NASA NTRS · 19720024297
Oxygen-hydrogen injector performance and compatibility with ablative chambers
Abstract
An 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.
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Wanhainen, J. P.. 1972-09-01. Oxygen-hydrogen injector performance and compatibility with ablative chambers. https://ntrs.nasa.gov/citations/19720024297
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