An airfoil vane includes an outer ceramic wall that defines an airfoil section and a cavity that extends through the airfoil section. A jumper tube is disposed in the cavity for transferring cooling air. The jumper tube includes a wall, a through-passage circumscribed by the wall, and a thermal barrier coating disposed on the wall.

A seal system for a gas turbine engine includes a seal runner manufactured of a Molybdenum alloy material that provides a first coefficient of thermal expansion and a seal ring manufactured of a graphitic material that provides a second coefficient of thermal expansion greater than the first coefficient of thermal expansion.

The invention relates to a guide vane assembly for a turbomachine, comprising a guide vane, which has a guide vane airfoil; and a guide vane holder. The guide vane is mounted in the guide vane holder such that the guide vane can be moved about an axis of rotation. For this purpose, the guide vane has at least one axle element, which is inserted into the guide vane holder in such a way that an outer lateral surface of the axle element faces an inner lateral surface of the guide vane holder. A protective coating is applied to at least parts of the guide vane airfoil. A protective coating is applied to at least one of the lateral surfaces. The invention also relates to a compressor module, a turbomachine, and a method for producing a guide vane assembly.

A split ring seal has: a first circumferential end and a second circumferential end; an inner diameter surface and an outer diameter surface; a first axial end face and a second axial end face. A circumferentially distributed first plurality of open channels are along the first axial end face. A circumferentially distributed second plurality of open channels are along the second axial end face.

There is disclosed a bearing housing for a turbocharger. The bearing housing comprises a body and a mounting flange. The body is configured to receive one or more bearings. The one or more bearings are configured to support rotation of a shaft about an axis. The mounting flange extends around the body. The mounting flange comprises a plurality of bores, a first face and a plurality of cavities. The plurality of bores configured to receive a fastener therethrough. The first face is configured to engage a corresponding mounting flange of a turbine housing. The plurality of cavities are in communication with the plurality of bores. The plurality of cavities are axially recessed relative to the first face.

The present disclosure relates to a novel iron-based austenitic alloy for a turbocharger housing and to methods of its preparation.

There is provided a cobalt-based alloy product comprising: Co, C, N, B, Cr, Fe, Ni, W, Mo, Al, Si, and/or Mn with predetermined contents, and 0.5-4 mass % of an M component. The M component is a transition metal other than W and Mo and having an atomic radius of more than 130 pm. The product is a polycrystalline body of matrix phase crystal grains in which segregation cells are formed. There are at least two kinds of regions of the segregation cells wherein: a first region has an average size of 0.13-1.3 μm; a second region has an average size of 0.25-2 μm; and the average size of the second region is 1.3 times or more larger than that of the first region.

A rotor assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a rotor that has a hub carrying one or more rotatable blades. The rotor is mechanically attached to a shaft, and an annular seal is carried by the shaft. The annular seal includes a substrate, a first layer disposed on the substrate, and a second layer disposed on the first layer and arranged to establish a sealing relationship with the rotor. The second layer includes a solid lubricant that has molybdenum trioxide (MoO3). A method of sealing for a gas turbine engine is also disclosed.

A gas dynamic bearing includes a shaft extending along a central axis extending vertically, and a sleeve with a hole opening at least at one end of the sleeve in an axial direction, at least a portion of the shaft housed inside the hole. The sleeve includes dynamic pressure grooves in an inner peripheral surface of the hole. The shaft includes a core portion, and a protective portion that is disposed on an outer peripheral surface of the core portion and that includes at least a portion facing the inner peripheral surface of the hole in a radial direction. The protective portion includes a first protective portion and a second protective portion. The first protective portion is at least above or below the second protective portion in the axial direction, and includes at least a portion with a thickness in the radial direction more than a thickness of the second protective portion in the radial direction.

A method for forming a gas turbine engine component comprises the steps of forming a first portion from a high temperature alloy material, and forming a second portion from the high temperature alloy material, the first and second portions each defining an external surface and an internal surface. At least one heat transfer feature is formed directly on the internal surface of at least one of the first and second portions. The first and second portions are attached together to form a component. A component for a gas turbine engine is also disclosed.