高压涡轮工作叶片叶型设计研究  

Design of High Pressure Turbine Blade Profile

作　　者：C.B.雷兹尼克 V.I.亚什尼科夫 S.A.霍梅列夫 E.L.比卡 S.V.叶尔少夫 程燕[3] 陈云[3] 

机构地区：[1]伊夫琴科前进设计局,乌克兰扎波罗热 [2]机械工程研究院,乌克兰哈尔科夫 [3]中航工业沈阳发动机设计研究所,沈阳110015

出　　处：《航空发动机》2014年第4期25-29,共5页Aeroengine

摘　　要：针对高压涡轮工作叶片叶栅型面特征,采用可压燃气黏性流2维计算方法对高压涡轮工作叶片叶型进行了气动研究,并通过试验验证了优化设计,得到了叶栅气动设计参数。经与初始叶型对比,优化叶型在各状态下损失特性变化更为平缓,在超临界状态下效率更高,在λ2is=1.20状态下的损失减少了2.8%。该方法缩短了设计时间,并且节省了平面叶栅吹风试验的成本。Aiming at the blade cascade profile characteristics of the high pressure turbine, the dynamic analysis of the blade profile for the high pressure turbine was performed by the 2D calculation with a gas viscous flow. The dynamic design parameters of cascade were obtained by the optimization design of the experimental validation. Compared with the initial blade profiles, the loss characteristics change less on different operations, the efficiency is higher on the super critical condition, and the loss reduces 2.8% on λ 2is= 1.20 condition. This method has expedited the design progress and save the cost of air plane cascade test.

关 键 词：叶片叶型 叶栅 高压涡轮 计算方法 气动参数 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]