EVALUATION OF PERFORMANCE CHARACTERISTICS OF A HIGH CHAMBER PRESSURE OXIDIZER-RICH STAGED COMBUSTION GAS GENERATOR.
PURDUE UNIV LAFAYETTE IND JET PROPULSION CENTER
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The report describes an experimental investigation of the effects of high stagnation pressures, extremely oxidizer-rich mixture ratios, and various injector configurations on the performance characteristics of a liquid rocket combustor. These environmental conditions can be encountered in the propulsion gas supply for turbopump assemblies on liquid rocket propulsion systems, auxiliary power sources, or working fluid supply on thrust vector control systems. The storable, hypergolic propellants nitrogen tetroxide and a 50-50 mixture by weight of hydrazine and unsymmetrical dimethylhydrazine were selected for investigation. The experimental combustor consisted of a liquid propellant injector, combustion chamber, combustion chamber extensions, combustion gas mixing ring, and nozzle. Four different injectors, all of the liquid-liquid unlike impingement type, were employed in the investigation to examine the performance dependence on droplet size and injector configuration. Stagnation pressures were varied from 1050 psi to 3650 psi. The possible chemical kinetic effects on performance were isolated by varying the mixture ratio from 13 to 24 and employing combustors with significant changes in length. Author
- Liquid Propellant Rocket Engines