National Center for Hypersonic Combined Cycle Propulsion Update Presentation on June 16 th , 2011

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 PropulsionUpdate 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


3

Goals and Objectives


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


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.




-


6

Approach


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.


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


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


10

Schedule


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


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)


13

Research ResultsExperiments


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


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


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


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


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


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


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


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


Fuel Plume Imaging (FPI) Setup

22

FPI Setup Option I (Laser sheet from top wall)

Axial Distance

Mix

ing

Effic

ienc

y

CCDCamera

Flow Injector

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


Test Setup and Optical Access at Mach 5

• Combustor schlieren is not available at Mach 5• Combustor centerline FPI available

23


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


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



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


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


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 Air Mach 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


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


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,

psia

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


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



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



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



31




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


Mach 7 Test Conditions

32

Mach 7 Conditions (HyPulse) Flight

HyPulse-RST AR175 Noz

Dry Air

Mach 7 Conditions (HyPulse) Flight

HyPulse-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


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



34




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


35

Research ResultsDiagnostics


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”


37

Research ResultsModeling


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


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


40

Simulations of HYPULSE Experiments• X-Y Centerplane mesh

Forebody / inlet

IsolatorCombustor / nozzle

Closeup of inlet mesh

Closeup of combustor mesh


41

Collaboration


42

SDPTE (Hy-V) Test Program


43

SDPTE (Hy-V) Test Program

Advanced Propulsion Test Technology

(APTT)


44

Questions ?


45

Backup slides

National Center for Hypersonic Combined Cycle Propulsion Update Presentation on June 16 th , 2011

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