US 12,215,593 B1
Turbine shroud assembly with inter-segment damping
David J. Thomas, Indianapolis, IN (US); Aaron D. Sippel, Indianapolis, IN (US); Ted J. Freeman, 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. 18/678,892.
Int. Cl. F01D 25/28 (2006.01); F01D 5/22 (2006.01); F01D 11/00 (2006.01)
CPC F01D 25/28 (2013.01) [F01D 5/225 (2013.01); F01D 11/005 (2013.01); F05D 2240/11 (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,
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, and
a seal assembly configured to block gases from escaping the gas path radially between the first shroud segment and the second shroud segment, the seal assembly including a strip seal and a damping coil, the strip seal having an axial segment that 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 damping coil arranged axially along the axial segment of the strip seal to apply a radial inward force to the axial segment of the strip seal so that the strip seal is urged radially inwardly to maintain engagement of the strip seal with the first shroud wall and the second shroud wall while allowing for radial misalignment of the first blade track segment relative to the second blade track segment during use of the turbine shroud assembly.