Int. J. Turbomach. Propuls. Power, Volume 3, Issue 4 (December 2018) – 2 articles
Cover Story (view full-size image): Leading edge impingement systems are increasingly being used for high-pressure turbine blades in gas turbine engines. The flow structure in such systems can be very complex, and high-resolution experimental data is required for engine-realistic systems to enable code validation and optimal design. This paper presents spatially resolved experimental heat transfer distributions for an engine-realistic impingement system for multiple configurations, with jet Reynolds numbers in the range of 13000–22000, to which RANS CFD simulations are then compared. Experimental results show variation in heat transfer distributions for different geometries; however, average levels are primarily dependent on the jet Reynolds number. CFD simulations match the shape of the distributions well, but with a consistent over-prediction of around 10% at heat transfer levels. View the paper.
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