US 11,746,658 B2
Turbine shroud with containment features
Ted J. Freeman, Danville, IN (US); and Aaron D. Sippel, Zionsville, IN (US)
Assigned to Rolls-Royce Corporation, Indianapolis, IN (US)
Filed by Rolls-Royce Corporation, Indianapolis, IN (US)
Filed on Oct. 20, 2020, as Appl. No. 17/75,257.
Prior Publication US 2022/0120185 A1, Apr. 21, 2022
Int. Cl. F01D 5/14 (2006.01); F01D 25/24 (2006.01); F01D 11/08 (2006.01)
CPC F01D 5/143 (2013.01) [F01D 11/08 (2013.01); F01D 25/246 (2013.01); F05D 2230/64 (2013.01); F05D 2240/11 (2013.01); F05D 2260/36 (2013.01); F05D 2300/6033 (2013.01); Y10T 29/49323 (2015.01)] 20 Claims
OG exemplary drawing
 
11. A turbine shroud adapted for use in a gas turbine engine, the turbine shroud comprising
a first turbine shroud segment including a first carrier comprising a fore wall, and an aft wall, and arranged to extend circumferentially at least partway about a center axis, a first blade track segment, and a first intermediate carrier configured to couple the first blade track segment to the first carrier, at least one of the fore wall and aft wall extend radially inward past the first intermediate carrier, wherein the first blade track segment formed to include a first runner shaped to extend circumferentially partway around the center axis and a first attachment portion that extends radially outward from the first runner, the first runner directly facing a gas path of the gas turbine engine, and
a second turbine shroud segment arranged circumferentially adjacent to the first turbine shroud segment, the second turbine shroud segment including a second carrier arranged to extend circumferentially at least partway about the center axis, a second blade track segment, and a second intermediate carrier configured to couple the second blade track segment to the second carrier, wherein the second blade track segment formed to include a second runner shaped to extend circumferentially partway around the center axis and a second attachment portion that extends radially outward from the second runner, the second runner directly facing a gas path of the gas turbine engine,
wherein the first intermediate carrier is shaped to include a first intermediate carrier body coupled with the first attachment portion of the first blade track segment, a plurality of first retainers that extend radially outward from the first intermediate carrier body and into corresponding radially inward opening holes defined in the first carrier to couple the first carrier with the first intermediate carrier body, and a flange that extends circumferentially from a circumferential end of the first intermediate carrier body and engages an adjacent circumferential end of a second intermediate carrier body included in the second intermediate carrier to form an overlap therebetween.