Abstract
The complicated streamwise pressure gradient (SPG) environments in gas turbines affect the film cooling performance. In this research, shaped cooling hole with density ratio 1.5, blowing ratio 1.6, and acceleration coefficient, K=1e-6 is studied using Large Eddy Simulation (LES). LES results have been verified by experiment results. The differences between the Reynolds Average Navier – Stokes (RANS) results of zero pressure gradient (ZPG) and favorable pressure gradient (FPG) showed that the FPG keeps the jet closer to the wall surface, and the counter rotating vortex pair (CRVP) is compressed. The time-average and instantaneous flow field obtained from LES were analyzed to get the flow field details. Fast Fourier Transform (FFT) and Lumley triangle were used to analyze the vortices and the turbulence characteristics of the strong shear zone near the hole exit and downstream. The influences of FPG on horseshoe vortex, hairpin vortex and shear layer vortex were analyzed. The results showed that the hairpin vortex enhanced by FPG effect the film cooling performance of the downstream.
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