Abstract
AbstractThe operating gas temperatures of advanced military aero engines are continuously increasing to achieve a higher specific thrust. The gas temperature exposed by hot end components is beyond material allowable temperature limits. It is essential to cool these components to lower the metal temperatures to meet the designed life. Effusion cooling technique effectively brings down the hot components’ metal temperature. The present study is focused on the numerical prediction of cooling effectiveness from effusion cooling holes. Conjugate heat transfer analysis is carried out using ANSYS Fluent ver.14.5 to estimate the film cooling effectiveness. The analysis is validated with experimental film cooling effectiveness data. K–ω SST turbulence model has given good agreement. To improve the film cooling effectiveness, further studies have been carried out by varying the geometrical parameters such as film hole inclination, porosity and thermal conductivity of the effusion plate. Three cases with different cooling configurations have been investigated.KeywordsConjugate heat transfer (CHT)PorosityEffectivenessEffusion plate
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