Abstract: A welded assembly includes a first sheet and a second sheet. The second sheet is disposed over a portion of the first sheet and defines an overlap portion between the first and second sheets. A weld fastening the second sheet to the first sheet in the overlap area connects the second sheet to the first sheet for distributing stress uniformly across a welded portion of the overlap area.

Abstract: An assembly is provided for mounting a turbine engine to an airframe. The turbine engine extends along an axial centerline and includes an engine core mount and an engine exhaust mount. The assembly includes a thrust pin linkage connecting and extending axially between a core thrust pin and an exhaust thrust pin. The core thrust pin is adapted to connect to the engine core mount, and the exhaust thrust pin is adapted to connect to the engine exhaust mount. One of the core thrust pin, the exhaust thrust pin and the thrust pin linkage is also adapted to connect to the airframe.

Abstract: A welded assembly includes a first sheet and a second sheet. The second sheet is disposed over a portion of the first sheet and defines an overlap portion between the first and second sheets. A weld fastening the second sheet to the first sheet in the overlap area connects the second sheet to the first sheet for distributing stress uniformly across a welded portion of the overlap area.

Abstract: A welded assembly includes a first sheet and a second sheet. The second sheet is disposed over a portion of the first sheet and defines an overlap portion between the first and second sheets. A weld fastening the second sheet to the first sheet in the overlap area connects the second sheet to the first sheet for distributing stress uniformly across a welded portion of the overlap area.

Abstract: A hanger for use in a gas turbine engine exhaust system comprises a first bracket, a second bracket, a pin and a bumper. The first bracket is for connecting to an exhaust duct or liner of the gas turbine exhaust system. The second bracket is for connecting to an exhaust duct or liner of the gas turbine exhaust system. The pin extends through the first and second brackets to bring the first and second brackets into pivotable engagement. The bumper is positioned adjacent the first or second bracket to inhibit movement of the first bracket relative to the second bracket.

Abstract: A seal assembly seals an interface between adjacent liner sections. The seal assembly comprises a seal carrier mounted to a first plate, a seal body overlapping at least a portion of the seal carrier to define a plane of travel between the seal body and the seal carrier, and at least one resilient member configured to bias the seal body against a second plate. The seal carrier includes an indented portion that extends radially inward of the plane of travel.

Abstract: A cooling system for a gas turbine engine includes a first structure movable relative to a second structure. The first structure has a cavity. A valve selectively controls fluid flow from a cooling source to the cavity. A valve is configured to move between first and second fluid flow positions in response to movement of the first structure. The first fluid flow position provides a greater amount of cooling fluid from the cooling source to the cavity than in the second fluid flow position.

Abstract: A welded assembly includes a first sheet and a second sheet. The second sheet is disposed over a portion of the first sheet and defines an overlap portion between the first and second sheets. A weld fastening the second sheet to the first sheet in the overlap area connects the second sheet to the first sheet for distributing stress uniformly across a welded portion of the overlap area.

Abstract: A mount assembly includes a main body, a bayonet, and a block. The bayonet is movable relative the main body to insert a portion of the bayonet into an internal cavity of the main body. The block is disposed within the internal cavity and is movable relative to the main body from a first position to a second position. In the first position, the bayonet is captured and held between the block and an inner wall of the internal cavity. In the second position, the block allows the bayonet to be removed from the internal cavity.

Abstract: A cooling air flow ejector has a primary nozzle position to entrain air from a secondary nozzle. Mixed air is provided into a downstream flow conduit to be directed to an exhaust liner for a gas turbine engine. A variable area device controls a volume of air passing through a primary nozzle. A control for the variable area device to control the size of an orifice within the variable area device controls the volume of air reaching the exhaust liner to be cooled.

Abstract: A hanger for use in a gas turbine engine exhaust system comprises a first bracket, a second bracket, a pin and a bumper. The first bracket is for connecting to an exhaust duct or liner of the gas turbine exhaust system. The second bracket is for connecting to an exhaust duct or liner of the gas turbine exhaust system. The pin extends through the first and second brackets to bring the first and second brackets into pivotable engagement. The bumper is positioned adjacent the first or second bracket to inhibit movement of the first bracket relative to the second bracket.

Abstract: An assembly is provided for mounting a turbine engine to an airframe. The turbine engine extends along an axial centerline and includes an engine core mount and an engine exhaust mount. The assembly includes a thrust pin linkage connecting and extending axially between a core thrust pin and an exhaust thrust pin. The core thrust pin is adapted to connect to the engine core mount, and the exhaust thrust pin is adapted to connect to the engine exhaust mount. One of the core thrust pin, the exhaust thrust pin and the thrust pin linkage is also adapted to connect to the airframe.

Abstract: A seal assembly seals an interface between adjacent liner sections. The seal assembly comprises a seal carrier mounted to a first plate, a seal body overlapping at least a portion of the seal carrier to define a plane of travel between the seal body and the seal carrier, and at least one resilient member configured to bias the seal body against a second plate. The seal carrier includes an indented portion that extends radially inward of the plane of travel.

Abstract: A mount assembly includes a main body, a bayonet, and a block. The bayonet is movable relative the main body to insert a portion of the bayonet into an internal cavity of the main body. The block is disposed within the internal cavity and is movable relative to the main body from a first position to a second position. In the first position, the bayonet is captured and held between the block and an inner wall of the internal cavity. In the second position, the block allows the bayonet to be removed from the internal cavity.

Abstract: A cooling system for a gas turbine engine includes a first structure movable relative to a second structure. The first structure has a cavity. A valve selectively controls fluid flow from a cooling source to the cavity. A valve is configured to move between first and second fluid flow positions in response to movement of the first structure. The first fluid flow position provides a greater amount of cooling fluid from the cooling source to the cavity than in the second fluid flow position.