MT1涡轮导叶边界层拟序结构分析  

Coherent Structure for the Boundary Layer of MT1 Turbine Vane

作　　者：史万里[1] 葛宁[1] 

机构地区：[1]南京航空航天大学能源与动力学院,南京210016

出　　处：《燃气涡轮试验与研究》2013年第4期28-32,62,共6页Gas Turbine Experiment and Research

摘　　要：采用自主开发的大涡模拟程序NUL-TURBO,对MT1高压涡轮导叶的跨声速流场进行了数值模拟。在对半叶高位置叶片表面等熵马赫数分布实验数据对比验证的基础上,研究了有无气膜冷却两种情况下叶片表面流场的拟序结构。结果表明:无气膜射流时,叶片吸力面近尾缘位置存在分离转捩过程,并在此过程中发现了发卡涡"森林"现象;有气膜射流时,射流出口位置叶片表面边界层直接转捩为湍流,并发现了叶片压力面逆转捩过程中存在的涡拉伸形态。The flow field of MT1 high pressure turbine vane was numerically simulated using NUL-TUR- BO, which was a large eddy simulation program developed. Based on the validation of isentropic Mach num-ber distribution test data, coherent structures of blade surface with and without film cooling were analyzed. Without film cooling, coherent structures of shock-induced separated flow transition were on blade suction surface near the trailing edge. With film cooling, the airflow of blade surface boundary layer on the jet exit directly transit to turbulence, and the vortex stretching by influence of reverse transition were shown.

关 键 词：高压涡轮导叶 大涡模拟 分离转捩 逆转捩 拟序结构 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]