Abstract
The unshrouded blade tip in a gas turbine needs to be cooled down due to the severe heat load. In this paper, multi-cavity tip structures were applied in the tip region to help enhance the cooling performance. Distributions of film cooling effectiveness (η) on multi-cavity tips were measured by pressure sensitive paint (PSP) approach under five different coolant blowing ratios. A turbulence-validated computational prediction was performed to help indicate the flow field of multi-cavity tips gap. Then, impact of tip gap on the multi-cavity tips film cooling performance was studied. Results show that multi-cavity tips mainly enhance the cooling performance at tip mid-portion compared with the classic one-cavity tip, but weaken it near the trailing edge (TE). Increasing the tip gap reduces cooling effectiveness values for most portion of the tip, but increases it near the TE. Lower aerodynamic losses were obtained in multi-cavity tips, especially for the leakage loss region.
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