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National Aeronautics and Space Administration
www.nasa.gov
Enabling Additive Manufacturing Technologies for
Advanced Aero Propulsion Materials & Components
Michael C. Halbig1 and Mrityunjay Singh2
1-NASA Glenn Research Center, Cleveland, OH
2-Ohio Aerospace Institute, Cleveland, OH
Pacific Rim Conference of Ceramic Societies, PACRIM13
Okinawa, Japan, Oct. 27-31, 2019.
• https://ntrs.nasa.gov/search.jsp?R=20190034069 2020-06-08T02:51:51+00:00Z
National Aeronautics and Space Administration
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Outline
• Background, Applications, and NASA Strategic Thrusts
• AM of CMCs and Polymer Materials for Turbine Engine Applications
– Laminated Object Manufacturing (OAI) for continuous fiber composites
– Binder Jet Printing for short fiber composites
– FDM of polymer-based materials
• AM of Materials and Components for Electric Motors
– CAMIEM intro: the objectives and approach
– New component designs for integration into the motor
– Direct writing of conductors
– Fabrication and evaluation of a baseline motor
• Summary and next steps
2
•
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Fused Deposition ModelingPlastic is heated and supplied
through an extrusion nozzle
and deposited.
Binder JettingAn inkjet-like printing head moves
across a bed of powder and
deposits a liquid binding material.
Direct Write PrintingControlled dispensing of
inks, pastes, and slurries.
Additive Manufacturing Technologies
3
• Filament
Binder solution Head ---- .,._.-
Pressure
UJ
Dispensing
Tip
~ heigh~~•--- Substrate
Platform
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Components for Turbine Engine Applications
Turbine Engines -Targeted Components (CMCs and PMCs)
4
Fan DuctShrouds & Vanes
Exhaust
Components
Combustor
Liners
NASA CMC Components from
Conventional Fabrication Methods
EBC Coated
SiC/SiC Vanes
Oxide/Oxide
Mixer Nozzle
SiC/SiC Combustion
Liners: Outer Liner and
EBC Coated Inner Liner
•
\ / INTAKE COMPRESSION EXHAUST
Combustion Chambers Turbine
Cold Section Hot Section / '
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Components for Electric Motor Applications
Radial Flux
Machine
Axial Flux Machine
Housing
Rotor
Magnet(s)Stator
Electric Motors- Targeted Components
(structural, functional, and electrical)
NASA Aeronautics
Research Six
Strategic Thrusts
Achieve and exceed N+2
and N+3 goals for
increased efficiencies and
reduced emissions.
STARC-ABL
Vertical
Lift
5
Uber ElevateNASA 15-PAX
tiltwing aircraft
Electrified Aircraft
3.
4.
Ultra-Efficient Commercial Vehicles • Pioneer technologies for big leaps in efficiency and
environmental performance
Transition to Low-Carbon Propulsion • Characterize drop-in alternative fuels and pioneer
low-carbon propulsion technology
•
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Laminated Object Manufacturing For Silicon
Carbide-Based Composites
Fabrics and Prepregs cut at
different laser powers/speeds
Universal Laser System (Two 60 watt
laser heads and a work area of 32”x18”)
LOM allows for continuous
fiber reinforced CMCs.
Prepregs for Composite Processing
• A number of SiC (Hi-Nicalon S, uncoated)
fabrics (~6”x6”) were prepregged.
• These prepregs were used for optimization
of laser cutting process.
• Baseline laser cutting data was also
generated for different types of SiC fabrics
(CG Nicalon, Hi-Nicalon, and Hi-Nicalon S)
Laser cut prepregs used
for composite processing
SEM specimens cut with
different laser power/speeds 6
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Fibers Used for Prepregs: SiC (Hi-Nicalon S Fibers, 5 HS weave)
Fiber Interface Coating: None
Prepreg Composition: Prepreg 5A Nano 2 + Si
• Dense matrix after silicon infiltration. However,
uncoated fibers are damaged due to exothermic
Si+C reaction.
• Fiber coatings needed to prevent silicon reaction
and provide weak interface for debonding and
composite toughness.
Green Preforms:
8 layers of prepregs; warm
pressed @75-85°C
7
Microstructure of SiC/SiC Composites Fabricated Using Single Step Reaction Forming Process plus Si Infiltration
Heat Treatment:
1475°C, 30 minutes
in vacuum
•
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Fibers Used for Prepregs: SiC (Hi-Nicalon S Fibers, 5 HS weave)
Fiber Coating: None
Prepreg Composition: Prepreg 5A Nano 2 + Si
Uncoated SiC fibers
show no visible damage
due to Si exothermic
reaction.
Green Preforms:
8 layers of prepregs; warm
pressed @75-85°C
Heat Treatment:
1475°C, 30 minutes
in vacuum
Micrographs show
good distribution of
SiC and Si phases.
8
Microstructure of SiC/SiC Composites Fabricated Using Single Step Reaction Forming Process plus Si Infiltration •
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Infiltration Green part
De-powdering
Powder Blending
Final Part
Binder Jet Additive Manufacturing of SiC
ExOne Innovent
An inkjet printing head
moves across a bed of
powder and deposits a
liquid binding material.
Binder jet printing capability allows for powder bed processing with
tailored binders and chopped fiber reinforcements for advanced ceramics. 9
• • •
• Binder solution ~---~
•
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Binder Jetting of SiC Fiber / SiC Matrix CompositesExOne Innovent
Fiber Reinforced Ceramic
Matrix Composite
High pressure turbine cooled doublet vane sections.
Si-TUFF iSiC fbers
(Advanced Composite Materials, LLC)
Constituents
SiC powder loaded SMP-10
SiC powder
SiC powder
~70 µm long and
~7 µm in diameter
•
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Processing
- Constituents
• SiC powders: Carborex 220, 240, 360, and 600 powders (median grain
sizes of 53, 45, 23, and 9 microns respectively). Used solely and in powder
blends
• Infiltrants: SMP-10 (polycarbosilane), SiC powder loaded SMP-10, phenolic
(C, Si, SiC powder loaded), pure silicon
• Fiber reinforcement: Si-TUFF SiC fiber; 7 micron mean diameter x 65-70
micron mean length
Microstructure
- Optical microscopy
- Scanning electron microscopy
Properties
- Material density (as-manufactured and after infiltration steps)
- Mechanical properties: 4-point bend tests
Approach for Additive Manufacturing of CMCs
Si-TUFF SiC fibers
(Advanced Composite
Materials, LLC)
Constituents
SiC powder loaded SMP-10
SiC powder
SiC
powder
Phenolic infiltrant
SiC powder
SiC powder
Processing, microstructure, and property correlations
provide an iterative process for improving the CMC materials.
11
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Binder Jetting: Density of SiC Panels
1.40
1.50
1.60
1.70
1.80
1.90
2.00
2.10
2.20
Den
sity
(g
/cc)
Density at as-processed through 1, 2, and 3 infiltrations
I5
N5
O5
G5
P6
Q6
0 321
Densities increased by up to 33% from additional
PCS infiltration steps and were maintained even at
higher SiC fiber loadings of 45, 55, and 65 vol.%.
2”x2” CMC
coupons
Polymer approach has a limitation
on achievable densities.
Melt infiltration methods
such, e.g. silicon melt, can
achieve near full density.
Multiple PCS infiltration steps.
45 vol. % Si Tuff fiber
65 vol. % Si Tuff fiber
55 vol. % Si Tuff fiber
75 vol. % Si Tuff fiber
12
Demonstration of full densification
through silicon melt-infiltration.
SiC
SiC
Silicon
infiltrationSiC
.......
.......
.......
.......
.......
.......
• ---1 I ~1-~·~~,,.,~J
National Aeronautics and Space Administration
www.nasa.gov 13
Carborex Powder mix with 65 vol.% Si-Tough SiC fiber, SMP-10 w/800 nano SiC particles vacuum infiltration.
Binder Jetting: Cross-Section and Fracture Surface from
SiC/SiC Sample with 65 vol.% SiC Fiber
Good densities achieved
with high fiber loading.
•
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Binder Jetting: 4 Point Flexure Tests of the
Monolithic SiC and CMC materials - at R.T.
0
10
20
30
40
50
60
70
80
0.00 0.02 0.04 0.06 0.08 0.10
Str
es
s (
MP
a)
Strain (%)
Non-Reinforced SiC - Set G
0
10
20
30
40
50
60
70
80
0.00 0.02 0.04 0.06 0.08 0.10
Str
es
s (
MP
a)
Strain (%)
65 vol. % SiC Fiber Reinforced SiC - Set N
The fiber loaded SiC materials had significantly higher
stresses and higher strains to failure.
Bend bars for
strength testing
14
•
National Aeronautics and Space Administration
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• Four point bend tests were conducted on samples after 4 SMP-10 infiltrations
• 50 mm long samples were loaded with a 20 mm loading span and 40 mm support span
• The maximum strength was 111 MPa
• For comparison: Dense CVD SiC and sintered alpha SiC bend strength ranges from 200-450 MPa
• Samples that were tested after 6 infiltrations showed no difference in strength
Recent SiC Binder Jetting Results
- Processing and Mechanical Strength Improvements
POC:
Craig Smith
NASA GRC
Optical Microscopy of AM
SiC after 4 PIP Cycles
15
Four Point Bend Strength
~ Average Strength - Average Density
120
100
20
120 2.5
2.4
ro 100 a..
2.3
~ .. ..c +-' ~
u C u ~ ~ 2.2 _, ~ vi ..,I .... I'll
2.1 i::::
2
1.9
ClJ Q
""C C (lJ
cc
80
60
40
20
0
0 1.8 Powder Powder Powder Powder 65% D, 70% D, 70% C,
A B C D 35% F 30% E 30% F
2
• •
2.1
0 0
• •• 0
0
0 <9
2.2
• • •
2.3
•
Density, g/cc
• 0
• 0
• •
2.4 2.S
National Aeronautics and Space Administration
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Demonstration of Polymer
Components from FDM
Engine Panel Access Door
Inlet Guide Vanes from
ABS and Ultem 1000
Acoustic Liner
Test Articles
High temp. polymers
with chopped carbon
fiber reinforcement.
Fortus
400
Lightweight
Structures
FDM Process
Standard Liner Complex Geometry Advanced Liner
Design
The focus is on unique structures,
high temperature capability, and
fiber reinforcement.
16
FDM head
temperature control
1 filament
rollers( OO J
• liquefier
supporting bars
_] <=:)x-yaxes
National Aeronautics and Space Administration
www.nasa.gov 17
0.1 mm
0.4 mm
Highest strength and modulus in CNT reinforced coupons
versus standard ABS Coupons. Less porosity for lower print heights.
Effect of print layer height
FDM of Composite Filaments for Multi-Functional ApplicationsPotential Missions/Benefits:
• On demand fabrication of as needed functional components in space
• Tailored, high strength, lightweight support structures reinforced with CNT
• Tailored facesheets for functional properties, i.e. wear resistance, vibration
dampening, radiation shielding, acoustic attenuation, thermal management
Color Fab,
copper fill
metal, PLA
Proto Pasta,
Magnetic iron, PLAGMASS,
Tungsten, ABS
GMASS,
Bismuth, ABS
C-Fiber Reinforced
ABS Filaments
Filaments used: ABS-standard abs, P-premium abs, CNT-w/carbon
nanotubes, C-w/chopped carbon, Home-lab extruded filament
n:, 0. \.!:I
2.5 ~------------,
] 2.0 +---¥~~ ~ -----::,
-g ~ II)
CNT
-a-5% C
---+-- Prem
-~ 1.5 +-----~ ---............ ::-----i-.-ABS ::J
40 ~ ----------------, nl a. ~~ -I---~~ --,-,----------, .. -= t~ -·~- ~::::::::~s;::;;~~~-7 .. ~ ~ -+---------~:,---------;
CII .. nl
0 >
E 20 +------------~ ---, E Home ::,
(b) 15 4-----,-----,-----,---r------i
1.0 -1--------,-----.--- 0.0 0.1 0.2 0.3 0.4 0.5
0.0 0.2 0.4 Layer Height, mm
layer Height, mm
-&- CNT
--e- p
~ ABS
---e- 5%(
Home
. •• •1 • • • • •• ::. • ; · • ••• • •• f . 7 • • :. ~·· .. . . . . ,, .. , . ~. . . •.. . ... .... .. , ......... ~
i • :,• • ~ . • • ·• ••• : . _,. •• . -f : . . : . . . .. . . ..; . · ... • !. •·~! .-.• , .:. ... • ..,. .• • • • lt . ' .. • .... •: • . ~~ .· .• . ... . . .. ·• .. ' .. .. . • • . • . . ,l • ••••.. . , : . ' ' . ·~· '. . . :. ... . . . . ' ... . . . _,. .
•:.:. /Ii~ ., l' .: •• ~ . . · •• V-• l ~ t • :,. : ...
•
- . ... . -·--...:
•
National Aeronautics and Space Administration
www.nasa.gov
Aircraft Utilizing Electric Motors
X-57: Distributed Propulsion
Greased Lightning GL-10
Urban Air
MobilitySTARC-ABL Hybrid Electric
Uber Elevate
NASA 15-PAX
tiltwing aircraft
Large Single Isle Transports
18
National Aeronautics and Space Administration
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Objective: Utilize additive manufacturing (AM) methods to achieve new motor
designs that have significantly higher power densities and/or efficiency.
Methods:
• New topologies with compact designs, lightweight structures, innovative
cooling, high copper fill, and multi-material systems/components.
• New component designs for the rotors, housing, finned stator cooling ring,
direct printed stator, and a wire embed stator.
• Compare new components/new motor against a baseline motor.
CAMIEM: Compact Additively Manufactured Innovative
Electric Motors
Mission: efficient, low emission
aircraft for Urban Air Mobility.
Compact Additively Manufactured Innovative Electric Motor (CAMIEM) team members:
NASA (GRC, LaRC, ARC), LaunchPoint Technologies and the University of Texas - El Paso
• Motor Width: ~ 7.5”• Total weight ~ 4lbs (1.8 kg)
CAMIEM Baseline Motor CAMIEM AM Motor Design
GRC Dynamometer
Already SOA due to compact design, high power density, and halbach array of magnets.
Projecting a 2x increase in Power Density to 10 kW/kg.
For development of advanced materials, structures, and components.
19
•
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Feasibility Assessment
Baseline Motor
Baseline Motor Testingfor baseline performance
Innovative Motor
DesignAircraft Level System Studies
Additive Manufacturing
Processes and Advanced
Components
Testing of “New” Motor
Configurations to Determine
Improved Performance
Feasibility
Assessed and
Benefits
Determined
20
• ~ -----~ ~..-, ·· I
IL_ _J
National Aeronautics and Space Administration
www.nasa.gov 21
AM and Hybrid Approaches for Electric Motor Components
Components of a Commercial
Axial Flux Motor
NASA Electric Motor with
AM Components
Additively Manufactured
Rotor Plate
Rotor Constituents:
• Permanent magnets.
• High strength structure
(typically metallic).
PCB Coreless StatorLitz Wire
Coreless Stator
Stator Constituents:
• Conductor: copper,
silver.
• Insulators: coatings,
dielectrics, epoxy, high
temp. polymer.
• Soft magnets (for cores):
iron alloys. Iron Core Stator with
Direct Printed Coils
Electric Motors Stators Rotors•
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Direct Printed StatorsBenefits – Higher magnetic flux, torque, and motor constant (Km). – Higher temp. capability of >220C instead of 160C for baseline stator.– Direct printed silver coils with high fill.
Stator Plate from Cobalt-Iron Alloy
Cirlex Middle Layer
Outer Rings22
Concept A
Details of machined features
Substrate
Silver paste
nScrypt 3Dn-300
4-point probe method
Direct Printed Silver Coils -High Current Test
l )
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Additively Manufactured Stator Plates
FDM from Extem (Tg of 311C) (left) and Ultem
1010 (TG of 217C) (right) FDM filament.
Low cost and rapidly manufactured sub-components may be
possible with further advancements or alternate AM processes.23
FDM
Process
Stator Plate from Cobalt-Iron Alloy
1200°C – 51.3% TD
500 μm
High Temp.
Polymer
Soft Magnet
Binder Jetting
Process: lay down of a me lt s t ran d
'..--- nozz le prototype ....,..,.,..- linewise
1'==~~=""1!;..... ........................ ~/" ap plicat ion
supporting s t ructure ~ base plate
e~e,soutlon ----- Electric magnetic laminated sheets
Laminated sheets which are coated by insulating layer
High Joule heat in plane which is perpendicular to the magnetic field
Insulating layer
X ::,
• Soft magnetic composite materials
Compacting powders which are covered with insulating film
Low Joule heat x along any direction u
Insulating film
Eddy current
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Fabrication Method Machine/EDM Machine/MillFabrication Time 4+ months 3 months
Fabrication Costs $21,400 $19, 870Material Costs $600 $330Total Costs $22,000 $20,200
Comparison of Methods to Obtain Outside
Fabrication for Channeled Plates for Stators
Concept B - Stator Plates from Ultem1010
Concept B - Stator Plates from Cirlex
Concept A - Stator Plates from Cobalt-Iron Alloy
3D Print/FDM1 week (92.3% reduction)
$1,000$0 (included in fab.)$1,000 (95.0% reduction)
Currently relying on machined stator plates.
•
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Samples were printed on
the nScrypt 3Dn-300.
Crucial Parameters:
–Print Speed
–Dispensing Pressure
–Nozzle Diameter
–Print Offset
–Valve Opening
Substrate
Trace
Thin Surface and Imbedded
Thick 4-Pt Probe Windings
4-point probe
method
Direct Printing for Innovative Stator Designs for Electric Motors
25
•
National Aeronautics and Space Administration
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Evaluation of Silver Pastes
Conductivity of bulk metals [Ωm]^-1:
-Silver: 6.3 x 107
-Copper: 6.0 x 107
Litz Wire ~60%
fill and less in
stator windings
Printed conductors will have a higher
effective conductivity than the Litz
wire conductors.
Sample 71017G: Heraeus
CL20-11127
Silver paste
PLAIN PASTE
Paste Composition Lowest Resistivity Obtained [Ωm] Conductivity [Ωm]^-1 Max Temp (*C) Vendor Resistivity
CL-11190 (Heraeus) 2.06 x 10-8 4.86 x 107 300 N/A
CB028 (DuPont) 2.82 x 10-8 3.54 x 107 175 7 – 10 (mΩ/sq/mil)
CL20-11127 (Heraeus) 3.6 x 10-8 2.78 x 107 300 N/A
CB100 (DuPont) 5.23 x 10-8 1.91 x 107 175 >7.5 x 10-8 Ωm
Ag-PM100 (Applied Nanotech) 9.13 x 10-8 1.10 x 107 300 >5 x 10-8 Ωm
Kapton (DuPont) 2.11 x 10-7 4.74 x 106 225 <5 (mΩ/sq/mil)
Substrate
26
••• •••• :.•-•-•-~ ·····•~ ~ .. _. _) . uuu
~
•
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Pastes Additions for Higher Electrical Conductivity
27
Additions of Graphene and
Carbon Nanostructures
Most Conductive Composites
Paste Composition Resistivity
[Ωm]
Conductivity
[Ωm]^-1
CB028 + 0.2 wt%
QUATTRO Graphene
8.148E-08 1.23E+07
Heraeus + 0.04 wt% CNS 8.297E-08 1.21E+07
CB028 + 0.1 wt%
QUATTRO Graphene
1.036E-07 9.65E+06
CB028 + 0.085 wt% CNS 1.114E-07 8.97E+06
Heraeus + 0.14 wt% CNS 1.191E-07 8.40E+06
CB028 + 0.2 wt% MONO
Graphene
1.261E-07 7.93E+06
CB028 + 0.5 wt% MONO
Graphene
1.419E-07 7.05E+06
Plain Pastes
Paste Composition Resistivity
[Ωm]
Conductivity
[Ωm]^-1
Plain CB028 2.82 E-08 3.54 E+07
Plain Heraeus 4.124E-08 2.42E+07
Peng-Cheng Ma, “Enhanced Electrical Conductivity
of Nanocomposites Containing Hybrid Fillers of
Carbon Nanotubes and Carbon Black.”
Y. Kim, et al. U.S. Patent 8,481,86, 2013 –
Conductive Paste Containing Silver
Decorated CNT
0 1.0 -0
-2 1.0 -04
E - 4 TARGET CONTENT OF CARBON ~ 1.0 -06
(..) -- tl3 en - 6 NANOTUBES REQUIRED -b8 FOR ELECTRICAL NETWORK ;~ 1.0 -0 · > Cl - 8 0 . 1 ~ 1 WE I GHT% ...
0 ·~ _J
1 l.O lO -10
- 12 1.0 -12
- 14 I .0E-l4 0 1 2 3 4 () L5 2 CONTENT OF CARBON NANOTUBES (WEIGHT%)
liellt (w ¼)
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Heraeus CL20-11127 Thermally Cured on Fiberglass (195C/1hr due to substrate limitations)
Sample Name Resistance [Ωm] Conductivity [Ωm]^-1
71017G 4.37 x 10-8 2.29 x 107
71017H 5.75 x 10-8 1.74 x 107
Heraeus CL20-11127 Thermally Cured on Vespel (300C/1hr)
72117A 4.12 x 10-8 2.42 x 107
Heraeus CL20-11127 Photonically Cured
71017A 4.89 x 10-8 2.05 x 107
71017B 4.55 x 10-8 2.20 x 107
71017C 6.04 x 10-8 1.65 x 107
DuPont CB028 Thermally Cured on Fiberglass (150C/1hr)
032917-6 2.82 x 10-8 3.54 x 107
Thermal/Oven
Curing
Photonic SinteringInvestigating the use for photonic sintering for printed silver inks.
• Rapid post processing of conductive patterns
• Few second to minute processing times without
damaging/heating the substrate
Photonic Sintering for
high through-put
Advanced Sintering Processes for
Higher Electrical Conductivity
Resistivity greatly improved from 8 ohm in
green state to 1.8 ohm after photonic sintering.
Potential, further optimization by investigating
offset distance, kV setting, pulses, duration
and nano-sized silver particles.
28
Xenon lamp
camera
Fiber optic light guide
llll Xenon lamp light
~ Deposited nanoparticles
••••• !Subsbalel
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Direct Printed Silver Coils - High Current Test
Temperature capability far exceeds that
of the baseline motor which is 180C.
Temperature decreases with extended heat
potentially due to self sintering and decreasing
resistance within the paste traces.
29
350
325
300
275
250
225
u -;- 200 ... ::l ~ 175 ... QI e 1so t2!
125
100
75
so
2S
0 2
• Temperature Observation Over Time with Varying Current
FlrstlO min
25A
10A
SA
4 s 6 8 9 lO 20 30 so 60
Time (Min)
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AFRC prop motor testing:
- Baseline motor
- Motor Version 1: Structural LaRC parts -
rotors and housing
GRC motor testing in a dynamometer:
- Baseline motor
- Motor Version 2: Structural LaRC parts -
rotors, housing, finned cooling ring
Baseline
Motor
V1. Motor
V2.
Motor
Dynamometer
Prop Test Stand
Testing of Motor Configurations
30
Mass =
1968 g
Mass = 1870 g
(5% less mass)
Total heat sink
mass = 92 g
Mass = 1833 g
(7% less mass)
NASA G RC Dyna Avg Motor Efficiency vs Avg Torque
105
95 ' 85 - 3000 RPM '?ft. > u 75 - 4000 RPM C: a,
65 ·.; :f - 5000 RPM w
55
45 - 6000 RPM
35 - 7500 RPM
0 2 4 6 8 10
Torque (N-M)
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Summary and Conclusions
Summary
• Good progress is being made in applying additive manufacturing methods to the
fabrication of components for turbine engine and electric motors.
• LOM offers continuous fiber reinforced CMCs while the binder jet method offers short
fiber reinforced SiC-based ceramics.
• AM offers the potential for electric motors with much higher efficiencies and power
densities.
• Additive manufacturing technologies were demonstrated to be capable of enabling
new innovative direct printed stator designs for electric motors.
• New electric motor component designs will offer performance gains through such
improvements as lighter weights, higher coil packing, higher coil electrically
conductive, higher temperature operation, and higher magnetic flux.
31
•
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The CAMIEM Team and AcknowledgementsSupport provided by the Convergent Aeronautics Solutions Project
within the ARMD Transformative Aeronautics Concepts Program.
Also Summer Interns at GRC (Anton Salem and Hunter Leonard) and LaRC.
Organization Name Role Organization Name Role
Glenn Research
Center
Michael Halbig (POC) PI and GRC POC
Armstrong Flight Research
Center
Ethan Niemen (POC) AFRC POC and ground testing
Mrityunjay "Jay" Singh Additive manufacturing
Otto Schnarr IIIElectric propulsion ground
testingValerie Wiesner Kirsten Fogg
Greg Piper / Daniel Gorican AM /Direct printing Patricia Martinez
Derek Quade Dynamometer
Langley Research Center
Samuel Hocker (POC) Additive manufacturing
Steven Geng Motors and magnets Christopher Stelter
Chip Redding Design Russell “Buzz” Wincheski NDE
Chun-Hua “Kathy" Chuang Insulator materials Stephen Hales Materials evaluation
Peter Kascak Electric Motors John Newman Computational materials
Jeff Chin System benefitsUniversity of Texas El Paso
Jose Coronel (POC)Stator winding and cooling
efficiencyLaunchPointTechnologies
Michael Ricci (POC)Baseline & innovative
motor designs
David Espalin
Brian Clark Ryan Wicker
Dave Paden
32
(
i!41i§i3=P• 1 N,:I TECHNOLOG I ES