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Abstract
The thermal effect of cool jets issuing into an incompressible hot crossflow at an angle over a turbine blade is the subject. Numerical solutions for 12 multiple flow arrangements with two flow ratios, two different hole spacings, and four different jet issuing angles document strong to moderate secondary vortex structures spanning normal to the direction of the jet. This fully three-dimensional flowfield strongly influences the cooling performance of the hole-blade system. For a generalized body-fitted three-dimensional finite volume model, computational results suggest an optimum hole spacing and low issuing angle for maximum cooling efficiency.