US 12,228,044 B1
Turbine shroud system with ceramic matrix composite segments and dual inter-segment seals
David J. Thomas, Indianapolis, IN (US); Ted J. Freeman, Indianapolis, IN (US); Aaron D. Sippel, Indianapolis, IN (US); Clark J. Snyder, Indianapolis, IN (US); and Steven Hillier, London (GB)
Assigned to Rolls-Royce Corporation, Indianapolis, IN (US); and Rolls-Royce plc
Filed by Rolls-Royce Corporation, Indianapolis, IN (US); and Rolls-Royce plc, London (GB)
Filed on Jun. 26, 2024, as Appl. No. 18/755,463.
Int. Cl. F01D 11/08 (2006.01); F01D 25/24 (2006.01)
CPC F01D 25/24 (2013.01) [F01D 11/08 (2013.01); F05D 2230/60 (2013.01); F05D 2240/55 (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 and a first attachment feature that extends radially outward from the first shroud wall, wherein the first shroud wall has a first radial outer surface and a first radial inner surface that defines the first portion of the gas path,
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 and a second attachment feature that extends radially outward from the second shroud wall, wherein the second shroud wall has a second radial outer surface and a second radial inner surface that defines the second portion of the gas path, 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,
wherein the first strip seal extends axially along the first radial outer surface of the first shroud wall and 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 extends circumferentially into the first shroud wall of the first blade track segment, the second shroud wall of the second blade track segment, the first carrier segment, and the second carrier segment.