0.846Velocity 71.7RPM 750
Omega 78.5d 0.175
area 0.000249
,,isc(mu) 1.24E-05k 0.0153
B
0.0150
19.00.127
0.950163.6
522.4582.20.039
268690.0234
0,84621.2
75078.5
0.223
0.0008351.24E-05
0.0153
B
0.015119.0
0.127
0.950161.7
516.3581.3
0.03927141
0.02520.846
21.4750
78.50.223
0.000835
1.24E-050.0153
C
0.0150
16.50.196
2.280163.6522.4
582.20.223
116840.4325
0.8465.7
75078.5
0.3600.003095
1.24E-050.0153
C
0.015116.5
0.196
2.280161.7
516.3581.3
0.22211803
0.46540.846
5.8
750
78.50.360
0.003095
1.24E-050.0153
#/secin
inin
psia
deg RdegR
#/ft^3ft/sec
rad/secinin^2
lb/sec-ftBTU/ft-hr-F
#/secin
in
in
psiadegR
deg R
#/ft^3ft/sec
rad/secinin^2
lb/sec-ftBTU/ft-ltr-F
91
1.15 Full Scale Model
High Coolant Flow Rate
750 rpm
Test # : 14.2 Date:
Location AFlowrate 0.0150
Radius 19.0H 0.127
W 0.283Pc 161.9Tc 523.5
Tw 583.6
ROb 0.011REd 70508BUOY 0.0020
Density 0.835
Velocity 72.2RPM 750
Omega 78.5d 0.175area 0.000249
visc(mu) 1.25E-05k 0.0154
B0.0150
19.00.127
0.950145.0
523.5583.60.034
268210.0184
0.748
24.075078.5
0.2230.000835
1.25E-050.0154
C0.0150
16.50.196
2.280145.0523.5
583.60.198
116640.3394
0.748
6.5750
78.5
0.3600.003095
1.25E-050.0154
#/sec
inin
in
psiadeg R
degR
#/ft^3
It/sec
rad/secinin^2
Ib/sec-ftBTU/ft-hr-F
92
9.3 Sample Data Table for Stationary Test Condition and Medium Flowrate
(Test # 6.2, TC 2)
Time
O1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
16
17
18
19
2O21
22
23
24
25
26
27
28
29
3O
31
32
33
34
35
36
3738
39
4O
41
42
43
44
45
46
47
45
49
50
51
52
5354
55
55
57
58
59
6O
61
62
63
64
65
66
67
T¢
119.9115.5
106.997.2
90.985.4
80.3
77.5
75.1
72.8
70.9
69.6
68.5
67.5
66.6
65.9
65.3
64.6
63.9
63.4
63.162.7
62.3
62.0
61.7
61.4
60.9
60.6
60.6
60.4
60.2
60.2
60.0
59.8
59.4
59.3
59.2
59.0
58.8
58.858.6
58.5
58.3
58.3
58.2
58.1
57.9
57.8
57.7
57.6
57.4
57.5
57.5
57.457.3
57.2
57.2
57.157.0
56.958.9
58.958.8
59.758.6
56.5
58.4
56.4
Tw
120.7
120.6
119.5
118.0
115.8
113.9
111.6109.9
108.3
108.9
105.4
104.1
103.0
101.9
100.6
99.5
98.5
97.6
96.5
95.6
95.0
94.393.5
92.8
92.1
91.4
90.7
90.2
89.8
89.4
88.8
88.3
87.8
87.3
86.8
86.4
86.1
65.7
65.3
64.9
64.6
84.283.9
63.663.3
63.0
82.6
82.3
82.0
81.8
81.6
81.4
81.2
81.0
80.7
80.4
80.2
79.9
79.6
79.4
79.2
79.1
78.7
78.5
78.4
78.2
78.1
78.0
• To
119.9
119.4
117.8
115.1
113.2
111.3
109.0107.5
108.1
104.7
103.2
100.1
101.1
100.1
99.0
98,2
97.5
96.7
95.8
95.2
94.6
94.0
93.392.8
92.3
91.9
91.4
90.9
90.5
90.1
89.7
89.3
89.0
88.6
88.2
87.9
87.6
87.3
86.9
86.7
86.4
86.165.8
65.565.3
65.1
64.8
54.6
84.5
84.2
63.9
83.7
83.6
83.4
83.1
83.0
82.9
82.7
82.4
82.3
82.1
81.9
81.7
81.6
81.4
81.2
81.1
80.9
Tw'
O.O00E+O0
-1.818E+03
-4.499E+03
-6.693E+03
-5.995E+03
-6.476E+03
-6.638E+03
-6.077E+03
-5.648E+03
-5.310E+03
-4.933E+03
-4.580E+03
-4.372E+03
-4.195E+03
-4.109E+03-3.829E+03
-3.630E+03
-3.355E+03
o3.257E+03
-2.870E+03
-2.752E+03
-2.745E+03
-2.616E+03
-2.535E+03
-2.388E+03-2.236E+03
-2.195E+03
-1.899E+03
-1.768E+03
-1.826E+03
-1.771 E+03-1.703E+03
-1.755E+03
-1.647E+03
-1.615E+03
-1.493E+03
-1.427E+03
-1.315E+03
-1.397E+03
-1.322E+03
-1.223E+03
-1.221 E+03
-1.132E+03
-1.119E+03
-1.167E+03
-1.185E+03-1.063E+03
-9.698E+02-9.076E+02
-8.724E+O2-7.656E+O2
-7.797E+00-7.692E+O2
-8.988E+02
-9.489E+02
-9.166E+02
-9.125E+02
-9.013E+02
-8.588E+O2
-7.174E+02
-7.829E+02
-7.736E+02
-7.501E+02
-6.513E+00
-5.626E+02
-5.411E+O2
-5.620E+02
-5.171E+02
Q
1.0(X)E-02
3.020E+01
1.175E+022.390E+02
3.292E+02
3.888E+02
4.517E+02
4.960E.H)2
5.209E+02
5.4O6E+02
5.567E+02
5.667E+02
5.748E+00
5.829E+02
5.915E+02
5.975E+02
6.000E+026.001E+02
5.998E+02
5.965E+02
5.908E+025.895E+02
5.888E+02
5.871E+02
5.846E+02
5.803E+02
5.768E+02
5.706E+02
5.617E+02
5.509E+02
5.543E+02
5.506E+02
5.486E+02
5.465E+02
5.432E+02
5.393E",'02
5.342E+925.288E+02
5.253E+02
5.230E+02
5.164E+02
5.141E+02
5.100E+02
5.058E+02
5.033E+02
5.004E+02
4.998E+02
4.945E+02
4.888E+O2
4.637E+02
4.762E+02
4.729E+02
4.689E+02
4.676E+024.685E+02
4.680E+024.667E+02
4.654E+024.635E+02
4.592E+02
4.5,56E+02
4.541E+024.519E+02
4.481E+02
4.426E+O2
4.375E+02
4.339E+02
4.305E+02
H NUR NU QW &T HR Z_o/p1.000E-02 1.000E-O2 1.000E-02 1.000E-02 8.020E-01 1.000E-02 -O.0014 *
5.913E+00 3.209E+01 3.063E+01 3.133E+01 5.057E+00 6.195E+O0 -0.0088
9.319E+00 5.387E+01 4.863E+01 1.280E+02 1.240E+O1 1.032E+01-0.0017
1.150E+01 6.559E+01 6.052E+01 2.539E+02 2.037E+01 1.246E+01 -0.0360
1.320E+01 7.597E+01 6.994E+01 3.495E+02 2.437E+01 1.434E+01 -0.0433
1.363E+01 7.769E+01 7.261E+01 4.064E+02 2.787E+01 1.458E+01-0.0497
1.440E+01 8.278E+01 7.717E+01 4.726E+02 3.060E+01 1.545E+01 -0.0549
1.532E+01 8.732E+01 8.24OE+01 5.119E+02 3.153E+01 1.624E+01 -0.0568
1.571E+01 8.955E+01 8.477E+01 5.356E+02 3.227E+O1 1.660E+01 -0.0583
1.586E-=,O1 9.021E+01 8.562E+01 5.530E+02 3.317E+01 1.667E+O1 -0.0601
1.614E+01 9.215E+01 8.755E+01 5.700E+02 3.356E+01 1.699E÷01 -0.0610
1.640E+01 9.361E+O1 8.914E+O1 5.786E+02 3.361E+01 1.722E+01-0.0613
1.670E+01 9.529E+01 9.093E+01 5.85,4E+02 3.346E+01 1.750E+01 -0.0612
1.695E+01 9.681E+01 9.248E+01 5.928E+O2 3.341E+01 1.775E+01 -0.0612
1.739E+01 9.984E+O1 9.505E+01 6.031E+02 3.3O2E+01 1.827E+01 -0.0607
1.780E+01 1.O21E+02 9.743E+01 6.075E+02 3.256E+01 1.866E+01 -0.0600
1.806E+01 1.036E+02 9.897E+O1 6.089E+02 3.221E+01 1.890E+01 -0.0595
1.821E+01 1.045E+02 9.995E+01 6.083E+02 3.194E+01 1.905E+01 -0.0591
1.842E+01 1.061E+02 1.012E+02 6.096E+02 3.156E+O1 1.932E+01 -0.0585
1.850E+01 1.064E+02 1.018E+02 6.041E+02 3.124E+01 1.934E+01 -0.056O
1.652E+01 1.063E+02 1.020E+O2 5.968E+02 3.091E+01 1.931E+01 -0.05751.863E+01 1.070E+02 1.026E+02 5.954E+O2 3.066E+01 1.942E+01 -0.0571
1.886E+01 1.08BE.H02 1.041E+02 5.961E+O2 3.022E+01 1.972E+01 -0.0564
1.906E+01 1.099E+O2 1.052E+O2 5.935E+02 2.982E+01 1.990E+01 -0.0557
1.922E+01 1.108E+02 1.062E+02 5.906E+02 2.944E+01 2.006E+01 -0.0551
1.932E+01 1.116E+O2 1.068E+02 5.867E+02 2.907E+01 2.018E+01 -0.0545
1.934E+01 1.117E+02 1.070E+02 5.827E+02 2.886E+O1 2.019E+01 -0.0542
1.933E+01 1.116E+02 1.071E+02 5.757E+02 2.856E+01 2.016E+01 -0.0536
1.922E+01 1.107E+02 1.065E-H)2 5.650E+02 2.628E+01 1.998E+01 -0.0531
1.920E+01 1.106E+02 1.064E+02 5.603E+02 2.807E+O1 1.996E+01 -0.6528
1.943E+01 1.125E+02 1.078E+02 5.6O0E+02 2.76OE+01 2.029E+01 -0.0520
1.958E+01 1.132E+00 1.086E+O2 5.549E+02 2.720E+O1 2.040E+01 -0.0513
1.972E+01 1.14OE+O2 1.094E+02 5.528E+02 2.691E+01 2.054E+01 -0.0508
1.990E+01 1.154E+02 1.165E+02 5.515E+02 2.655E+01 2.077E+01 -0.0502
1.978E+01 1.145E+02 1.099E+02 5.471E+02 2.656E+01 2.060E+O1 -0.0502
1.988E+01 1.152E+O2 1.106E+02 5.431E+02 2.623E+01 2.071E+01 -0.0496
1.984E+01 1.148E+02 1.104E+02 5.372E+02 2.6O3E+01 2.064E+01 -0.0493
1.979E+01 1.145E+02 1.101E+02 5.319E+02 2.584E+01 2.059E+01 -0.0490
1.987E+01 1.153E+O2 1.107E+02 5.293E+02 2.556E+01 2.071E+01 -0.0485
2.000E+01 1.16OE+O2 1.114E+02 5.264E+O2 2.528E+O1 2_083E+O1 -0.0480
1.995E+01 1.156E+02 1.112E+02 5.211E+O2 2.512E+01 2.074E+01 -0.0477
1.999E+01 1.161E+02 1.114E+02 5.177E+02 2.486E+01 2.082E+01 -0.0473
1.987E+01 1.152E+O2 1.108E+02 5.124E+02 2.482E+01 2.065E+01 -0.0472
1.995E+01 1.158E+02 1.113E+02 5.034E+02 2.449E+01 2.076E+01 -0.0466
2.003E+01 1.163E+O2 1.118E+02 5.059E+02 2.428E+01 2.083E+01 -0.04622.018E+01 1.173E+02 1.126E+02 5.055E+02 2.4O6E+01 2.101E+01 -0.0459
2.025E+01 1.179E+O2 1.131E+02 5.032E+02 2.384E+01 2.1tlE+01 -0.04552.019E+01 1.173E+02 1.128E+02 4.971E+02 2.367E+01 2.100E+01 -0.0452
2.010E+01 1.168E+02 1.123E+02 4.913E+02 2.350E+01 2.090E+01 -0.0449
2.000E+01 1.162E+02 1.118E+02 4.658E+02 2.338E+01 2.078E+01 -0.0446
1.975E+01 1.145E+02 1.104E+02 4.797E+02 2.342E+01 2.O48E+01 -0.0447
1.977E+01 1.148E+O2 1.106E.HT2 4.749E+02 2.313E+01 2.053E+01 -0.0442
1.973E+01 1.145E+02 1.103E+02 4.704E+02 2.299E+01 2.046E+01 -O.04391.979E+01 1.149E+02 1.107E+O2 4.694E+02 2.285E+01 2.055E+01 -0.0437
2.001E+01 1.165E+02 1.120E+02 4.716E+02 2.263E+01 2.084E+01 -0.0433
2.018E+01 1.175E+02 1.129E+02 4.704E+02 2.242E+01 2.098E+01 -0.0429
2.03OE+01 1.182E+O2 1.137E+02 4.689E+02 2.221E+01 2.111E+01 -0.0426
2.040E+01 1.189E+02 1.143E+02 4.677E+02 2.204E+01 2.122E+01 -0.0423
2.O48E+01 1.196E+O2 1.145E+O2 4.664E+O2 2.186E+O1 2.134E+01 -0.0419
2.O44E+01 1.191E+02 1.146E+02 4.612E+O2 2.170E+01 2.126E+01 -0.0416
2.044E+01 1.190E+02 1.145E+02 4.570E+O2 2.153E+01 2.123E+01 -0.0413
2.046E+01 1.191E+02 1.147E+02 4.555E+O2 2.144E+01 2.125E+01 -0.0412
2.057E+01 1.202E+O2 1.153E+02 4.548E+O2 2.121E+01 2.144E+01 -0.0408
2.047E,_'-O1 1.193E+02 1.148E+02 4.498E+02 2.114E+01 2.128E+01 -0.0406
2.031E+01 1.183E+02 1.139E+02 4.440E+02 2.105E+01 2.109E+01 -0.0405
2.016E+01 1.174E+02 1.131E+02 4.387E+O2 2.097E+01 2.092E+01 -0.0403
2.002E+01 1.165E+02 1.123E+02 4.351E+02 2.095E+01 2.077E+01 -0.04031.994E+O1 1.161E+02 1.119E+02 4.318E+02 2.087E+01 2.069E+01 -0.0401
94
68 56.3
69 56,570 56.4
71 56.3
72 56.3
73 56.3
74 56.3
75 56.276 56.3
77 56.2
78 56.3
79 56.280 56.1
61 56.0
82 56.8
83 56.7
84 55.6
85 55.8
86 55.8
87 56.888 55.7
89 55.5
90 56.4
91 55.4
92 55.4
93 55.4
94 56.4
95 55.4
95 55.497 56.4
98 55.4
99 55.5
100 55.5
101 56.3
102 56.4
103 55.3
194 55.3
105 56.3
106 55.2
107 55.2
108 55.2
109 55.2
110 55.2111 55.1
112 55.1
113 55.2
114 55.0
115 55,0
116 55.0
117 55.0
118 54.9
119 54.9
120 54.9
121 55.0
122 54.9
123 54.8
124 54.8
125 54.9
126 54.8127 54.9
128 54.9
129 54.9
130 54.9131 54.8
132 54.7
133 54.8
134 54.7135 54.6
136 54.7
77.9 80.8-3.976E+02 4.249E+02 1.968E+01
77.8 80.7-5.041E+02 4.209E+02 1.969E+01
77.7 80.5-6.535E+02 4.219E+02 1.979E+01
77.4 80.4-5.239E+02 4.210E+02 1.994E+01
77.3 80.3-6.696E+02 4.200E+02 2.004E+01
77.1 80.1-6.430E+02 4.208E+02 2.026E+0176.9 79.9-5.712E+02 4.189E+02 2.033E+01
76.7 79.8-4.873E+02 4.151E+02 2.027E+01
76.6 79.7-4.861E+02 4.115E+02 2.027E+01
76.5 79.6-4.742E+02 4.089E+02 2.018E+01
76.4 79.4-5.279E+02 4.074E+02 2.022E+01
76.2 79.4-6.012E+02 4.078E+02 2.035E+01
76.2 79.3-6.022E+02 4.083E+02 2.036E+01
75.8 79,2-5.620E+02 4.077E+02 2.054E+01
75.7 79.1-5.246E+02 4.058E+02 2.038E+01
75.5 79.0-5.599E+02 4.043E+02 2.043E+01
75.3 78.8-5.169E+02 4.030E+02 2.046E-',-01
75.3 78.7-4.422E+02 3.999E+0_ 2.054E+01
75.1 78.6-4.566E+02 3.971E+02 2,053E+01
75.0 78.5-3.559E+02 3.937E+02 2.045E+01
74.9 76.4-3.779E+02 3.900E+02 2.031E+01
74.8 78.2-4.184E+02 3,885E+02 2.015E+01
74.6 78.1-3.230E+02 3.857E+02 2.008E+01
74.6 78.0-2.835E+02 3.814E+02 1.989E+01
74.5 77.9-2.646E+02 3.776E+02 1.972E+01
74.5 77.9-2.809E+02 3.747E+02 1.962E+01
74.4 77.8-3.251E+02 3.731E+02 1.960E+0174.3 77.8-,4.563E+02 3.741E+02 1.981E+01
74.2 77.7-4.069E+02 3.748E+02 1.997E+01
74.0 77.5-4,100E+02 3.737E÷02 2.006E+01
73.9 77.4 -3.032E+02 3.711E+02 2.006E÷01
73.8 77.3-3.888E+02 3.692E+02 2.012E+01
73.7 77.2-3.530E+02 3.685E+02 2.022E+01
73.7 77.1-3.127E+02 3.662E+02 1.998E+01
T3.6 77.1-3.583E+02 3.647E+02 2,007E+0173.5 77.0-2.434E+02 3.922E+02 1.996E+01
73.4 76.9-3.775E+02 3.607E+02 1.996E+01
73.2 76.6-3.524E+02 3.611E+02 2.013E+01
73.1 76.7-2.657E+02 3.586E+02 1.995E+01
73.1 76.6-1.670E+02 3.540E+02 1.977E+01
73.1 76.5 -2.148E+02 3.505E+02 1.965E+01
73.0 76.5-1.851E+02 3.482E+02 1.946E+01
73.0 76.4 -2.271E+02 3.462E+02 1.944E+01
72.9 76.3-2.903E+02 3.460E+02 1.945E+01
72.9 76.2-3.322E+02 3.467E+02 1.946E+01
72.7 76.1-4.062E+02 3.481E+02 1.989E+01
72.6 76.0 -3.604E+02 3.488E+02 1.991E+01
72.5 75.9-3.445E+02 3.479E+02 1.989E+01
72.4 75.9 -3.560E+02 3.473E+02 1.993E+01
72.3 75.8-3.126E+02 3.462E+02 2.001E+01
72.2 75.7-2.528E+02 3.438E+02 1.987E+01
72.1 75.7-2.551E+92 3.419E+02 1.987E+01
72.1 75.6-3.240E+02 3.417E+02 1.990E+01
72.0 75.5-4.108E+02 3.430E+02 2.022E+01
71.8 75.5-4.385E+02 3.450E+02 2.036E+0171.7 75.4-2.946E+02 3.438E+02 2.033E+01
71.6 75.3-2.329E+02 3.400E+02 2.018E+01
71.5 75.2-2.746E+02 3.379E+02 2.026E÷01
71.5 75.1-1.671E+02 3.352E+02 2.009E+0171.5 75.1-1.658E+02 3.316E+02 1.994E+01
71.5 75.0-1.230E+02 3.285E+02 1.980E+01
71.5 75.0-1.585E+02 3.261E+02 1.967E+01
71.4 75.0-2.783E+02 3.266E+02 1.971E+01
71.3 74.9-2.879E+02 3.279E+02 1.986E+01
71.2 74.9-3.084E+02 3.283E+02 1.994E+01
71.1 74.8-2.690E+02 3.279E+02 2.017E+01
71.0 74.7-1.726E+02 3.252E+02 1.994E+01
71.0 74.6-1.619E+02 3.221E+02 1.974E+01
70.9 74.6-1.913E+02 3.205E+02 1.970E+01
1.143E+02 1.195E+02 4.252E+02 2.088E+01 2.037E+01 -0.0401
1.145E+02 1.105E+02 4.216E+02 2.068E+01 2.039E+01 -0.03971.153E+02 1.111E+02 4.233E+02 2.061E+01 2.054E+01 -0.0396
1.165E+02 1.120E+02 4.233E+02 2.041E+01 2.074E+01 -0.0393
1.168E+02 1.126E+02 4.211E+02 2.025E+01 2.079E+01 -0.0390
1.183E+02 1.138E+02 4.227E+02 2.007E+01 2.106E+01 -0.0387
1.168E+02 1.142E+02 4.209E+02 1.991E+01 2.114E+01 -0.03841.183E+02 1.139E+02 4.164E÷02 1.978E+01 2.105E+01 -0.0381
1.183E+02 1.139E+02 4.129E+02 1o961E+01 2.105E+01 -0.0378
1.175E+02 1.134E+02 4.093E+02 1.958E+01 2.090E+01 -0.0376
1.179E+02 1.137E+02 4.083E+02 1.947E+01 2.098E+01 -0.0376
1.189E+02 1.144E+02 4.092E+02 1.935E+01 2.114E+01 .0.0374
1.187E+02 1.145E+02 4.090E+02 1.937E+01 2.112E+01 -0.0374
1.205E+02 1.155E+02 4.107E+02 1.916E+01 2.143E+01 -0.0370
1.191E+02 1.147E+02 4.072E+02 1.923E+01 2.117E+01 -0.0372
1.195E+02 1.150E+02 4.062E+02 1.911E+01 2.126E+01 -0.0369
1.196E+02 1.152E+02 4.041E+02 1.903E+01 2.124E+01 -0.0368
1.199E+02 1.156E+02 4.006E+02 1.880E+01 2.131E+01 -0.0364
1.200E+02 1.156E+02 3.982E+02 1.868E+01 2.132E+01 -0.0361
1.195E+02 1.152E+02 3.946E+02 1.859E+01 2.123E+01 -0.0360
1.186E+02 1.144E+02 3.909E+02 1.855E+01 2.107E+01 -0.0359
1.179E+02 1.135E+02 3.899E+02 1.863E+01 2.093E+01 .0.03601.173E+02 1.131E+02 3.866E+02 1.857E+01 2.082E+01 .0.0359
1.160E+02 1.121E+02 3.816E+02 1.854E+01 2.059E+01 -0.0359
1.151E+02 1.111E+02 3.782E+02 1.852E+01 2.042E+01 -0.0358
1.144E+02 1.105E+02 3.751E+02 1.847E+01 2.031E+01 -0.0357
1.144E+02 1.104E+02 3.739E+02 1.841E+01 2.030E+01 -0.03561.157E+02 1.116E+02 3.750E+02 1.826E+01 2.053E+01 -0.0354
1.168E+02 1.125E+02 3.759E+02 1.814E+01 2.072E+01 -0.0351
1.176E+02 1.131E+02 3.756E+02 1.800E+01 2.086E+01 -0.0349
1.173E+02 1.131E+02 3.720E+02 1.788E+01 2.080E+01 .0.0347
1.175E+02 1.134E+02 3.697E+02 1.774E+01 2.085E+01 .0.0344
1.183E+02 1.140E+02 3.697E+02 1.762E+01 2.098E+01 .0.0342
1.156E+02 1.126E+02 3.565E+02 1.772E+01 2.068E+01 .0.0344
1.174E+02 1.132E+02 3.656E+02 1.756E+01 2.081E+01 -0.0341
1.167E+02 1.125E+02 3.630E+02 1.755E+01 2.069E+01-0.0340
1.167E+02 1.126E+02 3.616E+02 1.747E+01 2.070E+01 .0.0339
1.180E+02 1.135E+02 3.625E+02 1.733E+01 2.091E+01 .0.0336
1.167E+02 1.125E+02 3.593E+02 1.738E+01 2.068E+01 .0.0337
1.154E+02 1.115E+02 3.541E+02 1.731E+01 2.045E+01 -0.0336
1.148E+02 1.109E+02 3.511E+02 1.725E+01 2.035E+01 -0.0335
1.134E+02 1.098E+02 3.482E+02 t.732E+01 2.011E+01 -0.0336
1.135E+02 1.097E+02 3.467E+02 1.723E+01 2.012E+01 -0.03341.137E+02 1.098E+02 3.468E+02 1.721E+01 2.015E+01 -0.0334
1.135E+02 1.098E+02 3.467E+02 1.724E+01 2.012E+01 -0.03341.168E+02 1.123E+02 3.502E+02 1.692E+01 2.070E+01 -0.0329
1.166E+02 1.124E+02 3.497E+02 1.694E+01 2.065E+01 -0.0329
1.165E+02 1.123E+02 3.489E+02 1.691E+01 2.063E+01 -0.0328
1.168E+02 1.125E+02 3.480E+02 1.685E+01 2.065E+01 -0.03271.172E+02 1.130E+02 3.473E+02 1.673E+01 2.076E+01 -0.0325
1.163E+02 1.122E+02 3.445E+02 1.673E+01 2.060E+01 -0.03251.162E+02 1.122E+02 3.423E+02 1.664E+01 2.057E+01 -0.0323
1.163E+02 1.124E+02 3.421E+02 1.681E+01 2.060E+01 -0.0323
1.168E+02 1.142E+02 3.443E+02 1.639E+01 2.100E+01 -0.0319
1.194E+02 1.150E+02 3.461E+02 1.637E+01 2.114E÷01 -0.0319
1.193E+02 1.149E+02 3.449E+02 1.634E+01 2.112E+01 -0.0318
1.182E+02 1.140E+02 3.407E+02 1.628E+01 2.092E+01 -0.0317
1.168E+02 1.145E+02 3.387E+02 1.611E+01 2.102E+01 -0.0314
1.176E+02 1.135E+02 3.357E+02 1.613E+01 2.082E+01 -0.0314
1.155E+02 1.127E+02 3.314E+02 1.607E+01 2.062E+01 -0.0313
1.158E+02 1.119E+02 3.287E+02 1.504E+01 2.049E+01 -0.0312
1.149E+02 1.111E+02 3.260E+02 1.603E+01 2.033E+01 -0.0312
1.154E+02 1.114E+02 3.271E+02 1.602E+01 2.042E+01 -0.0312
1.166E+02 1.122E+02 3.292E+02 1.596E+01 2.062E+01 .0.0311
1.168E+02 1.127E+02 3.289E+02 1.591E+01 2.067E+01 -0.0310
1.185E+02 1.140E+02 3.292E+02 1.571E+01 2.096E÷01 -0.0306
1.168E+02 1.127E+02 3.256E+02 1.577E+01 2.066E+01 .0.0307
1.155E+02 1.116E+02 3.223E+02 1.578E+01 2.042E+01 .0.0307
1.153E+02 1.114E+02 3.209E+02 1.573E+01 2.040E+01 --0.0306
95
137 54.7 70.9 74.5 -9.681E+01 3.179E+02138 54.7 70.9 74.4-1.440E+02 3.153E+02
139 54.7 70.9 74.3 -2.480E+02 3.158E+02
140 54.7 70.8 74.2 -3.249E+02 3.181E+02141 54.9 70.6 74.2 -3.718E+02 3.206E+02
142 54.7 70.5 74.2 -3.068E+02 3.212E+02
143 54.5 70.4 74.1 -2.303E+02 3.193E+02
144 54.5 70.4 74.1 -2.605E+02 3.179E+02
145 54.6 70.3 74.0 -2.215E+02 3.168E+02
145 54.5 70.2 74.0-1.541E+02 3.143E+02
147 54.6 70.2 73.9-1.226E+02 3.112E+02
148 54.6 70.2 73.8-1.761E+02 3.096E+02
149 54.6 70.1 73.8 -2.568E+02 3.103E+02
150 54.5 70.1 73.8 -2.739E+02 3.115E+02
1.953E+01 1.141E+02 1.104E+02 3.178E+02 1.575E+01 2.018E+01 -0.03071.947E+01 1.139E+02 1.101E+02 3.156E+02 1.567E+01 2.014E+01 -0.0305
1.959E+01 1.147E+02 1.108E+02 3.163E+02 1.560E+01 2.028E+01 -0.0304
1.979E+01 1.159E+02 1.119E+02 3.184E+02 1.554E+01 2.049E+01 -0.03032.038E+01 1.199E+02 1.151E+02 3.225E+02 1.521E+01 2.121E+01 -0.0297
2.031E+01 1.192E+02 1.148E+02 3.221E+02 1.528E+01 2.107E+01 -0.0298
2.007E+01 1.177E+02 1.135E+02 3.200E+02 1.538E+01 2.081E+01 -0.0300
2.0(X)E+01 1.17;2E+02 1.131E+02 3.184E+02 1.537E+01 2.072E+01 -0.0300
2.014E+01 1.182E+02 1.140E+02 3.176E+02 1.520E+01 2.089E+01 -0.0297
2.000E+01 1.172E+02 1.131E+02 3.147E+02 1.519E+01 2.072E+01 -0.0296
1.983E+01 1.160E+02 1.122E+02 3.111E+02 1.517E+01 2.051E+01 -0.0296
1.975E+01 1.155E+02 1.117E+02 3.096E+02 1.516E+01 2.042E+01 -0.0296
2.000E+01 1.174E+02 1.132E+02 3.112E+02 1.499E+01 2.076E+01 -0.0293
2.005E+01 1.176E+02 1.135E+02 3.121E+02 1.501E+01 2.079E+01 -0.0293
Where:
Time
Tc
Tw
To
Tw'
Q
H
NUR
NU
QWAT
HR
Ap/p
Seconds past start of transient portion of the test
Average coolant inlet temperature, °F
Wall temperature, F
Average coolant outlet temperature, OF
Temporal derivative of the wall temperature variation, OF/hr
Heat flux without paint correction, Btu/ft2/hr
Heat transfer coefficient without paint correction, Btu/ft2/hrFF
Nusselt number with paint correction based on d=l inch, HR*d/k
Nusselt number without paint correction based on d=l inch, HR*d/k
Heat flux with paint correction, Btu/ft2/hr
Temperature difference with paint correction, Tw-Tc, OF
Heat transfer coefficient with paint correction, Btu/ft2/hrFF
Density ratio, -(Pb - Pw)/Pb =-(Tw- Tb)/Tw
96
9.4 Adjusted Thermocouple Results
97
Re = 13,000
a) Tin
140'
120'
100
8O
60'
40-50
RO8T01 Data eeeeeTC02 '
eeeeeTC03_TC01{k@_{_TC04
Tin, avg
i i 1 | 61 i i * I
0 50 100 150Time, sec
0
E-,
140
120
I00'
80 ¸
b) Tou t
R08T01 Data eeeeeTCZ1_eeTC22a_.sTC23
--Tout, avg
6O
4°s'd.......6........s'd.......ido.......isoTime, sec
c) Leading Surface
140
120
100
so
RO8T01 Data eeeeeTC01s_eeeTC02a_a_TC03
_ewTC04
_TC05
_TC07
60
4°s_ .......6........5_.......i60.......i_oTime, sec
d) Trailing Surface
140'
120
I00
80
60
40-50
R08T01 Data
_8TC12_a_aTC13
v_"_vTC14
,J-&a-_TC15BH_-_TC17
Illllll_llJllllll|ll,lllllll
0 50 I00 150
Time, sec
Figure 9.4-1. Thermocouple Data for Liquid Crystal Test on Leading Surface
With _ = 0 rpm.
98
Re= 13,000
a) Leading Surface b) Trailing Surface ,
__,_ °eeeeTC01" I i000 I ROBT01 Data _eee TC121000 R08T01 Data eeeee TC02
-4 // "%. _ TC03 l -I I -a. _.s_.s TC13I V _ _ zco4 1 I I \. _'rc14
J I _ _ TCI5
I I _ _ TCOS i _ J __ _. _ TClV
Ic Iz
c_ c_ i0 50
I00 0 50 I00 150 0 50 I00Time, sec Time, sec
c) Leading Surface
I000 _ ROBT01 Data eeeeeTC01
seeeeTC02
5_ A-_,_TC031 _v_,TC04
_TCO5z_ e_B-_TC07
t _TC08
100
10
t_
o
8
0 50 100Time, sec
d) Trailing Surface
1000 _ R08T01 Data
TCl2_ TC13
_ TCI4TCI5
._ _ _ TC17TCI8
"5
I00
1 i s i i i i i i t _ , i i i i i i i i i i , _ i15o o 5o i66Time, sec
1
50
Figure 9.4-2. Results From Thermocouple Data for Liquid Crystal Test on Leading
Surface With _ = 0 rpm.
99
Re = 13,000
140
120
100
a) Tin
R06T02 Data eoOOOTC02eem_e_TC03_,_TC01_TC04
--- Tin. avg
80'
oo
4°-ag ....... 6........ bg ....... idb ....... iaoTime, see
"d0
(-_
b) Tou t
140
120
100
80,
6O
R06T02 Data_TC21_TC22_r_TC23
*
0 III I''ll'i''ll' '1611 '|'l'll'|i ' ' I ' I I I I I
-50 0 50 100 150Time, sec
c) Leading Surface
140.
120'
100
0
80E._
R06T02 DataeeoeoTC01_TC02_TC03
, v_v_vTC04,_-_TC05e-e-e_TC07
60'
O fllll iliM Jl IIlll4 5_ ....... 6.... 5b "16b' 'i5oTime, see
d) Trailing Surface
140 _ RO6T02 Data
120
100
j so
60 ¸
40-50
eeeeeTCll_TC12_a_TC13_TC14_TCl5
_'_ _ TC17
Illllll_lll#111111#1|llllll#
0 50 100 150Time, see
Figure 9.4-3. Thermocouple Data for Liquid Crystal Test on Trailing Surface
With _ = 0 rpm.
I00
Re = 13,000
a) Leading Surface b) Trailing Surface ,
.1 1ooo --1ooo _ _ roszo2pat. _ _ r \ _ TcI_-i II _x\ _ TC03 [ | ] _ _ TCI3| I/ _ v-v_vv TC04 [ -] [ _ vvv_v TCI4J I "_. _ TC05 I -, "_ _ zcts
_ I00
I00 0 50 100 150 0 50 i00 150Time, see Time, sec
c) Leading Surface
looo i_1_o_o_ pat,, ooo__C01
_eeee TC02TC03
v_,eee TC04_a-a-aa TC05_ TCO7_ TC08
100
[-.. 10
50 100Time, sec
i50
I000
°_
I00
2
10
d) Trailing Surface
R06T02 Data eeeeeTClltmeeeTCl2_TCI3v_TCl4_-_TCI5_TCI7_TCI8
....... ' sb ........ i66 ....... isoTime, see
Figure 9.4-4. Results From Thermocouple Data for Liquid Crystal Test on Trailing
Surface With _ = 0 rpm.
I01
EOI
•rods O_Tz= U q:l!M
a_ejan S _u!p_o'- I uo ]so/. I_ISSaD p!nb!q aoj _eCl oldno:_omuou, i "S-_r'6 aan_!..4
oos 'otu!.I. oos 'owt!j_ogl 00_ og 0 Og- Og_ OOI og 0 og--
......... ' ......... ' ......... ' ......... 0_' ......... ' ......... ' ......... ' ......... O_
8IO&mnnnn
.O9
og0
"x"J
OOI
.08I
a_3_Tns _.m_. sl (p
80D&3031
_l_(I 8019_H
09
0
'-z'J
OOI
.08I
O_zI
oos 'or, n_logI OOI og 0 Og-
......... '............................. O_
09
.og
-4
OOI
08__A_ '_no& --
88D_88D&_ISD_ooooo _fl g0&9IH
O_I
_n° l (q
oos 'ou.q,LOgl OOI og 0 og--
tllllllll|lili'Ittllt'It_it'tllt Ittllit O_
IOO&__OD_80o&oeeee _':t_G _0&glH
.09
-0g
OOI
08I
O_'I
_4
000"£I = o'tl
Rc = 13,000
a) Leading Surface
1000
I RlflT03 Data _ TC02
TC03
_ TC04_s_-DTC07
5-
d
:I
II oolt.........,.........,.........0 50 100
Time, see
b) Trailing Surface
i000 j R16T03 Data eeeee TC11
I TC12
TC13TC14
I "_. _ TC17
d
10150 0 50 100 150
Time, see
I000
o
8_J
c) Leading Surface
R16T03 Data_eee_ TC02
TC03TC04TC05
z _ TC07
100
2-
lO
2
10 50 100
Time, see
i000
8_J
150
2
100
10
d Trailing Surface
RI6T03 Data
TC14
2 _ TCI5TC17TC18
1 o ......... 5b........ i66 ....... i5oTime, see
Figure 9.4-6. Results From Thermocouple Data for Liquid Crystal Test on Leading
Surface With _ = 450 rpm.
.103
Re = 13,000
a) Tin140
120
100
aO,E--,
R10T02 Data eeeeeTC02_TC03_._a_-_TC01(H),0,_TC04
°
60
405'6 ....... 6........ gb ....... i6o ....... i5oTime, see
b) Tou t140
P
E-*
120
100
80
60
40-50
R10T02 Data GeeeeTC21eeeesTC22
il lllll i Itllllllll.illIl lll|lililIllll!
0 50 100 150Time, seo
c) Leading Surface
140 _ RIOT02 Data
I120
100
80,
60
eeeeeTC01_TC02_a_TC03
v_vTC04
A-a_TC05H-B_eTC07
4o_5_ ....... 6........ 'if) ....... i 6b....... i5oTime, sec
140
120
100
d) Trailing Surface
R10T02 Data eeeeeTCll_TCI2a_._TC13
_TCI4
_TC15_TC17
60"
4°5_ ....... 6........ _b ....... idb ....... i50Time, see
Figure 9.4-7. Thermocouple Data for Liquid Crystal Test on Trailing Surface
With £_ = 450 rpm.
104
Re = 13,000
a) Leading Surface b) Trailing Surface ,
1000 _ RIOT02 Data _eeTC017 1000 _ R10T02 Data oeeeeTC11 imn \_. 8eeee TC02 | / seeee TC12 I
q I/ x,k.._ _ TC03 [ 1 a _ TC13 JJ U x_x v._v ZC04 } | (=_- _ TC14 II! _ \"_ _TCOS/ ][ _ _TCtSl41 _ _ _TC071 d I _ _TClV I ',
C_ 5
100 0 O0 100 150 i00" 0 50 i00 150
Time, sec Time, sec
c) Leading Surface d) Trailing Surface
1000 I oeeee TC01_seeeTC02
_TC04_TC05_-_TC07_TC08
100
8q_
RIOT02 Data I000 _eeeeeTCll R10T02 Datal -IE_eee TC12
l l_ TCI4I_ I_ zclsI z4 _ TC17
10 10
0 50 100 150 0 50 100 150Time, sec Time, sec
Figure 9.4-8. Results From Thermocouple Data for Liquid Crystal Test on Trailing
Surface With _ = 450 rpm.
105
Re = 13,000
a) Tm
140.
120'
100
80E-.,
6O
40-50
R16T04 Data eeeeOTC02_TC03_TC01_TC04
I IIIIII II _111111 ] III1 III IIII I IIIII ,1111
0 50 100 150Time, see
b) Tou t
140
F_0
0
120
i00"
80'
6O
40-50
R16T04 Dataeeeee TC21
TC22TC23
ii i lllliil ii ii lllll i lll*ImlIllllllllJEl
0 50 100 150Time, see
c) Leading Surface140
120
100
BO
60
40-50
R16T04 Data_eeeeTC02_TC03vv_v_TC04
___ _TC05_e_TC07
I, IIII, II ]11 II II IIIII III IIII I|1 IIIIII11
0 50 100 150Time, sec
140'
120
100
6O
d) Trailing Surface
40-50
R16T04 Data _eOTC11_TC12_TC13v_TC14
_TC15b_-B-HTC17
II II I11tl II I II II II I II II It1111tl II Iltll I
0 50 I00 150Time, sec
Figure 9.4-9. Thermocouple Data for Liquid Crystal Test on Leading Surface
With _ = 750 rpm.
106
Re = 13,000
a) Leading Surface b) Trailing Surface ,
I000 _ R16T04 Data "[ 1000 _ RI6T04 Data _ TCll
JTC02 [ t _ TC12TC03
/AN.- _ TC04 _ TC13_ _ TC14
l I _t _ TC05 I _._. _ TC15
d d
100 ...... _ 1000 50 100 150 0 50 I00 150
Time, sec Time, sec
c) Leading Surface d) Trailing Surface
i000
°..,
o 100
[...
I R16T04 Data
TC04TC05TC07
TC08
i000?
110 50 100 150
Time, see
RI6T04 Data oeeee TCI1
_eae TCI2
TC13TCI4TC15
TC17(HHH_ TC18
0 50 i00 150Time, see
Figure 9.4-10. Results From Thermocouple Data for Liquid Crystal Test on Leading
Surface With _ = 750 rpm.
107
E-,
140
120
100"
Rc = 13,000
a) Tin
80.
6O-
40"-50
R12T02 Data oeeeeTc02_TC03_TC01
i ; , | , ; . , , ii , s, ,, , * iil ,* , ,, , i i i, , | , ,. , s i
0 50 100 150Time, see
140
120
i00
ao.E-,
b) Tou t
60.
4O-50
R12T02 Data eeeee TC21TC22TC23
0 50 100 150Time, sec
c_
140
120
100"
c) Leading Surface
BO
6oi
R1RT02 Data eeeeeTC01_TC02_a_TC03vv_vTC04_,_-aTC05
40 'I'''' 'fill' 'IIL ''' If'' 'i''' 'ii''l' ' if'
--50 0 50 100 150Time, sec
d) Trailing Surface
140
120
100'
BO'
6oi
R12T02 Data eeeeeTCllmmeeeTCl2_TC13_v_,_TCl4
_TC15_TC17
0' ,,i;,l, ,, IS,,, ,,If| I, II,,, ,ili,|lillill
--50 0 50 100 150Time, sec
Figure 9.4-11. Thermocouple Data for Liquid Crystal Test on Trailing Surface With
= 750 rpm.
108
Re = 13,000
a) Leading Surface
I000 i000Rl_r02 Data _ TC01
eeeee TC02TC031IK _ zco4
1 I N, _ TC0SIf %. _ Tco7
d d
2_ 2-
100 1000 50 100 150 0
Time, see
b) Trailing Surface
R12T02 Data oeeee TC11
seeee TC12TC13
TC14
_ TC15[ _ _ TC17
.........s'o........ idd ....... isoTime, see
"5
8
c) Leading Surface
1000 _ eeeeeTC01 R12T02 Data
-I_ TC02 A5-I _ TC03 It
-I _ TC04 A ]A_t_J _ TC05 i,_ n_u_
z _ TC07
i00
10
1 10 50 150I00
Time, sec
d) Trailing Surface
i000
o 100 _
-
h_ I0 :
2-
R12T02 Data oeeee TC11
8_eee TC12TC13TCI4
TC15TC17
¢_¢d_ TCIB
o.........5b........i6d ........i5oTime, see
Figure 9.4-12. Results From Thermocouple Data for Liquid Crystal Test on Trailing Surface
With f_ = 750 rpm.
109
Form ApprovedREPORT DOCUMENTATION PAGE OMBNo. 0704-0188
Public reportingburdenfor this collectionof Infomlatic_lb esti.maled.to average 1.h_. r I_. rW, Includingthe._._Umel.or_revk__ng ins=_, s_,_,;,,_ e_..ist_=.__c_rC_..l_gatheringand maintainingthe data needed, ano _,ng ano reviewingme comc_ono_ immrrmm., oeno _vrr.,_=.* ,.t_u,.,_ .,? uuff,=, m,,_.w _=,I y.__._"_,_ -_k_o, o__nforma,en.induulngsu0ge_nsforredu_ng_ bumn.tow_in_en Hpa_,a_-s Sm_. 0y_e3_."for2_.Opy..rp_..._a_. Rep0aMS._.'"en_Davis Highway,Suite 1204, Arlington,VA _:".'J02-4302,and to the Office ¢4Managementarm uudget, P,apem_omHeou_uoflr'roje_ (u,'u4-ulee), wasnr, gzm'_,_., ,:u._.
1. AGENCY USE ONLY (Leave blanlO 2. REPORTDATE 3. P,_PORTTYPEANDDA]_SCOVERED
May 1996 Final Contractor Report
4. TITLE AND SUBTITLE 5. FUNDING NUMBERS
Heat Transfer Experiments in the Internal Cooling Passages of a CooledRadial Turbine Rotor
e. AUTHOR(S)
B.V. Johnson and J.H. Wagner
7. pERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES)
United Technologies Research CenterSilver Lane
East Hartford, Connecticut
9. SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS{ES)
National Aeronautics and Space AdministrationLewis Research Center
Cleveland, Ohio 44135-3191
WU-505-452-10
C-NAS3-25952
8. PF.IqFORMING ORGANIZATIONREPORT NUMBER
E-10155
10. SPONSORING/MONITORINGAGENCY REPORT NUMBER
NASA CR-198472
11. SUPPLEMENTARY NOTES
Project Manager, Kestutis C. Civinskas, Prop_ion Systems Division, NASA Lewis Research Center, organization code
2760, (216) 433-3944.
12a. DISTRIBUTION/AVAILABILITY STATEMENT
Unclassified -Unlimited
Subject Category 07
This publication is available from the NASA Center for AeroSpace Information, (301 ) 621--(I390,
12b. DI:SlHIBUTION CODE
13. ABSTRACT (Maximum 200 words)
An experimental study was conducted (1) to experimentally measure, assess and analyze the heat transfer within theinternal cooling configuration of a radial turbine rotor blade and (2) to obtain heat transfer data to evaluate and improve
CFD procedures and turbulent transport models of internal coolant flows. A 1.15 times scale model of the coolant
passages within the NASA LeRC High Temperature Radial Turbine was designed, fabricated of Lucite and iustmmentedfor transient heat transfer tests using thin film surface thermocouples and liquid crystals to indicate temperatures. Tran-
sient heat transfer tests were conducted for Reynolds numbers of one-fourth, one-half, and equal to the operating
Reynolds number for the NASA Turbine. Tests were conducted for stationary and rotating conditions with rotationnumbers in the range occurring in the NASA Turbine. Results from the experiments showed the heat transfer characteris-tics within the coolant passage were affected by rotation. In general, the heat transfer increased and decreased on the sides
of the straight radial passages with rotation as previously reported from NASA-HOST-sponsored experiments. The heattransfer in the tri-passage axial flow region adjacent to the blade exit was relatively unaffected by rotation. However, theheat transfer on one surface, in the transitional region between the radial inflow passage and axial, constant radius
passages, decreased to approximately 20 percent of the values without rotation. Comparisons with previous 3-D numeri-cal studies indicated regions where the heat tmusfer characteristics agreed and disagreed with the present experiment.
14. SUBJECT TERMS
Radial turbine; Cooling; Internal cooling; Cooling passages; Heat transfer
17. SECURITY CLASSIFICATIONOF REPORT
Unclassified
_ISN7540-01-280-5500
;18. SECURITY CLASSIFICATIONOF THIS PAGE
Unclassified
19. SECURITY CLASSIFICATIONOF ABSTRACT
Unclassified
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11816. PRICE CODE
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