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Low loss injector for Space Shuttle main engine. Center director's discretionary fundAn efficient propellant injection method to raise the Space Shuttle Main Engine (SSME) thrust and payload is discussed. Relatively large diameter injector elements with low pressure loss are recommended for the main combustion chamber and the pre-burners. Smaller losses admit more propellant flow which then raises thrust. Payload is not only gained by specific impulse but also by thrust. The chamber pressure is stabilized by selecting the proper cavity size for the injector elements while reducing the injection pressure loss which normally is kept high for stability. The rather large injector element recesses provide acoustic damping which makes baffles and acoustic absorbers unnecessary. A tenfold reduction of flow induced stresses which are rather high in the present design is shown. Relaxed tolerances, fewer elements, and better maintenance are offered. The study was conducted under a center director discretionary fund assignment.
Document ID
19840011401
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Vonpragenau, G. L. (NASA Marshall Space Flight Center Huntsville, AL, United States)
Date Acquired
September 4, 2013
Publication Date
February 1, 1984
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
NASA-TM-82567
NAS 1.15:82567
Accession Number
84N19469
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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