US 12,410,725 B1
Turbine shroud assemblies with air activated pistons for biasing buffer cavity seals
Ted J. Freeman, Indianapolis, IN (US); Aaron D. Sippel, Indianapolis, IN (US); David J. Thomas, Indianapolis, IN (US); Clark J. Snyder, Indianapolis, IN (US); and Grant Cook, Indianapolis, IN (US)
Assigned to Rolls-Royce Corporation, Indianapolis, IN (US)
Filed by Rolls-Royce Corporation, Indianapolis, IN (US)
Filed on May 31, 2024, as Appl. No. 18/680,758.
Int. Cl. F01D 11/08 (2006.01)
CPC F01D 11/08 (2013.01) [F05D 2230/60 (2013.01); F05D 2240/11 (2013.01); F05D 2240/55 (2013.01); F05D 2260/30 (2013.01)] 17 Claims
OG exemplary drawing
 
1. A turbine shroud assembly for use with a gas turbine engine, the turbine shroud assembly comprising:
a carrier segment arranged circumferentially at least partway around an axis, the carrier segment including an outer wall, a first support wall that extends radially inward from the outer wall, and a second support wall that extends radially inward from the outer wall at a location spaced apart axially from the first support wall to define an attachment-receiving space, and the first support wall formed to include a radially-inwardly opening first channel that extends circumferentially relative to the axis and at least one buffer air passageway that extends radially into the forward support wall and opens into the first channel,
a blade track segment arranged circumferentially at least partway around the axis to define a portion of a gas path of the gas turbine engine, the blade track segment having a shroud wall that extends circumferentially partway around the axis and an attachment feature that extends radially outward from the shroud wall into the attachment-receiving space formed in the carrier segment, and
a buffer air seal assembly arranged in the first channel between the forward support wall of the carrier segment and the shroud wall of the blade track segment to block gases from flowing between the carrier segment and the blade track segment, the buffer air seal assembly including a seal that extends circumferentially relative to the axis and axially across the first channel,
wherein the at least one buffer air passageway is configured to discharge buffer air radially inward away from the carrier segment into the first channel to urge the seal radially inward into engagement with the shroud wall of the blade track segment,
wherein the buffer air seal assembly further includes a bias member compressed radially between the carrier segment and the seal to apply a bias force to the seal to bias the seal radially inward towards the shroud wall of the blade track segment, and
wherein the seal is formed to include an inner groove that extends radially inward into the seal and circumferentially relative to the axis and at least one through hole that extends radially through the seal and opens into the inner groove to allow the buffer air to flow through the seal into the inner groove.