Abstract: A digital computer method was given for simulating aero-engine acceleration dynamic performance based on the engine component characteristics The simulations of a twin-spool turbojet were presented The two layer iterations for predicting the effects of variable nozzle area on acceleration dynamic response of the engine were developed It was found that the transient operating time during accelerations could be considerably reduced enlarging nozzle area Numerical simulations also show that the acceleration dynamic operations of the engine can be optimised using proper nozzle area controls

Key words: Turbojet engine;Variable area nozzle;Acceleration performance;Numerical simulation

摘要： 基于发动机各部件特性 ,应用流动参数变比热容计算方法对某型双轴发动机加速过程进行了数值分析。发展了一种双层迭代方法 ,成功地模拟了变喷管喉道面积对发动机加速性的影响 ,并初步给出了改善发动机加速性的变喷管调节方案。

关键词: 涡轮喷气发动机;可调截面喷管;加速性能;数值仿真