1. Steady State Heat Transfer Analysis on Injector
Actual Injector Half
Modeled Injector Half
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Thrust Chamber Assembly Concept Design Review

2. Outline of Procedure Used
Get Chamber Properties from NASA code
Density
Sonic Velocity
Viscosity
Specific Heat
Thermal Conductivity
Pick Mach number tangent to surface: 0.4
Steady state heat transfer iteration for gas-side wall temperature for oxidizer and fuel sections
Compute fuel pressure loss through injector
2/10/2005
Thrust Chamber Assembly Concept Design Review

3. Thrust Chamber Assembly Concept Design Review
Fuel-Side Analysis
Copper Wall
Fuel Flow
Camber Gases
Convection
Conduction
Convection
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Thrust Chamber Assembly Concept Design Review

4. Gas-side Wall Temperature Iteration Steps
Guess Gas-Side Wall Temperature, Twg
Bartz Equation:
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Thrust Chamber Assembly Concept Design Review

5. Thrust Chamber Assembly Concept Design Review
Fuel-Side Iteration
Gas-Side Heat Flux:
Fuel-side Wall Temperature:
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Thrust Chamber Assembly Concept Design Review

6. Thrust Chamber Assembly Concept Design Review
Fuel-Side Iteration
Seider-Tate Forced Convection:
Correlations as a function of temperature at 350psi for transport and physical properties of Propene from NIST Chemistry Web book
Temperature at previous position used, Tinitial=405°R
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Thrust Chamber Assembly Concept Design Review

7. Thrust Chamber Assembly Concept Design Review
Fuel-Side Iteration
Fuel-side Heat Flux:
If fuel-side heat flux = gas-side heat flux, continue, else choose another guess for Twg
Fuel Temperature at current position:
2/10/2005
Thrust Chamber Assembly Concept Design Review

8. Thrust Chamber Assembly Concept Design Review
Fuel-Side Iteration
Pressure Iteration:
Move to next axial position and repeat
2/10/2005
Thrust Chamber Assembly Concept Design Review

9. Oxidizer-Side Analysis
Copper Wall
Stagnant O2
Camber Gases
Conduction
Convection
Fixed Temperature, Liquid O2 = 162°R
Copper Wall
Same procedure as fuel-side except Two is fixed at liquid oxygen temperature
2/10/2005
Thrust Chamber Assembly Concept Design Review

10. Thrust Chamber Assembly Concept Design Review
Fuel-Side Results, M = 0.4
dTwg ≈ 82°R
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Thrust Chamber Assembly Concept Design Review

11. Thrust Chamber Assembly Concept Design Review
Overall Results, M = 0.4
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Thrust Chamber Assembly Concept Design Review

12. Fuel Convective Heat Transfer Coefficient
2/10/2005
Thrust Chamber Assembly Concept Design Review