Abstract

In this paper, numerical simulation is performed to predict combined impingement and film cooling on a model of the turbine blade leading edge by the heat flow coupling method. The first-stage rotor blade leading edge of the GE-E³ engine high-pressure turbine is adopted for the simulation. The relative performances of turbulence models are compared with experimental data and the results show that standard k-ω model is the best, based on simulation accuracy. The standard k-ω model is adopted for the simulation. A grid independence study is also carried out. Five different mass flow ratios and seven different film cooling hole configurations are studied in detail. The results indicate that (1) the overall film cooling effectiveness on the leading edge surface and the Nusselt number on the target surface increase with increases of coolant mass flow ratio; (2) the blade leading edge temperature decreases with an increase in mass flow ratio; and (3) the area-averaged overall film cooling effectiveness increases with a decrease in spanwise film cooling injection angle, when the injection angle is lower than 25°, while it does not change much otherwise.

摘要

在本文中，通过热流耦合方法对涡轮叶片前缘模型进行了数值模拟，以预测组合冲击和气膜冷却。仿真采用GE-E ³发动机高压涡轮的一级旋翼前缘。将湍流模型的相关性能与实验数据进行了比较，结果表明，基于模拟精度，标准k-ω模型是最好的。标准k-ω采用模型进行仿真。还进行了网格独立性研究。详细研究了五种不同的质量流量比和七种不同的薄膜冷却孔配置。结果表明：（1）前缘表面的整体气膜冷却效率和靶表面的努塞尔数随着冷却剂质量流量比的增加而增加；(2)叶片前缘温度随着质量流量比的增加而降低；(3)当喷射角小于25°时，面积平均整体气膜冷却效率随着展向气膜冷却喷射角的减小而增加，否则变化不大。