Performance and Stability Analyses of Rocket Thrust Chambers with Oxygen/Methane Propellants

摘要: Liquid rocket engines using oxygen and methane propellants are being considered by the National Aeronautics Space Administration (NASA) for future in-space vehicles. This propellant combination has not been previously used in flight-qualified engine systems developed NASA, so limited test data analysis results available at this stage of early development. As part activities Propulsion Cryogenic Advanced Development (PCAD) project funded under Exploration Technology Program, NASA Marshall Flight Center (MSFC) evaluating capability to model combustion performance stability propellants. activity proceeding about two years paper is a summary date. Hot-fire oxygen/methane devices modeling investigations have come from several sources, including multi-element injector tests with gaseous 1980s, single element through Constellation University Institutes both liquid conducted MSFC PCAD. For latter, impinging coaxial injectors included. Configurations were modeled one-dimensional codes, Rocket Combustor Interactive Design Analysis code Coaxial Injector Combustion Model. Special effort was focused on how these codes can be priori, what anchoring or calibrating features need applied, improved future. Low frequency instability (chug) occurred, frequencies ranging 150 250 Hz, liquid/liquid propellants, techniques Wenzel Szuch. High-frequency also occurred first tangential (1T) mode, 4500 Analyses transverse mode resonances empirical methods Hewitt.