涡轮叶片气热耦合壁温及压力分布计算与分析  

Conjugate heat transfer simulation and analysis of wall temperature and pressure distribution on a turbine blade

作　　者：李卓轩 沙云东[1] 骆丽[1] LI Zhuoxuan;SHA Yundong;LUO Li(Key Laboratory of Advanced Measurement and Test Technique for Aviation Propulsion System,Shenyang Aerospace University,Shenyang 110136,China)

机构地区：[1]沈阳航空航天大学辽宁省航空推进系统先进测试技术重点实验室,沈阳110136

出　　处：《沈阳航空航天大学学报》2024年第1期1-8,共8页Journal of Shenyang Aerospace University

基　　金：两机专项子项(项目编号:JH2021001G)。

摘　　要：针对气冷涡轮叶片建立了耦合分析数值模拟计算平台,采用气热耦合的方法,对径向气冷MARKⅡ型叶片进行三维气热耦合数值模拟。分析了该内冷涡轮叶片的多场耦合特性,并将计算结果与试验值进行对比。对比结果表明:湍流模型的选择影响叶片表面的温度分布,但对叶片表面压力分布影响较小;在选择的6种湍流模型中,SSTk-ω湍流模型对该流场状态模拟的效果较好,叶片表面温度和压力与试验结果最接近,满足工程上的计算要求。考虑涡轮进口总温径向不均匀时,会在叶片尾缘形成局部高温区,增加了叶身的温度梯度,可适当改进冷却方式,以提高叶片强度。Established a coupling analysis numerical simulation platform for air-cooled turbine blades,and a three-dimensional conjugate heat transfer numerical simulation for radial air-cooled MARK II blades was carried out using the conjugate heat transfer method.The multi-field coupling characteris‐tics of the air-cooled turbine blades were analyzed,and the numerical results were compared with the experimental results.The results show that the choice of turbulence model affects the temperature distri‐bution but has little influence on the pressure distribution on the blade surface;Among the six turbu‐lence models selected,the SST k-ωturbulence model can simulate the flow field better,and the tem‐perature and pressure on blade surface are the closest to the test results,which meets the engineering calculation requirements.When the total temperature at the turbine inlet is non-uniform in the radial di‐rection,a local high-temperature zone is formed at the trailing edge of the blade,which increases the temperature gradient on the blade.Therefore,the cooling method can be improved to enhance the blade strength.

关 键 词：涡轮叶片 气热耦合 流场结构 数值仿真 湍流模型 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]