Patent ID: 7837441
Filing Date: 2010-11-23
Classification: B22C,F01D,F05D

Abstract:
1. A gas turbine engine component comprising: a platform and an airfoil extending outwardly of the platform, the airfoil having a suction wall and a pressure wall; a plurality of central channels received within said airfoil and extending from said platform outwardly toward a tip of said airfoil; said central channels each being provided with plural crossover holes for directing cooling air to at least one core channel associated with each of the pressure and suction walls, and a supply to supply air to the central channels, through said crossover holes, and against a wall of said core channels; skin cooling holes formed in said pressure and suction walls, such that the air can pass through the skin cooling holes from said core channels; and said core channels being supplied entirely from said central channel, with said core channels extending from a closed bottom wall to a top wall, with said cross-over holes supplying the impingement air into said core channels.