hypervelocity combustion regime pis: dan cresci, ron hanson, jack edwards, chris goyne research...
TRANSCRIPT
Hypervelocity Combustion Regime
PIs: Dan Cresci, Ron Hanson, Jack Edwards, Chris Goyne
Research Staff: C.Y. Tsai, Jay Jeffries
Graduate Students: Michael Smayda, Ian Schultz, Chris Goldenstein, Patrick Vogel
National Center for Hypersonic Combined Cycle Propulsion
Update Presentation on June 16th, 2011
AFSOR-NASA Hypersonics Fundamental Research Review
National Center for Hypersonic Combined Cycle Propulsion
2
Outline• Goals and Objectives• Approach
– Roadmap– Test Plan – Analysis Plan
• Schedule• Research results
– Experiments– Diagnostics– Modeling
• Collaboration• Questions
National Center for Hypersonic Combined Cycle Propulsion
3
Goals and Objectives
National Center for Hypersonic Combined Cycle Propulsion
4
Experimental Focus Areas
• Focus Area 1– Measurement of reacting flow turbulence statistics and novel
fuel-air mixing and flame holding schemes through the development and application of advanced diagnostics
• implement the Tunable diode laser absorption spectroscopy (TDLAS) measurements of temperature, velocity, pressure and several species (H2O, O2, CO2 and selected hydrocarbons) in HYPULSE for measurement in the pulsed, hypervelocity facility
• Focus Area 2– Development of benchmark data sets with quantified
experimental uncertainty for the purposes of developing accurate RANS, hybrid LES/RANS, and LES models
• extend the experimental data set to Mach 7 and Mach 10
• generate quantitative data sets for model development/validation
National Center for Hypersonic Combined Cycle Propulsion
5
Experimental Focus AreasFOCUS AREA DUAL INLET RIG DUAL-MODE SCRAMJET
(DMSJ)SCRAMJET
Mach 3 - 4 Mach 4 - 6 Mach 5 - 10
NASA Glenn (conducted in collaboration with NASA)
University of Virginia Supersonic Combustion Facility
NASA HYPULSE at ATK GASL
High-speed inlet
Low-speed inlet
Isolator Combustor Combustor
1) Turbulence-chemistry interaction and the advancement of fuel-air mixing, flame holding and diagnostics
- - - CARS and RayleighPLIFTDLAS (Tomographic and LOS)PIVSchlierenHigh freq. press.
TDLAS (LOS)High freq. pressHeat fluxSchlierenFuel Plume Image
2) Benchmark data sets for RANS, hybrid LES/RANS, and LES models
High freq. press.Low freq.press.Schlieren
High freq. press.Low freq. press.Schlieren
PIV SchlierenHigh freq. press.Low freq. press.
CARS and RayleighPLIFTDLAS (Tomographic and LOS)PIVSchlierenHigh freq. press. Low freq. press.
TDLAS (LOS)High freq. pressHeat fluxSchlierenFuel Plume Image
3) Performance improvements and control of mode-transition
High freq. press.Low freq. press.
High freq. press.Low freq. press.
High freq. press.Low freq. press.
High freq. press.Low freq. press.
-
National Center for Hypersonic Combined Cycle Propulsion
6
Approach
National Center for Hypersonic Combined Cycle Propulsion
7
Roadmap
• Hypervelocity Regime– Mach 5 - 10
2009 2010 2011 2012 2013 2014
Experiments
Modeling
Diagnostics
Design modelDefine diagnostics
Build/install modelMach 5 testing
Mach 7 testing Mach 10 testing
RANS RANS/LES-RANS
Define diagnosticsTDLAS/wall pressures and
temperatures/flow visualization
Dual Mode Exp.
National Center for Hypersonic Combined Cycle Propulsion
Test Plan
• Test Facility– HyPulse Reflected Shock Tunnel (RST) Operation– Nozzles: AR 35 for Mach 5, AR175 for Mach 7, and AR225 for Mach 10
• Test Article– Hy-V Engine-A Flowpath– New cowl piece with side wall windows, optical access and heat flux measurements
on top wall
• Instrumentation – PCB, heat flux gauge, schlieren, fuel plume image– TDLAS
• Test Conditions– Mach 5-q1500 psf: dry air, Tt=2230 R, Mn=5.2, test time= 12 ms– Mach 7-q1000 psf: dry air, Tt= 3850 R, Mn=7.3, test time= 6 ms– Mach 10-q1000 psf: dry air, Tt= 6950 R, Mn=6.9, test time= 3 ms– Fuel: Silane Fuel Mixture (20%SiH4-80% H2 by volume); ER= 0 to 0.6
8
National Center for Hypersonic Combined Cycle Propulsion
Analysis Plan(Experimental Data Sets to be Acquired for Model Development/Validation)
• Raw Data– Axial pressure profile at body wall centerline– Axial heat flux profile at cowl wall centerline– Schlieren images at isolator and combustor (Mach 7 & 10 only) – FPI (Fuel Plume Image) at combustor centerline– Vertical profile of PIW (Path Integrated Water) concentration and temperature at
selected axial locations
• Reduced Data– Fuel jet penetration– Axial mixing efficiency profile– Axial combustion efficiency profile
• For CFD Model Validation– Turbulence model: pressure data, temperature & heat flux profiles; separation; shock
pattern; boundary layer thickness
– Mixing/Ignition model: mixing/combustion efficiency
– Combustion chemistry/kinetics: combustion efficiency
9
National Center for Hypersonic Combined Cycle Propulsion
10
Schedule
National Center for Hypersonic Combined Cycle Propulsion
11
Schedule
• Year 1 (8/1/09 – 7/31/10)– Establish test objectives– Define diagnostics requirements– Define test configuration (adapting existing hardware)– Collaborate with diagnostic team– Define diagnostic plan
• Based on current test series, additional diagnostics point will be determined and incorporated
• Year 2 (8/1/10 – 7/31/11)– Design– Fabrication– Instrumentation
In Progress
In Progress
National Center for Hypersonic Combined Cycle Propulsion
12
Schedule (continued)
• Year 3 (8/1/11 – 7/31/12)– Model installation– Checkouts– Testing series #1 (~1 month)
• Year 4 (8/1/12 – 7/31/13)– Testing series #2 (~1 month)
• Year 5 (8/1/13 – 7/31/14)– Testing series #3 (~1 month)
National Center for Hypersonic Combined Cycle Propulsion
13
Research ResultsExperiments
National Center for Hypersonic Combined Cycle Propulsion
14
Hypulse Test Facility
Hyper-X Scramjet ModelMach 7, 10, 15
NASA GTXMach 7, 10
GASL 6.5” Dia. Mach 8 Gun-Launched Projectile
• The NASA HYPULSE facility at GASL has been used for various airbreathing propulsion tests
• Multi-mode facility operations allow simulations from Mach 5 to 25 in a single facility with rapid turn around time
• Short duration nature allows uncooled hardware
• Agreement between X43 flight and HYPULSE data has validated the use of pulse test technique for aeropropulsion testing
National Center for Hypersonic Combined Cycle Propulsion
Leverage SDPTE (Hy-V) Program
DMSJ flowpath geometries for a) original University of Virginia direct connect rig and b) Hypulse Flowpath A 15
531 2 4
National Center for Hypersonic Combined Cycle Propulsion
Leverage SDPTE (Hy-V) Program
ATK Ground Tests- Medium & short duration- Clean & vitiated
TBIV
HYPULSEUVa Direct-connect tests- Long duration- Clean & vitiated
Flight- Medium duration- Atmospheric air
Prediction of Flight Performance- Thrust- Combustor pressure- Isolator pressure- Inlet operability- Heat flux
• Resolve ground testing issues related to the duration of the test flow and related to test medium effects on dual-mode scramjet engine performance
16
National Center for Hypersonic Combined Cycle Propulsion
Leverage SDPTE (Hy-V) Program• Engine tests at Mach 5 &7 conditions have been completed• Test rig is currently available and has been disassembled awaiting
cowl modifications
17
National Center for Hypersonic Combined Cycle Propulsion
18
Leverage SDPTE (Hy-V) Program
• SDPTE Program conducted by UVa, ATK GASL and Va Tech.• Funded by APTT Program, TRMC
HYPULSE Capabilities:- NASA Facility at ATK GASL- Mach 5 to Mach 25- Nozzle exit diam. Approx. 26”- Test time 10-15 ms.
Flowpath A
PedestalAssembly
Flowpath B
M5 Facility NozzleJet Stretcher
Test Article
National Center for Hypersonic Combined Cycle Propulsion
Flowpath A Instrumentation:- 52 Pressure measurements- 21 Heat flux measurements
-5 original, 16 new- No Thermocouples
• NCHCCP Program conducted by UVa, ATK GASL, Stanford and NCSU• Funded by AFOSR, NASA
19
NCHCCP Program
Flowpath A
PedestalAssembly
Flowpath B
M5 Facility Nozzle Test Article
Removed for NCHCCP Program
National Center for Hypersonic Combined Cycle Propulsion
20
HyPulse Engine Cowl/Sidewall
Radiation heaterSample Panel
Supersonic Nozzle
• New engine cowl piece will be built• Sidewall windows and top wall optical & heat flux gauge inserts will
be added• Top wall HFG and optical inserts are interchangeable.
4.86
0.07
8.14
11.00 4.00
2.001.500.07
National Center for Hypersonic Combined Cycle Propulsion
HyPulse Engine Sidewall Windows
1
a
b SPIV, CARS, Rayleigh, TDLAS, PLIF
c
d
c*
e
a bbb edd d da*a* a*
SPIV, CARS, Rayleigh, TDLAS
c* c*
SPIV, CARS, Rayleigh, TDLAS, PLIF, TDLAT, combustion efficiency
CARS, TDLAS
SPIV, CARS, Rayleigh, TDLAS, PLIF, TDLAT, combustion efficiency
a*
* Subject to changeAll dimensions in inches
• HyPulse engine window locations are consistent with those in UVa’s Dual Mode Engine
21
National Center for Hypersonic Combined Cycle Propulsion
Fuel Plume Imaging (FPI) Setup
22
FPI Setup Option I (Laser sheet from top wall)
Axial Distance
Mix
ing
Eff
icie
ncy
CCDCamera
Flow Injecto
r
FPI Setup Option II (Laser sheet from side wall)
Laser Sheet
Mie Scattering of SiO2 particles Produced in-situ from Silane combustion (SiH4 + Air)
•Uniform distribution, combustion tracking, particle size less certain•Produced using dry seeder in fuel system
•1 μm diameter powder, mixing tracking, uniform distribution less certain•Reference AIAA -96-2222 for additional information
Laser:Nd: YAG Laser; Wavelength: 532 nmEnergy: 120 mJ per pulse per laserRepetition Rate: 15 x 2 Hz; Pulse width: 3-5 ns
Camera:Asynchronous ~50 μsec shutter; 1300 x 1030 CCD
National Center for Hypersonic Combined Cycle Propulsion
Test Setup and Optical Access at Mach 5
• Combustor schlieren is not available at Mach 5• Combustor centerline FPI available
23
National Center for Hypersonic Combined Cycle Propulsion
Test Setup and Optical Access at Mach 7 & 10
• Mach 7 & 10 nozzle is 26” longer • Both combustor schlieren and FPI are available at Mach 7 & 10
24
National Center for Hypersonic Combined Cycle Propulsion
Mach 5 Flight
25
Mach 5, q=1500 psf, Dry Air
2.961.45
1.00
Cowl Shock-I
Cowl Shock-II
Shock Angle, deg 18.02 19.48Mach 3.64 3.33
P, psia 2.95 4.59T, R 651 740
Rho, lbm/ft3 0.0122 0.0168mw 28.97 28.97
a, ft/s 1249 1329V, ft/s 4551 4432
Gamma_eq 1.397 1.392q, psf 3938 5114
Ht_0K, Btu/lbm 570.3 570.3Pt, psia 303 301
Tt, R 2231 2231Pt2, Psia 52.1 68.0
A_Capture, in^2 1.500 1.500Mass Capture, pps - -
Free Stream
AoA, deg 0.0Mach 5.000
P, psia 0.595T, R 396
Rho, lbm/ft3 0.00406mw 28.96
a, ft/s 975V, ft/s 4875
Gamma_eq 1.399q, psf 1499
Ht_298K, Btu/lbm 441Ht_298K-Ht_0K, Btu/lbm 129
Ht_0K, Btu/lbm 570Pt (P01), psia 346.2
Tt (T01), R 2230Pt2, Psia 19.56
Pt2/Pt 0.0565W/A, lbm/ft^2-s 19.80A_Capture, in^2 -
MassCapture1D, pps -MC-Ratio-BL -
Mass Capture, pps -
Cowl Lip
Shock Angle, deg 19.38Mach 4.00
P, psia 1.786T, R 565
Rho, lbm/ft3 0.00853mw 28.97
a, ft/s 1166V, ft/s 4665
Gamma_eq 1.402q, psf 2884
Ht_298K, Btu/lbm 441Ht_298K-Ht_0K, Btu/lbm 129
Ht_0K, Btu/lbm 570Pt, psia 302
Tt, R 2232Pt2, Psia 37.96
Pt2/Pt 0.126W/A, lbm/ft^2-s 39.78A_Capture, in^2 2.178
MassCapture1D, pps 0.602MC-Ratio-BL 0.719
Mass Capture, pps 0.432
National Center for Hypersonic Combined Cycle Propulsion
Mach 5 Flight Simulation
26
• Hypulse M5 test conditions match the Mn, Ps & Ht at the cowl lip for flight at Mach 5.0, q1500 psf and 0 deg AoA
HyPulseMn=5.2Pt=368 psiaTt=2230 RPs=0.515 psiaTs=373 R
FlightMn=5.0q=1500 psfPs=0.595 psiaTs=393 R
AR35
AoA = 0 deg
AoA = 1.1 deg
Mn=4.0Ps=1.79 psiaTs=565 R
Mn=4.0Ps=1.79 psiaTs=565 R
Alt = 72 kft
National Center for Hypersonic Combined Cycle Propulsion
Mach 5 Test Conditions
27
Mach 5.0 Conditions (HyPulse)
Flight M5.0HyPulse-RST
AR35 Noz Dry Air
Mach 5.0 Conditions (HyPulse)
Flight M5.0HyPulse-RST
AR35 Noz Dry Air
Test Gas Dry Air Dry AirMach 5.0
xAr 0.00962 0.00962 q, psf 1500xN2 0.78089 0.78088 h, ft 71886
xO2 w/o NOx 0.20950 0.20950xH2O 0.00000 0.00000 FB Angle, deg 10.0 10.0xCO2 0.00000 0.00000 AoA, deg 0.00 1.13
xO2 in NOx 0.00000 0.00015 Flow deflection, deg 10.00 11.13Free Stream Nozzle Exit Cowl Lip Cowl Lip
A/A*_Effective - 32.1 Shock Angle, deg 19.38 20.08Mach 5.00 5.183 Mach 4.00 4.00
P, psia 0.595 0.515 P, psia 1.786 1.786T, R 393 373 T, R 565 565
Rho, lbm/ft3 0.00409 0.00372 Rho, lbm/ft3 0.00853 0.00854mw 28.97 28.96 mw 28.97 28.97
a, ft/s 975 946 a, ft/s 1166 1166V, ft/s 4877 4904 V, ft/s 4665 4663
Gamma_eq 1.410 1.399 Gamma_eq 1.402 1.402q, psf 1510 1392 q, psf 2884 2886
q_Gamma_1.40 1500 1393 q_Gamma_1.40 2879 2882Ht_298K, Btu/lbm 441 441 Ht_298K, Btu/lbm 441 440
Ht_298K-Ht_0K, Btu/lbm 129 129 Ht_298K-Ht_0K, Btu/lbm 129 129Ht_0K, Btu/lbm 570 570 Ht_0K, Btu/lbm 570 569
Pt (P01), psia 352 368 Pt, psia 302 302Tt (T01), R 2231 2230 Tt, R 2232 2230
Pt2, Psia 19.70 18.16 Pt2, Psia 37.96 37.99Pt2/Pt 0.0560 0.0494 Pt2/Pt 0.126 0.126
W/A, lbm/ft^2-s 19.92 18.22 W/A, lbm/ft^2-s 39.78 39.82A_Capture, in^2 - - A_Capture, in^2 2.178 2.178
MassCapture1D, pps - - MassCapture1D, pps 0.602 0.602MC-Ratio-BL - - MC-Ratio-BL 0.719 0.719
Mass Capture, pps - - Mass Capture, pps 0.432 0.433
National Center for Hypersonic Combined Cycle Propulsion
Expected Nozzle Plenum and Exit Pressures Profiles for the Mach 5 Conditions
28
0.000.010.020.030.040.050.060.07
-10 -8 -6 -4 -2 0 2 4 6 8 10
Pt2/
Pt
r (in.)
I14 CFD-M5 DryAir
0.000.010.020.030.040.050.060.07
-10 -8 -6 -4 -2 0 2 4 6 8 10
Pt2/
Pt
r (in.)
I14 Pt2/Pt_DryAir (Mn=5.18) Pt2/Pt_Core_Mesd
0
100
200
300
400
500
600
-2 0 2 4 6 8 10 12 14 16 18 20 22
P, p
sia
Time_shift, ms
Pt S31A, B Test Window• Steady state test duration up to 12 ms is available at Mach 5
• Nozzle core flow size is about 12 inches
National Center for Hypersonic Combined Cycle Propulsion
Expected Engine Pressure Profile for the Mach 5 Conditions
29
02468
101214161820222426
10 15 20 25 30 35 40 45 50 55
P_no
rmal
ized
, psi
a
X, in.
Engine A (BodyCenter)
Flowpath A
Tare
20%Silane, ER=0.3
• 20% Silane-80% H2 fuel mixture will be used as the engine fuel to ensure auto-ignition
• Combustor pressure: 10-20 psia for ER=0.30
National Center for Hypersonic Combined Cycle Propulsion
Mach 7 Flight
30
Mach 7, q=1000 psf, Dry Air
3.70 1.451.00
Cowl Shock-I
Cowl Shock-II
AoA, deg 14.50 15.71Mach 4.72 4.29
P, psia 1.649 2.874T, R 814 954
Rho, lbm/ft3 0.00547 0.00814mw 28.97 28.97
a, ft/s 1392 1502V, ft/s 6573 6440
Gamma_eq 1.387 1.379q, psf 3674 5244
Ht_0K, Btu/lbm 1059 1059Pt (P01), psia 836 821
Tt (T01), R 3853 3853Pt2, Psia 48.4 69.4
A_Capture, in^2 1.500 1.500Mass Capture, pps - -
Free Stream
AoA, deg 0.0Mach 7.00
P, psia 0.202T, R 409
Rho, lbm/ft3 0.00134mw 28.96
a, ft/s 990V, ft/s 6935
Gamma_eq 1.400q, psf 999
Ht_298K, Btu/lbm 930Ht_298K-Ht_0K, Btu/lbm 129
Ht_0K, Btu/lbm 1059Pt (P01), psia 1149
Tt (T01), R 3848Pt2, Psia 13.25
Pt2/Pt 0.0115W/A, lbm/ft^2-s 9.27A_Capture, in^2 -
MassCapture1D, pps -MC-Ratio-BL -
Mass Capture, pps -
Cowl Lip
Shock Angle, deg 16.38Mach 5.25
P, psia 0.876T, R 679
Rho, lbm/ft3 0.00349mw 28.97
a, ft/s 1275V, ft/s 6691
Gamma_eq 1.396q, psf 2425
Ht_298K, Btu/lbm 928Ht_298K-Ht_0K, Btu/lbm 129
Ht_0K, Btu/lbm 1057Pt, psia 842
Tt, R 3848Pt2, Psia 31.80
Pt2/Pt 0.0378W/A, lbm/ft^2-s 23.32A_Capture, in^2 2.178
MassCapture1D, pps 0.353MC-Ratio-BL 0.727
Mass Capture, pps 0.256
National Center for Hypersonic Combined Cycle Propulsion
Mach 7 Flight Simulation
31
• Hypulse M7 test conditions match the Mn, Ps & Ht at the cowl lip for flight at Mach 7.0, q1000 psf and 0 deg AoA
FlightMn=7.0q=1000 psfPs=0.202 psiaTs=409 R
HyPulseMn=7.3Pt=1287 psiaTt=3848 RPs=0.171 psiaTs=376 R
AR175
Mn=5.25Ps=0.876 psiaTs=679 R
Mn=5.25Ps=0.876 psiaTs=679 R
AoA = 0 deg
AoA = 0.9 deg
Alt = 95 kft
National Center for Hypersonic Combined Cycle Propulsion
Mach 7 Test Conditions
32
Mach 7 Conditions (HyPulse)
FlightHyPulse-RST AR175 Noz
Dry Air
Mach 7 Conditions (HyPulse)
FlightHyPulse-RST AR175 Noz
Dry Air
Test Gas Dry Air Dry AirMach 7.0
xAr 0.00962 0.00962 q, psf 1000xN2 0.78088 0.78088 h, ft 95055
xO2 w/o NOx 0.20950 0.20950xH2O 0.00000 0.00000 FB Angle, deg 10.0 10.0xCO2 0.00000 0.00000 AoA, deg 0.00 0.93
xO2 in NOx 0.00564 0.00564 Flow deflection, deg 10.00 10.93
Free Stream Nozzle Exit Cowl Lip Cowl Lip
A/A*_Effective 148.2 180.6 Shock Angle, deg 16.38 17.02Mach 7.00 7.32 Mach 5.25 5.25
P, psia 0.202 0.171 P, psia 0.876 0.876T, R 409 376 T, R 679 679
Rho, lbm/ft3 0.00134 0.00122 Rho, lbm/ft3 0.00349 0.00349mw 28.96 28.96 mw 28.97 28.97
a, ft/s 990 951 a, ft/s 1275 1275V, ft/s 6935 6963 V, ft/s 6691 6692
Gamma_eq 1.400 1.399 Gamma_eq 1.396 1.396q, psf 999 920 q, psf 2425 2425
q_Gamma_1.40 1000 921 q_Gamma_1.40 2433 2433Ht_298K, Btu/lbm 930 930 Ht_298K, Btu/lbm 928 928
Ht_298K-Ht_0K, Btu/lbm 129 129 Ht_298K-Ht_0K, Btu/lbm 129 129Ht_0K, Btu/lbm 1059 1059 Ht_0K, Btu/lbm 1057 1057
Pt (P01), psia 1149 1287 Pt, psia 842 842Tt (T01), R 3848 3848 Tt, R 3848 3848
Pt2, Psia 13.25 12.01 Pt2, Psia 31.80 31.80Pt2/Pt 0.0115 0.0093 Pt2/Pt 0.0378 0.0378
W/A, lbm/ft^2-s 9.27 8.52 W/A, lbm/ft^2-s 23.32 23.32A_Capture, in^2 - - A_Capture, in^2 2.178 2.178
MassCapture1D, pps - - MassCapture1D, pps 0.353 0.353MC-Ratio-BL - - MC-Ratio-BL 0.727 0.727
Mass Capture, pps - - Mass Capture, pps 0.256 0.256
National Center for Hypersonic Combined Cycle Propulsion
Expected Nozzle Plenum and Exit Pressures Profiles for the Mach 7 Conditions
33
H98 (M7-DryAir)
0
400
800
1200
1600
2000
-2 0 2 4 6 8 10 12
Pt, p
sia
Time, ms
Pt_avg Time_Avg
0
4
8
12
16
20
-2 0 2 4 6 8 10 12
Pt2,
psi
a
Time, ms
Pt2_avg Time_Avg
0.000
0.005
0.010
0.015
0.020
-15 -10 -5 0 5 10 15
Pt2/
Pt
z (in.)
H98 (M7-DryAir) Pt2/Pt _avg= 0.00944
• Steady state test duration up to 8 ms for Mach 7
• Nozzle core flow size about 16 inches
National Center for Hypersonic Combined Cycle Propulsion
Mach 10 Flight Simulation
34
• Hypulse M10 test conditions match the Mn, Ps & Ht at the cowl lip for flight at Mach 10.0, q1000 psf and 4 deg AoA
FlightMn=10.0q=1000 psfPs=0.099 psiaTs=445 R
HyPulseMn=6.91Pt=3039 psiaTt=6952 RPs=0.368 psiaTs=846 R
AR225
Mn=5.64Ps=1.16 psiaTs=1265 R
Mn=5.64Ps=1.16 psiaTs=1210 R
AoA = 4 deg
AoA = -2.4 deg
Alt = 111 kft
National Center for Hypersonic Combined Cycle Propulsion
35
Research ResultsDiagnostics
National Center for Hypersonic Combined Cycle Propulsion
36
Stanford TDLAS Measurements
• Non-intrusive measurement strategy for data to validate CFD models
• Spatially and temporally-resolved measurements of T and H2O
– Simultaneous measurements for 5 locations on 1” flow duct
– Made possible through use of miniaturized optics
• Sequential HyPulse runs for sensor data at different axial locations to match measurement locations with UVa’s direct connect tunnel
Supersonic Air Exhaust
Optical Fibers
5 Beam PathsH2 Fuel Injector Ramp
L~1”
National Center for Hypersonic Combined Cycle Propulsion
37
Research ResultsModeling
National Center for Hypersonic Combined Cycle Propulsion
38
CFD Analysis – NCSU
• NCSU team– Commenced late May, 2011 (Patrick Vogel hired ¼ time to
perform this work)– Mesh generation using GridGen– Steady and possibly unsteady RANS simulations of reactive flow
in HYPULSE inlet / combustor / nozzle• Kinetics of silane / hydrogen mixtures (Jachimowski and Mclain,
NASA TP 2129, 1983)
• 7 additional species (SiH2, SiH3, SiH4, SiH2O, HSiO, SiO, SiO2)
• 23 additional reactions
– Comparisons with TDLAS line-of-sight measurements, wall pressure, wall heat transfer
In Progress
National Center for Hypersonic Combined Cycle Propulsion
39
Simulations of HYPULSE Experiments
• Mesh generation (11.6 M cells, ½ plane symmetry)
Forebody / inlet
Isolator
Combustor / nozzle
Closeup of inlet Closeup of combustor
National Center for Hypersonic Combined Cycle Propulsion
40
Simulations of HYPULSE Experiments
• X-Y Centerplane mesh
Forebody / inlet
IsolatorCombustor / nozzle
Closeup of inlet mesh
Closeup of combustor mesh
National Center for Hypersonic Combined Cycle Propulsion
41
Collaboration
National Center for Hypersonic Combined Cycle Propulsion
42
SDPTE (Hy-V) Test Program
National Center for Hypersonic Combined Cycle Propulsion
43
SDPTE (Hy-V) Test Program
Advanced Propulsion Test Technology
(APTT)
National Center for Hypersonic Combined Cycle Propulsion
44
Questions ?
National Center for Hypersonic Combined Cycle Propulsion
45
Backup slides