Abstract
This paper deals with an experimental convective heat transfer investigation around a high pressure gas turbine film cooled rotor blade. The measurements were performed in the von Karman Institute short duration isentropic light piston compression tube facility allowing a correct simulation of Mach and Reynolds number as well as free stream to wall and free stream to coolant temperature ratios. The airfoil was mounted in a linear stationary cascade environment and heat transfer measurements were obtained by using platinum thin film gages painted on a blade made of machinable glass ceramic
The coolant flow was ejected simultaneously through the leading edge (3 rows of holes), the suction side (2 rows of holes),and the pressure side (1 row of holes). The coolant hydrodynamic behavior is described and the effects of overall coolant to free stream mass weight ratio,oolant to free stream temperature ratio, and free stream turbulence intensity on the convective heat transfer distribution are successively described.
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Arts, T. (1991). Convective Heat Transfer with Film Cooling Around a Rotor Blade. In: Angelino, G., De Luca, L., Sirignano, W.A. (eds) Modern Research Topics in Aerospace Propulsion. Springer, New York, NY. https://doi.org/10.1007/978-1-4612-0945-4_14
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DOI: https://doi.org/10.1007/978-1-4612-0945-4_14
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