Abstract
In modern gas turbines, sufficient cooling is required for preventing the blade tip region from being ablated due to the increasing of operating temperature. In this work, an experiment was conducted focusing on the film cooling performance of the multi-cavity tips (one cavity, two cavities, three cavities and four cavities) with two different cavity depths. The distributions of film cooling effectiveness on these multi-cavity tips were measured by the pressure sensitive paint (PSP) technique under five coolant blowing ratios. In addition, a validated computational method was performed to make further insight into the coolant flow pattern near the tip and the aerodynamic loss. Results showed that performance of superiority in film cooling is achieved on the central portion of the multi-cavity tips, compared to the conventional cavity tip. The uniformity of effectiveness values in film cooling is improved by a deeper cavity depth. The effectiveness values of the tip surface increase first and then decrease with an increase of blowing ratio. The aerodynamic performance of these multi-cavity tips was assessed as well.
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