Design and performance of a liquid-hydrogen, liquid-oxygen gas generator for driving a 1000-horsepower turbine
National Aeronautics and Space Administration, 1962 - Technology & Engineering - 28 pages
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13 inches 9 inches annular orifices approximately 1.0 Axial temperature measurements chamber diameter chamber gas velocity chamber-exit characteristic exhaust velocity combustion chamber Combustion temperature thermo combustion-chamber length complete mixing constant oxidant flow decrease in temperature design and performance enthalpy exhaust nozzle exhaust pipe flow area flow coefficient ft/sec fuel-weight ratio gas temperature GAS-GENERATOR DESIGN ground electrode horsepower Hot-gas temperatures obtained Hydrogen and Liquid ignition system impinging injector injection injector assembly injector configuration injector design injector face injector plenum Isentropic lb/sec lb/sq Lewis Research Center liquid-oxygen gas Mach number misalinement nozzle throat nozzle-throat area oxidant flow rate oxygen jets oxygen orifices percent pound per second pressure drop propellant flow rate propellant injector pure oxygen radial ratio of specific ratios between 0.490 resulted second and oxidant shown in figure Single thermocouples spark specific heats streaks of hot temperature profile tested thermocouple locations tion total propellant flow turbine Vaporization wall cooling