Saturn Booster Liquid-Oxygen Heat Exchanger Design and Development
Liquid propellant rocket vehicles require tank pressurization during powered flight to prevent pump cavitation and provide tank structural rigidity. In the Saturn booster, liquid-oxygen tank pressurant is obtained by evaporating liquid oxygen, bled from the main liquid-oxygen pump discharge of each engine, in eight heat exchangers, one extracting heat from each turbine exhaust. The problem was to develop a heat exchanger which would satisfy the pressurization requirements for two different engine thrust levels while operating at a steady flow rate and pressure.
KeywordsHeat Exchanger Liquid Oxygen Tank Pressure Heat Exchanger Surface Turbine Exhaust
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