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
Key words
film cooling/cooling for turbine blade/tip leakage flow/numerical simulation
维普
万方数据