高压级涡轮非轴对称端壁造型数值研究  

Numerical Investigation with Non-axisymmetric Endwall Profiling in High Pressure Turbine

作　　者：彭绍辉[1] 任丽芸[1] 李维[2] 

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重点实验室,北京100083 [2]中国航空动力机械研究所,湖南株洲412002

出　　处：《燃气涡轮试验与研究》2008年第1期38-42,共5页Gas Turbine Experiment and Research

基　　金：国家自然科学基金(50776003);国防重点实验室基金(9140C4103010603)

摘　　要：非轴对称端壁造型在叶轮机械的设计中得到了越来越多的重视。本文以某高压涡轮为研究对象,通过对端壁面上凸、端壁面下凹和轴对称端壁流场的数值模拟,分析了非轴对称端壁造型对涡轮性能的影响,探讨了非轴对称端壁造型降低流场二次流流动损失的机理。结果表明:采用非轴对称上凸端壁可提高涡轮气动效率0.57%,而采用非轴对称下凹端壁则导致效率下降0.56%,合理使用非轴对称端壁造型技术可有效降低二次流流动损失并提高涡轮气动性能。Numerical simulation has been carried out in conventional turbine cascade and two kinds of turbine cascade with non-axisymmetric endwall. Comparison and analysis of the results between the axisymmetric endwall and non-axisymmetric endwall has been completed to find out how non-axisymmetric endwall profiling affects the secondary flow in turbine. The result shows： The efficiency increases 0.57% than the conventional turbine cascade when the lower endwall of turbine cascade protrudes upward and it decreases 0.56% than the conventional turbine cascade when the lower endwall of turbine cascade protrudes downward. It is a useful tool to reduce the secondary flow and increases the efficiency with non-axisymmetric endwall profiling.

关 键 词：二次流 非轴对称端壁造型 涡轮 

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]