Abstract: An airfoil that includes an airfoil body having a root and a tip, and convex and concave sides that extend between a leading edge and a trailing edge. The airfoil also includes at least a first cladding element that is attached to the airfoil body. The first cladding element includes a first portion and a second portion. The second portion is configured to separate from the first portion when the first cladding element encounters a force of at least a predetermined amount.

Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a bearing compartment, a seal runner, a seal configured to cooperate with the seal runner to seal the bearing compartment, and a catcher in contact with the seal runner to minimize deflection of the seal runner. A method is also disclosed.

Abstract: A rotor disk assembly for a gas turbine engine includes a rotor disk with a multiple of blade slots, the rotor disk defined about an axis; a sleeve received within each of the multiple of blade slots; and a ceramic matrix composite rotor blade received within each of the multiple of sleeves.

Abstract: A fiber composite component, comprising a basic element which comprises fibers embedded in a matrix material. A production method for a fiber composite component. A structural component, comprising a support element and the reinforcement element and also a production method for a structural component. The fiber composite component comprises a base element, comprising fibers embedded in a matrix material, and a reinforcement element, comprising fibers embedded in a matrix material wherein the base element and the reinforcement element are interconnected, a hole leads through the base element and the reinforcement element, wherein fibers of the base element that are adjacent to the hole are severed, and fibers of the reinforcement element that are adjacent to the hole are continuous.

Abstract: A method for managing icing conditions on a rotary aircraft via one or more ice protection controllers. The method includes steps for receiving an icing condition signal from an icing rate sensor at an ice protection controller, determining, in response to the icing condition signal, a de-icing signal based at least in part a liquid water content (LWC). The method further includes steps for transmitting, via a digital communication bus disposed in at least part of a slip ring assembly, the de-icing signal to a upper distributor to cause the upper distributor to transmit power to one or more heating elements for a respective rotor blade.

Abstract: A nozzle assembly for a gas turbine engine and methods for assembling a nozzle assembly are provided. In one example aspect, the nozzle assembly includes an outer wall and an inner wall radially spaced from the outer wall. The outer wall defines a plurality of mounting openings spaced circumferentially from one another. The inner wall defines a plurality of mounting openings spaced circumferentially from one another. The mounting openings defined by the inner wall are positioned circumferentially between adjacent mounting openings defined by the outer wall. The nozzle assembly includes vanes that are inserted through the mounting openings of the outer wall in a radially inward direction and vanes that are inserted through the mounting openings of the inner wall in a radially outward direction in an alternating manner.

Abstract: A component of a rotor system is provided and includes a disk and a reinforcing ring. The disk includes an airfoil element, a web extending radially inwardly from the airfoil element and an arm element extending axially from the web. The reinforcing ring is formed of fiber reinforced materials and is disposed to fit about the arm element.

Abstract: Embodiments of the present disclosure are directed to an interface for a fan that includes a first bracket coupled to the fan, where the fan is configured to direct a flow of air through an opening of a duct, and the opening comprises a central axis extending therethrough, a second bracket coupled to a frame surrounding the opening of the duct, where the first bracket and the second bracket are configured to surround the opening of the duct, the second bracket is configured to support the first bracket, and the second bracket is partially radially within the first bracket relative to the central axis of the opening, and a gasket disposed between the first bracket and the second bracket, where the first bracket, the second bracket, and the gasket are configured to sealingly engage with one another without mechanical securement.

Abstract: A rotary part for a pump and related systems and methods are provided. The rotary part can be rotated in a forward direction about a rotation axis X-X and may include shroud(s) and expelling vane(s). The expelling vane(s) may have a leading side facing in the forward direction characterised in that the leading side includes a forwardly inclined section which is inclined forwardly.

Abstract: A fan module containing a fan is used to cool a computing device or system. The fan module is mounted within a chassis, and contains a housing, a locking body, and lever. The housing of the fan module contains a housing, a locking body, and lever. The housing of the fan module defines a hollow interior that houses the fan. The locking body is coupled to the housing and is moveable between a locked position and an unlocked position. When in the locked position, the locking body extends through a locking aperture in the floor of the chassis. When in the unlocked position, the locking body rises above the locking aperture in the floor of the chassis. Moving the lever from the first position to the second position causes the locking body to move from the locked position to the unlocked position.

Abstract: A compressor with negative coefficient of thermal expansion case material comprising a rotor having blades with tips, the case including an inner case comprising a negative coefficient of thermal expansion material, and a tip clearance located between the tips and the inner case; wherein the tip clearance is maintained responsive to a flow of air over the negative coefficient of thermal expansion material.

Abstract: A variable vane actuation system for a gas turbine engine includes a stem section that forms a base and a contoured section that extends from the base along an axis. A vane arm comprising a claw section received onto the contoured section and a fastener fastened to the contoured section to load the claw section to the base.

Abstract: An airfoil for disposition and exposure to flow in a hot gas duct of a turbomachine is provided. The airfoil has a suction-side wall and a pressure-side wall with respect to its exposure to the flow in the gas duct, the side walls converging in an upstream end region toward a leading edge and converging in a downstream end region toward a trailing edge. The airfoil further has a cavity structure therein which is enclosed between an inner wall surface of the suction-side wall and an inner wall surface of the pressure-side wall when viewed in a cross-sectional plane axially parallel to a longitudinal axis of the turbomachine. When viewed in the cross-sectional plane, at least one of the inner wall surfaces, normalized to a mean camber line of the airfoil as a reference, extends with a change in curvature into at least one of the end regions in such a way that a clearance width of the cavity structure is increased at the at least one end region.

Abstract: A diffuser case support structure for a gas turbine engine includes a fairing disposed circumferentially about a longitudinal axis. The fairing defines a plurality of passages circumferentially spaced apart and forming at least a portion of a fluid path between a compressor and a combustor of the gas turbine engine. A diffuser frame includes a plurality of struts. Each of the plurality of struts is disposed between a pair of adjacent passages of the plurality of passages. The diffuser frame is configured to couple an inner diffuser case to an outer diffuser case. A sliding joint is formed between the fairing and the diffuser frame, the sliding joint comprising a fastener extending generally axially through an aperture disposed in the fairing.

Abstract: Disclosed is a tilting type rotor including: a body part in which a longitudinal direction is formed at both sides, a receiving space is provided therein, and a sliding hole having a through-hole shape is provided in the longitudinal direction at inner lower portions of both end portions; a servo part formed at the center of the body part and having a rotational shaft vertical to the longitudinal direction of the body part; a tilting part tilted in a manner in which the other end portion is rotated as one end portion is connected to both end portions of the body part; a rotor part provided to generate thrust and connected to the tilting part; and a link part connected to the servo part and connected to the tilting part.

Abstract: A turbine rotor blade row includes: a plurality of turbine rotor blades disposed along a circumferential direction of a hub. An inter-blade flow channel has a first cross-sectional shape perpendicular to a radial direction of the hub at a first position in the radial direction, and a second cross-sectional shape perpendicular to the radial direction of the hub at a second position farther from the hub than the first position in the radial direction. The first cross-sectional shape has a throat portion between an inlet and an outlet of the inter-blade flow channel in an axial direction of the hub.

Abstract: A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream most end, and more upstream locations. A turbine section has a high pressure turbine. A first tap taps air from at least one of the more upstream locations in the main compressor section, passes the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger. A second tap taps air from a location closer to the downstream most end than the location(s) of the first tap. The first and second tap mix together and are delivered into the high pressure turbine. An intercooling system for a gas turbine engine is also disclosed.

Abstract: Various embodiments include gas turbine seals and methods of forming such seals. In some cases, a turbine includes: a first arcuate component adjacent to a second arcuate component, each arcuate component including a slot including one or more slot segments located in an end face and a seal assembly disposed in the slot. The seal assembly including a plurality of seal segments forming at least one T-junction where a first seal segment intersects a second seal segment and at least one shim seal. The plurality of seal segments define at least one chute gap. The at least one shim seal disposed in a slot proximate the at least one T-junction of the plurality of seal segments. The at least one shim seal positioned on a sidewall of the second seal segment and extending a partial length of the sidewall. The at least one shim seal seals the at least one chute gap to prevent a flow therethrough of a gas turbine hot gas path flow.

Abstract: A component for a gas turbine engine comprises an airfoil having an outer surface. One or more cooling passages can be disposed within the airfoil, having a cooling passage extending along a trailing edge. A plurality of cooling channels can extend from the cooling passage through the trailing edge. At least one flow element and at least one film hole can be disposed in the cooling channel or the trailing edge passage adjacent the cooling channel. The flow element and the film hole can be in a predetermined relationship with one another providing improved flow to the film hole.

Abstract: A cooling assembly comprises a pin disposed inside a first chamber of an airfoil. The first chamber is disposed inside the tip end comprising a tip floor. The pin extends from a first end to a second end along a pin axis. The first end is coupled with a first surface of the first chamber and the second end is coupled with an inner floor surface of the tip floor such that the pin increases a structural load support level of the tip floor. A cooling conduit is placed inside the pin through which coolant flows. The cooling conduit is elongated along and extends around a conduit axis and is fluidly coupled with conduit channels disposed between the first and second ends of the pin. The conduit channels direct coolant out of the cooling conduit or direct coolant into the cooling conduit.