某型弹用涡喷发动机安装性能分析

推进技术 ›› 2003, Vol. 24 ›› Issue (1): 12-16.

某型弹用涡喷发动机安装性能分析

王占学,乔渭阳,蔡元虎

西北工业大学航空动力与热力工程系陕西西安710072;西北工业大学航空动力与热力工程系陕西西安710072;西北工业大学航空动力与热力工程系陕西西安710072

发布日期:2021-08-15

Analysis of installation performance of the missile turbojet engine

Dept. of Aeroengine Engineering, Northwestern Polytechnical Univ., Xi’an 710072, China;Dept. of Aeroengine Engineering, Northwestern Polytechnical Univ., Xi’an 710072, China;Dept. of Aeroengine Engineering, Northwestern Polytechnical Univ., Xi’an 710072, China

Published:2021-08-15

摘要/Abstract

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

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

王占学,乔渭阳,蔡元虎. 某型弹用涡喷发动机安装性能分析[J]. 推进技术, 2003, 24(1): 12-16.