旋转涡轮叶片端部气膜冷却的数值计算  

NUMERICAL SIMULATION OF FILM COOLING IN ROTATING BLADE TIP

作　　者：杨汇涛[1] 曹玉璋[1] 

机构地区：[1]北京航空航天大学

出　　处：《航空动力学报》1998年第3期285-288,共4页Journal of Aerospace Power

摘　　要：旋转情况下，考虑离心力场的浮升力以及科氏力对流动的影响，用ＳＩＭＰＬＥ方法，ｋ－ε湍流模型，并考虑了壁面函数，数值模拟了叶片端部的气膜冷却。和以往观点不同的是：旋转叶片与非旋转的相比，绝热温比高，气膜冷却有所改善，但换热系数大，并初步分析了原因。Numerical simulation of film-cooling in two types of blade tip in rotating case is completed by SIMPLE method.Turbulent eddy viscosity is determined by k-ε two equation model,while the wall function is considered in boundary layer.The simulation shows that centrifugal and Coriolis forces affect the flow and centrifugal force also brings about buoyancy,which is different from the usual viewpoint that the rotation has no effect on heat transfer and film cooling in blade tip.The result also indicates that the cooling effectiveness of the rotating blade is better than that of non-rotating one in the range considered.

关 键 词：气膜冷却 叶片 数值模拟 涡轮 航空发动机 

分 类 号：V232.4[航空宇航科学与技术—航空宇航推进理论与工程] V231.1