<p>Film cooling performance of the cylindrical film holes and the bifurcated film holes on the leading edge model of the turbine blade are investigated in this paper. The suitability of different turbulence models to predict local and average film cooling effectiveness is validated by comparing with available experimental results. Three rows of holes are arranged in a semi-cylindrical model to simulate the leading edge of the turbine blade. Four different film cooling structures (including a cylindrical film holes and other three different bifurcated film holes) and four different blowing ratios are studied in detail. The results show that the film jets lift off gradually in the leading edge area as the blowing ratio increases. And the trajectory of the film jets gradually deviate from the mainstream direction to the spanwise direction. The Case 0 and Case 1 have better film cooling effectiveness at low blowing ratio while the Case 2 and Case 3 have better film cooling effectiveness at high blowing ratio. And the film cooling effectiveness of Case 2 and Case 3 increase with the increasing the blowing ratio. Additionally, the advantage of transverse bifurcated holes in film cooling effectiveness is more obvious in the downstream region relative to the cylindrical holes. The Area-Average film cooling effectiveness of Case 2 is 38% higher than that of Case 0 when blowing ratio is 2.</p>

Numerical Analysis on the Leading Edge Film Cooling of Bifurcation Holes for Gas Turbine Blade

Paper Proceedings: https://asmedigitalcollection.asme.org/HT/HT2021/volume/84874

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