平面叶栅中冷气射流三维分离的数值模拟  

Numerical simulation on three-dimensional separation of cooling jet in cascade

作　　者：杨科[1] 王松涛[1] 王仲奇[1] 冯国泰[1] 

机构地区：[1]哈尔滨工业大学能源科学与工程学院,黑龙江哈尔滨150001

出　　处：《推进技术》2003年第1期43-46,共4页Journal of Propulsion Technology

基　　金：国家 973资助项目 (G19990 2 2 3 0 7);国家自然科学基金资助项目 (5 99760 0 7)

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 。The influence of cooling jet on plane cascade was studied. Three-order Godunov scheme and the Baldwin-Lomax turbulent model were used to solve the three-dimensional Navier-Stokes equations. The cooling jet hole was located at the position of 5 mm, 10 mm, 43 mm, 50 mm 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 of jet angle would has.

关 键 词：平面叶栅 冷气射流 数值模拟 射流场 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]