Abstract: An assembly adapted for use in a gas turbine engine. The assembly includes a support component comprising metallic materials, a supported component comprising ceramic matrix composite materials, and an attachment pin configured to couple the supported component to the support component. The attachment pin includes compliant features to distributes loads applied to the supported component.

Abstract: The present disclosure provides a two-stage blade adjusting device for a counter-rotating axial flow fan. A blade adjusting operation shaft is adjusted to drive a pair of bevel gears to transfer power to a threaded pair coaxial with a transmission shaft, the threaded pair transforms rotary motion of the bevel gears into linear motion to push thrust discs in hubs, the blade installation angle of a first impeller is thus adjusted, and a spacer bush transfers the power to adjust the blade installation angle of a second impeller, so that synchronous adjustment of two-stage blade installation angles is realized. The device is simple and compact in structure and low in manufacturing and maintenance cost, and can be widely applied to large, medium and small counter-rotating axial flow fans.

Abstract: A vane body of a guide vane includes a leading edge, and a trailing edge which is located closer to a runner than the leading edge, when located radially outside the runner. A projection extending in a direction from the trailing edge toward the leading edge is provided on an internal-diameter side blade face of the vane body, at least in any one of one side area of the internal-diameter side blade face and the other side area thereof in an axial direction of a guide vane rotation shaft, the internal-diameter side blade face being disposed on a side of the runner. The projection has a projection rear end of an arcuate shape, which projection rear end is formed to extend along a rotation trajectory which is drawn by the trailing edge when the vane body is rotated about the guide vane rotation shaft.

Abstract: A sealing arrangement for sealing a pressure chamber in a high pressure pump which is bound by a first and a second bounding element, includes a separate sealing element which has a first sealing surface for co-operating with the first bounding element, as well as having a second sealing surface for cooperating with the second bounding element. The two sealing surfaces are inclined with respect to one another and each have a groove for receiving a sealing ring. The sealing element is arranged in such a way that it can be displaced totally along one of the bounding elements on the application of pressure.

Abstract: A stator vane is comprised of: an airfoil section elongated in a radial direction relative to an axis; an outer band section continuous to an outer end of the airfoil section and bent in a circumferential direction relative to the axis; a first hook section continuous to a leading end in the axial direction of the outer band section and bent outward in the radial direction; a second hook section continuous to a trailing end in the axial direction of the outer band section and bent outward in the radial direction; an inner band section continuous to an inner end of the airfoil section and bent in the circumferential direction; a flange section continuous to an end in the axial direction of the inner band section and bent inward in the radial direction; and a reinforcement fiber fabric continuous throughout these sections and unitized with a ceramic.

Abstract: Embodiments of a stage for a turbomachine have been provided herein. In some embodiments, a stage for a turbomachine may include a bearing having a housing, the bearing defining an interior cavity; an outer ring disposed radially outward from the housing; and a plurality of airfoils disposed between the housing of the bearing and the outer ring.

Abstract: A method of remanufacturing a turbine component is provided. This method includes removing a donor portion from a damaged component; removing a to-be-replaced portion from a serviceable component generally equivalent to the donor portion leaving a remainder; and welding the donor portion to the remainder. A BOAS for a gas turbine engine is also provided that includes a serviceable BOAS with a donor portion from a damaged BOAS welded thereto.

Abstract: In some embodiments, a rotorcraft includes an engine, a rotor hub assembly mechanically coupled to the engine and a plurality of rotor blade assemblies rotatably mounted to the rotor hub assembly. Each of the rotor blade assemblies includes a rotor blade having a leading edge and an erosion shield system extending spanwise along the leading edge of the rotor blade. The erosion shield system includes a plurality of erosion shield segments positioned adjacent to one another forming joints therebetween wherein, the joints deform responsive to strain experienced by the rotor blade, thereby isolating the erosion shield segments from at least a portion of the strain experienced by the rotor blade.

Abstract: An air duct for a wind power plant is configured to guide air along a circumference of a supporting structure, in particular a tower, of the wind power plant. The wind power plant also includes an air guide and provides methods of manufacturing the air guide for the wind power plant and retrofitting the wind power plant with the air guide.

Abstract: A turbine blade of a gas turbine engine is described which includes an airfoil extending away from the hub platform to a blade tip. The airfoil defines a leading edge, a trailing edge, and a span-wise length extending between the platform and the blade tip. A hot-corrosion-resistant coating is located on the leading edge of the airfoil within a radially inner portion thereof, the radially inner portion extending away from the hub platform a desired distance along the span-wise length.

Abstract: A manifold including a stepped louvre to control airflow along a fan blade. A fan blade for use in a high volume, low-speed fan, wherein the fan blade includes a body portion, a leading edge portion and a trailing portion. The leading edge portion of the fan blade includes a series of steps extending along the length of the leading edge. The fan distributes airflow from the manifold.

Abstract: A method and decoupler for disengaging an output shaft from an engine in a back drive event with a backdrive decoupler. The backdrive decoupler includes a threaded shaft and a retention mechanism selectively coupling the output shaft to the threaded shaft. In a backdrive event, the decoupler decouples the output shaft from a drive shaft.

Abstract: The stiffness of a rotor part is varied over its circumference to allow damper rings to effectively work in high speed applications. Circumferentially spaced-apart pockets may be defined in the rotor to create discontinuous strain to increase the force required to lock the damper ring in the groove above the centrifugal force of the ring when the rotor is rotating.

Abstract: A multistage compressor for a gas turbine engine is disclosed. The compressor includes a plurality of compressor stages, each stage including in axial flow series a row of rotor blades and a row of stator vanes; a hub to which a radially inner end of each rotor blade of the rows of rotor blades is connected; and a casing that circumscribes the rows of rotor blades and the rows of stator vanes. An aerofoil portion of each of the rotor blades and/or the stator vanes of one or more of the plurality of compressor stages is profiled in a spanwise direction such that the aerofoil portion has a trailing edge that is angled more towards an axial direction of the multistage compressor in regions of the aerofoil portion proximal to the casing and the hub than in a mid-region of the aerofoil portion.

Abstract: The present application relates to a de-icing splitter lip for a low-pressure compressor of a turbofan aircraft engine. The splitter lip surrounds the primary flow and includes an annular splitter wall with a circular leading edge, an outer shroud connected to the splitter wall, and a heating device in an electric ribbon that de-ices the splitter lip. The splitter lip further includes an elastic element made of elastomer, holding the heating device on the inside of the splitter wall. The elastic element is compressed, pre-loaded, in the splitter lip. Thus, the elastic element exerts a force F clamping the heating device against the splitter wall and the outer shroud in order to improve thermal contact. The present application also provides a method for assembling a splitter lip.

Abstract: A water pump has a pump housing (2) having therein a pump chamber (3); a drive shaft (7) rotatably supported in the pump housing (2); a pulley (5) having a flange wall (5a) fixed to one end portion of the drive shaft (7), the pulley (5) being formed integrally with the drive shaft (7) with synthetic resin material containing glass fiber material (25); and an impeller (8) secured to the other end portion of the drive shaft (7) so as to be able to rotate integrally with the drive shaft (7), the impeller (8) being accommodated in the pump chamber (3). Six penetration holes (23) are formed at the flange wall (5a), and the glass fiber material (25) existing around the penetration hole (23) is oriented at random. With this, decrease in strength of the pulley (5) can be suppressed.

Abstract: A method of manufacturing an aircraft blade is provided. The method includes attaching a fluid communicator to a plug tool connected to a blade plug, opening a passage in the blade plug using the plug tool, communicating fluid to or from a blade cavity through the passage using the fluid communicator, and sealing the passage in the blade plug using the plug tool.

Abstract: A gas turbine engine component includes a rotor blade having a squealer tip comprising a projecting lip, the rotor blade further having a raised rim running along both edges of each projecting kip of the squealer tip, and an abrasive coating formed of hard particles embedded in a retaining matrix covering a tip region of the rotor blade within an area bounded by the raised rim. The raised rim has a height of between 50% and 75% of a mean diameter of the hard particles.

Abstract: A damper ring is mounted in frictional engagement with a radially inwardly facing surface of a circumferential groove defined in a rotary part of a gas turbine engine. Energy dissipation is provided via sliding friction of the ring in the groove. Pressure relief dimples are provided around the outer diameter of the ring for locally reducing contact pressure at the outer diameter below a value at which the damper ring locks in the groove by friction forces when subject to centrifugal loads.

Abstract: A leaf seal for sealing off a shaft rotating around an axis, particularly in a gas turbine, is disclosed. The leaf seal includes a plurality of leaves arranged spaced apart from one another, where the leaves are produced integrally with a basic element supporting the leaves by a generative production process. A process for producing a leaf seal for sealing off a shaft rotating around an axis is also disclosed.