Experiments on an Oxidizer-Rich Preburner for Staged Combustion Cycle Rocket Engines

摘要

In this study, characteristics of the oxidizer-rich preburner for the staged combustion cycle rocket engine were investigated. The preburner test model employed simplex injectors for fuel and oxidizer injection. The body of the combustor was protected by regenerative cooling with liquid oxygen. Stable ignition of the preburner was realized by an auxiliary propellants supply. At design and off-design test conditions, the preburner showed stable performance. Depending on the test conditions, combustion pressure varied from 19.2 to 20.0 MPa. Exhaust gas temperature changed from 545.34 to 743 K, and it showed uniform distribution. Pressure fluctuations were also controlled within 1% of the combustion pressure in all cases.