The invention concerns a transition duct for a multi-stage compressor of a gas turbine engine. Regions of the inner surface of the duct are provided with a predetermined and dissimilar surface roughness to optimise gas flow efficiency within the duct.

A combustion engine component is disclosed. The combustion engine component comprises a body that includes a first surface in operative thermal communication with a hot combustion gas, and a second surface in operative fluid communication with a cooling fluid. Also, as disclosed in greater detail below, the second surface includes a first surface contour feature configured to increase a contact angle of a liquid on the second surface.

An object is to provide a turbine housing with a simple structure whereby it is possible to reduce flow resistance of exhaust gas and improve efficiency of a turbocharger. A turbine housing made by casting has an opening part formed on a hub side of a scroll part, the opening part having a radius R2 which satisfies a relationship R1<R2, provided that R1 is a radial directional distance from an axis of a turbine wheel to a tip of a shroud part and R2 is a radial directional distance from the axis to an inner peripheral edge of a hub-side wall surface of the scroll part. A roughness of a flow-path surface in a region A is smaller than in a region B, provided that the region A is a predetermined range from the tip of the shroud part and the region B is a predetermined range adjacent to the region A, among flow-path surfaces of the shroud part and the scroll part facing a scroll flow path on an outer side, in a radial direction, of the tip of the shroud part.

A method of depositing abradable coating on an engine component is provided wherein the engine component is formed of ceramic matrix composite and one or more layers, including at least one environmental barrier coating, may be disposed on the outer layer of the CMC. An outermost layer of the structure may further comprise a porous abradable layer that is disposed on the environmental barrier coating and provides a breakable structure which inhibits blade damage. The abradable layer may be gel-cast on the component and sintered or may be direct written by extrusion process and subsequently sintered.

An impeller manufacturing method includes: integrally forming an impeller by an additive manufacturing method using a metal powder, the impeller including a disk which has a disk shape about an axis, a plurality of blades which are formed on a surface facing a first side in an axial direction of the disk with gaps therebetween in a circumferential direction about the axis, and a cover which covers the plurality of blades from the first side in the axial direction; processing the integrally formed impeller by a hot isostatic pressing; and causing a polishing fluid containing abrasive grains to flow through a flow path formed between the disk, the cover, and the blades in the impeller after the processing with the hot isostatic pressing and while pressurizing the polishing fluid to perform fluid polishing.

The present invention relates to a preform and a method for producing a TiAl-based turbine wheel, and particularly relates to a preform for use in producing a TiAl-based turbine wheel having a relatively thin tip thickness of a turbine blade and having excellent mechanical properties and a method for producing a TiAl-based turbine wheel using such a preform.

The invention relates to a clamping system (1) comprising a clamping jaw (7) mounted on the shaft of a pneumatic or hydraulic cylinder (4), wherein said cylinder has a structure which drives the clamping jaw towards its clamping position when the pneumatic or hydraulic energy supply of the cylinder is interrupted, the pneumatic or hydraulic energy supply of the cylinder opposing the clamping, and where means (8) are provided for locking the cylinder when the clamping jaw is in a non-clamped position.

A method of fabricating a reinforcing edge (10) of a turbine engine blade (70) in which there is provided a blank (10) of the reinforcing edge and an indentation is imprinted in said blank so as to form a rough surface (S). A reinforcing edge (10) obtained by such a method.

An inter-blade vibration damper for a gas turbine engine has an elongate damper body. The damper body is formed as a truncated cone and has a longitudinal axis. The elongate damper body is formed as a truncated cone. A conic surface of the damper body contacts a portion of a first blade and a portion of an adjoining second blade.

Disclosed is a rotating component for a turbine engine including a first rotating component having a first snap surface and a second rotating component having a second snap surface wherein the first snap surface is configured to interlock with the second snap surface, and further wherein at least one of the first snap surface and the second snap surface have a friction enhancing material.