相似理论在航空发动机总体性能仿真中的应用  

Application of Similarity Theory in Aeroengine Performance Simulation

作　　者：赵军[1] ZHAO Jun(Aviation Engineering Institute,Civil Aviation Flight University of China,Guanghan Sichuan 618307,China)

机构地区：[1]中国民航飞行学院航空工程学院,四川广汉618307

出　　处：《计算机仿真》2023年第1期79-84,共6页Computer Simulation

基　　金：四川省教育厅自然科学项目(16ZB0035);中国民用航空飞行学院科学研究重点基金(ZJ2016-01)。

摘　　要：以相似理论为指导研究了外界大气温度、飞行高度和飞行马赫数变化时对发动机总体性能参数的影响,并进行了各换算参数的变化曲线研究。结果表明构建的模型发动机换算燃油流量的最佳θ指数为0.67,该值和发动机型号相关,具体的发动机需要单独优化;同时发现,对于温度参数来讲,即使是同一款发动机,不同截面处的换算温度的最佳θ指数也不一致。通过七个初猜值的相似换算值与换算低压转速的变化规律研究,发现在保持飞行马赫数不变的情况下换算参数的曲线离散性较小,仿真计算中以飞行马赫数为参变量构造多条初猜值曲线,保证迭代计算初值的合理性,能较好的降低迭代次数,提高数字仿真速度。Under the guidance of similarity theory, the effects of ambient air temperature, flight altitude and flight Mach number on the overall performance parameters of the engine were studied, and the change curves of the corrected parameters were also studied. The results show that the optimal theta index of the corrected fuel flow is 0.67,which is related to the engine model. The specific engine needs to be optimized separately. At the same time, it is found that for the temperature parameters, even for the same engine, the optimal theta index of the corrected temperature at different sections is not consistent. It is found that the discreteness of the corrected parameter curve is small when the flight Mach number remains unchanged. In the simulation calculation, the flight Mach number can be used as a parametric variable to construct several initial guess curves to ensure the rationality of the initial value of iterative calculation, thus reduce the number of iterations and improve the speed of digital simulation.

关 键 词：航空发动机 相似理论 换算参数 总体性能 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]