Numerical Investigation of the Blade Cooling Effect Generated by Multiple Jets Issuing at an Angle into an Incompressible Horizontal Cross Flow
نویسنده
چکیده
The thermal effect of cool jets issuing into an incompressible hot cross flow at an angle over a turbine blade is the subject. Numerical solutions for twelve multiple flow arrangements with two flow ratios, two different hole spacing 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 flow field strongly influences the cooling performance of the hole-blade system. For a generalized body-fitted threedimensional finite volume model, computational results suggest an optimum hole spacing and low issuing angle for maximum cooling efficiency.
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