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NASA Environmentally Responsible Aviation . Sriram Ganesan & Mukul Atri Final Year B.Tech-M.Tech Dual Degree Students mentored by Dr. Abhijit Kushari Department of Aerospace Engineering Indian Institute of Technology Kanpur. Presentation Outline. - PowerPoint PPT Presentation
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Sriram Ganesan & Mukul Atri Final Year B.Tech-M.Tech Dual Degree Students
mentored byDr. Abhijit Kushari
Department of Aerospace Engineering
Indian Institute of Technology Kanpur
NASA Environmentally Responsible Aviation
2Team VAAYUNovember 15, 2011
Presentation Outline
• Baseline aircraft -Hybrid Wing Body Concept• Baseline Engine-GE90• After Dilation• Geared Turbofan• Stator Noise Reduction• Lean Direct Injection Combustors• Spiroid winglets• Golf-ball wings• Weights estimate
3Team VAAYUNovember 15, 2011
Hybrid Wing Body Concept
• Supercritical outer wing profile• Shorter landing gear via better tail clearance• Propulsive efficiency via Boundary Layer Ingestion (BLI)• 30% reduction in structural weight • Drooped leading edge device• Faired undercarriage for reduction in noise
Source : N+3 Aircraft Concept Designs and Trade Studies, Final Report
4Team VAAYUNovember 15, 2011
Variable Area Nozzle• Reduced jet noise during takeoff, landing• Low fan speed operation• Cruise: Pitch trim- minimizes profile drag• Approach : increased drag using thrust vectoring combined with
elevons
5Team VAAYUNovember 15, 2011
GE 90 Engine Data
• sdCruise Take-off
Height (Km) 10.668 0
Mach No. 0.850 0RAMPR 1.590 1FPR 1.650 1.580LPCPR 1.140 1.100HPCPR 21.5 23OPR 40.44 39.97BPR 8.1 8.4
Cruise Takeoff
Ta 218.820 288.16
Pa 0.239 1.014
TIT (K) 1380.0 1592.0
ma(kg/s) 576.0 1350.0
Thrust (kN) 69.2 375.3
mf(kg/s) 1.079 2.968
SFC (mg/N-s) 15.6 7.91
Intake Fan Compressor Turbine Nozzle Combustion
Polytrophic Efficiency
0.980 0.930 0.910 0.930 0.950 0.99
6Team VAAYUNovember 15, 2011
Trade -Off Plots
7Team VAAYUNovember 15, 2011
Mixed ExhaustState of Art • Augmenters- Low bypass Turbofan Engines
- Takeoff, climb and combat- Atomized fuel ignites the mixture
• Annular Mixers- Shearing effect at stream interface- Low mixing efficiency
• Forced Mixers- Intertwined chutes force mixing- High pressure losses
Source : http://shirshosengupta.blogspot.com/ 2011/04/ jet-engines-101.html
Courtesy of Pratt & Whitney
8Team VAAYUNovember 15, 2011
After Dilation1) Diffuser
2) Mixing Zone
3) Nozzle 6) Iris Nozzle
5) Bleed Valve
4) Bypass Duct
• High pressure differential between core and bypass• Bleed Valve- controls bypass bleed factor κ• Iris nozzle-allows various modes of operation
12
3
4 5
6
9Team VAAYUNovember 15, 2011
Modes of Operation
κ=0 κ=0.4 κ=0.8
10Team VAAYUNovember 15, 2011
Boundary conditionsInlet conditions:Bypass: Core :• P08=62689 Pa P05=38143 Pa
• T08=291.97 K T05=576.69 K
• P8=52848 Pa P5=37467 Pa
Exit:• Pa=23900Pa• Ta=218 K
11Team VAAYUNovember 15, 2011
Temperature Profile• 2-d simulations conducted
using ANSYS fluent• Mixing converts thermal
energy to kinetic energy• Quick dissipation due
to efficient turbulent mixing
12Team VAAYUNovember 15, 2011
Velocity Profile• Mixing at the interface• Bleed valve optimization • Uniformity of profile across exit
13Team VAAYUNovember 15, 2011
Pressure Profile• Propagation of Pressure fronts• Core expands to ambient
pressure• Bypass flow exits in
under-expanded state
14Team VAAYUNovember 15, 2011
ResultsEngine GE90 in cruise GE90 with κ=0.6 GE90 with κ=0.7 GE90 with κ=.9
Thrust(N) 69219 70439 70767 71432
SFC(mg/N/s) 15.588 15.318 15.247 15.105
Exit Velocity of Core/Mixer (m/s)
368 293.3 292.8 295.1
Exit Velocity of Bypass (m/s)
248 283.0 289.6 290.9
Exit Pressure of Core/Mixer (Pa)
24094 33606 33897 34110
Exit Pressure of Bypass
41649 36146 35421 35223
Exit area of Core/Mixer(m^2)
1.011 3.22 3.569 4.260
Exit area of Bypass(m^2)
3.593 1.384 1.035 0.344
Net Gain in Thrust - 1.76% 2.24% 3.2%
15Team VAAYUNovember 15, 2011
Summary• Significant reduction in jet noise.
- proportional to 8th power of velocity gradient- 64% reduction in velocity gradient
• 3.2% decrease in SFC for κ=0.9• Noise due to internal mixing• Dynamic Instabilities• Materials & Actuators
16Team VAAYUNovember 15, 2011
Geared Turbofan• High BPR desired due to increase in SFC• Increase in fan diameter• Lower RPM operation required
for preventing shock losses• Efficiency of LPC decreases at lower RPM• Planetary reduction gear box used
17Team VAAYUNovember 15, 2011
Benefits
• Low FPR and bypass exit velocity• Low fan RPM, low fan noise and jet noise• High propulsive efficiency• Length reduction of low-pressure spool components like LPC,
LPT and thus a reduction in engine weight• Relatively higher LPC and LPT efficiency than the normal
turbofan engines
18Team VAAYUNovember 15, 2011
Stator Noise Reduction
Source: E. Envia, M. Nallasamy, ‘Design Selection and Analysis of a Swept and Leaned Stator Concept’,Journal of Sound and Vibration (1999) 228(4), 793-836, Article No. jsvi.1999.2441
19Team VAAYUNovember 15, 2011
Stator Configurations• Leaned stator: tangential rotation about the baseline radial position• Swept Stator: axial rotation about the baseline radial position• Aft-position radial stator (APRF): stator position displaced by a
distance equal to the distance between the leading edge of the rotor and the swept stator
• Results of high-sweep angles(300) are marginally better than those of APRF
• APRF requires only small changes to the engine
20Team VAAYUNovember 15, 2011
Results
Noise reduction due to modification in bladeLocation Swept only(300)
(dB)Sweep(300) + lean(-300) (dB)
Aft-position radial stator (dB)
Take-off 15 18 13
Approach 7 8 7
Cutback 13 17 15
Total 35 43 35
*-Values are averaged over upstream and downstream for 2 X BPF tone
21Team VAAYUNovember 15, 2011
Lean Direct Injection Combustors
• Injects fuel into multiple zones• Reduces local temperature• Allows lean combustion• LDI combustors reduce LTO NOx emissions by 15-20%
22Team VAAYUNovember 15, 2011
Golf-ball wings
• Golf-ball wings + smart structures => flap-less wings
• Actuation can produce “dimples”• Larger Cl max • Differentiated operation of actuators
can eliminate the need for ailerons as well
• Application is similar to that of vortex generators on wings
Source: http://www.aerospaceweb.org/question/aerodynamics/q0215.shtml
23Team VAAYUNovember 15, 2011
Spiroid Winglets
• Reduction of Induced drag• 10% reduction in fuel burn for short journeys• Testing on-going for
long flights
Profile
Drag
Skin friction drag
Induced drag
Total Drag
Source: Aviation Partners, http://www.aviationpartners.com/future.html
24Team VAAYUNovember 15, 2011
Weights EstimateComponent Weight (in kgs)
Fan Weight (Single Gear Drive Fan) 1296
Nacelle Weight 760
Compressor (3 LPC+12 HPC) 1564
Combustor 325
Turbine(4 LPT+3 HPC) 2506
Accessories & Others 500
Total Weight 6951
25Team VAAYUNovember 15, 2011
The desire to fly is an idea handed down to us by our ancestors who... looked enviously on the birds soaring freely through space... on the infinite highway of the air.
-Wilbur Wright
As we embark on the challenge of greener aviation, the envy remains and the quest continues……
26Team VAAYUNovember 15, 2011
Many thanks to• Dr. Abhijit Kushari, our project mentor who contributed his time
and knowledge for this design• Vivek and Anandh for their invaluable help in conducting the
computational simulations• Dr. Elizabeth Ward for prompt responses to all the queries and
concerns through out the project• Dean Resource Planning and Generation Office (DRPG) and
Department of Aerospace Engineering, IIT Kanpur for travel support to attend the forum
27Team VAAYUNovember 15, 2011
References1. N+3 Aircraft Concept Designs and Trade Studies, Final Report2. http://www.pw.utc.com/products/commercial/purepower-pw1000g.asp 3. Vivek Sanghi and B. K. Lakshmanan 2002 “Optimum Mixing of Core and
Bypass Streams in High-Bypass Civil Turbofan”, Journal of Propulsion and Power Vol 18, No.4, July-August 2002
4. Pearson, H., “Mixing of Exhaust and Bypass Flow in a Bypass Engine,” Journal of Royal Aeronautical Society, Vol. 66, Aug. 1962, pp. 528–530
5. Frost, T. H., “Practical BypassMixing Systems for Fan Jet Aero Engine,”The Aeronautical Quarterly, May 1966, pp. 141–160.
6. http://www.grc.nasa.gov/WWW/RT/RT1997/5000/5860harrington.htm7. http://en.wikipedia.org/wiki/Propelling_nozzle#Iris_nozzles8. http://en.wikipedia.org/wiki/Geared_turbofan
(continued..)
28Team VAAYUNovember 15, 2011
9. C. Riegler, C. Bichlmaier ‘The Geared Turbofan Technology-Opportunities, Challenges and Readiness Status’, http://www.mtu.de/en/technologies/engineering_news/others/Riegler_Geared_turbofan_technology.pdf
10. Philip G. Hill, Carl R. Peterson , Mechanics and Thermodynamics of Propulsion11. Ilan Kroo ,‘Drag due to Lift: Concepts for Prediction and Reduction’, , Annu.
Rev. Fluid Mech. 2001. 33:587–61712. http://www.flightglobal.com/blogs/flightblogger/2008/06/spiroid-wingtip-te
chnology-the.html13. http://www.jet-engine.net/civtfspec.html14. E. Envia, M. Nallasamy, ‘Design Selection and Analysis of a Swept and Leaned
Stator Concept’, Journal of Sound and Vibration (1999) 228(4), 793-836, Article No. jsvi.1999.2441
15. Richard P. Woodward, David M. Elliott, Christopher E. Hughes and Jeffrey J. Berton ‘Benefits of Swept-and-Leaned Stators for Fan Noise Reduction’,
16. www.stanford.edu/~cantwell/AA283.../GE90_Engine_Data.pdf