Materials compatibility with oxidizer-rich gases at elevated temperatures and pressure

摘要

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.