An assembly for a gas turbine engine has: a fan case with a forward end, an aft end, and an inner surface extending from the forward end of the fan case to the aft end of the fan case; an acoustic liner having a forward end, an aft end, and an acoustic liner body that extends continuously from the forward end of the acoustic liner to the aft end of the acoustic liner; an inlet case located forward of the forward end of the fan case, the forward end of the acoustic liner being secured to the inlet case, and wherein the acoustic liner body is positioned against an inner surface of the inlet case and an inner surface of the fan case, and the aft end of the acoustic liner is secured to the fan case between the forward end and the aft end of the fan case.

Gas turbine engines are described. The engines include high and low pressure turbine systems, a mid-turbine frame system arranged axially between the high and low pressure turbine systems, and a cooling air conduit fluidly connected to the mid-turbine frame system. A flow diverter assembly is installed between the cooling air conduit and the mid-turbine frame system. The flow diverter assembly includes a mounting plate to mount to the mid-turbine frame system, a manifold defining a manifold cavity on a first side of the mounting plate, a conduit connector for connecting to the cooling air conduit, and a diverter body extending from a second side of the mounting plate opposite the manifold. The diverter body has a solid base and a plurality of apertures arranged about a circumference thereof. The manifold cavity is fluidly connected to an interior of the diverter body through an aperture formed in the mounting plate.

Disclosed is a compressor housing and method of assembling. The compressor housing may comprise an outer volute, a cavity, an impeller cover, a compressor diffuser and an inner volute. The outer volute includes a back wall and a curved casing. The back wall may include a receptacle and a first plurality of annular steps. The receptacle configured to receive an alignment pin. The cavity is configured to receive the compressor impeller and is at least partially defined by the back wall of the outer volute and the impeller cover. The impeller cover is configured to fragment during impact with the compressor impeller during a failure condition of the compressor impeller. The impeller cover is disposed between the inner volute and the cavity. The compressor diffuser is disposed between the back wall and the impeller cover.

An assembly for mounting an auxiliary component to an engine case of a gas turbine engine includes a support bracket, the support bracket having a first end configured for attachment to a first flange of the engine case, a second end configured for attachment to a second flange of the engine case, and an intermediate portion located intermediate the first end and the second end; a bearing member disposed within the intermediate portion; a locator disposed within the bearing member; a first plurality of bolts configured to attach the first end of the support bracket to the first flange; a second plurality of bolts configured to attach the second end of the support bracket to the second flange; and a mechanical fuse.

An assembly for mounting an aircraft engine to an aircraft includes an engine casing flange having a first annular wall extending radially to terminate at an annular rim. A second flange of an additional engine component mounted aft of the engine casing includes a second annular wall. An aft mount bracket has an annular body extending uninterrupted about the center axis and a spigot extending axially from the annular body, the spigot extending circumferentially about an entire circumference of the annular body. The aft mount bracket is axially disposed between the engine casing flange and the additional engine component, with corresponding holes in the first annular wall, second annular wall and aft mount bracket being circumferentially aligned, and the spigot radially abutting the annular rim of the engine casing flange.

A housing for a rotor of an engine is provided. The housing forms an interior space for accommodating the rotor that is defined by a housing wall and the housing wall (W) circumferentially surrounds the rotor that is accommodated inside the housing. The housing has at least one service opening which is provided in the housing wall for maintenance and/or repair work and through which the interior space is accessible from the outside. The service opening is provided in the area of two facing flange sections of the housing, wherein the service opening is closed by at least one closure part that is received at least partially inside a gap formed between the facing flange sections and fixated therein in a releasable manner.

Provided is a turbocharger with further improved thermal efficiency. The turbocharger includes a heat shielding plate disposed between a center housing and a turbine housing. The center housing rotatably and pivotally supports a rotating shaft that connects a turbine impeller and a compressor impeller, and the turbine housing houses the turbine impeller. The turbocharger includes: a first flange portion; a second flange portion formed corresponding to the first flange portion; a clamp member combining the first flange portion and the second flange portion and fixing the mutual positional relationship; and a heat insulating ring interposed between an end surface, which is a heat shielding plate fixing portion that fixes the heat shielding plate, and the heat shielding plate on an inner peripheral side with respect to the first flange portion and the second flange portion.

Turbomachine output bearing support extending according to an axial direction, said support being formed by one and the same piece and comprising an annular inner wall having an inner side and an outer side, an annular outer wall and a twist support.

A variable-capacity turbocharger includes a nozzle flow passage in which a gas is capable of flowing therethrough from a scroll flow passage toward a turbine impeller, a connecting pin connecting flow passage wall surfaces forming the nozzle flow passage, and nozzle vanes arranged in a rotation direction of the turbine impeller. At least one of the flow passage wall surfaces includes an inner peripheral side wall surface extending radially inward of a first reference line extending in the rotation direction, an outer peripheral side wall surface which is a plane extending radially outward from a second reference line extending in the rotation direction and parallel to a plane orthogonal to rotation axes of the nozzle vanes, and an intermediate wall surface which is a plane extending from the first reference line to the second reference line and parallel to the plane extending orthogonal to the rotation axes of the nozzle vanes.

A fixing device fixes a relative position in a rotational direction of an outer member and an inner member of a stationary body of the rotary machine, and includes: a radial pin that is inserted into a through hole passing through the outer member in a radial direction of a rotary machine and having a stepped portion formed therein to have a larger diameter at a portion on an outer side in the radial direction of the rotary machine than at a portion on an inner side in the radial direction, that has a part on the inner side in the radial direction of the rotary machine to be inserted into a concave portion of the inner member, and that has a flange portion on the outer side in the radial direction of the rotary machine.