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: 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 heat shield for a mid-turbine frame has a conical body, including at least one axial retention feature, at least one circumferential retention feature, and at least one radial retention feature.

Abstract: Rotor blades and methods for joining blade components of rotor blades are provided. A method includes positioning an insert between and in contact with a first blade component and a second blade component. At least one of the first blade component or the second blade component includes a thermoplastic resin. The insert includes a thermoplastic resin and an energy absorptive pigment. The method further includes heating the thermoplastic resin of the at least one of the first blade component or the second blade component and the thermoplastic resin of the insert. The method further includes cooling the thermoplastic resin of the at least one of the first blade component or the second blade component and the thermoplastic resin of the insert. The heating step and the cooling step join the first blade component, the second blade component and the insert together.

Abstract: A nozzle for a gas turbine engine, including an airfoil having an exterior surface, flange and radially compressive contact face. Also included is an airfoil support frame having a mating face positioned in engagement with the contact face. A non-orthogonal engagement angle is provided in order to transmit a compressive force to the airfoil.

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: An apparatus is provided for a vertical take-off and landing aircraft. The apparatus includes a rotor head with a rotor hub and a plurality of rotor blade attachment structures. The attachment structures are disposed about and extend radially out from the rotor hub. Each of the attachment structures may be configured from or otherwise include flexible matrix composite material. In addition or alternatively, the rotor head may be a monolithic bearingless rotor head.

Abstract: A wind turbine blade comprising a lightning protection system is provided. The lightning protection system comprises a lightning conductor located along a longitudinal portion of the wind turbine blade and is coupled to an electrical ground. A lightning receptor module is arranged on an external surface of the wind turbine blade and electrically coupled to the lightning conductor. An elongate receptor band is installed on the external surface of the wind turbine blade, over the lightning receptor module, and the receptor band is arranged to receive a stroke of lightning and transfer electrical current from the lightning stroke to the lightning conductor through the lightning receptor module. Further, the elongate receptor band comprises a crease in a longitudinal cross-sectional profile of the elongate receptor band. A method of installing a lightning protection system on a wind turbine blade is further provided.

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: 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: A composite vane body formed of a composite material of a thermosetting resin or a thermoplastic resin, and reinforced fibers, and a metal sheath that is bonded to a leading edge section of the composite vane body via a soft adhesive to cover the leading edge section are included, and an adhesive filling section in which the soft adhesive is filled, a plurality of leading edge side contact sections that come into contact with a curved section corresponding to a leading edge of the metal sheath, and a plurality of protrusions that come into contact with a planar section corresponding to a vane surface of the metal sheath, with at least a same height as a thickness of a layer of a requisite amount of the soft adhesive filled in the adhesive filling section are formed in the leading edge section of the composite vane body. Attachment of the metal sheath to the leading edge section can be performed easily with high precision.

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: A compressor is provided including a casing, a hub, a flowpath, a plurality of blades defining a plurality of axially extending compressor stages and an endwall treatment formed in the casing on at least two downstream most stages of the plurality of compressor stages. The remaining stages of the plurality of compressor stages located upstream of the at least two downstream most stage are devoid of any endwall treatment. Each of the endwall treatments faces a tip of each blade in the at least two downstream most stages. The tip of each blade and the endwall treatment are configured to move relative to each other. The endwall treatment formed in the casing on at least two downstream most stages of the plurality of compressor stages is configured to extend a stall margin to delay stall due to ice ingestion. A method and engine application are disclosed.

Abstract: It is disclosed an arrangement of a rotor and at least a blade. The blade includes a root, a platform and an airfoil. The rotor includes a seat for the root. The root has side walls which complement side walls of the seat and axial walls between the side walls. A chamber is provided between the root and the rotor. A shank cavity is provided between the root and the platform. A lock plate facing at least an axial wall is connected to the rotor and the blade. The lock plate has at least a slot on a side facing the root.

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 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: 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 first non-contacting dynamic rotor seal interfaced with a spool, the first non-contacting dynamic seal operates to seal adjacent to an outer diameter and a second non-contacting dynamic rotor seal with respect to the spool, the second non-contacting dynamic seal operates to seal adjacent to an inner diameter.

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.