Abstract
Blade tip leakage is responsible for reducing the aerodynamic performance and increasing the thermal load. In order to obtain better cooling efficiency, the thermodynamic performance of different film hole arrangements and blowing ratios have been compared and analyzed in a cavity tip structure. Reynolds-averaged Navier–Stokes equation simulations at five blowing ratios from 0.25 to 2.0 have been carried out for three stream-wise and four pitch-wise film hole arrangements. Based on the reference flow field of the cavity without any coolant, the mechanism of the cooling air influence is analyzed by investigating the flow structure and the vortex development in the tip region. It is found that in the stream-wise arrangements and pitch-wise arrangements, the scheme SW1, in which the film holes are arranged along the suction surface, and the scheme PW2, in which the air film holes are arranged at 0.2 times the axial position, provide the maximum average film cooling efficiency of 0.235 and 0.282, respectively. However, the effective cooling area of SW1 is greater than that of PW2, which are 39.2% and 41.3%, respectively. At the lower blowing ratios, the cooling efficiency increases with the increase in the blowing ratio; however, at the higher blowing ratios, the cooling effect is affected by the clearance size and cavity depth when the coolant impinges on the casing wall.
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