航空发动机整机空气系统流动与传热数值模拟

Numerical Simulation of Flow and Heat Transfer in Air System of an Aero-Engine

为了研究航空发动机整机空气系统内流动与传热特性,以涡扇发动机整机空气系统为研究对象,分析了发动机真实状况下空气系统内的流动与传热特性。采用Mixture多相流模型进行数值计算,得到了该系统的速度场、压力场和温度场。结果表明:该系统内的流场是复杂的多涡流场,多个出口出现燃气倒灌;整个系统的腔压从前到后大致逐渐升高;由于主流通道燃气的入侵,导致高低压涡轮盘的温度较高,后轴承腔内滑油的冷却作用较为明显。研究结果为空气系统的设计提供了理论依据。

In order to study the flow and heat transfer in the aero-engine air system,the air system of a tur⁃bofan engine was analyzed.The flow and heat transfer in the aero-engine air system under real working conditions were analyzed.Mixture multiphase model was used to simulate the velocity,pressure,and temperature.Results show that the flow field is a complex multi-vortex flow filed,and multiple outlets have gas backflow.The pressure increases gradually from front to back.Due to the invasion of the outer duct gas,the temperature is high of the high and low pressure turbine disk,and the cooling effect of the lubricating oil in the back bearing cavity is obvi⁃ous.The result provides a theoretical basis for the design of the air system.