Patent ID: 8784052
Filing Date: 2014-07-22
Classification: F01D,F05D

Abstract:
1. A gas turbine engine shroud comprising: a first annular ceramic wall including an inner side for resisting high temperature turbine engine gases and an outer side with a plurality of radial slots; and a second annular metallic wall positioned radially outward of and enclosing the first annular ceramic wall and including a plurality of radial tabs in communication with the slot of the first annular ceramic wall such that the first annular ceramic wall and second annular metallic wall are affixed, wherein at least one of the tabs includes an opening through the at least one of the tabs to increase ductility of the at least one of the tabs, wherein the first annular ceramic wall encloses rotatable turbine blades and the first annular ceramic wall surrounds stator vanes, wherein the opening extends into the second annular metallic wall.