民用飞机涡扇发动机短舱TPS低速构型数值模拟

摘要

TPS(Turbofan Propulsion Simulator)本身的失速特性对于运输类飞机低速带动力风洞试验有着重要的影响,而当代大量的低速带动力试验均采用TPS来模拟涡扇发动机的喷流效应.通过对TPS初始构型和修形后两个构型的数值模拟,研究了TPS唇口下垂位置和头部半径对失速特性的影响.结果表明,TPS唇口处较高的负压峰值和较大的逆压梯度引起TPS构型本身的大面积分离；将TPS唇口下垂和增大唇口头部半径能够有效降低TPS唇口处的负压峰值和逆压梯度,明显改善TPS构型的失速特性.%Stall characteristics of turbofan propulsion simulator (TPS) have significant influence on the low speed powered wind tunnel test of civil aircraft, and TPS is widely used in most of the current low speed powered wind tunnel tests to simulate the jet effect of turbine engine. Influences of the TPS nacelle lip drop location and nose radius on the stall characteristics are investigated by numerical simulations of the initial configuration and the modified configuration. Simulation results indicate that high suction peak and adverse pressure gradient exist at the TPS nacelle lip and induce large area separation over the outer surface. Dropping the location and increasing the nose radius can effectively reduce the suction peak and adverse pressure gradient at the TPS lip and improve the stall characteristics remarkably.