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Steady-State Heat Transfer Analysis on Injector Half-Thrust Chamber Assembly Concept Design

This concept design review outlines the procedure used for steady-state heat transfer analysis on the injector modeled half-thrust chamber assembly. Calculate chamber properties, conduct gas-side and fuel-side analyses, iterate on temperatures, pressure, and heat flux, and utilize correlations for propene properties. Obtain detailed results and convective heat transfer coefficients.

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Steady-State Heat Transfer Analysis on Injector Half-Thrust Chamber Assembly Concept Design

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

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

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

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

  6. 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 Thrust Chamber Assembly Concept Design Review

  7. 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: Thrust Chamber Assembly Concept Design Review

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

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

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

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

  12. Fuel Convective Heat Transfer Coefficient Thrust Chamber Assembly Concept Design Review

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