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)
Date Acquired
August 10, 2013
Publication Date
June 1, 1982
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 82-1153Report Number: AIAA PAPER 82-1153