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fuel/oxidizer-rich high-pressure preburnersThe analyses, designs, fabrication, and cold-flow acceptance testing of LOX/RP-1 preburner components required for a high-pressure staged-combustion rocket engine are discussed. Separate designs of injectors, combustion chambers, turbine simulators, and hot-gas mixing devices are provided for fuel-rich and oxidizer-rich operation. The fuel-rich design addresses the problem of non-equilibrium LOX/RP-1 combustion. The development and use of a pseudo-kinetic combustion model for predicting operating efficiency, physical properties of the combustion products, and the potential for generating solid carbon is presented. The oxygen-rich design addresses the design criteria for the prevention of metal ignition. This is accomplished by the selection of materials and the generation of well-mixed gases. The combining of unique propellant injector element designs with secondary mixing devices is predicted to be the best approach.
Document ID
19820002372
Document Type
Contractor Report (CR)
Authors
Schoenman, L.
(Aerojet Liquid Rocket Co. Sacramento, CA, United States)
Date Acquired
September 4, 2013
Publication Date
October 1, 1981
Subject Category
PROPELLANTS AND FUELS
Report/Patent Number
NASA-CR-165404
Funding Number(s)
CONTRACT_GRANT: NAS3-21753
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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