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.

The present invention relates to a rotor assembly for a rotary machine such as a gas turbine. The present solution provides a sealing wire located inside a groove engraved in the rotor body. The sealing wire is responsive to radial centrifugal forces acting during normal operation of the machine, and moves radially in the groove until a sealing configuration is achieved such to prevent damaging hot leakage towards machine components.

Methods are provided for manufacturing a component. In one method, first material is cast into a first body. At least a portion of the first body is machined. Second metal material is cast onto at least the machined portion of the first body to form a monolithic second body. A first portion of the second body is formed by the first metal material. A second portion of the second body is formed by the second metal material. The second metal material is different from the first metal material.

A method is provided for manufacturing a component. This method includes additively manufacturing a crucible for casting of the component. A metal material is directionally solidified within the crucible to form a metal single crystal material. A sacrificial core is removed to reveal a metal single crystal component with internal passageways. A component is provided for a gas turbine engine that includes a metal single crystal material component with internal passageways. The metal single crystal material component was additively manufactured of a metal material concurrently with a core that forms the internal passageways. The metal material was also remelted and directionally solidified.

The application describes methods of making composite bodies including fibre-reinforced composite material with carbon fibre reinforcement and also a metal-containing portion (4). The metal-containing portion (4) is formed by laying up metal reinforcement elements, such as tapes of titanium alloy, among the carbon fibre reinforcement tapes which make up the composite body. The proportion of metal reinforcement may increase progressively towards the surface and/or towards an edge (14) of the composite body. In an example, metal leading and trailing edges (14,15) of a fan blade (1) are integrally formed in this way.

A turbine airfoil is provided with at least one insert positioned in a cavity in an airfoil interior. The insert extends along a span-wise extent of the turbine airfoil and includes first and second opposite faces. A first near-wall cooling channel is defined between the first face and a pressure sidewall of an airfoil outer wall. A second near-wall cooling channel is defined between the second face and a suction sidewall of the airfoil outer wall. The insert is configured to occupy an inactive volume in the airfoil interior so as to displace a coolant flow in the cavity toward the first and second near-wall cooling channels. A locating feature engages the insert with the outer wall for supporting the insert in position. The locating feature is configured to control flow of the coolant through the first or second near-wall cooling channel.

A variable turbine geometry may include guide blades mounted rotatably in a blade carrier via one blade bearing pin for each guide blade, a blade lever arranged at an end of the blade bearing pin that faces away from the respective guide blade, and an articulated lever for a simultaneous adjustment of the guide blades via an adjusting ring arranged between two adjacent blade levers. The articulated lever may be provided with a stop contour, and when one of a maximum flow position or a minimum flow position is reached, the stop contour may lie against one of the two adjacent blade levers to define the one of the maximum flow position or the minimum flow position.

There is provided a turbocharger which can reduce whirl vibration. The turbocharger includes a shaft connecting a turbine and a compressor, a bearing housing having a bearing portion turnably supporting the shaft, and a sliding bearing interposed between the shaft and the bearing portion. The bearing portion is formed of an aluminum-based material, the shaft is formed of a steel material, and the sliding bearing is formed of a copper-based material.

A fan frame includes a first frame and a second frame. The first frame includes at least a first sidewall and a first connecting element, wherein the first connecting element is disposed on the first sidewall. The second frame includes at least a second sidewall and a second connecting element, wherein the second connecting element is disposed on the second sidewall and at least partially overlapped with the first connecting element. The second connecting element includes a first end and a second end in a first direction, wherein the first end and the second end are bent toward the first connecting element, respectively, for grasping the first connecting element. As a result, the accuracy error and the precision error are avoided, the stresses are internally counterbalanced, and the deformation of the fan frame is avoided.

A composite blade includes a composite airfoil section having airfoil pressure and suction sides extending chordwise between airfoil leading and trailing edges, a dovetail root attached to airfoil section and a blade shank therebetween, and a metallic leading edge shield covering an axially extending portion of airfoil section including at least a portion of airfoil leading edge and a radially and chordwise extending portion of a leading edge portion of the blade shank. Leading edge portion may be cut back from airfoil leading edge and a shank leading edge aft or downstream of airfoil leading edge. A nose may extend along a shield leading edge of the metallic leading edge shield with pressure and suction side legs extending aftwardly from nose along airfoil pressure and suction sides. Light weight insert may be located between nose and airfoil leading edges.