Establishment Of Design Method For Liquid Hydrogen Regenerative Cooling Combustor Of Lox/hydrogen Rocket Engine

摘要

An optimum method for design of a liquid hydrogen regenerative cooling combustor for the LOX/hydrogen engine was constructed using the author's previous empirical correlation of C efficiency and calculation model for combustion characteristics, and the present calculation model for the heat load characteristics for LOX/hydrogen combustion. Using this method, the atomization characteristics of the injected LOX jet, the combustion performance including combustion stability, and the heat load on the combustor were evaluated for LOX/hydrogen upper-stage engines such as the LE-5, RL-10 and HM-7. This method was then applied to the LE-5B engine, which is the derivative engine of the LE-5 and has . been used as the second stage of the H-2A launcher, to improve combustion stability and to optimize configuration of the injector and combustor. A reduction of about 30% in chamber length of it with sufficient combustion performance was achieved by such optimization.