Shroud sealing for a gas turbine engine
AssigneeGeneral Electric Company
InventorSergio Filippi
Life of this patent
Estimating the term…
Abstract
A shroud assembly for gas turbine engine defining an axial direction, a radial direction, and a circumferential direction includes a shroud segment extending substantially along the circumferential direction and including a forward wall and an aft wall spaced along the axial direction from one another and defining a cavity therebetween; and a hanger assembly including a first attachment member and a seal member, the first attachment member attached to one of the forward wall or the aft wall of the shroud segment, and the seal member positioned within the cavity and interference fit against the other of the forward wall or the aft wall of the shroud segment.
Claims20
A shroud assembly for a gas turbine engine defining an axial direction, a radial direction, and a circumferential direction, the shroud assembly comprising:
- a shroud segment extending substantially along the circumferential direction and comprising a forward wall and an aft wall spaced along the axial direction from one another and defining a cavity therebetween;
- and
- a hanger assembly comprising a first attachment member and a second attachment member,
- wherein the first attachment member comprises a forward portion and a first seal member, wherein the forward portion is attached to the forward wall of the shroud segment and the first seal member is positioned within the cavity and interference fit against the forward wall of the shroud segment, and
- wherein the second attachment member comprises a second seal member positioned within the cavity and interference fit against the aft wall of the shroud segment, and wherein the second seal member is sloped towards the aft wall of the shroud segment.
A gas turbine engine defining an axial direction, a radial direction, and a circumferential direction, comprising:
- a compressor section, a combustion section, and a turbine section in serial flow relationship and together defining a core air flowpath;
- and
- a shroud assembly positioned in at least one of the compressor section and the turbine section and at least partially defining the core air flowpath, the shroud assembly comprising:
- a shroud segment extending substantially along the circumferential direction and comprising a forward wall and an aft wall spaced along the axial direction from one another and defining a cavity therebetween;
- and
- a hanger assembly comprising a first attachment member and a second attachment member, wherein the first attachment member comprises a forward portion and a first seal member, wherein the forward portion is attached to the forward wall of the shroud segment and the first seal member is positioned within the cavity and interference fit against the forward wall of the shroud segment, and wherein the second attachment member comprises a second seal member positioned within the cavity and interference fit against the aft wall of the shroud segment, and wherein the second seal member is sloped towards the aft wall of the shroud segment.
A hanger assembly for a gas turbine engine defining an axial direction, a radial direction, and a circumferential direction, the hanger assembly comprising:
- a first attachment member comprising a forward portion and a first seal member, the forward portion and first seal member defining a first gap therebetween for receipt of a forward wall of a shroud segment of the gas turbine engine;
- and
- a second attachment member comprising an aft portion and a second seal member, the aft portion and second seal member defining a second gap therebetween for receipt of an aft wall of the shroud segment of the gas turbine engine, the second seal member configured to be interference fit against the aft wall of the shroud segment when installed in the gas turbine engine;
- wherein the second seal member is sloped towards the aft portion of the second attachment member such that the second seal member is interference fit against the aft wall of the shroud segment when installed in the gas turbine engine, and wherein the first seal member is sloped towards the forward portion of the first attachment member such that the first seal member is interference fit against the forward wall of the shroud segment when installed in the gas turbine engine.
Dependencies are inferred from the claim text.