一种航空发动机全状态性能模型

采用基于脊背特性的压气机和涡轮部件性能的参数表示方法建立了航空燃气涡轮发动机全状态性能仿真计算模型.使用该模型对某单轴涡喷发动机的地面节流特性进行了计算模拟,并且与传统的发动机性能模型的计算结果进行了对比.结果表明:主要截面参数的平均相对误差不超过07%,说明该模型在慢车以上转速与传统模型具有相同的计算精度.使用该模型同时对该单轴涡喷发动机的空中风车状态、地面起动加速的全过程、以及减速全过程进行了数值模拟,验证了该模型的全状态性能仿真能力,计算结果定性地符合发动机在各个不同工作状态的物理特征及变化趋势. 

A full states performance model for aero engine

A full states performance simulation model for aero engine was established by using the parametric representation based on the backbone characteristics of compressor and turbine.Part loading performance of a turbojet engine at sea level static condition was simulated through the model.Compared with the traditional model,results showed the average errors of the main parameters were no more than 0.7 ％,indicating the full states model had the same precision as the traditional model above idle speed.The simulations for windmill state,ground starting and acceleration to maximum power,and deceleration from maximum power to zero were performed respectively by using the full states model.The ability of simulating full states performance of engine was verified.The results are qualitatively consistent with the operative characteristics and physical laws of the engine.