Patent ID: 7097424
Filing Date: 2006-08-29
Classification: F01D,F05D

Abstract:
1. A gas turbine engine component comprising: an airfoil portion having a pressure side and a suction side; a platform adjacent a root portion of said airfoil portion, said platform having a leading edge, a suction side edge, a pressure side edge, and a trailing edge; means within said platform for cooling at least one of a platform edge adjacent said pressure side of said airfoil and said trailing edge, said cooling means having a first outlet for blowing cooling air onto the platform in a region adjacent the suction side edge; wherein said platform cooling means includes a first micro-circuit within said platform adjacent said suction side; and wherein said first micro-circuit has an L-shape with a first leg extending along said suction side and a second leg extending in a direction parallel to said trailing edge.