涡轮导叶端壁安装间隙泄漏流气动特征数值模拟研究  

Numerical simulation of aerodynamic characteristics of turbine guide vane end-wall installation clearance leakage flow

作　　者：曾飞 甘明瑜 宋玉琴[3] 张伟昊[4] 王宇凡 薛君 ZENG Fei;GAN Mingyu;SONG Yuqin;ZHANG Weihao;WANG Yufan;XUE Jun(AECC Hunan Aviation Powerplant Research Institute,Zhuzhou 412002,China;College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;College of Science,Hunan University of Technology,Zhuzhou 412007,China;National Key Laboratory of Science and Technology on Aero-Engine Aerothermodynamics,School of Energy and Power Engineering,Beihang University,Beijing 100191,China)

机构地区：[1]中国航发湖南动力机械研究所,湖南株洲412002 [2]南京航空航天大学能源与动力学院,江苏南京210016 [3]湖南工业大学理学院,湖南株洲412007 [4]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科技重点实验室,北京100191

出　　处：《推进技术》2024年第10期56-65,共10页Journal of Propulsion Technology

基　　金：国家科技重大专项(J2019-Ⅱ-0009-0029)。

摘　　要：为研究导叶端壁安装间隙泄漏流的影响,本文围绕某双级涡轮开展了数值研究,分析了导叶端壁有无间隙、间隙大小等因素对涡轮流场和性能的影响。结果表明,端壁安装间隙的泄漏流仅在后半段形成,前半段受通道内较大压力的影响形成主流入侵现象,主流入侵范围占间隙出口面积的44%以上;随间隙宽度的增大,主流入侵现象呈增强趋势,这必然使得端壁侧面面临极大的热负荷;泄漏流流出后卷起泄漏涡,并引起端区气流欠转,导致下游动叶负荷降低,且影响了动叶通道端区旋涡演化,其带来的涡轮级效率差异为0.41%~1.12%,总功率差异为0.38%~0.82%。In order to study the influence of clearance leakage flow on guide vane end-wall installation,a numerical study was carried out on a two-stage turbine.The influences of the presence or absence of clearance and the size of clearance on turbine flow field and performance are analyzed.The results show that the leakage flow is only formed in the second half of the endwall clearance,and the front half is affected by the greater pres⁃sure in the channel to form a mainstream intrusion phenomenon.The main flow intrusion area accounts for more than 44%of the clearance outlet area.With the increase of the gap width,the mainstream intrusion phenomenon increases,which inevitably makes the side of the endwall face great heat load.The leakage flow generates the leakage vortex and causes the flow under rotation in the end zone,which leads to the lower rotor blade load reduc⁃tion and affects the vortex evolution in the end zone of the moving blade passage.The turbine stage efficiency dif⁃ference brought by the leakage flow is about 0.41%~1.12%,and the total power difference is 0.38%~0.82%.

关 键 词：燃气涡轮 端壁安装间隙 泄漏流动 端区旋涡结构 气动性能 

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]