Gas turbine engine shroud sealing arrangement
AssigneePratt & Whitney Canada Corp.
InventorsEric Durocher, Martin Jutras
Life of this patent
Estimating the term…
Abstract
A ring seal is mounted in the annular gap between a shroud platform overhanging portion and the surrounding shroud support to minimize cooling air leakage through the shroud.
Claims9
A turbine blade tip shroud assembly comprising an annular shroud support having at least one radially inner annular flange defining a groove, a shroud supportively engaged in said groove, said shroud having a platform, the platform having a hot gas path side and a back side, an annular gap being defined radially inwardly of said groove between said back side of said platform and a radially inwardly facing side of said at least one annular flange, and a ring seal having a spring-loaded annular sealing portion and a radial flange extending from one end of said spring-loaded annular sealing portion, the spring-loaded annular sealing portion extending axially in said annular gap in sealing engagement with said back side and said radially inwardly facing surface of said at least one annular flange, and wherein the radial flange is in axial abutment relationship with an axially facing surface of one of said shroud and said at least one annular flange of said shroud support, wherein said spring-loaded annular sealing portion has a wave-shaped pattern including a pair of radially inwardly located peaks in contact with said back side of said platform and one radially outwardly located peak in contact with said radially inwardly facing surface of said at least one annular flange.
A ring seal in combination with a turbine shroud adapted to surround a stage of turbine blades, the turbine shroud comprising a supped ring and a shroud mounted within said support ring, the shroud comprising a platform having an aft overhanging portion, said aft overhanging portion having a gas path side and a back side opposite said gas path side, said back side defining with an opposed facing radially inner surface of said support ring an annular gap, said ring seal being mounted in said annular gap and maintained in sealing engagement with said radially inner surface of said support ring and said back side of said aft overhanging portion of said platform, wherein said support ring has an aft annular flange extending radially inwardly from an inner surface thereof, and wherein said annular gap is defined between said aft annular flange and said aft overhanging portion, and wherein said ring seal has a radial flange abutting against a forwardly axially facing surface of said aft annular flange.
A method for sealing a turbine shroud assembly comprising a shroud and a shroud support, the shroud comprising a platform overhanging portion having a gas path side and an opposed back side, the back side being spaced-radially inwardly from a radially inner surface of an aft annular flange extending radially inwardly from an inner surface of the shroud support, the method comprising:
- mounting an annular seal in sealing engagement with said back side of the platform overhanging portion and the radially inner surface of the aft annular flange of the shroud support, and abutting a radial flange of the annular seal against a forwardly axially facing surface of the aft annular flange.
Dependencies are inferred from the claim text.