Patent ID: 9163519
Filing Date: 2015-10-20
Classification: F01D

Abstract:
1. A gas turbine engine blade shroud assembly comprising: a ceramic airfoil tip shroud including a circumferentially extending outer platform, at least one seal tooth supported by and extending radially outwardly away from and circumferentially parallel to the outer platform, a shroud cap supported on the outer platform, the shroud cap being less brittle than the outer platform, the shroud cap including a horizontally or circumferentially extending shroud cap base having horizontally or circumferentially spaced apart clockwise and counter-clockwise distal ends, the at least one seal tooth mounted on and extending radially outwardly away from the shroud cap base, clockwise and counter-clockwise facing clockwise and counter-clockwise contact surfaces located at the clockwise and counter-clockwise distal ends respectively, the clockwise contact surface being aft facing and the counter-clockwise contact surface being forward facing or the clockwise contact surface being forward facing, and the counter-clockwise contact surface being aft facing, and the clockwise and counter-clockwise facing clockwise and counter-clockwise contact surfaces located on horizontally or circumferentially spaced apart clockwise and counter-clockwise side legs at the clockwise and counter-clockwise distal ends respectively of the shroud cap base.