考虑结构重量的部分冠涡轮泄漏流动控制研究  

Leakage Flow Control of Partial Shrouded Turbines Considering Structure Weight

作　　者：黄东铭 张伟昊[1] 王宇凡 蒋首民 陈云 王鹏 HUANG Dongming;ZHANG Weihao;WANG Yufan;JIANG Shoumin;CHEN Yun;WANG Peng(National Key Laboratory of Science and Technology on Aero-Engine Aero-thermodynamics,School of Energy&Power Engineering,Beihang University,Beijing 100191,China;AECC Shenyang Engine Research Institute,Shenyang 110015,China)

机构地区：[1]北京航空航天大学能源与动力工程学院航空发动机气动热力国家级重点实验室,北京100191 [2]中国航发沈阳发动机研究所,沈阳110015

出　　处：《工程热物理学报》2023年第10期2696-2704,共9页Journal of Engineering Thermophysics

基　　金：国家科技重大专项(J2019-II-0019-040)。

摘　　要：本文对某型部分冠低压涡轮叶冠泄漏流动的流动特征和损失进行了分析,探讨了部分冠容腔内的损失机理,对部分冠叶冠结构进行了气动优化和结构减重两个阶段的优化设计,分析了气动优化设计前后流动和损失的变化。结果表明叶冠容腔出口腔内存在严重的主流入侵现象与周向泄漏;由此引发的掺混损失使得出口腔内的损失最为显著,占叶冠容腔总损失的80%;优化后的叶冠缘板结构能够有效消除周向泄漏,抑制主流入侵从而提升涡轮级性能0.54%;合理设计叶冠结构可以实现相比原型部分冠减重6.1%的同时提升0.48%涡轮级效率。In this paper,the fow characteristics and losses of the leakage flow in a partial shrouded low-pressure turbine are analyzed.The loss mechanism in the shroud cavity is discussed.The shroud geometry has experienced two stages of aerodynamic optimization and weight optimization.The changes of flow characteristics and loss before and after the aerodynamic optimization are analyzed.The result shows that there is serious mainstream ingress and circumferential leakage in the exit cavity;The resultant mixing loss makes the loss in the exit cavity the most significant,accounting for 80%of the total loss inside the shroud cavity;The optimized shroud geometry can effectively eliminate the circumferential leakage,suppress mainstream ingress,improving turbine stage performance by 0.54%;Reasonable design of the shroud geometry can sustain the turbine stage efficiency improvement by 0.48%and obtain a weight reduction by 6.1%compared to the datum shroud geometry.

关 键 词：部分冠 涡轮 叶冠结构 泄漏流 泄漏损失 

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]