| 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 |
| DOI： |
| 分类号:V435 |
| 基金项目: |
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| Analysis of installation performance of the missile turbojet engine |
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WANG Zhan xue, QIAO Wei yang, CAI Yuan hu
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Dept. of Aeroengine Engineering, Northwestern Polytechnical Univ., Xi’an 710072, China
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| 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 |
