Film Cooling Performance on Suction Side of Turbine Blade With Two Rows of Subregional Compound Angle Holes
Under the function of passage secondary flow,the film track on the suction side de-flects from both ends to the middle of the blade.In order to solve this problem,a film cooling model with two row subregional compound angle holes for high pressure turbine blade suction sur-face is designed in this paper.The effects of secondary flow and compound angle on film cool-ing performance were analyzed by numerical simulation.The results show that in the root re-gion,the upstream films of SS1 are less deflected by the horseshoe vortex,but the downstream films of SS2 is much more deflected by the stronger passage vortex than the upstream films.The uniformity of film.coverage can be improved by adding subregional compound angle towards the endwall on the suction side.When the compound angle increases to about 30°,the detachment phenomenon of jet can be eliminated.Comparing with the simple Angle condition,the aver-aged spanwise film cooling effectiveness in the maximum compound angle condition is increased by 13.9％.
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