Prediction and evaluation of aerodynamic stability of high bypass ratio turbofan engine deployed with thrust reverser

被引：0
|
作者：
Wang Z. [1 ]
Shen X. [2 ]
Hu J. [1 ]
机构：
[1] College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing
[2] Aero Engine (Group) Corporation of China Shenyang Engine Research Institute, Shenyang
来源：
Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica | 2017年 / 38卷 / 02期
基金：
中国博士后科学基金;
关键词：
Aerodynamic stability; Experimental verification; Flow field distortion; High bypass ratio turbofan engine; Numerical simulation; Reverser flow re-ingestion; Thrust reverser;
D O I：
10.7527/S1000-6893.2016.0143
中图分类号：
学科分类号：
摘要：
Three-dimensional CFD numerical simulation, engine stability calculation and bench test of engine inlet distortion are combined to predict and assess the influence of re-ingestion of the reverser flow on the aerodynamic stability of the high bypass ratio turbofan engine when the thrust reverser is deployed. By means of three-dimensional CFD numerical simulation, the distortion degree of the engine inlet flow field is acquired. On this basis, the aerodynamic stability of the engine is predicted by the stability calculation program, and the prediction results are verified by the engine bench test. The CFD calculation results show that, with the decrease of the relative flow Mach number, the possibility of re-ingestion of the reverser flow is increased, and the inlet flow field distortion of the outboard engine is the most serious when the relative flow Maher number decreases to 0.05. The results of stability calculation analysis and engine bench test in the inlet distortion situation show that, in the assessment of the target state, if the inlet distortion is only caused by the re-ingestion of the reverser flow, the engine will not be unstable. © 2017, Press of Chinese Journal of Aeronautics. All right reserved.
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