液氧/煤油推进剂液体火箭发动机循环动力平衡分析

Cycle Power Balance Analysis for Liquid Rocket Engine with LO_2/RP—1 Propellant Combination

本文对以液氧/煤油为推进剂的发生器循环和分级燃烧循环方案进行了分析,求出了各种循环方案的最大室压,给出了室压、推力、燃烧室混合比和喷管出口直径对发动机比冲和系统平衡参数的影响,并探讨了平衡参数对效率、涡轮压比和发生器(或预燃室)

The gas generator cycle and staged combustion cycle with LO_2/RP—1 propellants combination have been analyzed in this paper. The maximum combustion chamber pressure for various cycles has been found. The effect of combustion chamber pressure, sea level thrust, chamber mixture ratio, nozzle exit diameter on engine specific impulse and system balance parameters is given. The sensitivity dependences of effeciences, turbine pressure ratio, gas generator (or preburner) mixture ratio and other design parameters on balance parameters have been investigated