Abstract: A combustor for a gas turbine engine includes a combustor shell, a burner seal, and a burner seal retainer. The combustor shell includes metallic materials and is formed to define an interior combustion space. The burner seal includes ceramic matrix composite materials and is configured to extend through apertures formed in the combustor shell and the heat shield. The burner seal retainer is configured to retain the burner seal to the combustor shell.

Abstract: A propulsion unit includes a gas turbine engine arranged along an axis and an exhaust system coupled to the gas turbine engine. The gas turbine engine includes an engine core configured to discharge a core flow and a fan configured to be driven by the engine core to discharge a bypass flow. The exhaust system receives the mixed bypass and core flows from the gas turbine engine.

Abstract: An exhaust nozzle for use with a gas turbine engine includes an outer shroud, an inner plug spaced radially apart from the outer shroud, and at least one support vane that is coupled to the outer shroud. The outer shroud and the inner plug cooperate to provide an exhaust nozzle flow path therebetween. The at least one support vane interconnects the outer shroud and the inner plug to support the inner plug in the exhaust nozzle flow path.

Abstract: An exhaust nozzle for use with a gas turbine engine includes an outer shroud, an inner plug spaced radially apart from the outer shroud, and at least one support vane that is coupled to the outer shroud. The outer shroud and the inner plug cooperate to provide an exhaust nozzle flow path therebetween. The at least one support vane interconnects the outer shroud and the inner plug to support the inner plug in the exhaust nozzle flow path.

Abstract: A propulsion unit includes a gas turbine engine arranged along an axis and an exhaust system coupled to the gas turbine engine. The gas turbine engine includes an engine core configured to discharge a core flow and a fan configured to be driven by the engine core to discharge a bypass flow. The exhaust system receives the mixed bypass and core flows from the gas turbine engine.

Abstract: An exhaust nozzle for use with a gas turbine engine includes an outer shroud and a nozzle-plug assembly coupled to the outer shroud. The nozzle-plug assembly includes an inner plug and at least one support vane that is coupled to the outer shroud to support the inner plug in an exhaust nozzle flow path.

Abstract: A system may be provided that includes a hot section component of a gas turbine engine. The hot section component includes a dual wall, which includes a first wall and a second wall. The first wall includes multiple impingement cooling holes extending through the first wall. The second wall is positioned adjacent the first wall. The first wall and the second wall together define a cooling passage between the first wall and the second wall. Multiple pockets are in a surface of the second wall. Each of the pockets is positioned opposite a respective one of the impingement cooling holes. Each of the pockets is configured to receive a cooling fluid from the respective one of the impingement cooling holes and direct the cooling fluid into the cooling passage. The cooling passage includes a single cooling passage into which the pockets are configured to direct the cooling fluid.

Abstract: A combustor adapted for use in a gas turbine engine includes a metallic combustor shell forming an interior space, a heat shield, and a liner arranged in the interior space of the metallic case. The liner defines a combustion chamber in which fuel is burned during operation of a gas turbine engine.

Abstract: A propulsion unit includes a gas turbine engine arranged along an axis and an exhaust system coupled to the gas turbine engine. The gas turbine engine includes an engine core configured to discharge a core flow and a fan configured to be driven by the engine core to discharge a bypass flow. The exhaust system receives the mixed bypass and core flows from the gas turbine engine.

Abstract: A propulsion unit includes a gas turbine engine arranged along an axis and an exhaust system coupled to the gas turbine engine. The gas turbine engine includes an engine core configured to discharge a core flow and a fan configured to be driven by the engine core to discharge a bypass flow. The exhaust system receives the mixed bypass and core flows from the gas turbine engine.

Abstract: An exhaust nozzle for use with a gas turbine engine includes an outer shroud and a nozzle-plug assembly coupled to the outer shroud. The nozzle-plug assembly includes an inner plug and at least one support vane that is coupled to the outer shroud to support the inner plug in an exhaust nozzle flow path.

Abstract: An exhaust nozzle for use with a gas turbine engine includes an outer shroud, an inner plug spaced radially apart from the outer shroud, and at least one support vane that is coupled to the outer shroud. The outer shroud and the inner plug cooperate to provide an exhaust nozzle flow path therebetween. The at least one support vane interconnects the outer shroud and the inner plug to support the inner plug in the exhaust nozzle flow path.

Abstract: A combustor liner assembly is provided including an inlet wall, an inner wall, an outer wall, and a plurality of fasteners. The inlet wall has an opening into a combustion chamber. The inner wall is coupled to the inlet wall at a first end of the combustor liner. The inner wall defines a radially inner end of the combustion chamber. The outer wall includes a plurality of segments. The plurality of segments define a radially outer end of the combustion chamber. A first portion of the plurality of fasteners couples each of the plurality of segments to another of the plurality of segments. A second portion of the plurality of fasteners couples at least one of the plurality of segments to the inlet wall at the first end of the combustor liner.

Abstract: A combustor adapted for use in a gas turbine engine includes a metallic combustor shell forming an interior space, a heat shield, and a liner arranged in the interior space of the metallic case. The liner defines a combustion chamber in which fuel is burned during operation of a gas turbine engine.

Abstract: A combustor for a gas turbine engine includes a combustor shell, a burner seal, and a burner seal retainer. The combustor shell includes metallic materials and is formed to define an interior combustion space. The burner seal includes ceramic matrix composite materials and is configured to extend through apertures formed in the combustor shell and the heat shield. The burner seal retainer is configured to retain the burner seal to the combustor shell.

Abstract: Devices, systems, and methods of a casing for a heat suppression system of a gas turbine engine exhaust include a heat shield and an insulation layer for arrangement between the heat shield and an outer skin.

Abstract: A seal assembly can accommodate deflection between two components through a cartridge that is slidingly engaged with a slide plate.

Abstract: A fuel injection system may include a fuel spray nozzle including a nozzle head and a nozzle stem. The nozzle head may include an air channel and a swirler in fluid communication with the air channel. The nozzle stem may extend into a compressor discharge pressure cavity and convey fuel to the air channel. The air channel may combine air from the swirler with the fuel from the nozzle stem and convey a mixture of fuel and air to a combustor. The fuel injection system may further include a scoop. The scoop may be coupled to the fuel spray nozzle. The scoop may receive air that flows into the compressor discharge pressure cavity from a diffusor. An outer surface of the fuel spray nozzle and an inner surface of the scoop define a duct in fluid communication with the swirler. The swirler may receive air from the duct.

Abstract: A system may be provided that includes a hot section component of a gas turbine engine. The hot section component includes a dual wall, which includes a first wall and a second wall. The first wall includes multiple impingement cooling holes extending through the first wall. The second wall is positioned adjacent the first wall. The first wall and the second wall together define a cooling passage between the first wall and the second wall. Multiple pockets are in a surface of the second wall. Each of the pockets is positioned opposite a respective one of the impingement cooling holes. Each of the pockets is configured to receive a cooling fluid from the respective one of the impingement cooling holes and direct the cooling fluid into the cooling passage. The cooling passage includes a single cooling passage into which the pockets are configured to direct the cooling fluid.

Abstract: Devices, systems, and methods of a casing for a heat suppression system of a gas turbine engine exhaust include a heat shield and an insulation layer for arrangement between the heat shield and an outer skin.