US 12,188,365 B1
Method and apparatus for ceramic matrix composite turbine shroud assembly
David J. Thomas, Indianapolis, IN (US); Christopher Downie, Cypress, CA (US); Aaron D. Sippel, Indianapolis, IN (US); Ted J. Freeman, Indianapolis, IN (US); and Clark Snyder, Indianapolis, IN (US)
Assigned to Rolls-Royce Corporation, Indianapolis, IN (US); and Rolls-Royce High Temperature Composites Inc., Cypress, CA (US)
Filed by Rolls-Royce Corporation, Indianapolis, IN (US); and Rolls-Royce High Temperature Composites Inc., Cypress, CA (US)
Filed on Dec. 4, 2023, as Appl. No. 18/528,739.
Int. Cl. F01D 11/12 (2006.01); F01D 25/00 (2006.01); F01D 25/24 (2006.01); F01D 5/28 (2006.01)
CPC F01D 25/246 (2013.01) [F01D 11/122 (2013.01); F01D 25/005 (2013.01); F01D 5/288 (2013.01); F05D 2240/15 (2013.01); F05D 2300/6033 (2013.01); F05D 2300/611 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A turbine shroud assembly adapted for use with a gas turbine engine, the turbine shroud assembly comprising a shroud segment made of ceramic matrix composite materials, the shroud segment comprising:
a heat shield that extends circumferentially partway around an axis of the gas turbine engine, the heat shield having primary body surfaces comprising an inner surface, a first outer surface spaced apart radially from the inner surface, a first end surface that extends between and interconnects the inner surface and the first outer surface,
an attachment feature that extends radially outward from the heat shield, the attachment feature having a first attachment surface that extends radially outward from the first outer surface of the heat shield, and
a multi-layer coating applied to the shroud segment, the multi-layer coating comprising:
a surface layer comprising a monolithic silicon carbon material that extends over the inner surface, the first outer surface, and along a portion of the first attachment surface of the attachment feature,
a bond layer comprising a silicon metallic material that extends over the surface layer on the associated surfaces and the first end surface of the primary body surfaces on the heat shield,
a barrier layer comprising a first environmental barrier coating material that extends over the bond layer, and
an abradable layer comprising a second environmental barrier coating material that has a different porosity than the first environmental barrier coating material that extends over the barrier layer on the inner surface, the first outer surface, and along a portion of the first attachment surface of the attachment feature.