A turbocharge includes: a compressor wheel; a turbine wheel configured to rotate with the compressor wheel; a turbine housing disposed so as to cover the turbine wheel; a bearing supporting a rotational shaft of the turbine wheel rotatably; and a bearing housing accommodating the bearing. One of the turbine housing or the bearing housing includes a fin portion protruding toward the other one of the turbine housing or the bearing housing so as to extend along an axial direction of the rotational shaft, and, between the turbine housing and the bearing housing, a cavity is formed on each side of the fin portion with respect to a radial direction of the rotational shaft.

Turbomachinery comprising a turbine housing (200) with an engagement formation (210) and a casing (400) for electrical machinery, the casing (400) including an engagement recess (410). Furthermore, the engagement recess (410) comprises a cantilever member (420) and is adapted to receive the engagement formation (210). Finally, the engagement recess (410) and engagement portion (210) are configured such that during operation of said turbomachinery the engagement formation undergoes thermal expansion to expand relative to the engagement recess and exert pressure on the cantilever (member 420). In this way, an improved apparatus for centralising the turbine housing (200) in relation to the casing (400) is provided.

Methods and systems are provided for a turbocharger. In one example, a system comprises a compressor housing clamped to a bearing housing via a clamp ring. The clamp ring may be configured to at least partially detach the compressor and allow the compressor to rotate and/or shift in response to a force.

A turbocharger includes a gripping unit gripping a turbine-housing side flange portion and a bearing-housing side flange portion to couple a turbine housing and a bearing housing. In a state where the turbine housing and the bearing housing are coupled by the gripping unit, an elastic force in a direction to separate the turbine-housing side flange portion and the bearing-housing side flange portion from each other is applied to each of the turbine housing and the bearing housing.

In a flange fastening structure, a turbocharger includes a wastegate decentered from a center of a first flange that surrounds an outlet opening of the turbocharger. A bolt of a V-band that fastens the first flange on the turbocharger to a second flange on an exhaust passage member is disposed in a first region. The first region is a region composed of two sector-shaped regions each having a central angle of 90 degrees from a straight line from the center through a point that is on the first flange and that is closest to a maximum opening portion of the wastegate toward a corresponding side in a circumferential direction.

A centrifugal compressor is provided. The centrifugal compressor includes a housing and a rotatable assembly mounted for rotation about an axis within the housing. The rotatable assembly includes an impeller forming part of a compressor stage. A first air intake is located at a first end of the apparatus, the first air intake providing an air source for the compressor stage and a second air intake is located at a second end of the apparatus. A thrust plate is attached to the rotatable assembly, the thrust plate including at least one interior channel so that air entering the second air inlet passes through the at least one interior channel.

In a flange cooling structure of a gas turbine engine, one of a first flange and a second flange is a high pressure flange that faces a first region, and the other of the first flange and the second flange is a low pressure flange that faces a second region. A contact surface of the high pressure flange or a contact surface of the low pressure flange includes a cooling groove that communicates with the first region and the second region.

An electric power generating device for an aircraft, which is driven by an output of an aircraft engine, comprises an input shaft to which a driving force of the engine is transmitted; a transmission arranged with the input shaft; an electric power generator arranged with the input shaft and the transmission and driven by an output of the transmission; a driving force transmission mechanism disposed on a first end side of the input shaft in an axial direction thereof, the driving force transmission mechanism being configured to transmit the output from the transmission to the electric power generator; and a casing including a mounting section on the first end side of the input shaft in the axial direction, wherein the transmission includes an input section provided on a second end side of the input shaft in the axial direction, the input section being configured to receive as an input a rotational driving force from the input shaft, and an output section provided on the first end side of the input shaft in the axial direction, the output section being configured to output to the driving force transmission mechanism the rotational driving force whose speed has been changed, and wherein the driving force transmission mechanism has an inner space and the input shaft is inserted into the inner space.

The damper segment can be assembled between adjacent segments of a pressurized gas pipe of an aircraft engine. The damper segment can have a proximal end, a distal end, a rigid tube at the proximal end, a damper tube extending between the rigid tube and the distal end, the damper tube being made of a metal mesh, a proximal catch structurally connecting a proximal end of the damper tube to the rigid tube, and a distal catch structurally connected between a distal end of the damper tube and the distal end, the damper tube having an unsupported length extending between the distal catch and the proximal catch, the rigid tube having a liner portion projecting into the distal segment, the liner portion extending internally relative the damper tube.

A gas turbine engine includes an engine unit and an inlet. The engine unit includes an engine core that includes a compressor, a combustor, and a turbine and a nacelle arranged circumferentially around at least a portion of the engine core. The inlet is removably coupled with the nacelle and configured to conduct fluid into the engine unit. The inlet includes a nose and an intake lip arranged circumferentially around the nose to define an intake passage that extends through the inlet.