Abstract: The present invention relates to a blade pitch control apparatus for a small size wind power generator. More specifically, the present invention relates to a blade pitch control apparatus for a small size wind power generator configured to accomplish continuous generation by continuously maintaining the necessary rotating force of the blade by systematically operating the ball screw, spinner driver, and pitch angle controller when the rotation number of blades exceeds the reference rotation number by over wind speed, so that the blade pitch is automatically controlled.

Abstract: A method includes (a) depositing a layer of a powder material on a work stage, the layer having a thickness, (b) solidifying a portion of the layer based upon data that defines an insert with a body that is shaped to fit into a cavity in a gas turbine engine component, and (c) lowering the work stage by the thickness. Steps (a)-(c) can then be repeated until the insert is complete. The insert can then be removed from the work stage. An insert formed by the above process is also disclosed.

Abstract: A fan casing assembly comprising an annular casing member for circumferentially surrounding a fan, and an annular fan track liner comprising a plurality of circumferentially adjacent liner panels. The annular fan track liner is positioned radially inward of the annular casing member. A tilting arrangement is provided and configured to selectively circumferentially tilt one or more of the liner panels, such that, in the event of a fan blade being released from a fan, the tilting arrangement can initiate tilting of one or more liner panels so that the liner panels can trim one or more of the remaining fan blades.

Abstract: A rotary machine characterized by being equipped with: a rotary drive part; a drive shaft that is rotated about a horizontally extending axis by the rotary drive part; a large gear that is fixed to the drive shaft; a bearing part that rotatably supports the drive shaft, and to which a lubrication oil is supplied; multiple pinions that are driven by being engaged with the large gear; multiple compression parts that are arranged so as to correspond to the multiple pinions and are respectively rotated by the pinions; and a plate that is installed between the bearing part and the large gear and covers at least a portion of the bottom half of the large gear so as to separate the large gear and the bearing part from each other.

Abstract: An apparatus comprises a gas turbine engine having a compressor. The compressor airfoil member is disposed in the compressor and has a camber angle variation along a chord and a concave pressure side surface at a tip portion of the compressor airfoil member from a leading edge to an intermediate-chord location. This first camber shape results in a normalized camber angle that reaches at least 0.4 in the first 10% of normalized chord, and the normalized camber angle is defined as ? ? = ? i - ? ? i - ? e where ?i is inlet metal angle, ?e is exit metal angle, and ? is a camber angle at a given chord location.

Abstract: To provide a steam turbine stationary blade adapted to remove a liquid film effectively. A steam turbine stationary blade with a hollow region therein, the steam turbine stationary blade includes a plurality of slots and arranged in lines in a direction of a chord length, the plurality of slots communicate with a working fluid flow passageway and with the hollow region, and extends in a direction of a blade length, and at least one connecting portion disposed so that for each of the most downstream slot of the plurality of slots and, a surface directed toward the working fluid flow passageway is positioned closer to the hollow region than to a surface of the steam turbine stationary blade, and so that the connecting portion connects both sidewall surfaces of each of the most downstream slots, in the direction of the chord length.

Abstract: The invention provides a lightning protection system for a wind turbine blade (10), whose structure comprises two structural shells (11, 13) with two caps (19, 21) formed by carbon fiber laminates and two spars (15, 17). In addition to a first subsystem formed by one or more lightning receptors connected to one or two conductor cables the lightning protection system comprises a second subsystem formed by lateral lightning receptors (30, 31) arranged at the leading and trailing edges of the wind turbine blade (10) in at least two cross sections (22, 23) of it connected with the caps (19, 21) and connecting means between the two subsystems for equipotentializing the lightning protection system.

Abstract: A gas turbine engine includes a flow control mechanism operable to direct at least a portion of a fan airflow from a secondary flow path into a core flow path.

Abstract: Fan blade containment system includes circular tile layer of annular ceramic tiles attached to and extending radially inwardly from a shell, radially inner and outer annular surfaces of ceramic tiles bonded to a radially inner composite layer and the shell respectively with elastomeric inner and outer adhesive layers respectively. Elastomeric adhesive layers between circumferentially adjacent overlapped or scarfed edges along circumferential edges of the ceramic tiles overlap and mate along oppositely facing surfaces of adjacent ones of the ceramic tiles. Inner and outer adhesive layers and elastomeric adhesive layer may be a double-sided adhesive foam tape. Scarfed edges may be bevels or rabbets. Shell may be made of a metal or composite material. Fan blade containment system may be bonded to and extend inwardly from fan case circumscribing fan blades of a fan. Inner composite layer and composite outer shell may be co-cured with ceramic tiles therebetween.

Abstract: A turbocharger (300) having a rotatable shaft (312) passing through a bearing housing (303) with a turbine-end bearing support (580) with a support bar (600). A turbine-end bearing support (580) may include the support bar (600) with radial supports (610) and (620) connected to each opposite side (492) and (494) of cavity (496) of the bearing housing (303) wherein oil can flow in recesses (640) and (650) above the radial supports (610) and (620). Each radial support (610) and (620) of the support bar (600) is preferably integrated in the corresponding side (492) and (494). A turbine-end bearing support (580) may also include the support bar (600) with a rod portion (622) forming a bottom tie support bar (612) that supports the bottoms of both bearing supports (490) and (580), which are top-supported by the bearing housing (303). Each support bar (600) is preferably integral with the bearing support (580).

Abstract: The present application relates to a segmented inner shroud of a low-pressure compressor for an axial-flow turbine engine. The shroud includes an axial tubular wall, and a row of apertures formed in the axial wall. Each aperture has opposing edges situated to either side of a stator vane positioned in the aperture for the purpose of its attachment. The axial wall includes a radial flange which passes through the apertures in the circumferential direction of the shroud, so as to form a mechanical link between the opposing edges of the apertures. This mechanical seal permits the opposing edges to be joined together through each aperture, which improves the rigidity and the sealing. The shroud exhibits an E-shaped profile forming a sandwich structure with the annular sealing fins of the rotor, or sealing lips. The present application also relates to a method for the assembly of stator vanes abutting radially against the transverse radial flange.

Abstract: A gas turbine stage, in particular to an aircraft gas turbine. This gas turbine includes at least one casing having at least one bleed duct and at least one bore, and further includes at least one variable guide vane having a trunnion, a rotary plate, and a guide vane airfoil. The trunnion is disposed in the bore, and the guide vane airfoil is integrally formed with the rotary plate. The guide vane airfoil integrally formed with the rotary plate extends beyond this rotary plate in such a way that, viewed in the direction of flow of the gas path of the gas turbine, a flag corner of the guide vane airfoil, which corner faces the bleed duct and/or is in particular a virtual one, is located downstream of the beginning of the inlet opening of the bleed duct.

Abstract: A device removes moisture from a hydraulic medium (2) with at least one gaseous drying medium (3). The drying medium (3) is air and/or some other working gas with a moisture absorption capability. The drying medium is conducted by a delivery device (4) from an area surrounding the hydraulic medium (2) to the hydraulic medium (2) when the moisture content of the gaseous drying medium (3) is lower than the degree of water saturation of the hydraulic medium (2).

Abstract: A gas turbine engine including an axial high pressure compressor having expansion slots in the outer rim of the rotor section. The expansion slots may be positioned between blades of a rotor segment. The fore end of the slots may have an axial seal which is coupled to the inner surface of the outer rim in the first rotor segment, and may comprise a fin configuration. The axial seal may be integral to the inner surface of the outer rim. The compressor may comprise a plurality of expansion slots and axial seals, including in a plurality of rotor segments.

Abstract: The present invention relates to a fan wheel structure comprising a cover body connected with a plurality of fan blades, a hub, and a plurality of fan blades. The cover body is disposed on a hub. The hub has a top surface and a receiving space defined on the top surface. Each of the fan blades has a joining end protruding into the receiving space. The cover body has a clamping side combined with the top surface of the hub and a plurality of joining grooves spaced around the cover body and individually combined with the corresponding joining ends of the fan blades to fix the fan blades.

Abstract: A component is provided and comprises at least one wall comprising a first and a second surface. At least one film cooling hole extends through the wall between the first and second surfaces and has an outlet region at the second surface. The film cooling hole includes a first expansion section being a side diffusion portion and a second expansion section being a layback diffusion portion, wherein the side diffusion portion is upstream and spaced from the layback diffusion portion.

Abstract: A vane assembly for a gas turbine engine is disclosed in this paper. The vane assembly includes an inner platform, an outer platform, and a ceramic-containing airfoil. The ceramic-containing airfoil extends from the inner platform to the outer platform. A reinforcement spar made from a metallic material extends from the inner platform to the outer platform through a hollow core of the ceramic-containing airfoil.

Abstract: A gas turbine engine comprising a casing, a bonding patch (10, 22) bonded to a surface of the casing, and a liner attached to the bonding patch. The bonding patch (10, 22) comprising a bonding region (12) configured to receive an adhesive for bonding the patch (10, 22) to a surface. A plurality of de-bonding elements (16) is configured to be movable relative to the bonding region (12) in response to an energizing signal.

Abstract: A turbomachine has a seal which mates to a plurality of airfoils. The seal is formed from an abradable aluminum based material having a plurality of hard phase particles embedded therein and having a melting point higher than a melting point of the melting point of the abradable coating matrix alloy.

Abstract: What is described is a wear resistant seal system that is adapted for resisting wear of a rotating part in a gas turbine engine as it rotates against a stationary part in the engine. The system includes an axially rotable member including an abrasive tip having a first tensile strength. The system also includes a stationary structure radially exterior and adjacent to the rotable member and including an abradable material. The abradable material includes a matrix material having a second tensile strength that, at least in a first temperature range, is lower than the first tensile strength and a filler material interspersed with the matrix material.