Patent ID: 8246297

Claim:
A turbine static shroud of a gas turbine engine disposed around a rotational axis of the engine and comprising a turbine shroud platform extending from a leading edge to a trailing edge, the platform having a hot gas side and a back side, the hot gas side configured to encircle at least a portion of blade tips of a turbine blade set, the platform having first and second legs extending radially outwardly from the back side with respect to the rotational axis of the engine, a plurality of exit passages disposed radially outwardly and entirely spaced from the platform with respect to the rotational axis of the engine, the exit passages extending through at least one of said legs and terminating at respective opposed leg surfaces, each passage having a central axis intersecting the platform at an intersection point and the passage configured to direct an air stream through said leg to impinge on a surface of the back side, the intersection point of the central axis of each of the passages disposed on the surface, the surface extending out of a plane defined by the back side.