空气涡轮火箭发动机性能仿真分析  

Simulation analysis of air turbo rocket engine

作　　者：朱岩[1] 吴弈臻 马元[1] 南向谊[1] ZHU Yan;WU Yizhen;MA Yuan;NAN Xiangyi(Xi'an Aerospace Propulsion Institute,Xi'an 710100,China)

机构地区：[1]西安航天动力研究所,陕西西安710100

出　　处：《火箭推进》2021年第3期67-73,共7页Journal of Rocket Propulsion

基　　金：军事科学院预先研究项目(STS/MY-KFKT-2017004)。

摘　　要：针对空气涡轮火箭(ATR)发动机展开研究,在建立发动机全系统数学模型仿真系统的基础上,研究不同推进剂组合对发动机性能影响,并采用发动机组件关键参数对推力比冲影响分析方法,确定发动机关键参数范围,结果表明:推力方面液氧甲烷(LOX/CH_(4))推进剂更具优势,比冲方面液氢液氧(LOX/LH_(2))推进剂具有很大优势。发现涡轮效率提高对发动机比冲增益最为显著,每提高1%涡轮效率比冲平均增加9.1 s;压气机效率的影响次之,比冲平均增加8.0 s。随着涡轮和压气机效率的增加,发动机比冲增加而推力下降;随着燃烧效率的增加,发动机推力和比冲均增加。Based on the whole system mathematical model of Air Turbo Rocket,this paper focuses on Air Turbo Rocket engine research and the influence of different propellants on the engine.And based on the analysis the influence of key parameters of engine components on thrust and specific impulse,the range of key engine parameters was determined.The result shows:the liquid oxygen and methane propellant have relative advantage in thrust,and the liquid hydrogen and oxygen propellant have great advantage in specific impulse.The increase in turbine efficiency has the most significant impact on the engine specific impulse,for every 1%increase in turbine efficiency,the specific impulse increases by an average of 9.1 s.The effect of compressor efficiency is second,the specific impulse increases by an average of 8.0 s.As the efficiency of turbine and compressor efficiency increases,engine specific impulse increases and thrust decreases.As combustion efficiency increases,engine specific impulse and thrust increase.

关 键 词：ATR发动机 敏感参数 性能指标 推进剂 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]