A retaining assembly may comprise a bracket assembly having a first end and a second end. The first end may be configured to mount to a clamping band. The retaining assembly may further comprise a retention component. The retention component may have a clevis coupled to the second end. The retaining assembly may be coupled to an otherwise loose external component on a gas turbine engine. The retaining assembly may keep the otherwise loose external component fixed to the gas turbine engine during maintenance operations and prevent the otherwise loose external component from being lost or misplaced.

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 turbine includes a turbine impeller, a turbine housing disposed so as to cover the turbine impeller and internally forming a scroll flow passage through which an exhaust gas flows, and a throat forming portion which is provided as a separate piece from the turbine housing. The throat forming portion is disposed to face a section of the turbine housing and forms a hub-side wall surface of a throat portion of the scroll flow passage in an axial direction, the section forming a shroud-side wall surface of the throat portion.

A turbocharger includes a turbine housing defining a turbine housing interior, a turbine wheel disposed in the turbine housing interior, a compressor housing defining a compressor housing interior, a compressor wheel disposed in the compressor housing interior, and a shaft coupled to the compressor wheel and the turbine wheel. The turbocharger also includes a bearing housing assembly including a bearing housing defining a bearing housing interior, and an anti-rotation assembly. The anti-rotation assembly includes a bearing assembly disposed in the bearing housing interior, an anti-rotation spacer disposed in the bearing housing interior and about the shaft, and a retaining ring disposed about the shaft and coupled to the anti-rotation spacer to axially retain the anti-rotation spacer in the bearing housing interior. The anti-rotation spacer has an engagement member engageable with the retaining ring and configured to limit rotation of the retaining ring relative to the anti-rotation spacer.

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.

A clamp for connecting a first component end to a second component end is provided. The clamp includes a web extending between a first end and a second end, each end being provided with a connecting device for connecting said web ends to each other so that the clamp encloses the component ends. The clamp further includes an alignment structure, which alignment structure is configured to fit with corresponding engagement structures provided at the first component end and the second component end for circumferentially positioning the clamp relative to the component ends.

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.

A V-clamp fastens a clamping flange of a turbine housing and a clamping flange of a bearing housing in a rotation axis direction of a connecting shaft so that the clamping flanges are fixed to each other. An annular heat shield plate is disposed between the turbine housing and the bearing housing. The heat shield plate is clamped by the turbine housing and the bearing housing. A clearance is disposed in an entire area between an opposed surface of the clamping flange of the turbine housing and an opposed surface of the clamping flange of the bearing housing.

A rotary machine include: a rotational shaft; an impeller mounted to the rotational shaft; an impeller housing accommodating the impeller; a bearing housing accommodating a bearing which supports the rotational shaft rotatably, the bearing housing being fastened to the impeller housing; and a fastening member fastening the impeller housing and the bearing housing in an axial direction of the rotational shaft. The impeller housing, the bearing housing, and the fastening member each includes a contact surface in a direction intersection with an axial direction of the rotational shaft. A thin-plate member formed separately from the impeller housing, the bearing housing, and the fastening member is interposed between at least two of the contact surfaces.

A turbine includes a turbine impeller, a turbine housing disposed so as to cover the turbine impeller and internally forming a scroll flow passage through which an exhaust gas flows, and a throat forming portion which is provided as a separate piece from the turbine housing. The throat forming portion is disposed to face a section of the turbine housing and forms a hub-side wall surface of a throat portion of the scroll flow passage in an axial direction, the section forming a shroud-side wall surface of the throat portion.