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- W2326982078 abstract "A program has recently been completed to examine the dynamic stability characteristics of a large hydrogen and liquid oxygen injector. The injector program was conducted in a design-to-cost, low risk approach in order to reduce component and engine life cycle costs. The objective of the testing was to subject the combustion process to pressure perturbations produced with high explosive charges. An ablative chamber was utilized during the dynamic stability tests. The testing was conducted in order to demonstrate the combustion stability margin of the injector which utilized acoustic cavities and injector face baffles. Results of the testing exhibited extremely short damp times with nominal temperature hydrogen fuel and no response to the high explosive when running with cold hydrogen. The design, fabrication, and testing of the injector were conducted for the U.S. Air Force as part of the McDonnell Douglas EELV/Delta IV contract F04701C-95-0035." @default.
- W2326982078 created "2016-06-24" @default.
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- W2326982078 date "1997-07-06" @default.
- W2326982078 modified "2023-09-27" @default.
- W2326982078 title "Development of a low cost 650,000 lbf thrust H2/O2 booster engine injector" @default.
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- W2326982078 doi "https://doi.org/10.2514/6.1997-3314" @default.
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