基于平行压气机模型的发动机整机性能计算方法

为了满足航空发动机型号设计、适航审定等阶段所采用的仿真模型能够快速有效计算进气畸变对发动机性能影响的需要,开展了基于平行压气机模型的发动机整机性能计算方法研究。在发动机整机性能通用仿真系统基础上,通过继承、关联等方法,构建平行压气机部件类；以发动机整机性能仿真模型迭代计算参数作为子压气机出口边界约束,进行子压气机工作点迭代计算,从而获得压气机、发动机工作点及发动机整机性能；以某型混合排气加力式双转子涡扇发动机为仿真对象,分别计算了设计点性能和进气畸变条件下的非设计点性能,验证了计算方法的有效性,并分析了进气畸变对压气机及发动机整机性能的影响。

Calculation Method of Engine Overall Performance Based on Parallel Compressor Model

In order to meet the need of using simulation models in the stages of aircraft engine model design and airworthi-ness certification to quickly and effectively calculate the impact of intake distortion on engine performance, a study is con-ducted on the calculation method of engine overall performance based on parallel compressor model. On the basis of a general simulation system for engine performance, parallel compressor component classes are constructed through inheri-tance, association, and other methods; using the iterative calculation parameters of performance simulation model of the entire as the boundary constraint for the outlet of the sub-compressor, the operating point of the sub-compressor are itera-tively calculated to obtain the compressor, engine operating points, and overall engine performance; a certain type of hy-brid exhaust afterburner dual rotor turbofan engine is used as the simulation object to calculate the design point perfor-mance and the off-design point performance under inlet distortion conditions, verifying the effectiveness of the calcula-tion method and analyzing the impact of inlet distortion on the overall performance of the compressor and engine.