涡轮叶片间隙泄漏流干涉下气膜冷却的流动试验及数值模拟  

Experiment and Numerical Simulation of Turbine Blade Film Cooling under Interference of Tip Gap Leakage Flow

作　　者：杨小平 钱浩 潘进 YANG Xiaoping;QIAN Hao;PAN Jin(AVIC Sichuan Gas Turbine Research Institute,Mianyang 621024,China;College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]中国航发四川燃气涡轮研究院,四川绵阳621024 [2]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《机械制造与自动化》2024年第5期135-139,共5页Machine Building & Automation

基　　金：中国航发四川燃气涡轮研究院委外课题。

摘　　要：气膜冷却是涡轮叶片的一种重要冷却手段。为了研究涡轮叶片的间隙泄漏对气膜冷却的影响机制与规律,采用GE-E3高压涡轮叶片开展PIV光学试验测量和非定常数值计算研究。分析不同气膜孔位置、雷诺数、吹风比等主要参数对气膜冷却流动的影响规律,发现间隙泄漏流干涉下不同位置气膜孔射流的流场效果差别较大;主流雷诺数在一定范围内对气膜孔射流的影响较小;吹风比的变化显著改变了气膜孔射流的横向发展和叶顶气膜孔射流的强度,使吸力侧泄漏涡存在远离叶片表面的趋势,同时一定程度上抑制了压力侧的泄漏流发展。Film cooling is an important cooling method for turbine blade.In order to study the influence mechanism and law of tip gap leakage flow of turbine blades on film cooling,the GE-E3 high-pressure turbine blade was applied to carry out PIV experimental tests and unsteady numerical calculation investigation.The influence of different film cooling hole position,inlet Reynolds number,blowing ratio and other main parameters on the film cooling flow was analysed.It is found that the flow field effects of the film cooling hole jet at different positions under the interference of the tip gap leakage flow varify greatly;the mainstream Reynolds number has a minor impact on the film cooling jet within a certain range;the variation of blowing ratio significantly changes the lateral development of the film cooling jet and the strength of the film cooling jet at the top of the blade,keeping the leakage vortex on the suction side far away from the blade surface and inhibiting the leakage flow development on the pressure side to a certain extent at the same time.

关 键 词：气膜冷却 涡轮叶片冷却 间隙泄漏流 数值模拟 

分 类 号：TP391.9[自动化与计算机技术—计算机应用技术]