An apparatus is provided for a turbine engine. This turbine engine apparatus includes a turbine engine component that includes a sidewall and a cooling aperture. The cooling aperture includes an inlet, an outlet, a meter section, a diffuser section and a transition section between and fluidly coupled with the meter section and the diffuser section. The cooling aperture extends through the sidewall from the inlet to the outlet. The meter section is at the inlet. The diffuser section is at the outlet. The transition section is configured to accommodate lateral misalignment between the meter section and the diffuser section.

A vibration damping system for a turbine nozzle or blade includes a vibration damping element including a plurality of contacting members including a plurality of damper pins. Each damper pin includes a body. A wire mesh member surrounds the body of at least one of the plurality of damper pins. The wire mesh member has a first outer dimension sized for frictionally engaging within a body opening in the turbine nozzle or blade to damp vibration. Spacer members devoid of a wire mesh member may also be used. The damper pins can have different sizes to accommodate contiguous body openings of different sizes in the nozzle or blade. The body opening can be angled relative to a radial extent of the nozzle or blade.

The film cooling structure includes a wall part and a cooling hole inclined such that an outlet is positioned rearward of an inlet. The cooling hole includes a straight-tube part and a diffuser part. The diffuser part includes a flat surface, a curved surface curved rearward and forming, together with the flat surface, a semicircular or semi-elliptical channel cross section larger than that of the straight-tube part, a first section and a second section extending from the first section toward the outlet. In the first section, an area of the channel cross section increases as it approaches the outlet. In the second section, the area of the channel cross section increases as it approaches the outlet at an increase rate smaller than that of the first section or is constant. The diffuser part has a width equal to or twice greater than the depth of the diffuser part.

Turbomachine components and compressors are provided. The turbomachine component includes a platform and a mounting portion that extends from the platform. The mounting portion includes a dovetail received by a slot defined in the turbomachine. The slot includes a floor and a ceiling. The dovetail includes an inner surface and an outer surface. A hole is defined in the dovetail from an inlet at the inner surface to an end wall. The hole has a cylindrical portion and a tapered portion. A mechanical spring is disposed within the hole and in contact with the floor and the end wall such that the outer surface of the dovetail is forced into contact with the ceiling of the slot.

The invention concerns a flow straightener unit (1) for a fan module of a turbomachine, the straightener unit (1) comprising a plurality of blades (2) distributed about an axis of rotation, each blade (2) is made of a composite material and comprises an aerofoil (21) and a root (22) intended to be assembled on a hub (4) of the turbomachine. The unit (1) comprises a centring and attachment plate (3) of the blade (2) on the turbomachine intended to be attached to the hub (4) at a determined azimuthal position and to the root (22) of the blade (2), the plate (3) is designed to be screwed to the hub (4) by screws (51a) that are longitudinal with respect to the axis of rotation of the unit (1) and screwed to the root (22) of the blade (2) by screws (52) that are radial with respect to the axis of rotation of the unit (1).

A turbine shaft used for a turbocharger including a turbine and a compressor includes a turbine impeller, and a rotor shaft joined on one end side to the turbine impeller. The rotor shaft includes a fitting region configured to fit with a compressor impeller of the compressor by inserting the other end side of the rotor shaft into a through hole formed in the compressor impeller, a fastening region formed between the fitting region and the other end side of the rotor shaft, and configured to allow fastening by a fastening part, and a tapered part having a maximum outer diameter at a position closest to the turbine impeller in the fitting region and formed such that an outer diameter of the rotor shaft decreases from the position closest to the turbine impeller toward a tip side of the compressor impeller.

The invention relates to an assembly for a turbine engine, comprising a radially inner shaft (3) and a radially outer shaft (7), said shafts (7, 8) being coaxial and extending along an axis (X), means (11, 15) for coupling said inner and outer shafts (7, 8) in rotation, means (22) for axially holding the inner shaft (8) relative to the outer shaft (7), means for centring the inner shaft (8) relative to the outer shaft (7), characterised in that the centring means comprise a shim (14) for radial centring and for axial positioning, this shim being frustoconical and interposed between a frustoconical centring surface (13) of the inner shaft (8) and a corresponding frustoconical centring surface (10) of the outer shaft (7).

A method of forming a ceramic matrix composite component having an internal cooling circuit includes wrapping at least a first sheet around a first mandrel, wrapping at least a second sheet around a second mandrel, creating a first plurality of holes in the first sheet corresponding to a plurality of openings in the first mandrel, creating a second plurality of holes in the second sheet corresponding to a plurality of openings in the second mandrel, aligning the first mandrel and the second mandrel such that the first plurality of holes face and are aligned with the second plurality of holes, wrapping at least a third sheet around both the first mandrel and second mandrel to form a preform, the preform comprising each of the first sheet, the second sheet, and the third sheet, and densifying the preform. The first sheet, second sheet, and third sheet are formed from a ceramic fiber material.

A blower has a blower housing of clamshell construction, including two housing members having a scroll back wall molded with radial draft, an impeller and a motor within the housing, and a static tap connected to the housing. The impeller has a backplate with a backplate back surface region of substantially the same radially converging shape as that of a front surface region of the scroll back wall formed by the radial draft, providing a substantially uniform axial gap between the backplate back surface region and the scroll back wall. The impeller has a ring connected by a skirt to the back plate to define a stepped area behind the ring. The impeller includes impeller blades extending forwardly from the impeller backplate and the ring and back fins extending rearwardly from the ring. The blower has a scroll width of about twice an impeller exhaust width.

A vibration damping element for a vibration damping system for a turbine nozzle or blade includes an elongated body and a wire mesh member that surrounds the elongated body. The wire mesh member has a first outer dimension in an inoperative state and a second, larger outer dimension in an operative state. In the operative state, the wire mesh member frictionally engages with an inner surface of a body opening in the turbine nozzle or blade to damp vibration. In the inoperative state, the wire mesh member slides freely in the body opening in the turbine nozzle or blade. A retention system includes a retention member on the elongated body that fixes the wire mesh member relative to a length of the elongated body in the operative state in the body opening of the turbine nozzle or blade.