Test verification of LOX/RP-1 high-pressure fuel/oxidizer-rich preburner designsTwo fuel-rich and two oxidizer-rich preburner injectors are tested with LOX/RP-1 in an investigation of performance, stability and gas temperature uniformity over a chamber pressure range from 1292 to 2540 psia. Fuel-rich mixture ratios range from 0.238 to 0.367 and oxidizer-rich mixture ratios range from 27 to 48, and carbon deposition data are collected by measuring the pressure drop across a turbine simulator flow device. The oxidizer-rich testing demonstrates the feasibility of oxidizer-rich preburners, indicating equilibrium combustion as predicted, and the measured fuel-rich gas composition and C-asterisk performance are in excellent agreement with kinetic model predictions indicating kinetically-limited combustion.
Document ID
19820051497
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Lawver, B. R. (Aerojet Liquid Rocket Co. Sacramento, CA, United States)