气膜冷却孔对涡轮发动机非定常流动的影响

Effect of Film Cooling Hole on Turbine Engine Unsteady Flow

为了研究气膜冷却孔对涡轮发动机非定常流动的影响,将发动机工作区比作平板,采用Realizable k-ε紊流模型,在SIMPLE算法基础上,利用有限体积法对控制方程进行离散。针对不开槽姊妹孔、开槽圆柱孔以及开槽姊妹孔3种不同气膜孔型模拟了随时刻变化的过程。结果表明:开槽姊妹孔由于主射流掺混比不开槽姊妹孔剧烈,因此冷却效率比不开槽姊妹孔高;开槽圆柱孔的反向涡旋对比开槽姊妹孔大,所以开槽圆柱孔对壁面的冷却效果比开槽姊妹孔的好。

In order to study the effects of unsteady flow with film cooling holes on turbine engine,the paper compared the work place of turbine engine to a flat,adopted Realizable k- ε turbulence model based on SIMPLE algorithm,and discretized the control equation using finite volume method. Numerical simulation of development process was performed on three different shape holes： sister holes without groove,groove cylindrical hole and groove sister holes. The result shows that the acting of jet and cross of groove sister hole is more acute than that of sister hole without groove,then the film cooling effectiveness of groove sister holes is higher than that of sister holes without groove. The counter-rotating vortex pair of groove cylindrical hole is bigger than that of the groove sister holes,the cooling effectiveness of groove cylindrical hole is inferior to that of groove sister holes.