某型发动机高导气动优化设计  

Aerodynamic Optimization Design of High Pressure Turbine Passage for Engine

作　　者：李苑 向鑫 朱敬德 张周康 LI Yuan;XIANG Xin;ZHU Jingde;ZHANG Zhoukang(AECC Guiyang Engine Research Institute,Guiyang 550081,China;School of Aircraft Engineering,Nanchang Aeronautical University,Nanchang 330063,China)

机构地区：[1]中国航发贵阳发动机设计研究所,贵州贵阳550081 [2]南昌航空大学飞行器工程学院,江西南昌330063

出　　处：《机械制造与自动化》2022年第3期204-207,共4页Machine Building & Automation

基　　金：江西省微小航空发动机重点实验室开放基金项目(Ef202006420)。

摘　　要：在对涡轮通道进行优化和修正时,需要考虑热载荷和离心载荷的影响,才可获得较优的涡轮气动性能。从实际工程问题出发,采用数值模拟手段,在考虑上述因素影响的基础上,研究高导叶片的流道高度和尾缘气膜冷却劈缝局部修型对涡轮性能的影响规律。结果表明:最佳流道应在设计基础上扩张1.6%,可使涡轮效率提高0.25%,高涡功率提升0.6%;而尾缘气膜冷却劈缝的距离会影响压力面载荷分布,从而影响涡轮气动性能,存在最佳的劈缝距离使得涡轮气动效率最优。In order to obtain better turbine aerodynamic performance,the influence of thermal load and centrifugal load should be considered in the optimization and modification of turbine passage.In terms of the practical engineering problems,numerical simulation method is used to study the influence of the channel height of high pressure turbine vane and the local modification at the trailing edge slot on the turbine performance.The results show that the optimal flow channel should be expanded by 1.6%based on the design,which can increase the turbine efficiency by 0.25%and the turbine power by 0.6%.The splitting distance of the trailing edge film cooling slit will have influence over the load distribution on the pressure surface,thus affecting the aerodynamic performance of the turbine,in the presence of an optimal splitting distance to optimize the aerodynamic efficiency of the turbine.

关 键 词：高导叶片 数值模拟 气动优化 

分 类 号：TH122[机械工程—机械设计及理论]