A multi-component fastener is provided having a body and a sleeve. The body has a shank that extends lengthwise between a head and a distal end. The shank includes a first outer surface. The body includes a first material. The sleeve has a wall defined by an outer surface and an inner surface. The inner surface defines an interior cavity. The wall extends lengthwise between a first end and a second end. At least a portion of the sleeve outer surface contiguous with the first end is threaded. The sleeve includes a second material that is dissimilar to the first material. A portion of the shank including the distal end is disposed within the interior cavity of the sleeve. The sleeve and the shank are fixed to one another.

A rotary assembly for a turbine engine is provided. The assembly includes a rotor with two consecutive rotor stages equipped with a plurality of movable vanes, and an annular rotor shroud connecting the two consecutive rotor stages; and a stator including a stator stage, provided with a plurality of fixed vanes and disposed between the two rotor stages, and an annular stator ring mounted on the fixed vanes. Either the rotor shroud or the stator ring bears at least one wiper designed to cooperate with an abradable track on the other of the rotor shroud and stator ring, such that the rotor shroud includes at at least one of its upstream or downstream ends an inclined contact portion resting on an inclined bearing surface of the corresponding rotor stage, the bearing surface being the outer surface of a projection extending from a base portion of the corresponding rotor stage.

A flange joint assembly includes a first structure including a first flange and a second structure including a second flange coupled to the first flange to form a joint therebetween. The second flange includes a radially outer surface. The flange joint assembly also includes a compression ring coupled to at least the radially outer surface and configured to apply a compressive force to the radially outer surface to reduce an amount of tension stress within said second flange.

A compressor adapted for use in a gas turbine engine includes an impeller, a diffuser, and a deswirler. The impeller is arranged circumferentially about an axis and configured to rotate about the axis. The diffuser is arranged circumferentially around the impeller to receive the air from the impeller. The deswirler is configured to receive the air from the diffuser and to conduct the air into a combustion chamber.

A gas turbine engine includes a compressor assembly that is rotationally coupled to a shaft. The engine includes a radial diffuser assembly coupled to a shroud of the compressor assembly and positioned to receive compressed air from a centrifugal impeller. The radial diffuser assembly includes a first arcuate wall and a second wall, and a near axial diffuser coupled to the radial diffuser assembly and positioned to receive the compressed air from the radial diffuser assembly. The gas turbine includes a gas seal coupled between the second wall and a wall of the near axial diffuser, the gas seal configured to prevent the compressed air from passing through the seal while allowing relative motion between the radial diffuser assembly and the near axial diffuser.

A center vent tube aligning mechanism which aligns a center vent tube inserted into a hollow shaft is provided with: an annular portion which is coaxially provided with the center vent tube in an outer side of the center vent tube in a radial direction thereof; a flexible portion which protrudes in a direction along an axis of the center vent tube from the annular portion; an abutting portion which is connected to the flexible portion and which abuts an inner circumferential surface of the shaft; and a cylindrical sleeve which surrounds the center vent tube from the outer side in a radial direction of the center vent tube and which is supported by a reaction force that the abutting portion receives from the inner circumferential surface of the shaft.

An engine assembly having an internal combustion engine, a turbine module including a turbine casing, a support casing rigidly connecting the turbine casing to a remainder of the assembly, and an inlet scroll connected to the turbine casing without any direct rigid connection to the support casing. The inlet scroll includes an inlet pipe for each engine exhaust port. An exhaust pipe is provided for each exhaust port, connected to and providing fluid communication between the respective exhaust port and inlet pipe. The exhaust pipe is movable relative to at least one of the exhaust port and the inlet pipe at a corresponding connection therewith. One of the exhaust and inlet pipes floatingly extends through an opening defined in the support casing. The assembly may be a compound engine assembly.

A gas turbine structure includes a first housing and a second housing, one of the first and second housings being located around the other of the first and second housings such that a core flow passage is obtained between the first and second housings. The gas turbine structure further includes an elongate structural member extending in a structural member direction from the first housing to the second housing and the gas turbine structure further includes a fairing circumferentially enclosing at least a portion of the structural member.

A gas turbine engine component assembly comprises a first component and a second component circumferentially spaced from the first component relative to an engine center axis. A first baffle is associated with the first component. A second baffle is associated with the second component. Each of the first and second baffles includes at least one radial baffle tab. A gap is between the first and second baffles to define a cooling air inlet. A first coverplate is associated with the first baffle to cover a first portion of the gap. A second coverplate is associated with the second baffle to cover a second portion of the gap. The first and second coverplates are separate from each other, and include at least one coverplate radial tab that cooperates with an associated at least one baffle radial tab to prevent leakage gaps between the first and second baffle plates and the first and second coverplates.

A flexible seal is used to seal between two adjacent gas turbine components. The flexible seal includes at least one metal ply having a forward end, an aft end axially separated from the forward end, and an intermediate portion between the forward end and the aft end. The intermediate portion defines a continuous curve in the circumferential direction, such that the aft end is circumferentially, and optionally radially, offset from the forward end. A plurality of relief cuts is defined through the at least one metal ply between the forward end and the aft end to increase flexibility and improve sealing in seal slots that are radially offset from one another.