Patent ID: 9085988
Filing Date: 2015-07-21
Classification: F01D,F05D,Y02T

Abstract:
1. An apparatus comprising: a gas turbine engine having a fluid cooled airfoil member disposed in a flow path and having a plurality of walls extending along a span of the member and enclosing an open interior, the walls forming a cooling passage therebetween, an inner wall of the plurality of walls extending into the flow path beyond an end of an outer wall of the plurality of walls, a base extending from the inner wall, the base being located at the end of the outer wall of the fluid cooled airfoil member and serving as a base portion of a squealer and serving to enclose the open interior of the fluid cooled airfoil member; and a plurality of apertures in the airfoil member extending from the enclosed open interior and having an upstream inlet and a downstream exit and operable to pass a fluid therethrough oriented to cool the inner wall that extends beyond the end of the outer wall, wherein the downstream exits of the apertures are non-circular, and wherein the plurality of apertures extending from the enclosed open interior are bounded by the inner wall and the outer wall, and the plurality of apertures extend around an entire perimeter of the inner wall, the entire perimeter extending from a trailing edge around a pressure side to a leading edge, and from the leading edge around a suction side returning to the trailing edge.