摘要
气膜冷却是保证航空发动机涡轮导向叶片正常工作的重要方法之一。为研究在较高涡轮前温度条件下气膜孔布置对叶片前缘降温的效果,采用ANSYS CFX的RNG k-ε模型对选定叶片进行了叶片前缘气膜冷却仿真。根据驻点、流动分离点等条件确定了气膜孔位置,并根据仿真效果对气膜孔布置进行调整。通过仿真结果表明,调整好位置的气膜孔对叶片前缘的冷却效果比较明显。
Film cooling is one of the important methods to ensure the turbine guide blade of aircraft engine working normally .In order to research the cooling effect that the gas film holes have on the leading edge of the blade under a higher turbine inlet temperature ,this paper adopts ANSYS CFX's RNG k‐εturbulence mode to simulate the film cooling effect of the leading edge of the blade and to determine and adjust the po‐sition of the gas film hole according to the stagnation point and the flow separation point .Simulation re‐sults show that the gas film with a well‐adjusted position has a better cooling effect on the leading edge of the blade .
出处
《西安航空学院学报》
2015年第1期3-8,19,共7页
Journal of Xi’an Aeronautical Institute
