航空发动机性能与空气系统联合仿真方法研究

Research on Joint Performance Simulation Method of Aero-engine and Air System

随着军用航空发动机性能的不断发展,热端部件温度不断提高,为确保热端部件稳定工作所需的空气系统冷却气质量流量不断增加,空气系统对发动机总体性能的影响加剧。为准确计算发动机所需的冷却气质量流量,提出一种航空发动机总体性能与空气系统联合仿真模型搭建方法,并计算某型发动机整机模型地面条件下不同节流状态及大气温度偏差下压气机各级的引气百分比及涡轮进出口冷却气质量流量。结果表明:随着高压转子转速的降低,压气机各级引气百分比略有上升,引气质量流量下降;在相同转速下,随着大气环境温度的下降,引气百分比下降。

With the continuous development of military aero-engine performance,the temperature of the hot end components is constantly increasing.In order to ensure the stable operation of the hot end components,the cooling gas mass flow rate of the air system is increasing,and the influence of the air system on the overall performance of the engine is aggravated.In order to accurately calculate the cooling gas mass flow rate required by the engine,this paper proposes a joint simulation model construction method of the overall performance of the aero-engine and the air system,and calculates the bleed air percentage of each stage of the compressor and the mass flow rate of the turbine inlet and outlet cooling gas under different throttling states and atmospheric temperature deviations under the ground conditions of a certain engine model.The results show that with the decrease of the speed of the high-pressure rotor,the percentage of bleed air at all stages of the compressor increases slightly,and the mass flow rate of the bleed air decreases.At the same speed,with the atmospheric ambient temperature decrease,the percentage of bleed air decreases.