高压涡轮非对称叶冠表面热负荷特性研究  

Study on Heat Load Characteristics of Asymmetric Blade Shroud Surface of High Pressure Turbines

作　　者：周成 武思宇 王杰[1] 鄢强 高杰[1] ZHOU Cheng;WU Siyu;WANG Jie;YAN Qiang;GAO Jie(College of Power and Energy Engineering,Harbin Engineering University,Harbin 150001,Heilongjiang Province,China)

机构地区：[1]哈尔滨工程大学动力与能源工程学院,黑龙江省哈尔滨市150001

出　　处：《中国电机工程学报》2023年第19期7559-7568,共10页Proceedings of the CSEE

基　　金：国家科技重大专项(2017-III-0010-0036);国家自然科学基金项目(51979052);黑龙江省优秀青年科学基金项目(YQ2020E024)。

摘　　要：高压涡轮带冠叶片工作于高温、高压和高转速的恶劣环境中,导致叶冠容易发生掉块现象,这严重威胁到燃气涡轮发动机的安全运行。因此,有必要研究不同参数对涡轮叶冠表面热负荷变化的影响以及作用机制,该文着重分析不同叶冠结构、宽变工况对叶冠表面热负荷变化的影响,同时,根据叶冠表面壁面热流密度的分布和变化规律,对叶冠结构形状进行改进,最终达到降低叶冠表面热负荷的目的。研究结果表明:由于篦齿的密封作用,叶冠后缘容腔内的泄漏流流动比叶冠前缘稳定,导致叶冠后缘的壁面热流密度分布比前缘更加规律。宽变工况条件下,主要通过影响叶冠前缘的壁面热流密度分布进而改变叶冠表面的热负荷。最后发现对叶冠后缘切削10%的面积,可以降低叶冠表面热负荷高达19.2%,这为今后新型涡轮带冠叶片设计提供参考。High-pressure turbine shrouded blade works in the harsh environment of high temperature,high pressure and high speed,which is prone to block dropping.This seriously threatens the safe operation of gas turbine engine.Therefore,it is necessary to study the influence and action mechanism of different parameters on the change of heat load on the shroud surface.This paper focuses on the analysis of the different shroud structures and wide variable working conditions on the change of heat load on the shroud surface.At the same time,according to the distribution and variation of wall heat flux on the surface of shroud,the structure shape of shroud can be improved to reduce the heat load.Results show that,due to the sealing of labyrinth seals,the leakage flow in the shroud cavity at the trailing edge of shroud is more stable than that at the leading edge,resulting in a more regular wall heat flux at the trailing edge of shroud compared with that at the leading edge.Under wide variable working conditions,the changing of heat load on the shroud surface is mainly affected by the wall heat flux distribution on the trailing edge of the shroud.Finally,by cutting 10%of the area of the trailing edge of the shroud,the heat load on the shrouds surface can be reduced by 19.2%.This can provide reference for the design of new turbine shroud blades in the future.

关 键 词：高压涡轮 带冠叶片 叶冠表面热负荷 宽变工况 壁面热流密度 

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]