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Numerical study was performed to investigate the fluid flow and heat transfer characteristics of the combined cooling of impinging and film in the leading edge of a typical turbine blades at rotating state. The configuration is consisted of entering gas, leading edge and trailing edge blocks. The outflow configuration of hole is simplified into slot. Computation was carried for the different rotating number and heat flux. The results of analysis may lead to the following conclusions: (1)The distribution of flow field and heat transfer are affected by centrifugal force, coroilis force and buoyancy; (2)With the increasing of rotating numbers, average Nusselt numbers of the impingement surfaces of leading edge and trailing edge decrease; (3)With the increasing of heat flux, the change of heat transfer of the impingement surfaces of trailing edge and leading edge is smooth with rotating numbers increasing; (4)The heat transfer of the impingement surface of trailing edge is higher than leading edge.