Investigation of a Gas Generator and Turbine Assembly with Metallized Propellants

摘要

An experimental program was conducted to investigate the operation of a gas generator and turbine with metallized liquid propellants (N2O4/alumizine) and to determine the magnitude of problems associated with solid deposition and erosion in the gas-generator combustion chamber and turbine. The turbine assembly utilized in the test program was a component of the turbopump used on the Jupiter engine. A gas generator was designed for this turbine and tests conducted to evaluate its operating characteristics. Several injector configurations were tested and a durable injector, acceptable for the latter phases of the program, was developed. Tests with the nozzle assembly from the turbine first stage demonstrated that solid particles in the gas stream would not cause significant problems in these nozzles. Tests were then conducted with the complete two-stage turbine. This turbine was successfully operated for durations up to 25 seconds with the only detrimental effects being moderate solid deposition in the second-stage nozzles. On other tests severe localized burning of the turbine hardware occurred. This was attributed to hot streaks in the turbine inlet gases resulting from an irregular spray pattern. A degradation of turbine efficiency because of the condensed-phase particles in the gas stream was indicated. (Author)