Atul Kohli

TL;DR: In this paper, the authors investigated the performance and velocity field for discrete round holes inclined at an injection angle of 55 deg and compared it to typical round film cooling holes, with an injection rate of 35 deg. All experiments were performed at a density ratio of DR = 1.6, using cryogenic cooling of the injected air.

TL;DR: In this article, the effects of pin spacing on heat transfer and pressure loss through pin fin arrays for a range of Reynolds numbers between 5000 and 30,000 were evaluated and it was shown that spanwise pin spacing had a larger effect than streamwise spacing on array pressure loss while streamwise and spanwise spacing had an even larger effect on array heat transfer.

TL;DR: In this paper, the authors focused on internal cooling of turbine airfoils using a single row of circular pin fins that is oriented perpendicular to the flow and showed that the heat transfer augmentation relative to open channel flow is the highest for smallest spanwise spacings and lowest Reynolds numbers.

TL;DR: In this paper, the heat transfer of a low-pressure turbine blade geometry with both flat and three-dimensional contoured endwalls was investigated. And the authors found that heat transfer levels were reduced by 20 percent in regions of high heat transfer with the contoured contour endwall, as compared to the flat endwall.

TL;DR: In this paper, a simulated film cooled turbine blade leading edge was used to determine the normalized "metal temperature" representative of actual engine conditions, ensuring that the normalized wall temperature, i.e. the overall effectiveness, was matched to that for the engine.