某型弹用涡喷发动机安装性能分析  

Analysis of installation performance of the missile turbojet engine

作　　者：王占学[1] 乔渭阳[1] 蔡元虎[1] 

机构地区：[1]西北工业大学航空动力与热力工程系,陕西西安710072

出　　处：《推进技术》2003年第1期12-16,共5页Journal of Propulsion Technology

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 。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.

关 键 词：涡轮喷气发动机 安装性能 进气道阻力 数值计算 弹用发动机 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]