US 12,258,880 B1
Turbine shroud assemblies with inter-segment strip seal
Aaron D. Sippel, Indianapolis, IN (US); Ted J. Freeman, Indianapolis, IN (US); David J. Thomas, Indianapolis, IN (US); and Clark J. Snyder, Indianapolis, IN (US)
Assigned to Rolls-Royce Corporation, Indianapolis, IN (US)
Filed by Rolls-Royce Corporation, Indianapolis, IN (US)
Filed on May 30, 2024, as Appl. No. 18/678,880.
Int. Cl. F01D 11/08 (2006.01); F01D 11/00 (2006.01); F01D 25/24 (2006.01)
CPC F01D 25/246 (2013.01) [F01D 11/003 (2013.01); F05D 2230/60 (2013.01); F05D 2240/11 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A turbine shroud assembly for use with a gas turbine engine, the turbine shroud assembly comprising:
a first shroud segment including a first carrier segment arranged circumferentially at least partway around a central axis and a first blade track segment supported by the first carrier segment to define a first portion of a gas path of the turbine shroud assembly, the first blade track segment having a first shroud wall that extends circumferentially partway around the central axis, a first attachment flange that extends radially outward from the first shroud wall, and a second attachment flange that extends radially outward from the first shroud wall axially spaced apart from the first attachment flange, wherein the first shroud wall has a first radial outer surface and a first radial inner surface, the first radial outer surface includes a first portion and a second portion that extends circumferentially away from the first portion and is spaced radially outward from the first portion, and the first shroud wall is formed to include a first recess that extends circumferentially into the first shroud wall,
a second shroud segment arranged circumferentially adjacent the first shroud segment about the central axis, the second shroud segment including a second carrier segment arranged circumferentially at least partway around the central axis and a second blade track segment supported by the second carrier segment to define a second portion of the gas path of the turbine shroud assembly, the second blade track segment having a second shroud wall that extends circumferentially partway around the central axis, a first attachment flange that extends radially outward from the second shroud wall, and a second attachment flange that extends radially outward from the second shroud wall axially spaced apart from the first attachment flange of the second blade track segment, wherein the second shroud wall has a second radial outer surface and a second radial inner surface, the second radial outer surface includes a first portion and a second portion that extends circumferentially away from the first portion of the second radial outer surface and is spaced radially outward from the first portion of the second radial outer surface, and the second shroud wall is formed to include a second recess that extends circumferentially into the second shroud wall, and
a plurality of seals extending circumferentially into the first shroud segment and the second shroud segment to block gases from escaping the gas path radially between the first shroud segment and the second shroud segment, the plurality of seals including a first strip seal and a second strip seal, the first strip seal extends axially along the first portion of the first radial outer surface of the first shroud wall and the first portion of the second radial outer surface of the second shroud wall to block the gases from passing radially between and beyond the first shroud wall and the second shroud wall, and the second strip seal is located radially inward of the first strip seal and extends circumferentially into the first recess formed in the first shroud wall of the first blade track segment and the second recess formed in the second shroud wall of the second blade track segment to provide a heat shield for the first strip seal to protect the first strip seal from heat of the gases in the gas path,
wherein the second strip seal includes an axial segment that extends axially between a first end and a second end thereof opposite the first end and an aft radial segment coupled with the second end of the axial segment and extending axially aft and radially outward from the second end of the axial segment toward the first strip seal,
wherein the first recess is defined by a first radially-outer wall, a first radially-inner wall spaced radially inward from the first radially-outer wall, and a first side wall extending between and interconnecting the first radially-outer wall and the first radially-inner wall, the first radially-outer wall located radially between the first strip seal and the second strip seal.