Abstract: The influence of cooling jet on plane cascade was studied. Three order Godunov scheme and the Baldwin Lomax turbulent model were applied to solve the three dimensional Navier Stokes equations. The cooling jet hole was located at the position of 5mm, 10mm, 43mm, 50mm in axial coordinate respectively. At each position four different jet angles :30°, 60°, 90°and 120°were set respectively. The results show that the jet angle has little effect on the flow if the coolant hole is near to the leading edge. Nearer to the trailing edge the coolant hole is, more effect on the flow the jet angle would has.

Key words: Turbine cascade;Gas jet;Cooling;Numerical simulation;Separation

摘要： 为了研究冷气射流对平面叶栅气动特性的影响 ,采用三阶精度Godunov格式和B L湍流模型求解三维N S方程 ,对冷气孔处于气冷涡轮叶栅的轴向位置为 5mm ,10mm ,4 3mm和 5 0mm ,喷射角度分别为 3 0°,60°,90° ,12 0°条件下进行了 16组方案计算。结果表明 ,叶片前缘冷气孔角度对流场底影响较小。越接近叶片尾缘 ,冷气孔角度对流场的影响越明显

关键词: 涡轮叶珊;气体射流;冷却;数值仿真;分离