Materials Compatibility With Oxidizer Rich Gases At Elevated Temperatures And Pressure
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Materials Compatibility with Oxidizer-Rich Gases at Elevated Temperatures and Pressure
Author | : National Aeronautics and Space Administration (NASA) |
Publisher | : Createspace Independent Publishing Platform |
Total Pages | : 102 |
Release | : 2018-07-18 |
Genre | : |
ISBN | : 9781723201622 |
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An investigation of oxygen compatibility and resistance to ignition of candidate materials for use in a liquid rocket engine designed to incorporate an oxidizer rich preburner-LOX turbopump configuration was discussed. The program was divided into two basic tasks. The first task was to develop a preliminary design of an oxidizer turbopump preburner section complete with thermal and MS Parameter analyses and to develop a conceptual design of the main injector with a preliminary engine specification as the final product. The second task was directed totally at testing materials in oxygen-rich environments. Unspecified Center HIGH ENERGY OXIDIZERS; LIQUID ROCKET PROPELLANTS; PROPELLANT PROPERTIES; ROCKET OXIDIZERS; TURBINE PUMPS; COMPATIBILITY; MATERIALS TESTS; PERFORMANCE PREDICTION; ROCKET TEST FACILITIES...