Patent ID: 8328507
Filing Date: 2012-12-11
Classification: F01D,F05D

Abstract:
1. A seal assembly for a gas turbine engine, comprising: a seal support member configured for rotation within the gas turbine engine around an axial centerline of the engine, wherein the support member has a thickness extending between a first surface and a second surface; at least one knife edge seal blade member extending outwardly from the first surface, wherein the blade member includes a central portion extending between a base end and a distal knife edge end, and wherein the base end is attached to the first surface of the seal support member; and at least one cooling fin extending outwardly from the second surface, and oppositely aligned with the blade member; wherein the at least one cooling fin comprises a cooling fin width that extends between a first cooling fin side and a second cooling fin side, and a cooling fin height that extends outwardly from the second surface to a cooling fin distal end; and wherein the cooling fin height is greater than the cooling fin width.