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- W2339804961 abstract "Gas turbines operate under very high fluid temperatures which may damage turbine blades. In order to prevent failure of turbine blades resulting from these excessive operating temperatures, a comprehensive cooling technique known as film cooling can be incorporated during blade designing process. To maintain the balance between excessive heating and excessive cooling of the turbine blades an optimum cooling technique has been designed. Numerical analysis has been carried out to find the film cooling effectiveness (centreline and spatially averaged). Variation of film cooling effectiveness has been determined along the downstream of cooling holes. The computational model has been validated with benchmark experimental literature. The study compares film cooling effectiveness over various blowing ratios (M), various hole shapes and rearrangement of holes. FLUENT solver has been used for the computational analysis using the standard RANS shear stress transport turbulence model. Computational results reveal that the effectiveness increases with increase in blowing ratios. On the other hand, film cooling effectiveness decreases due to coolant jet lift off and due to intermixing of coolant and mainstream flow. The best results were obtained for fan-shaped holes with blowing ratio (M) = 0.60. Spatially averaged effectiveness for fan-shaped holes was found to be higher as compared to other hole shapes." @default.
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- W2339804961 date "2016-01-01" @default.
- W2339804961 modified "2023-10-14" @default.
- W2339804961 title "Numerical Investigation of Film Cooling Effectiveness in Turbine Blades" @default.
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