Abstract: The method for installation performance computation of missile turbojet engine was given. Based on the total pressure recovery computation and drag of S inlet, nozzle/afterbody analysis, the computer programs calculating the installation performance of missile turbojet engine were edited. With this program, the effect of customer’s bleeding, horsepower extracting, installation of inlet/nozzle and temperature on engine performance were computed. The results indicate that the installation performance should be computed to determine the effect of every installation factors.

Key words: Turbojet engine;Installation performance;Inlet drag;Nozzle/afterbody drag;Numerical calculation

摘要： 在分析S形进气道的总压损失以及进气道、喷管 后体外部阻力计算方法的基础上 ,建立了针对某型号导弹涡喷发动机的安装性能的计算程序 ,并结合实际飞行条件 ,对用户附加引气、功率输出、进气道、喷管安装和环境温度对该发动机性能的影响进行了计算。结果表明 ,引气和提取功率影响不大 ,而进气道总压损失和进、排气系统的外部阻力有重要影响 ,环境温度有一定影响 ;而且由于弹用涡喷发动机的推力比较小 ,必须考虑安装性能计算 ,以便准确判断每一种安装因素所造成的性能损失 ,为设计和使用方提供理论指导依据

关键词: 涡轮喷气发动机;安装性能;进气道阻力;喷管后体阻力;数值计算