Blade Making Patents (Class 29/889.7)
  • Publication number: 20140271207
    Abstract: A rotor blade assembly for a gas turbine engine includes two aerofoil members joined together at their roots by a blade assembly attachment web. The rotor blade assembly is made from a composite material, for example an organic fibre composite material. The blade assembly attachment web is used to attach a plurality of rotor blade assemblies to the rest of the gas turbine engine in order to form a rotor stage. The rotor stage may, for example, be the fan stage of a turbofan gas turbine engine.
    Type: Application
    Filed: August 15, 2013
    Publication date: September 18, 2014
    Applicant: ROLLS-ROYCE PLC
    Inventor: Andrew James DRANE
  • Publication number: 20140255194
    Abstract: A rotor blade for use in a turbine of a turbine engine is described. The rotor blade may include an airfoil that extends from a connection with a root. The airfoil may include a pressure sidewall and a suction sidewall that define an outer periphery and an outboard tip. The rotor blade may further include a tip shroud assembly disposed at the outboard tip of the airfoil. The tip shroud assembly includes a non-integral tip shroud.
    Type: Application
    Filed: December 21, 2012
    Publication date: September 11, 2014
    Applicant: General Electric Company
    Inventor: General Electric Company
  • Publication number: 20140255204
    Abstract: An aerodynamic fan nosecone for a gas turbine engine is provided and includes a fan nosecone that may be made of composite material. To improve airflow transition to the blade members, aerodynamic fairings are provided and are secured to an exterior surface of the nosecone which enhances fuel economy. The fairings may be secured to the nosecone by various methods, including providing for the fairings to be changed out and replaced with other fairings on the same nosecone assembly.
    Type: Application
    Filed: September 24, 2013
    Publication date: September 11, 2014
    Applicant: Rolls-Royce Corporation
    Inventors: Trevor John Totten, Jonathan Michael Rivers, Eric William Engebretsen
  • Patent number: 8826537
    Abstract: A method for making a rib for an aerofoil structure, the aerofoil structure including a skin component, the method including the steps of scanning the inner surface of the skin component to determine the surface profile thereof, providing a rib having a rib body and a rib foot protruding from the body, machining a foot surface profile into the rib foot, the foot surface profile being arranged to complement the skin inner surface profile where the rib foot is intended to abut the skin component.
    Type: Grant
    Filed: October 17, 2008
    Date of Patent: September 9, 2014
    Assignee: Airbus Operations Limited
    Inventors: Amir Kayani, Ian L Gray
  • Publication number: 20140248157
    Abstract: A blade or vane of different roughness and a process for producing such a blade or vane are presented. The performance of the blade or vane of a compressor or of a turbine can be improved because of the different configuration of the roughness of the surfaces on the suction side and the pressure side of the blade or vane.
    Type: Application
    Filed: October 24, 2013
    Publication date: September 4, 2014
    Inventor: Fathi Ahmad
  • Publication number: 20140245752
    Abstract: A system for attaching a rotating blade in a turbine includes a bush having an axial slot and a radial slot that intersects with the axial slot. A radial retention member fits within the radial slot, and an axial retention member fits within the axial slot and engages with the radial retention member. A method for attaching a rotating blade in a turbine includes inserting a bush into an axial passage in a rotor wheel and inserting a radial retention member into a radial passage in the rotor wheel and through at least a portion of the bush. The method further includes inserting the rotating blade in a slot in the rotor wheel, inserting the radial retention member into a retention slot in the rotating blade, and inserting an axial retention member into the bush.
    Type: Application
    Filed: January 2, 2013
    Publication date: September 4, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventor: GENERAL ELECTRIC COMPANY
  • Patent number: 8821127
    Abstract: A blade assembly for a groove of a wheel of rotating machinery is described. The blade assembly includes, a blade root having two longitudinal sides, a base, and a roof, wherein the profile of the longitudinal sides includes a rounded surface, a blade connected to the roof of the blade root, and one or more keys juxtaposed along each longitudinal side of the blade root, each key having an inboard side and an outboard side, wherein the profile of the inboard side of each key is configured to mate with the profile of the blade root. The blade assembly allows replacement of a compressor blade without the need for unstacking the rotor to gain access to the damaged blade.
    Type: Grant
    Filed: April 21, 2011
    Date of Patent: September 2, 2014
    Inventor: Ken Knecht
  • Publication number: 20140241895
    Abstract: A fluid turbine blade and method of fabrication are provided. The fluid turbine blade includes a centrally disposed longitudinal spar having a substantially circumferential cross section. The fluid turbine blade also includes at least one chord stiffener coupled to the longitudinal spar. The fluid turbine blade further includes a torsionally compliant segmented skin coupled to the at least one chord stiffener. The centrally disposed longitudinal spar and the torsionally compliant segmented skin are functionally decoupled to relieve the torsionally compliant segmented skin of one or more of a flapwise load condition, an edgewise load condition and a torsional load condition.
    Type: Application
    Filed: February 27, 2013
    Publication date: August 28, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Chandra Sekher Yerramalli, Peggy Lynn Baehmann, Ken Ivcar Salas, Mohammad Salah Attia, Haifeng Zhao
  • Publication number: 20140241890
    Abstract: In some examples, an apparatus may include a gas turbine engine component comprising a blade, a platform forming an airflow surface from which the blade extends on one side, and a motion weld receiving surface disposed on a non-airflow side of the platform, and a disk having a motion weld disk portion to receive the motion weld receiving surface of the gas turbine engine component and form a motion weld coupling when the disk and gas turbine engine component are coupled, wherein, prior to coupling, the gas turbine engine component further includes a blade stalk disposed on the non-airflow side of the platform and in which is formed the motion weld receiving surface.
    Type: Application
    Filed: December 18, 2013
    Publication date: August 28, 2014
    Applicant: Rolls-Royce Corporation
    Inventors: Roy David Fulayter, Jonathan Michael Rivers
  • Patent number: 8814523
    Abstract: In at least one implementation, a method of making a turbine blade may include providing a preform having a hollow cross-section, hydroforming the preform to form a turbine blade body comprising a shell that includes a continuous hollow portion along its interior, and providing a mounting portion attached to the body to mount the turbine blade to a hub. In one or more implementations of the method, the mounting portion may be provided during the step of hydroforming the preform and the mounting portion may be formed from the same preform as the turbine blade body.
    Type: Grant
    Filed: February 17, 2011
    Date of Patent: August 26, 2014
    Assignee: Vari-Form, Inc.
    Inventors: Martin L. Bliss, Trevor M. Clark, Jose U. Coelho, Timothy R. Flint, Blair J. Longhouse
  • Patent number: 8814528
    Abstract: A production method enables use of ultrasonic forming but does not leave a bonding face in a final product. One cuts into a plate member having a first side face and a second side face from the first side face toward the second side face to form a slit that does not reach the second side face; seals lips of the slit to leave an opening; causes superplastic forming of the plate member by pressurizing the plate member in a mold with gas through the opening; and cuts out a portion including the sealed lips.
    Type: Grant
    Filed: January 22, 2010
    Date of Patent: August 26, 2014
    Assignee: IHI Corporation
    Inventor: Takayuki Iwasaki
  • Patent number: 8813361
    Abstract: In a gas turbine blade where a part of the ?? phase precipitation strengthened type Ni-based alloy base material is composed of a weld metal, the weld metal is a Ni-based alloy containing Ta from 4.8 to 5.3 wt. %, Cr from 18 to 23 wt. %, Co from 12 to 17 wt. %, W from 14 to 18 wt. %, C from 0.03 to 0.1 wt. %, Mo from 1 to 2 wt. %, and Al of 1 wt. % or less, in which the oxygen content is 0 to 30 ppm, the Ti content from 0 to 0.1 wt. %, and the Re content from 0 to 0.5 wt. %. A blade base metal is manufactured by the step of stripping, the step of solution heat treatment where the ?? phase is dissolved again, the step of welding in an inert gas chamber by a TIG method using a welding wire where the weld metal can be obtained, the step of HIP treatment at 1100° C. to 1150° C., and the step of an aging treatment at 835° C. to 855° C.
    Type: Grant
    Filed: August 17, 2011
    Date of Patent: August 26, 2014
    Assignee: Hitachi, Ltd.
    Inventors: Shinya Imano, Kunihiro Ichikawa, Hiroyuki Doi, Katsumi Tanaka
  • Publication number: 20140234109
    Abstract: A method of making a root end joint for a wind turbine. A plurality of root segments (10) are formed of a composite material. Each has an arcuate end face (11) which subtends an angle of 90° or less and has a plurality of connection holes (12). The segments are joined together side-by-side to build up the circular profile of the root end. The segments include a proportion of uni-axial to multiaxial fiber which decreases from the arcuate end face towards the opposite end.
    Type: Application
    Filed: April 24, 2014
    Publication date: August 21, 2014
    Applicant: BLADE DYNAMICS LIMITED
    Inventors: Paul Trevor HAYDEN, Peter Anthony BROOME
  • Publication number: 20140234117
    Abstract: An apparatus to reduce wear and friction between CMC-to-metal attachment and interface, including a metal layer configured for insertion between a surface interface between a CMC component and a metal component. The surface interface of the metal layer is compliant relative to asperities of the surface interface of the CMC component. A coefficient of friction between the surface interface of the CMC component and the metal component is about 1.0 or less at an operating temperature between about 300° C. to about 325° C. and a limiting temperature of the metal component.
    Type: Application
    Filed: November 26, 2012
    Publication date: August 21, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventor: GENERAL ELECTRIC COMPANY
  • Publication number: 20140227100
    Abstract: The invention concerns a blade (1) designed to be fitted to the rotor of a rotating machine, said blade being characterized in that it exhibits a modular construction including: a rigid, median module (4) formed by a coffer (12), which is itself formed by joining two side panels (13, 14) that are connected to one another by at least one side rail (15), the side panels (13, 14) being connected by at least one weld executed on an internal protuberance on the said side panels that is set back from the intrados (11) and the extrados (1E) of the blade (1), an upstream module (7) forming a leading edge and added onto the upstream portion of the median module, a downstream module (8) forming a trailing edge and added onto the downstream portion of the median module Blades for rotating machines and corresponding fabrication methods.
    Type: Application
    Filed: September 21, 2012
    Publication date: August 14, 2014
    Inventors: Alain Godichon, Guy Constant Delaisse
  • Publication number: 20140215783
    Abstract: The present invention relates to a production facility (100, 200, 300, 400, 500) for forming elongated products, in particular wind turbine blades, wherein elongated mould assemblies (110a, 110b, 210a, 210b, 310a, 310b, 410a, 410b, 510a, 510b) may be accessed on the basis of an appropriate transport system (150, 250, 350, 450, 550) comprising at least one support member (251a-h, 151, 251, 351, 451, 551) laterally positioned between the elongated mould assemblies. The support member (251a-h, 151, 251, 351, 451, 551) is positioned so as to enable a rotational movement of an arm (121a, 121b, 221a) or is configured to change position or comprises a rotatable carrier element (259). For example, an elongated support member (151, 251, 351, 451, 551) may be positioned in a non-interference position, in which one or both mould assemblies can be moved into a position so as to form a composite mould assembly.
    Type: Application
    Filed: July 19, 2012
    Publication date: August 7, 2014
    Applicant: VESTAS WIND SYSTEMS A/S
    Inventors: Anton Bech, Raul Garcia Tapia, Aksel Petersen
  • Publication number: 20140219808
    Abstract: A sheath for a fan airfoil having a leading edge and a trailing edge in a chordwise direction, a tip and a root in a spanwise direction, a suction side and a pressure side includes a solid portion to wrap around the airfoil leading edge; a first wing attached to the suction side of the airfoil; and a second wing attached to the pressure side of the airfoil. At least one of the first wing and the second wing extends at least about 35% of the chord of the airfoil.
    Type: Application
    Filed: October 1, 2012
    Publication date: August 7, 2014
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventor: United Technologies Corporation
  • Patent number: 8793872
    Abstract: The present invention provides a method for manufacturing a closed impeller that has a simple configuration and enables fusion in a very accurate position. The method includes: forming a frustum-shaped front plate and a disk-shaped base plate formed therebelow, upper surfaces of a plurality of unit impeller blade plates made from a synthetic resin extending in radial directions which are formed as impeller blade tip surfaces, with sharp-pointed ridge-like protrusions having an acute upper end and a width less than a width of the impeller blade tip surface being integrally formed on the impeller blade tip surfaces. In the method, an inner surface of the front plate and the plurality of impeller blade tip surfaces are formed as parts of conical surfaces and formed so that the cone apex angles of the two conical surfaces are equal to each other.
    Type: Grant
    Filed: March 19, 2010
    Date of Patent: August 5, 2014
    Assignee: Yamada Manufacturing Co., Ltd.
    Inventors: Ryouhei Adachi, Song Fei, Hisayoshi Ono
  • Publication number: 20140212293
    Abstract: An aircraft rotor blade having a root portion having a through seat and designed for connection to the rotor; and a main portion extending from the root portion. The blade is produced by polymerizing an assembly having a main structure of composite material, and a composite material covering defining the outer surface of the blade. At the root portion, the main structure has a contoured block; and a lamina member extending about at least part of the block, and having a first part adhering to a first peripheral portion of the block, and a second part spaced apart from and facing a second peripheral portion of the block to form the seat; the lamina member having a pre-preg of continuous unidirectional fibres.
    Type: Application
    Filed: February 7, 2013
    Publication date: July 31, 2014
    Applicant: AGUSTAWESTLAND S.p.A.
    Inventor: AGUSTAWESTLAND S.p.A.
  • Patent number: 8789275
    Abstract: A wind turbine blade having a spar cap disposed between layers constituting an outer skin or disposed on an inner side of the outer skin and a method of manufacturing the wind turbine blade are provided, wherein in manufacture of the wind turbine blade, generation of manufacturing defects, such as misalignment and wrinkles in fabrics, can be suppressed and the time required for repairing the defects as well as for laminating the layers can be reduced. In the method of manufacturing the wind turbine blade having the spar cap as a main structural member of the blade disposed between the layers constituting the outer skin or disposed on the inner side of the outer skin, the spar cap is formed as a separate piece from the outer skin, and the spar cap, dry fiber fabrics for the layers constituting the outer skin, and a sandwich core member are collectively impregnated with resin under a vacuum process.
    Type: Grant
    Filed: July 9, 2009
    Date of Patent: July 29, 2014
    Assignee: Mitsubishi Heavy Industries, Ltd.
    Inventors: Kouji Esaki, Takao Kuroiwa, Nozomu Kawasetsu, Kentaro Shindo, Toru Matsuo
  • Patent number: 8782887
    Abstract: A method for producing a metal insert for protecting a leading or trailing edge of a compressor vane of an aeronautical machine made of a composite material, by stamping sheets and diffusion bonding between the sheets. The method includes: initially shaping the sheets by stamping to approximate the sheets to a shape of a suction side and pressure side of the insert; producing a core shaped inner cavity of the metal insert to be manufactured, one of the surfaces thereof reproducing an inner shape of the suction side of the insert and the other surface reproducing an inner shape of the pressure side of the insert; positioning the sheets around the core and securing the assembly; applying a vacuum and sealing the assembly by bonding; assembling the assembly by hot isostatic compression; cutting the assembly to extract the core and separate the insert; producing an outer profile of the insert by a final machining.
    Type: Grant
    Filed: March 18, 2011
    Date of Patent: July 22, 2014
    Assignee: SNECMA
    Inventors: Jean-Michel Patrick Maurice Franchet, Gilles Charles Casimir Klein
  • Publication number: 20140193268
    Abstract: An impeller (10) where each of the blades (34) includes a first part (14) which is positioned at a base end side of the hub (5) and a second part (24) which is positioned at a distal end side of the hub, the first part being formed by connecting a first hub surface curve (12) which extends along a hub surface of the hub and a first shroud surface curve (11) which extends along a shroud surface of the blade by a first group of lines (13), and the second part is formed by connecting a second hub surface curve (22) which extends along a hub surface of the hub and connects with the first hub surface curve and a second shroud surface curve (21) which extends along the shroud surface and connects with the first shroud surface curve by a second group of lines (23).
    Type: Application
    Filed: January 3, 2014
    Publication date: July 10, 2014
    Applicant: FANUC CORPORATION
    Inventors: SATORU KAWAI, KAZUYA OHTA
  • Patent number: 8770944
    Abstract: A component such as a turbine bucket or blade, and method for making the component, are presented. One embodiment is an article that comprises an airfoil casting portion comprising a plurality of integral regions, wherein the plurality of integral regions comprises a single-crystalline region and a columnar-grained region. Another embodiment is a method for fabricating an article. The method comprises providing a quantity of molten metal; providing a mold defining an airfoil portion having an axial direction and a transverse direction, wherein the airfoil portion of the mold comprises a single-crystal growth region and a columnar growth region disposed along the transverse direction from the single crystal growth region; introducing the molten metal into the mold; and solidifying the metal such that a solidification front progresses in the axial direction to produce an airfoil casting portion comprising a single-crystalline region and a columnar-grained region.
    Type: Grant
    Filed: March 31, 2011
    Date of Patent: July 8, 2014
    Assignee: General Electric Company
    Inventors: Akane Suzuki, Stephen Francis Rutkowski, Michale Francis Xavier Gigliotti, Jr.
  • Publication number: 20140182131
    Abstract: A method of fabricating a part by forging, the method including: measuring geometrical characteristics of the forged part; comparing a measured shape with a theoretical shape that is to be obtained for the part; deducing therefrom zones that are not in compliance with the theoretical shape and also thicknesses of material that need to be removed from the zones that are not in compliance; and polishing the zones of the forged part that are not in compliance to remove the deduced thicknesses of material by using a controlled abrasive band. The control of the abrasive band takes account of at least one parameter representative of wear of the abrasive band during polishing of zones that are not in compliance.
    Type: Application
    Filed: July 11, 2012
    Publication date: July 3, 2014
    Applicant: SNECMA
    Inventors: Beryl Cassandre Anne Mereaux, Benjamin Teboul
  • Publication number: 20140178204
    Abstract: Methods of manufacturing a fiber reinforced portion of a wind turbine rotor blade include disposing a continuous fiber mat adjacent a prefabricated layer, wherein the continuous fiber mat comprises randomly arranged reinforcing fibers and wherein the prefabricated layer comprises reinforcing fibers and a cured polymeric resin. The method further includes disposing a structural layer adjacent the continuous fiber mat opposite the prefabricated layer, wherein the structural layer comprises reinforcing fibers. The method then includes infusing a polymeric resin through at least the continuous fiber mat and curing the resin to form the fiber reinforced portion of the wind turbine rotor blade.
    Type: Application
    Filed: December 21, 2012
    Publication date: June 26, 2014
    Applicant: General Electric Company
    Inventors: Jamie Thomas Livingston, Jan Bakhuis
  • Publication number: 20140178206
    Abstract: A method for creating a blade (11) for a turbo-engine and such a blade are disclosed. Components (19) of the blade are produced by an additive production method such as selective laser melting or fusion, while a main body (18) is produced by casting, for example. The blade components (19) may consist of a different material than the basic body (18). The components or body may carry functions such as serving as drainage slots (24). Expense related to the use of additive production methods occurs only for the components (19) in which a complicated geometry, for example, must be implemented. The remaining components in the form of the main body (18), comprising the blade (27), the blade foot (28) and the blade head (29), can be cost-effectively implemented as a cast part or a sheet metal part.
    Type: Application
    Filed: July 20, 2012
    Publication date: June 26, 2014
    Inventors: Jens Göhler, Frank Kernstock, Olaf Rehme, Martin Schäfer
  • Publication number: 20140165347
    Abstract: A manufacturing system for manufacturing a rotor or parts thereof (rotor) includes a plurality of processing sections configured to process the rotor, and a plurality of maneuvering arrangements operatively configured to transport the rotor between and across the plurality of processing sections. The processing sections include a welding processing section to perform welding and related processes including testing, stacking, welding preparation, and welding. The processing sections further include a machining processing section to perform machining and related process including turning, milling and drilling on the rotor. The maneuvering arrangements include pallet and tilting units configured in the welding processing section to maneuver (tilt and transport) the rotor along a portion thereof. The maneuvering arrangements further include a transportation-setup station having work-piece and power shuttles to transport the rotor across the processing section.
    Type: Application
    Filed: December 17, 2013
    Publication date: June 19, 2014
    Applicant: ALSTOM TECHNOLOGY LTD
    Inventor: Reiner WENN
  • Publication number: 20140161616
    Abstract: A blade assembly for a gas turbine engine includes a rim seal including leading and trailing edge seal portions joined to one another by an axial portion. The leading and trailing edge seal portions and the axial portion together provide a notch. A blade has a root received in the notch. A rotating stage of a gas turbine engine includes a rotor including a slot. A rim seal includes leading and trailing edge seal portions adjoined to one another by an axial portion and providing a notch. A blade has a root received in the notch. A method of assembling a rotor stage includes inserting a root of a blade into a notch of a rim seal, and sliding the rim seal and blade into a rotor slot.
    Type: Application
    Filed: December 12, 2012
    Publication date: June 12, 2014
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventor: United Technologies Corporation
  • Publication number: 20140154085
    Abstract: A gas turbine, in particular an aircraft engine, having a housing in which at least one guide blade (12) is situated, the guide blade (12) including at least one shroud configuration (21) having a radially outer shroud (16) and having a shroud holding device (23) with the aid of which the shroud (16) is secured on the housing, as well as including a turbine blade (18) extending radially inward from the shroud configuration (21). The shroud holding device (23) or parts thereof include(s) at least one air passage channel (28), which permits a flow passage through the shroud holding device (23). The invention also relates to a guide blade (12) for placement on a housing of a gas turbine as well as a method for manufacturing such a guide blade (12).
    Type: Application
    Filed: March 11, 2013
    Publication date: June 5, 2014
    Applicant: MTU AERO ENGINES GMBH
    Inventor: MTU Aero Engines GmbH
  • Patent number: 8740571
    Abstract: A turbine bucket for use with a turbine engine. The turbine bucket includes an airfoil that extends between a root end and a tip end. The airfoil includes an outer wall that defines a cavity that extends from the root end to the tip end. The outer wall includes a first ceramic matrix composite (CMC) substrate that extends a first distance from the root end to the tip end. An inner wall is positioned within the cavity. The inner wall includes a second CMC substrate that extends a second distance from the root end towards the tip end that is different than the first distance.
    Type: Grant
    Filed: March 7, 2011
    Date of Patent: June 3, 2014
    Assignee: General Electric Company
    Inventor: Andres Garcia-Crespo
  • Publication number: 20140143991
    Abstract: A method for machining a robot-guided component with a tool which is fastened in an articulated manner to a tool holder is disclosed. The method includes detecting a deflection of the tool with respect to the tool holder from a desired position and changing a pose of a robot that is guiding the robot-guided component on a basis of the detected deflection.
    Type: Application
    Filed: October 26, 2011
    Publication date: May 29, 2014
    Applicants: INSYS Industriesysteme AG, MTU Aero Engines GmbH
    Inventors: Joerg Windprechtinger, Daniel Hodel
  • Patent number: 8732920
    Abstract: The invention provides tooling and a method for hot forging pieces of sheet metal that are to form metal reinforcement mounted on the leading or trailing edge of a turbine engine blade, by means of bottom and top matrices each presenting a twisted elongate surface for use in shaping an initially plane piece of sheet metal, the shaping surface of the bottom matrix presenting a high portion, a low portion, and two end zones. The bottom matrix includes studs for positioning and guiding the piece, the studs being situated at the periphery of the corresponding shaping surface.
    Type: Grant
    Filed: January 10, 2012
    Date of Patent: May 27, 2014
    Assignee: SNECMA
    Inventors: Gilbert Michel Marin Leconte, Jean-Michel Patrick Maurice Franchet, Gilles Charles Casimir Klein, Dominique Magnaudeix
  • Patent number: 8732949
    Abstract: A process for manufacturing a single-piece blisk, including: using an abrasive water jet to cut a block of material, so as to create blade preforms extending radially from a disk, then milling the blade preforms.
    Type: Grant
    Filed: March 25, 2009
    Date of Patent: May 27, 2014
    Assignee: SNECMA
    Inventors: Serge Berlanger, Sebastien Bordu, Thierry Jean Maleville, Christophe Charles Maurice Roca
  • Publication number: 20140137409
    Abstract: A method for finishing a shape of a component by machining, in which one area is produced by smelting with a thickened portion forming a first surface with a surrounding profile and a theoretical profile defined by a second surface, the method including: defining, on the second surface, a grid forming nodes and squares; defining each point over which the machining tool is to pass according to weighting coefficients equal to weight to be given to the nodes of the square in which the tool is located, to be the barycenter of assigned nodes of the coefficients; measuring, for each node located outside an outer limit, the delta between the first surface at the node and the theoretical position of the node; calculating deltas for each node within the outer limit by interpolation from already known deltas; using the weighting coefficients, defining the delta to be applied at each point.
    Type: Application
    Filed: June 21, 2012
    Publication date: May 22, 2014
    Applicant: SNECMA
    Inventors: Yvon Marie-Joseph Louesdon, Joseph Tami-Lizuzu, Daniel Quach, Patrick Wehrer, Didier Legeai
  • Publication number: 20140140827
    Abstract: A vane assembly has a vane including an inner platform with a mount rail extending radially inwardly toward an engine center axis. An air seal is attached to the inner platform. The air seal has a single-piece ring extending circumferentially about the engine center axis. A ring nut secures the air seal to the inner platform. A biasing member cooperates with the ring nut and air seal to seal fore and aft locations on the vane.
    Type: Application
    Filed: September 27, 2012
    Publication date: May 22, 2014
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventor: UNITED TECHNOLOGIES CORPORATION
  • Patent number: 8726504
    Abstract: The present invention relates to a method of producing turbine blade, which comprises, (a) forging a plurality of turbine blades in a state where the plurality of turbine blades are integrally connected in a longitudinal direction, (b) heat treating the plurality of turbine blades in the integrally connected state, (c) machining the plurality of turbine blades in the integrally connected state, and (d) separating the plurality of turbine blades into individual turbine blades. According to the method, the number of processes for the forging work can be decreased, and forging efficiency can be enhanced. Moreover, an amount of burr which occurs during the forging work can be reduced, and hence, a yield of material can be improved, as compared with a case where the turbine blade is forged as a single body.
    Type: Grant
    Filed: July 9, 2012
    Date of Patent: May 20, 2014
    Assignee: Daido Steel Co., Ltd.
    Inventors: Koji Kimura, Hiroshi Asano, Ikuno Kumazawa
  • Publication number: 20140130353
    Abstract: A method of manufacturing a turbine engine component comprises the steps of fabricating an inner hub, casting a plurality of blades, forming a blade ring, and bonding the blade ring to the inner hub. Each blade comprises a blade root and an airfoil body extending from the blade root. The blade ring comprises, at least in part, the plurality of blades coupled by a first bonding technique. The blade ring is bonded to the inner hub using a second bonding technique.
    Type: Application
    Filed: November 27, 2013
    Publication date: May 15, 2014
    Inventors: Harry L. Kington, William J. Howe
  • Publication number: 20140133987
    Abstract: A method for manufacturing a leading edge profile section of an aircraft lifting surface is provided. The method comprises the following steps: a) providing a set of laminated preforms of a composite material configured with a suitable shape for constituting the leading edge profile section; b) arranging said laminated preforms in a curing tooling and subjecting the assembly to an autoclave cycle to co-cure said laminated preforms; c) demoulding the curing tooling in a spanwise direction towards the aircraft symmetry plane. The invention also comprises a leading edge profile section manufactured by said method comprising in addition to the skin of the leading edge profile section, one or more of the following structural elements: an auxiliary spar, a longitudinal stiffener reinforcing an auxiliary spar, a longitudinal stringer reinforcing the skin of the leading edge profile.
    Type: Application
    Filed: July 16, 2013
    Publication date: May 15, 2014
    Applicant: AIRBUS OPERATIONS S.L.
    Inventors: Enrique GUINALDO FERNANDEZ, Francisco Javier HONORATO RUIZ, Francisco Jose CRUZ DOMINGUEZ
  • Publication number: 20140127025
    Abstract: There is provided a wind power installation rotor blade having a rotor blade root, a rotor blade tip, a rotor blade leading edge, a rotor blade trailing edge, a pressure side and a suction side. The rotor blade further has a rotor blade outer casing with at least one opening in the pressure and/or suction side for receiving handling means for fitting or removing the rotor blade. The rotor blade also has at least one fixing unit for fixing the handling means which are introduced through the at least one opening. The fixing unit is arranged in the interior of the rotor blade outer casing between the pressure side and the suction side.
    Type: Application
    Filed: May 29, 2012
    Publication date: May 8, 2014
    Applicant: Wobben Properties GmbH
    Inventor: Alexander Hoffmann
  • Publication number: 20140119940
    Abstract: A wind blade with a self-supporting structural framework, having multiple chord-wise members and one or more span-wise members is provided. Each of the multiple chord-wise members and the one or more span-wise members have an aerodynamic contour. The wind blade also comprises a fabric skin located over the self-supporting structural framework in a tensioned state to generate an aerodynamic surface, wherein the fabric skin is attached via multiple tensioning members to both the chord wise members and span wise members.
    Type: Application
    Filed: October 31, 2012
    Publication date: May 1, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Sriram Krishnamurthy, Wendy Wen-Ling Lin, Suresh Subramanian, Subbareddy Daggumati, Udit Kulmi, Prakash Kashiram Jadhav, Vasan Churchill Srinivasan Chandrasekaran
  • Publication number: 20140112778
    Abstract: Flag-type wind and/or water power generation features are described. Fluid-filled embodiments are described. The fluid may be employed for pumping effect and/or dynamic physical property change. Leading-edge and trailing-edge mounted flag architectures are described with various applications including flapping flag arrays and Vertical Axis Wind Turbines (VAWTs).
    Type: Application
    Filed: October 24, 2013
    Publication date: April 24, 2014
    Applicant: CALIFORNIA INSTITUTE OF TECHNOLOGY
    Inventors: Morteza Gharib, Julia Cosse, Daegyoum Kim
  • Patent number: 8701287
    Abstract: For shaping the leading edge (1) of blisk blades (2), the shape, amount and disposition of the material to be removed in a subsequent grinding and polishing process is determined beforehand over the entire blade length. The blade leading edge is milled such that an elliptical profile (3) has a material allowance (7) which over the length of the leading edge exactly corresponds to an expected material removal during the grinding and polishing process, so that a blisk blade is produced whose leading edge features an aerodynamically advantageous shape.
    Type: Grant
    Filed: April 6, 2009
    Date of Patent: April 22, 2014
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Liane Holze, Gregor Riedel
  • Patent number: 8689442
    Abstract: With the fabrication of integrally bladed rotors or stators (blisks) for gas-turbine engines, where the space confined by the pressure and suction side as well as the annulus surface is shaped by cutting and machining from the solid material, starting at the periphery of a ring or disk, a stiffness-optimized pre-machining contour is cut out in a cutting process at a certain distance from the pressure and suction side along straight control surfaces at a cutting angle varying in correspondence with the blade twist and along a conical surface extending at a certain distance from the annulus surface as well as along transition surfaces between the conical and the control surfaces, and subsequently finish machined by finish milling to produce the final contour of the blade, annulus and transition surfaces. The method reduces tool wear and is cost-effective.
    Type: Grant
    Filed: April 6, 2009
    Date of Patent: April 8, 2014
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Gregor Kappmeyer, Gregor Riedel
  • Patent number: 8689440
    Abstract: A method of forming a hollow component with an internal structure from first and second panels includes the step of forming at least one protrusion on a surface of at least one of the first and second panels by a material deposition process. The first and second panels are assembled into a preform the panels being oriented such that each panel defines an interior and an exterior facing surface, with the at least one protrusion extending from an exterior facing surface of a panel. The preform is expanded against a die, such that the at least one protrusion is transferred from the exterior surface of a panel to the interior surface of a panel so as to define an internal structure. Forming the at least one protrusion may include encapsulating an elongate member on the surface of a panel by a material deposition process.
    Type: Grant
    Filed: January 18, 2011
    Date of Patent: April 8, 2014
    Assignee: Rolls-Royce PLC
    Inventors: Oliver Michael Strother, Dean Gwynfryn Jones
  • Publication number: 20140093379
    Abstract: A gas turbine engine component is described which (100), comprises: a shell having an internal cavity for receiving a multi-part insert; a multi-part insert located within the cavity, wherein the multi-part insert comprises separate insert parts assembled in an abutting relation with one another within the cavity to provide the multi-part insert; an insertion aperture within a wall of the shell which is sized to receive each of the insert parts individually and wherein the multi-part insert cannot be withdrawn from the cavity through the insertion aperture when assembled.
    Type: Application
    Filed: October 2, 2013
    Publication date: April 3, 2014
    Inventors: Ian TIBBOTT, Dougal Richard JACKSON
  • Publication number: 20140093381
    Abstract: A turbine component, a turbine blade, and a turbine component fabrication process are disclosed. The turbine component includes ceramic matrix composite plies and a feature configured for preventing interlaminar tension of the ceramic matrix composite plies. The feature is selected from the group consisting of ceramic matrix composite tows or precast insert tows extending through at least a portion of the ceramic matrix composite plies, a woven fabric having fiber tows or a precast insert preventing contact between a first set of the ceramic matrix composite plies and a second set of the ceramic matrix composite plies, and combinations thereof. The process includes laying up ceramic matrix composite plies in a preselected arrangement and securing a feature configured for interlaminar tension.
    Type: Application
    Filed: October 3, 2012
    Publication date: April 3, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: John McConnell DELVAUX, Ronald Ralph CAIRO, Jason Robert PAROLINI
  • Publication number: 20140093383
    Abstract: A wind turbine includes a rotor having a hub and at least one blade having a torsionally rigid root, an inboard section, and an outboard section. The inboard section has a forward sweep relative to an elastic axis of the blade and the outboard section has an aft sweep.
    Type: Application
    Filed: January 23, 2008
    Publication date: April 3, 2014
    Inventor: Kyle Kristopher Wetzel
  • Patent number: 8683689
    Abstract: A method for manufacturing a hollow blade for a turbomachine is disclosed in which the blade is manufactured using a preform derived from external primary parts. A primary part including a root portion is formed by upset forging a bar in which material has been forced into a large volume area. Finish forging is done in at least two complementary stamping operations using an intermediate blank in order to limit costs and to use mechanical presses even for large and thin primary parts. Dies for forging the primary part are defined so as to double up at least the forging capacity of a press.
    Type: Grant
    Filed: August 22, 2005
    Date of Patent: April 1, 2014
    Assignee: SNECMA
    Inventors: Christine Deron, Alain Georges Henri Rene Lorieux, Philippe Rene Georges Joffroy, Jean-Louis Paul Victor Despreaux
  • Publication number: 20140086724
    Abstract: An internally cooled gas turbine engine component has a line of cooling air discharge holes, an internal cooling channel, an internal feed cavity for feeding cooling air from the channel to the discharge holes, and flow disrupting pedestals arranged in rows. A method of configuring the component includes: determining angles ? and ? of the directions of cooling air flow into the first and Nth rows, respectively; defining a change in angle ? of the direction of cooling air flow between rows as ?=(???)/N; and positioning the pedestals such that a line extending forward from the centre of each pedestal in the ith row at an angle {?+?(i?1)} intersects the (i ?1)th row at a location which is midway between two neighbouring pedestals of the (i?1)th row, i being an integer from 2 to N.
    Type: Application
    Filed: September 23, 2013
    Publication date: March 27, 2014
    Applicant: ROLLS-ROYCE PLC
    Inventors: Ian TIBBOTT, Dougal Richard JACKSON
  • Patent number: 8678768
    Abstract: A vertical axis turbine and method of making same is disclosed. The device and method comprise a plurality of blades rotatably disposed around an axis of rotation at a plurality of blade locations, each blade being twisted at a first angle about its longitudinal axis, each blade having its distal ends located a predetermined distance from the axis of rotation, each blade being bent at one or more central locations along the longitudinal axis so the one or more central locations are the same predetermined distance from the axis of rotation as the distal ends, each blade having a foil cross section perpendicular to the axis of rotation for maintaining unidirectional rotation of that blade about the axis of rotation in a fluid flow, and each blade having its longitudinal axis tilted at a second angle with respect to the axis of rotation.
    Type: Grant
    Filed: August 28, 2013
    Date of Patent: March 25, 2014
    Assignee: SEaB Energy Ltd.
    Inventor: Nicolas W. Sassow