Abstract: In one exemplary embodiment, a flow path component assembly includes a support structure that is a unitary component having an axial portion and a radial portion and an outer portion arranged between the support structure and a flow path. The outer portion defines a gap between the outer portion and the support structure axial portion. A flange extends into the gap.

Abstract: A rotor for a contrarotating turbine comprising a drum and a blading mounted inside, the drum comprising a hook delimiting a housing having an outer wall and an inner wall, the blading comprising a blade and an outer platform provided with spoiler placed inside the housing, wherein the rotor comprises a foil comprising an elastic inner wing and an outer wing, the outer wing being arranged radially between the spoiler and the outer wall, the inner wing having a first support with the inner wall and a second support with the spoiler, the inner wing being arranged in the housing so as to exert a force on the spoiler so as to press the spoiler against the outer wall via the outer wing.

Abstract: A vane guide assembly for a gas turbine engine, the vane guide assembly including: an airfoil having an end bonded to an opening of a platform by an adhesive; and a pull tab partially located in the adhesive and having a portion extending from a bondline formed by the adhesive.

Abstract: An airfoil assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, an airfoil that has an airfoil section extending from a root section. The airfoil section extends between a leading edge and a trailing edge in a chordwise direction and extends between a tip portion and the root section in a radial direction, and the airfoil section defining a pressure side and a suction side separated in a circumferential direction. A platform includes a first and second platform portions attached to the root section. Each of the first and second platform portions includes a shoe section and a platform section extending in the circumferential direction from the shoe section to establish a gas path surface, and the shoe sections of the first and second platforms are circumferentially arranged on opposed sides of the root section to capture the root section in a root cavity established between the shoe sections. A method of assembly is also disclosed.

Abstract: A vane arm connection system for a gas turbine engine, includes a vane stem having a flatted head; a vane arm having a claw engaging the flatted head; and a load spreader having a spreader body defining structure engaging the flatted head, and at least one extension extending laterally from the spreader body.

Abstract: Assembly for axial turbomachine, in particular for an aircraft turbojet, the assembly comprising: an annular casing with an internal surface (40); an annular row of stator baffles (26) with at least one stator baffle (26) comprising an airfoil (50) which extends radially from a fixing platform (34), the fixing platform (34) being fixed to the casing and having a polygonal outline; characterised in that it further comprises a gasket (80) comprising a frame, the outline of which conforms to the polygonal outline of the fixing platform (34), the frame being in radial contact with the fixing platform (34) and the casing in order to ensure a seal.

Abstract: A ring segment, a turbine, and a gas turbine having improved cooling performance are provided. The ring segment may include a shielding wall mounted to a turbine casing which accommodates a turbine blade and configured to face an inner circumferential surface of the turbine casing, a first hook part and a second hook part configured to protrude from the shielding wall toward the turbine casing to be coupled to the turbine casing, a main cavity formed between the first hook part and the second hook part, a plurality of first cooling passages configured to connect the main cavity and first side surfaces facing each other of the shielding wall, a plurality of second cooling passages configured to extend in a direction crossing the first cooling passage and connect the main cavity and second side surfaces facing each other of the shielding wall, and a chamber configured to be connected to the first cooling passages.

Abstract: A vane includes a ceramic airfoil section that has an airfoil wall defining a leading edge, a trailing edge, a pressure side, and a suction side. The ceramic airfoil section has an internal cavity. A support spar extends through the internal cavity for supporting the ceramic airfoil section. The support spar is spaced from the airfoil wall such that there is a gap there between. The support spar has an internal through-passage that is fluidly isolated from the gap in the ceramic airfoil section. A baffle is disposed in the gap and is spaced apart from the airfoil wall and the support spar so as to divide the gap into a plenum space between the support spar and the baffle and an impingement space between the baffle and the airfoil wall. The baffle has impingement holes directed toward the airfoil wall that connect the plenum space and the impingement space.

Abstract: A distributor sector of a turbine of a turbomachine, including an outer platform including a downstream cylindrical hook adapted to engage with the turbomachine casing, the hook including a part in which is formed a U-shaped anti-rotation notch including a bottom and two lateral walls extending from the bottom, the notch being at least partially covered by a wear insert inserted in the notch, the insert being removeable.

Abstract: A gas turbine engine includes a shroud ring, a vane ring, and a secondary flow assembly. The shroud ring extends around an associated turbine wheel and includes a carrier segment and a blade track segment comprising ceramic matrix composite materials. The blade track segment and the carrier segment defining a shroud cavity radially therebetween. The vane ring includes a heat shield comprising ceramic matrix composite materials that forms an outer platform, an inner platform, and an airfoil defining a heat shield cavity radially through the heat shield. The secondary flow assembly includes a recirculating flow circuit having a discharge tube and a vane pressurizing tube; and the secondary flow assembly is configured to cool the blade track segment. The flow circuit is further configured to pressurize the heat shield cavity thereby providing a seal against the gases from the primary gas path entering the heat shield cavity.

Abstract: Provided is an offshore structure, especially offshore wind turbine, including a platform that is connected to the seabed, especially via a foundation that carries the platform, and an appliance, wherein it comprises guiding means for guiding at least one tube or cable along a guidance path from a respective entry point at which the tube or cable enters the platform to a respective connection point at which the tube or cable is connected or connectable to the appliance.

Abstract: Wind turbines including a hub rotatably mounted on a frame are disclosed, wherein the hub includes a bearing arranged around the frame, a main hub body extending in an axial direction from a front end to a rear end, and including a central opening for fitting the main hub body around the bearing. A bearing adapter is attached to the bearing, and the bearing adapter is in contact with and fixed to an axially facing surface of the main hub body. Also methods for mounting are disclosed.

Abstract: An assembly for a multistage turbine of a turbomachine has a static sealing device and a nozzle with a radially outer end and an outer casing surrounding the nozzle. The static sealing device is arranged radially between a radially outer end of the nozzle and the outer casing. The static sealing device includes an annular seal borne by the nozzle and an annular structure that defines a plurality of radial annular walls. The walls are axially spaced apart from one another, and at least one first wall is in annular contact radially inwardly with the annular seal. A longitudinal dimension of the annular contact is less than a longitudinal dimension of the seal.

Abstract: Turbine nozzle for a turbomachine extending about an axis, the nozzle including a plurality of sectors each having at least one vane which extends radially between an internal platform and an external platform, the nozzle including at least two sealing strips each including a main portion configured to ensure the sealing between the nozzle and an element of the turbomachine which is adjacent to the nozzle, and a first portion folded relative to the main portion, the first folded portion being in contact with an outer face of at least one platform, each strip being held to the at least one platform by a clamping device configured to clamp the first folded portion between the outer face of the platform and the clamping device.

Abstract: A variable vane actuation system for a gas turbine engine includes a stem section, along an axis, the stem section includes a groove; a vane arm comprising a claw section received at least partially into the groove; a clip mounted to the claw section; and a fastener fastened to the stem section along the axis to retain the clip and the vane arm to the stem section.

Abstract: A gas turbine engine includes one of a turbine section and a compressor section having multiple stages. At least one of the stages defines an outer diameter comprised of a plurality of circumferentially arranged blade outer air seals. Each blade outer air seal is spaced from each adjacent blade outer air seal in the plurality of circumferentially arranged blade outer air seals via a mateface gap. The mateface gap is oblique to a radius of the gas turbine engine, such that air entering the mateface gap is directed to an inner diameter surface of at least one of the blade outer air seals in the plurality of blade outer air seals.

Abstract: A fan wheel for a fan is equipped with at least two fan blades with a wavy design. A fan has at least one such fan wheel. A system has at least one fan with such a fan wheel.

Abstract: A gas turbine engine support system includes a vane arc segment, a vane support arc segment piece configured to engage the vane arc segment, and a seal disposed radially between the vane arc segment and the vane support arc segment piece. The seal includes first and second seal sections. The first seal section has a floor wall and first and second side walls that project from the floor wall. The first and second side walls converge to define a disjointed corner. The second seal section nests with the first seal section and seals the disjointed corner.

Abstract: A seal assembly for a gas turbine engine according to an example of the present disclosure includes a seal that has a main body extending circumferentially between opposed mate faces. The main body has a sealing portion and an engagement portion extending outwardly from sealing portion along at least one of the mate faces. The main body has a core that has one or more core plies having a first fiber construction and arranged to establish an internal cavity. An overwrap has one or more overwrap plies having a second fiber construction and arranged to follow a perimeter of the one or more core plies to establish the engagement portion and the sealing portion, and the second fiber construction differs from the first fiber construction. The first fiber construction establishes a first target fiber volume fraction, the second fiber construction establishes a second target fiber volume fraction. A method of fabricating a seal for a gas turbine engine is also disclosed.

Abstract: A seal assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a seal that has a main body extending circumferentially between opposed mate faces. The main body has a sealing portion and an engagement portion extending outwardly from sealing portion along at least one of the mate faces. The main body includes one or more braided core plies having a first fiber construction and arranged to establish an internal cavity. An overwrap having one or more braided overwrap plies follows a perimeter of the one or more braided core plies to establish the engagement portion and the sealing portion. The one or more braided overwrap plies have a second fiber construction differing from the first fiber construction. A method of fabricating a seal for a gas turbine engine is also disclosed.