An article, a component, and a method of making a component are provided. The article includes a contoured proximal face and a contoured distal face. The contoured proximal face is arranged and disposed to substantially mirror a contour of an end wall of a component. The component includes a first end wall, a second end wall, and an article including a contoured proximal face secured to at least one of the first end wall and the second end wall. The method of making a component includes forming an article having a proximal face and a distal face, contouring the proximal face of the article to form a contoured proximal face that substantially mirrors a contour of a first end wall or a second end wall of the component, and securing the contoured proximal face of the article to one of the first end wall and the second end wall.

A turbocharger rotor shaft assembly and associated turbocharger that includes at least one turbine rotor member having a first face and an opposed second face; and a rotor shaft having a first end and an opposed second end distal from the first end, wherein the rotor shaft is connected to the at least one turbine rotor at a location proximate to the first end and projects outward therefrom, the rotor shaft having an outwardly oriented face and an interior chamber defined therein, the interior chamber having an interior chamber volume. The turbocharger rotor shaft also includes at least one thermal transfer material contained in the interior chamber of the rotor shaft that has a thermal conductivity value that is greater than the thermal conductivity value of the material of construction of the rotor shaft.

Particulate composite materials and devices comprising the same are provided.

A coupling assembly, including a first component and a second component overlapping one another in a join region; a joining device allowing the first component and the second component to rest against each other clampingly in the join region; the joining device including a clamp resting on the first component and the second component and having a bolt connection adapted for securing the clamp to the first and second component. The first component and the second component are manufactured from a ceramic matrix composite; the first component having a holding portion including a front side facing the clamp, a rear side facing away from the clamp, and a receiving opening; and the bolt connection having a bolt portion that extends through the receiving opening and, at the end thereof facing away from the clamp, having a bracing portion that is angled relative to the longitudinal axis of the bolt portion and that rests against the rear side of the holding portion.

An airfoil and a method of manufacturing an airfoil may be provided, where the airfoil comprises a core and a shell. The core comprises core ceramic fibers extending along a span of the airfoil. The shell surrounds the core and includes shell ceramic fibers. Substantially all of the core ceramic fibers are arranged in a radial direction. The airfoil may also be a ceramic matrix composite formed by infiltrating the core and the shell with a matrix material.

An aerofoil body for a gas turbine engine is provided. The aerofoil body has leading and trailing edge portions, wherein one of the leading and trailing edge portions is a morphable edge portion having a composite layer structure. The aerofoil body further has a non-morphing central portion which forms pressure and suction surfaces of the aerofoil body between the leading and trailing edge portions. The composite layer structure includes a return spring, one or more shape memory alloy layers, and a flexible cover for the return spring and the one or more shape memory alloy layers. The flexible cover defines pressure and suction surfaces of the aerofoil body at the morphable edge portion. The one or more shape memory alloy layers are electrically heatable to deform the layers against the resistance of the return spring, and thereby alter the pitch of the aerofoil body at the morphable edge portion.

A turbine vane assembly for use in a gas turbine engine includes an endwall, a flow path component, and a load-distribution system. The endwall is arranged around a central axis of the turbine vane assembly. The flow path component is configured to direct fluid flow through the turbine vane assembly. The load-distribution system is positioned between the endwall and the flow path component to distribute loads transmitted between the endwall and the flow path component.

A turbine shroud adapted to extend around a bladed turbine wheel to block gasses from passing over the bladed turbine wheel is disclosed. In a segmented embodiment, each turbine shroud segment may include a carrier segment and a blade track segment. The carrier segment may comprise metallic materials and may be formed to define an attachment-receiving space. The blade track segment may comprise ceramic matrix composite materials and may be formed to include an attachment portion that extends radially outward from the runner into the attachment-receiving space formed by the carrier segment.

An assembly adapted for use in a gas turbine engine is disclosed herein. The assembly includes a first component including metallic materials and a second component including ceramic matrix composite materials. A portion of the second component is configured to engage a portion of the first component directly so that the second component is supported in a predetermined position.

A turbine nozzle or a compressor diffuser includes sectors made of CMC material, each having an inner platform, an outer platform, and airfoils. An abradable material support ring is made up of sectors, each presenting upstream and downstream attachment tabs. Each inner platform presents on the inside an upstream hook and a downstream hook, and the abradable material support ring is supported by the nozzle or the diffuser by mutually engaging without fastening together firstly the end portions of the upstream attachment tabs and the upstream hooks and secondly the end portions of the downstream attachment tabs and the downstream hooks.