32nd Joint Propulsion Conference and Exhibit · 1996 · 42 citations · 4 references
EngineeringAerospace EngineeringMechanical EngineeringComputational Fluid DynamicsComputational Heat TransferHeat TransferEngine CoolingEngine Heat TransferHeat Transfer FundamentalsHeat Transfer ModelingNozzle DesignThermal DesignCoolingCooling Of Rocket NozzlesRegenerative CoolingRegeneratively Cooled NozzlesRocket Engine NozzlesTemperature Gradient AnalysisThermal ConductivityThroat Geometry
Abstract : This study proved that transpiration cooling provides a better cooling scheme than regenerative cooling for long operating duration, liquid-fueled rocket engine nozzles. This proof was made on the basis of maximum wall temperature. This study compared transpiration cooling to regenerative cooling in the throat region of the Space Shuttle Main Engine Main Combustion Chamber. The study also analyzed the effects of porosity, solid thermal conductivity, and porous sphere size on a porous wall made of packed spheres. The transpiration cooled nozzle operated 35% cooler than a regeneratively cooled nozzle, but the temperature gradient at the hot gas surface was 72 times greater than the regeneratively cooled nozzle.
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