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Oxygen-hydrogen injector performance and compatibility with ablative chambersAn experimental investigation was conducted to develop a high-thrust, high-performance, concentric tube injector element for use with near liquid hydrogen and liquid oxygen propellants. A parallel tube coaxial injector yielded 98 percent theoretical characteristic exhaust velocity efficiency. Installation of swirlers in the oxidizer tube improved performance but caused high ablative erosion near the injector. Film cooling significantly reduced ablative erosion near the injector but did not completely alleviate gouging adjacent to each outer injection element.
Document ID
19720024297
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Wanhainen, J. P. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 2, 2013
Publication Date
September 1, 1972
Subject Category
Thermodynamics And Combustion
Report/Patent Number
E-6926
NASA-TM-X-2615
Report Number: E-6926
Report Number: NASA-TM-X-2615
Accession Number
72N31947
Funding Number(s)
PROJECT: RTOP 113-31
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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