摘要
航空发动机可以对空气增压,并且增加气流温度,理论上存在应用于超声速引射系统的可能。分析了气源对引射器性能的影响以及引气对航空发动机的影响,介绍了3种航空发动机在超声速引射系统中可能的布局方案。针对某领域内的排气参数要求,分别对3种布局方案进行了计算分析。计算结果表明,当上游气体压强为0.044×10^(5) Pa和0.0293×10^(5) Pa时,通过合理选择发动机的布局以及工作参数,发动机可以直接将上游气体排出或者作为驱动气源应用于超声速引射系统。
The pressure and temperature of air flow can be increased by aero engine,so the application of aero engine in supersonic ejector system is possible.The effects of air source on ejector performance and the effects of bleeding on aero engine performance were analyzed.And 3 types of aero engine layout in supersonic ejector system were presented.According to the requirements of a supersonic ejector system,the performance parameters of all 3 types of aero engine layout were calculated.The calculation results indicate that when the pressure of the upstream gas is 0.044×10^(5) Pa and 0.0293×10^(5) Pa,aero engine can directly discharge the upstream gas or be used as the driving gas source for the supersonic ejector system by reasonable selecting the engine layout and working parameters.
作者
徐大川
阳玲
史煜
顾蕴松
任泽斌
XU Dachuan;YANG Ling;SHI Yu;GU Yunsong;REN Zebin(College of Aerospace Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;Facility Design and Instrumentation Institute,China Aerodynamics Research and Development Center,Mianyang 621000,China)
出处
《国防科技大学学报》
EI
CAS
CSCD
北大核心
2022年第4期125-133,共9页
Journal of National University of Defense Technology
基金
国家部委基金资助项目(8634002AA0301)。
作者简介
徐大川(1985-),男,安徽界首人,博士研究生,E-mail:xudachuan@nuaa.edu.cn;通信作者:任泽斌,男,副研究员,硕士,E-mail:renzebin401@163.com。
