In this paper, several aspects of these combustion instabilities are discussed, including injector, combustion chamber, feed system, and nozzle influences. Several of the initial configurations resulted in combustion instability of the workhorse gas generator assembly at a frequency near the first longitudinal mode of the combustion chamber. Over the past several years, development of the gas generator for the J-2X engine has progressed through a variety of workhorse injector, chamber, and feed system configurations on the component test stand at the NASA Marshall Space Flight Center (MSFC). ![]() The contract for development was let to Pratt & Whitney Rocketdyne in 2006. ![]() This engine, designated the J-2X, is a higher pressure, higher thrust variant of the Apollo-era J-2 engine. ![]() Analyses of Longitudinal Mode Combustion Instability in J-2X Gas Generator Development The National Aeronautics and Space Administration (NASA) and Pratt & Whitney Rocketdyne are developing a liquid oxygen/liquid hydrogen rocket engine for future upper stage and trans-lunar applications.
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