A coupling has: a first coupler rotatable about an axis and defining first connections distributed about the axis; a second coupler defining second connections distributed about the axis, the second connections offset from the first connections; and segments distributed about the axis and extending radially from the first connections to the second connections, a segment of the segments having a first end engaging a first connection of the first connections and a second end engaging a second connection of the second connections, the first end circumferentially offset from the second end, a face of the segment abutting against a face of the first coupler when the segment is inserted into the first connection in a first orientation such that a penetration depth of the segment into the first connection in the first orientation is less than the penetration depth in a second orientation opposite the first orientation.

A multipoint injection system includes a manifold with a plurality of flow passages defined through the manifold in the circumferential direction. The flow passages are spaced apart from one another in an axial direction. A plurality of feed arms extends radially inward from the manifold. Feed arm portions of the flow passages extend through each of the feed arms to respective outlets. The feed arm portions of the flow passages are within the axial width of the manifold. A plurality of injection nozzles are included, each in fluid communication with a respective one of the outlets. Each injection nozzle includes an air passage therethrough with an air inlet. The feed arms each follow a path that is circumferentially offset from the air inlets so each of the feed arms is clear from a flow path directly upstream in the axial direction of each of the air inlets.

A rotary machine assembly for a turbomachine, such as a rotor, having a rotor wheel where a plurality of circumferentially spaced female dovetail slots are obtained. The rotary machine assembly also comprises a plurality of blades. Between each blade and the adjacent one there is an interface angle. Each blade comprises a male dovetail, configured to fit with a corresponding female dovetail slot of the rotor wheel along an insertion direction. The female dovetail slots are shaped so that the insertion direction of each male dovetail is convergent with the rotation axis of the rotor wheel, so as to form with it an insertion angle, so as to insert gradually all the male dovetails into the female dovetail slots and packing them also gradually. A method for assembling a rotary machine assembly, which does not require any specific tool, is also disclosed.

The present invention provides an airfoil 110 with the squealer tip cooling system 50 for a turbine blade 100 at the blade tip 113, wherein the squealer tip cooling system 50 comprises a cooling passage 170 arranged within a squealer tip 117, wherein the cooling passage 170 at least partly extends toward a terminal end 74 of the squealer tip 117, and a pocket 172 at a lateral surface 75, 76 of the squealer tip 117, open externally and extending inwardly at least partly across the cooling passage 170. The pocket 172 intersects the cooling passage 170 and the pocket 172 comprises an impingement surface 70 facing the cooling passage 170, on which a cooling medium expelled through the cooling passage 170 impinges before being discharged externally through the pocket 172.

A seal segment comprises: a seal body having a plurality of thin-plate seal pieces that extend while being inclined forward in a rotational direction of a rotating shaft as the pieces draw farther inward in a radial direction of the rotating shaft, and that are layered in a circumferential direction of the rotating shaft; a pair of side plates extending in the circumferential direction so as to cover the seal body from both sides with respect to an axial direction of the rotating shaft; and a housing having a housing main body that accommodates the seal body while allowing the seal body to protrude inward in the radial direction, and an extending part that is provided to an end portion of the housing main body in the circumferential direction, and that extends inward in the radial direction along an end surface of the seal body in the circumferential direction.

A roller element device, in particular for a gas turbine engine, comprises an outer ring with an inner raceway, an inner ring with an outer raceway, and roller elements which are arranged between the raceways so as to roll thereon, wherein the outer ring and the inner ring are each connected via a connecting portion to a respective fixing portion for fixing to one of two components which are rotatable relative to each other about a rotation axis, and the connecting portions are formed such that the two raceways can be jointly tilted at least in portions relative to the rotation axis.

Methods for producing an annular casing for an aircraft turbine engine are provided. The annular casing includes an annular body made from a composite material based on a first resin, and a fire-resistant outer layer which covers an external annular surface of the body and which is made from a composite material based on a self-extinguishing second resin. The method includes preparing a strip of a glass fabric preimpregnated with said second resin, this strip including woven fibres oriented in directions that are perpendicular to one another and inclined by an angle of approximately 45° with respect to the axis of elongation of the strip, and applying the strip to the external surface of the body so as to cover the entirety of this surface in a single pass of the strip around the body.

In order to alleviate a mismatch problem of thermal deformation, in all directions, of a connecting and installing structure between a CMC turbine outer annular component and a metal intermediate casing, a connector and an anti thermal mismatch connecting device are provided. The rod part of the connector comprises a subtractive hollow section and a cylindrical section. The subtractive hollow section is composed of a central shaft, a plurality of supporting rib plates extending outwards from a peripheral surface of the central shaft and inclined radially relative to the central shaft, and a plurality of outer annular plates arranged around the central shaft, with a circumferential gap between adjacent outer annular plates. The supporting rib plate is connected with the central shaft and the outer annular plate, and the central shaft is connected with the cylindrical section. The anti thermal mismatch connecting device the connector.

A turbocharger includes a first housing configured to house a turbine impeller, a second housing configured to rotatably support a rotating shaft to which the turbine impeller is fixed, and a variable capacity mechanism configured to surround the turbine impeller and to guide a fluid to the turbine impeller. The variable capacity mechanism has a nozzle ring that faces the second housing. A first pin and a second pin extend between the second housing and the nozzle ring and are attached to one of the second housing and the nozzle ring. The other of the second housing and the nozzle ring is provided with a first guide in which an end portion of the first pin is disposed and a second guide in which an end portion of the second pin is disposed.

A center plug includes an inner skin, the inner skin extending along an axial centerline; an outer skin positioned radially outside the inner skin; a forward bulkhead connected to and extending radially outward from the inner skin; an aft bulkhead connected to and extending radially outward from the inner skin; and an acoustic panel, the acoustic panel including a first sheet having a first plurality of perforated walls and a first plurality of non-perforated walls, a second sheet having a second plurality of perforated walls and a second plurality of non-perforated walls, the first sheet being sandwiched together with the second sheet to form an N-shaped structure having a combined plurality of perforated walls and a combined plurality of non-perforated walls.