AIAA Freejet Test of the AFRL HySET Scramjet Engine Model at Mach 6.5 and 4.5

Transcription

1 A MA A _ A AIAA Freejet Test of the AFRL HySET Scramjet Engine Model at Mach 6.5 and 4.5 Richard

2 AIAA FREEJET TEST

3 INTRODUCTION Under the Hypersonic Technology Program (HyTech), the Air Force Research Laboratory Propulsion Directorate

4 MODEL DESCRIPTION Flowpath Lines TEST APPROACH The PTE flowpath features: a 2-ramp forebody, self-starting inlet, 6.0 inch width, a short isolator with a small divergence, diverging combustor sections,

5 Vitiated

6 (c)2001 American Institute

7 The ratios of the combustion efficiency and isolator pressure ratio divided

8 (c)2001 American Institute

9 ACKNOWLEDGMENTS The Hydrocarbon Scramjet Engine Technology Program

10 Figure 1: Performance Test Engine Figure 2. - PTE Flowpath Cross-Section Compared to the Full Scale Flowpath Cross-Section. Secondary Fuel Power Supply Control & Data Acquisition Console 800 kw B Endothermic Fuel Reactor *mmj> : Main Fuel Power Supply Portable Generator (SOOkWAC) Jbox - - -, ^ Secondary Fuel to Test Panel T Test Engine Figure 3: Schematic Representation of the Facility Fuel System American Institute of Aeronautics and Astronautics

11 BRSI/'LEGVI Figure 4: Photograph of PTE Installed into Leg VI Test Cabin Vitiator PTE Air Nozzle Figure 5. PTE Facility and Engine Installation Figure 6. Pitot Rakes at the Cowl Lip 10 American Institute of Aeronautics and Astronautics

12 Figure 7: Flow Fences Installed on the Inlet Ramp Boeing 3D CFD, CL Boeing 3D CFD, 4" Off CL Left Rake 2.72" Off CL Center Rake * Right Rake 1.5" Off CL cowl Cold, No Fence Cold, with Fences Hot, with Fences 1.0 i V PTE29 PTE30 PTE31 N "<0 0.0 Body 0 rho*u, lbm/fta2-s rho*u, lbm/fta2-s rho*u, lbm/fta2-s Figure 8. Comparison of Cowl Lip Inlet Profiles from PTE Test Data and 3D CFD at Mach American Institute of Aeronautics and Astronautics

13 CM (/> 0_ In oi Inlet Unstarted 0) Q. CO DC =5 (/> Run 87 Critical Point 0) 0) Run Throat Mach Number, M2 Figure 9. PTE and Inlet Test Isolator Data Pre-SiH4 ' ' Pre-SiH4 With-SiH4 ' ' ' With-SiH4 Post-SiH4 " ' Post-SiH4 Performance Point Tare - Body " " " Tare - Cowl Axial Distance Figure 10. Combustor Pressure Distributions from Run American Institute of Aeronautics and Astronautics

14 1.1u o 0 cn 0 cn C -" CD C CD Performance Valu "a5 ^ ~~ -...._. ETAC PS2.5/PS2 Figure 11. Relative PTE Performance Results at Mach 6.5 Pre-SiH4 ' - Pre-SiH4 With-SiH4 ' ' With-SiH4 Post-Si H4 ' ' Post-SiH4 Tare - Body i ^ " " " Tare - Cowl Q. Axial Distance Figure 12. Combustor Pressure Distributions from Run PS2.5/PS2 ETAC Figure 13. Relative PTE Performance Results at Mach American Institute of Aeronautics and Astronautics

15 Fuel Injector Manifold Fuel Injector Copper Wall Water Lines Figure 14. Temperature Distributions Around a Fuel Injector Flight Engine Temperature Stable Combustion Threshold DTfueM Tfuel2 DTfuelS D Tfuel4 Ignition Silane On Silane Off Figure 15. Fuel Manifold Temperatures During Run 70 Table 1. PTE Test Conditions Flight Mach Number Dynamic Pressure (psf) Test Runs 1 to to to American Institute of Aeronautics and Astronautics

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