An exhaust gas liner for a gas turbine includes an annular inner shell and an annular outer shell, which are arranged concentrically around a machine axis of the gas turbine to define an annular exhaust gas channel in between. The inner shell and/or said outer shell are composed of a plurality of liner segments, which are attached to a support structure. To compensate thermal expansion and achieving resistance against dynamic loads, the liner segments are fixed to the support structure at certain fixation spots, which are distributed over the area of said liner segments, such that said liner segments are clamped to said support structure through a whole engine thermal cycle without hindering thermal expansion.

A cooled flange connection of a gas-turbine engine is annular and includes a first flange of a first component, at least a second and central flange of a second component, and a third flange of a third component. At the contact area between the first and the second flange a first circumferential duct is provided that extends over at least part of the circumference. At the contact area between the second and the third flange a second circumferential duct is provided that extends over at least part of the circumference. The first and second circumferential ducts are connected to one another by axial connecting recesses. The first flange is provided with at least one inflow recess connected to the first circumferential duct. The third flange is provided with at least one outflow recess connected to the circumferential duct.

A method for assembling a plug assembly for plugging one or more ports of a gas turbine engine including that a connector body and a cover operably connected to the connector body are inserted into a sheath through-passage of a sheath. The connector body including a rotatable joint operably connecting the cover to the connector body. The method also includes that a biasing mechanism configured to apply a force to the cover is installed, the cover is rotated relative to the connector body via the rotatable joint, a top housing is slid over the biasing mechanism such that the biasing mechanism abuts a bottom end of the top housing or is located in a cavity defined within the top housing, and the top housing is secured together with the sheath.

Aspects of the disclosure regard a fan case assembly for a gas turbine engine, the fan case assembly comprising a fan case having an inner surface, a fan case liner having an outer surface, and a reclosable fastening system attaching the fan case liner to the fan case, the reclosable fastening system comprising two components, a first component being attached to the fan case inner surface and a second component being attached to the fan case liner outer surface.

Aspects of the disclosure regard a bolt assembly which comprises a bolt extending in a longitudinal direction through a flange connection, the bolt comprising a first portion and a second portion, the first portion comprising a threaded section at a first side of the flange connection and the second portion comprising a head portion at a second side of the flange connection. The bolt assembly further comprises a nut screwed on the threaded section and a spacer arranged between the nut and the flange connection or between the head portion and the flange connection. The bolt is comprised of a titanium alloy.

A nacelle of an aircraft propulsion assembly includes a front section and a main section. The nacelle also includes a junction flange between the front section and the main section including a plurality of deformable damper elements distributed along the inner peripheral edge of a stiffening frame of the nacelle. The damper element allows significant stresses to be absorbed between the engine flange and the stiffening frame. This configuration is particularly adapted to large nacelles. An aircraft propulsion assembly including such a nacelle is also described.

A gas turbine engine includes a fan case assembly adapted to extend around blades of a fan rotor included in the gas turbine engine. The fan case assembly includes an annular case that extends around an axis, an acoustic panel coupled to the annular case and configured to dampen vibrations and a bolting arrangement that couples the acoustic panel to the annular case.

The present invention relates to a multi jackbolt tensioner and methods of using the same. The present invention alleviates some of the problems associated with presently available multi jackbolt tensioners.

A windage cover for a plurality of fasteners coupling a ring gear assembly to an output shaft. The windage cover includes a clip retention member abutting an integral cover shell of the output shaft, and a foot portion configured to be inserted into a pilot groove between an integral lip and an arm portion of the output shaft. The windage cover also includes a wall portion connected to the foot portion, the wall portion being retained at one end of the wall portion by the clip retention member. The windage cover is configured to cover the plurality of fasteners.

A compressor adapted for use in for a gas turbine engine includes a diffuser and a housing. The diffuser is arranged circumferentially around an axis and includes a fore plate, an aft plate spaced apart axially from the fore plate to define a flow path therebetween, and a plurality of vanes that extend between the fore plate and the aft plate. The housing is arranged circumferentially about the axis and located adjacent the diffuser.