An assembly for forming a gas turbine engine according to an example of the present disclosure includes, among other things, a layup tool including a main body extending along a longitudinal axis and a flange extending radially from the main body, the flange defining an edge face slopes towards the main body to an axial face. At least one compression tool has a tool body having a first tool section and a second tool section extending transversely from the first tool section. The first tool section is translatable along a retention member in a first direction substantially perpendicular to the edge face such that relative movement causes the second tool section to apply a first compressive force on a composite article trapped between the axial face of the flange and the second tool section. A method of forming a gas turbine engine component is also disclosed.

An integrated bearing assembly includes a thrust bearing disposed along a face of a turbocharger casing in a turbocharger and extending circumferentially around an axis of rotation of a rotor of the turbocharger, and a dual film journal bearing radially disposed between the rotor and the turbocharger casing which can be semi-floating or fully floating. The journal bearing includes a shoulder step radially extending away from the rotor. The shoulder step of the journal bearing engages one or more of the thrust bearing or the turbocharger casing to prevent axial movement of the dual film journal bearing relative to the turbocharger casing.

An airfoil for a fan section of a turbine engine may include a fan blade or an outlet guide vane formed of a first material, and an edge guard disposed about an edge of the fan blade. The edge guard may include a matrix composite that has a toughness that is greater than a toughness of the first material. The airfoil may include a fan blade or an outlet guide vane. The first material of the airfoil may include a metal alloy and/or a matrix composite. A method of manufacturing an airfoil for a fan section of a turbine engine may include manufacturing an edge guard, attaching the edge guard to the airfoil.

A turbofan engine according to an example of the present disclosure includes, among other things, a fan, and an outer housing surrounding the fan to define a bypass flow path, a compressor, a turbine section including a fan drive turbine and a second turbine, an epicyclic gear system with a gear reduction, the fan drive turbine driving the fan through the gear system, and the gear system straddle-mounted by first and second bearings. The fan drive turbine has a first exit area at a first exit point and is rotatable at a first speed. The second turbine has a second exit area at a second exit point and is rotatable at a second speed. A first performance quantity is defined as the product of the first speed squared and the first area. A second performance quantity is defined as the product of the second speed squared and the second area.

A turbojet engine including a shaft surrounded by a low-pressure rotor surrounded by a coaxial and independent high-pressure spool, this turbojet engine including from upstream to downstream: a fan driven by the shaft; a low-pressure compressor carried by the rotor; an inter-compressor casing; a high-pressure compressor and a high-pressure turbine carried by the high-pressure spool; an inter-turbine casing; a low-pressure turbine carried by the rotor; an exhaust casing; this turbojet engine including an upstream rotor bearing carried by the inter-compressor casing; a downstream rotor bearing carried by the exhaust casing; a gearbox downstream of the downstream bearing and through which the rotor drives the shaft; a downstream shaft bearing downstream of the downstream rotor bearing.

A turbocharger includes a turbine housing including an interior surface defining a turbine housing interior. The interior surface extends between a turbine housing inlet and a turbine housing outlet. The turbine housing also includes a wastegate duct disposed downstream of the turbine housing inlet and defining a wastegate channel. The turbocharger also includes a valve seat disposed about the wastegate channel, with the valve seat having a valve seat plane extending along the valve seat. The turbocharger further includes a wastegate assembly including a valve element engageable with the valve seat. The wastegate channel extends along a channel axis, and the channel axis is obliquely oriented with respect to the valve seat plane such that the wastegate channel and the valve element are configured to direct exhaust gas to a catalytic converter.

A turbo fluid machine includes a rotary shaft configured to rotate in one rotational direction, and a radial foil bearing. The radial foil bearing includes: a bump foil formed of an elastic thin plate having a corrugated shape. The bump foil is divided into first and second foil portions located respectively on one side and on the other side in an axial direction of the rotary shaft. Ridges on the first foil portion are inclined in the other rotational direction of the rotary shaft while extending from an edge of the first foil portion adjacent to the other side toward the one side in the axial direction. The ridges on the second foil portion are inclined in the other rotational direction of the rotary shaft while extending from an edge of the second foil portion adjacent to the one side toward the other side in the axial direction.

A tie rod assembly structure, a gas turbine having the same, and a method of assembling tie rod are provided. The tie rod assembly structure includes a tie rod on which a plurality of rotor disks are mounted, a bearing support shaft mounted to the tie rod to support the rotor disks and on which a bearing is mounted, a first nut mounted on the tie rod on one side of the bearing support shaft, and a second nut that is fastened to the first nut to tension the tie rod and then is in close contact with the bearing support shaft to support the bearing support shaft.

A turbine exhaust case (TEC) has an outer case and an inner case structurally interconnected by a plurality of circumferentially spaced-apart struts. At least one of the struts has an airfoil body with a hollow core. The airfoil body has opposed pressure and suction sides extending chordwise from a leading edge to a trailing edge and spanwise from a radially inner end to a radially outer end. The radially inner end of the strut has a strut wall extension that extends through the inner case to a location radially inward of the inner case relative to the central axis.

A turbocharger includes a variable nozzle unit, a bearing housing, a circular heat shield plate located between a turbine impeller and the bearing housing, and a water chamber formed in the bearing housing. The heat shield plate is fixed by being pressed against the variable nozzle unit by a disc spring and is radially aligned by being fitted into the bearing housing by a fitting portion. The heat shield plate includes a fitting surface formed in the fitting portion and an inner peripheral heat shield portion projecting radially inward from the fitting surface and located with an axial gap between the inner peripheral heat shield portion and the bearing housing. At least a part of the water chamber exists at the same radial position as a radial position of the fitting portion.