涡轮转子凹槽叶尖泄漏流动气动热力特征  

Aero-Thermodynamic Characteristics of Tip Leakage Flow in Turbine Rotor with Squealer Tip

作　　者：邹正平[1,2] 姚李超[1] 轩笠铭 邵飞[1,3] 黄霖 贺晓娟 ZOU Zheng-ping;YAO Li-chao;XUAN Li-ming;SHAO Fei;HUANG Lin;HE Xiao-juan(National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics,School of Energy&Power Engineering,Beihang University,Beijing 100191,China;Research Institute of Aero-Engine,Beihang University,Beiji ng 102206,China;AECC Aero Engine Academy of China,Beijing 101304,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防重点实验室,北京100191 [2]北京航空航天大学航空发动机研究院,北京102206 [3]中国航空发动机研究院,北京101304

出　　处：《推进技术》2020年第9期1975-1987,共13页Journal of Propulsion Technology

基　　金：国家自然科学基金(51676005)。

摘　　要：为探索总结凹槽叶尖泄漏流动气动热力特征,利用实验和数值模拟方法,对叶尖凹槽内部旋涡相互作用机理和叶顶流动换热与泄漏流能量再分布等问题进行研究,并对凹槽叶尖参数化设计方法进行探讨。结果表明:搭建的考虑多因素实验台和可视化泄漏流动测量方案可以精确地捕捉到叶顶区域的流动结构;刮削涡在凹槽中起到"气动篦齿"作用,其形态特征的变化直接影响凹槽叶尖对泄漏流动的控制效果;高温泄漏流流体对叶片表面的冲击是叶尖热负荷提高的主要原因;合理选择叶尖气动参数和凹槽的几何参数可以有效控制刮削涡形态,最终提升叶尖气动热力性能。In order to explore and summarize the aero-thermodynamic characteristics of the tip leakage flow of squealer tip,experimental and numerical simulation methods are used to investigate the interaction mechanism of vortices in the squealer tip cavity,the tip region heat transfer and the energy redistribution of the leakage flow.The parametric design method of the squealer tip is also discussed.The results show that the multi-functional experimental platform and the visual leakage flow measurement scheme can precisely capture the flow structure in the tip region.An aero-labyrinth liked sealing effect is formed by the scraping vortex.Its shape characteristics directly affect the leakage flow controlling of squealer tip.The heat load increased in the squealer tip is mainly caused by the leakage flow impingement on the blade surface.By reasonable working condition and squealer tip geometry for organizing scraping vortex characteristics,the squealer tip can improve the turbine aero-thermodynamic performance effectively.

关 键 词：涡轮 凹槽叶尖 泄漏流动 旋涡结构 流动换热 精细化组织 

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]