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- W2995612222 abstract "Gas turbine operates at high fluid temperatures and it may damage gas turbine rotor and stator blades. To prevent failure of those blades due to excessive operating temperatures, a specific cooling method known as film cooling can be used during designing of those blades. To have a balance between large heating and excessive cooling of the blades, an optimum cooling technique has been proposed. To obtain cooling effectiveness of the blades, computational analysis has been carried out for this purpose. Variation of cooling effectiveness due to formation of a coolant film over the blade surface, has been computed along the downstream of cooling holes. The numerical model has been well validated with existing experimental literature. The present study compares cooling effectiveness over a range of blowing ratios (M). ANSYS FLUENT solver has been utilized for the numerical analysis using the K-ε standard turbulence model with enhanced wall function. Computational results showed that the effectiveness improves up to a certain value with increase in blowing ratios. Further increase in blowing ratios, the effective cooling performance decreases due to coolant jet lift off and intermixing of coolant and mainstream fluid flow. The best cooling performance were obtained with blowing ratio (M) = 1.00." @default.
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- W2995612222 date "2019-01-01" @default.
- W2995612222 modified "2023-10-14" @default.
- W2995612222 title "Analysis of film cooling effectiveness using computational approach" @default.
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- W2995612222 doi "https://doi.org/10.1063/1.5141173" @default.
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