Composite Blade Patents (Class 29/889.71)
  • Patent number: 10578078
    Abstract: A wind turbine rotor blade assembly and associated method include a rotor blade having a pressure side, a suction side, a leading edge, and a trailing edge extending in a generally span-wise direction between a tip and a root. An edge extension panel is attached along either of the leading edge or trailing edge (or along both edges) in a generally span-wise direction from adjacent the root towards the tip. The edge extension panels include a cured and hardened viscous material continuous core formed onto the leading or trailing edge with a contoured generally aerodynamic outer surface.
    Type: Grant
    Filed: June 12, 2017
    Date of Patent: March 3, 2020
    Assignee: General Electric Company
    Inventors: Aaron John Mashue, Bruce Clark Busbey, Christian A. Carroll
  • Patent number: 10576578
    Abstract: A field of rotary blades, and more particularly to a method of fabricating a leading edge shield for protecting such a blade. The method includes at least steps of performing initial plastic deformation on at least one sheet from a pressure side sheet and a suction side sheet, using additive fabrication to add a reinforcement with a fiber insert on at least one of the pressure and suction side sheets, closing the pressure and suction side sheets around a core after the initial plastic deformation and after adding the reinforcement, performing subsequent plastic deformation by pressing the pressure and suction side sheets against an outside surface of the core after the sheets have been closed around the core, and extracting the core.
    Type: Grant
    Filed: September 18, 2015
    Date of Patent: March 3, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Gilles Charles Casimir Klein, Jean-Michel Patrick Maurice Franchet, Dominique Michel Serge Magnaudeix
  • Patent number: 10487796
    Abstract: The present disclosure is directed to methods for attaching a plurality of surface features to a rotor blade of a wind turbine. Such methods may include direct molding of the surface features to the rotor blade, bonding arrays of connected components to the rotor blade and subsequently removing connections between components, as well as using a flexible template with or without a tinted adhesive.
    Type: Grant
    Filed: October 13, 2016
    Date of Patent: November 26, 2019
    Assignee: General Electric Company
    Inventors: James Robert Tobin, Murray Fisher, Madireddi Vasu Datta, Drew Adam Wetzel
  • Patent number: 10265792
    Abstract: A hybrid article is disclosed including a coating disposed on and circumscribing the lateral surface of a core having a core material. The coating includes about 35% to about 95% of a first metallic material having a first melting point, and about 5% to about 65% of a second metallic material having a second melting point lower than the first melting point. The coating is sinter-bonded to the core. A method for forming the hybrid article is disclosed including disposing the core in a die, introducing a slurry having the metallic materials into a gap between the lateral surface and the die, and sintering the slurry, forming the coating. A method for closing an aperture of an article is disclosed including inserting the hybrid article into the aperture, and brazing the hybrid article to the article, welding the aperture with the hybrid article serving as weld filler, or both.
    Type: Grant
    Filed: November 8, 2017
    Date of Patent: April 23, 2019
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Yan Cui, Srikanth Chandrudu Kottilingam, Brian Lee Tollison, Timothy Neal Pletcher, Richard Ryan Pilson
  • Patent number: 10174627
    Abstract: An airfoil for a gas turbine engine has a first layer forming a cavity having transitioning from a first thickness to a second thickness through a ply drop region. A second layer is secured to the first layer.
    Type: Grant
    Filed: February 5, 2014
    Date of Patent: January 8, 2019
    Assignee: United Technologies Corporation
    Inventors: Hoyt Y. Chang, Shelton O. Duelm
  • Patent number: 10138738
    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.
    Type: Grant
    Filed: February 17, 2016
    Date of Patent: November 27, 2018
    Assignee: IHI Corporation
    Inventors: Kenro Obuchi, Hiroyuki Yagi
  • Patent number: 10086459
    Abstract: A hybrid article is disclosed including a coating disposed on and circumscribing the lateral surface of a core having a core material. The coating includes about 35% to about 95% of a first metallic material having a first melting point, and about 5% to about 65% of a second metallic material having a second melting point lower than the first melting point. A method for forming the hybrid article is disclosed including disposing the core in a die, forming a gap between the lateral surface and the die, introducing a slurry having the metallic materials into the gap, and sintering the slurry, forming the coating. A method for closing an aperture of an article is disclosed including inserting the hybrid article into the aperture. Closing the aperture includes brazing the hybrid article to the article, welding the aperture with the hybrid article serving as weld filler, or a combination thereof.
    Type: Grant
    Filed: October 25, 2017
    Date of Patent: October 2, 2018
    Assignee: General Electric Company
    Inventors: Yan Cui, Srikanth Chandrudu Kottilingam, Brian Lee Tollison
  • Patent number: 10066599
    Abstract: A spar cap assembly is for a wind turbine rotor blade. The spar cap assembly has a spar cap reinforced with carbon fibers, comprising a lightning conductor, which is arranged so as to run along the spar cap, and at least one potential-equalizing element, which establishes an electrical connection between the spar cap and the lightning conductor. The carbon fibers of the spar cap, the lightning conductor and the at least one potential-equalizing element are embedded in a common polymer matrix and are configured as a prefabricated assembly for integration into a wind turbine rotor blade half-shell after the curing of the polymer matrix.
    Type: Grant
    Filed: April 7, 2015
    Date of Patent: September 4, 2018
    Assignee: Nordex Energy GmbH
    Inventors: Nick Ohlerich, Hendrik Klein, Nils-Hendric Schall
  • Patent number: 10035329
    Abstract: A hybrid article is disclosed including a coating circumscribing the lateral surface of a hollow core having a core material and a channel disposed within the lateral surface. The coating includes about 35% to about 95% of a first metallic material, and about 5% to about 65% of a second metallic material with a lower melting point than the first metallic material. A method for forming the hybrid article is disclosed including disposing the hollow core in a die, forming a gap between the lateral surface and the die, introducing a slurry having the metallic materials into the gap, and sintering the slurry, forming the coating. A method for closing an aperture of an article is disclosed including inserting the hybrid article into the aperture, and brazing the hybrid article to the article, welding the aperture with the hybrid article serving as weld filler, or a combination thereof.
    Type: Grant
    Filed: June 13, 2017
    Date of Patent: July 31, 2018
    Assignee: General Electric Company
    Inventors: Yan Cui, Srikanth Chandrudu Kottilingam, Brian Lee Tollison, Timothy Neal Pletcher, Richard Ryan Pilson
  • Patent number: 10018179
    Abstract: The present wind turbine blade comprises an airfoil structure comprising an airfoil shape, an internal support structure arranged spanwise along the length of the blade within the airfoil structure, and an elastic connection joining a portion of an inner surface of the airfoil structure with a portion of the internal support structure. The airfoil structure can be passively pitched relative to the internal support structure according to aerodynamic pressure distribution at different blade locations.
    Type: Grant
    Filed: August 18, 2014
    Date of Patent: July 10, 2018
    Assignee: GE Renewable Technologies Wind B.V.
    Inventor: Jaume Betran Palomas
  • Patent number: 9862046
    Abstract: A hybrid article is disclosed including a coating disposed on and circumscribing the lateral surface of a core having a core material. The coating includes about 35% to about 95% of a first metallic material having a first melting point, and about 5% to about 65% of a second metallic material having a second melting point lower than the first melting point. A method for forming the hybrid article is disclosed including disposing the core in a die, forming a gap between the lateral surface and the die, introducing a slurry having the metallic materials into the gap, and sintering the slurry, forming the coating. A method for closing an aperture of an article is disclosed including inserting the hybrid article into the aperture. Closing the aperture includes brazing the hybrid article to the article, welding the aperture with the hybrid article serving as weld filler, or a combination thereof.
    Type: Grant
    Filed: December 11, 2015
    Date of Patent: January 9, 2018
    Assignee: General Electric Company
    Inventors: Yan Cui, Srikanth Chandrudu Kottilingam, Brian Lee Tollison
  • Patent number: 9765634
    Abstract: The invention relates to a turbine engine blade, particularly made of composite material, including: on the one hand, an airfoil (10) which exhibits: a leading edge (12), a trailing edge (14) opposite to the leading edge (12), intrados (16) and extrados (18) lateral walls which connect the leading edge (12) to the trailing edge (14), et on the other hand, a structural reinforcement (20) including a base (24) extending into two fins (26, 28) and designed to be applied to the leading edge (12) and the lateral walls (16, 18) of the airfoil (10), characterized in that the fins (26, 28) of the structural reinforcement (20) and/or the lateral walls (16, 18) of the airfoil (10) are shaped to maintain an assembly space (30) with nonzero thickness between at least one of the fins (26, 28) and the airfoil (10) when the structural reinforcement (20) is in place on the airfoil (10), said assembly space (30) extending from a free end (27, 29) of said fin (26, 28) toward the base (24) of the structural reinforcement
    Type: Grant
    Filed: July 24, 2013
    Date of Patent: September 19, 2017
    Assignee: SNECMA
    Inventors: Vincent Fameau, Aude Abadie
  • Patent number: 9670788
    Abstract: A composite aerofoil vane for a gas turbine engine extends in use in a generally radial direction across an axially- and circumferentially-extending annular duct. The vane comprises a plurality of first reinforcing fibers extending in a generally radial direction and a plurality of second reinforcing fibers extending in generally axial and circumferential directions. The second fibers are interlaced with the first fibers so as to form a more unified and integrated structure, and to prevent the first reinforcing fibers from moving relative to one another.
    Type: Grant
    Filed: February 20, 2014
    Date of Patent: June 6, 2017
    Assignee: ROLLS-ROYCE plc
    Inventors: Matthew Ashley Charles Hoyland, Dale Edward Evans, Bijoysri Khan
  • Patent number: 9670789
    Abstract: A composite guide vane for a gas turbine structure is adapted to extend in a guide vane direction from a first housing towards a second housing of the gas turbine structure. The guide vane includes a guide vane length in the guide vane direction and the guide vane includes a first attachment portion with at least one first opening for attachment of the guide vane to the first housing. The first opening extends in a first opening direction which forms an angle with the guide vane direction. The guide vane includes a cover portion including a first material and a core portion which is at least partially enclosed by the cover portion.
    Type: Grant
    Filed: March 14, 2011
    Date of Patent: June 6, 2017
    Assignee: GKN Aerospace Sweden AB
    Inventors: Niklas Jansson, Robert Reimers
  • Patent number: 9650897
    Abstract: A fan blade comprises an airfoil portion and a sheath portion. The sheath portion has a sheath head section, a first sheath flank, and a second sheath flank, both flanks extending chordwise from the forward sheath section. The sheath portion is bonded to the airfoil portion such that the sheath head section covers the forward airfoil edge, defining a blade leading edge. The first sheath flank covers a portion of the first airfoil surface proximate the airfoil forward edge, jointly defining a blade suction surface. The second sheath flank covers a portion of the second airfoil surface proximate the airfoil forward edge, jointly defining a blade pressure surface. The first metallic material is an aluminum alloy containing between about 0.5 wt % and about 3.0 wt % of lithium.
    Type: Grant
    Filed: June 21, 2012
    Date of Patent: May 16, 2017
    Assignee: United Technologies Corporation
    Inventors: James L. Deal, John J. Schirra, Lee Drozdenko, William R. Graves, James O. Hansen, Michael A. Weisse, Thomas J. Watson
  • Patent number: 9617973
    Abstract: A wind turbine rotor blade is provided. The wind turbine rotor blade includes at least two blade sections and a connector for connecting adjacent blade sections, which connector has an inner connecting part of a first blade section and an outer connecting part of a second blade section, wherein the outer connecting part is adapted to enclose the inner connecting part; and a first seal arranged about a connecting part such that an outer surface of the inner connecting part, an inner surface of the outer connecting part, and the first seal form a mold; and an adhesive layer introduced to fill the mold. A wind turbine having a number of such rotor blades as well as a method of constructing such a wind turbine rotor blade are also provided.
    Type: Grant
    Filed: November 23, 2013
    Date of Patent: April 11, 2017
    Assignee: SIEMENS AKTIENGESELLSCHAFT
    Inventor: Jason Stege
  • Patent number: 9605651
    Abstract: A spar assembly for a rotor blade of a wind turbine is disclosed. The spar assembly includes a first spar cap segment and a second spar cap segment. The first spar cap segment is configured on an interior surface of a first blade segment and the second spar cap segment is configured on an interior surface of a second blade segment. Each spar cap segment includes an end having a joint section that is joinable at a chord-wise joint. Each of the first and second joint sections includes a plurality of holes formed therein. Further, the spar assembly includes a plurality of pins inserted into the plurality of holes of the first and second joint sections to join the first and second blade segments so as to improve stiffness of the rotor blade.
    Type: Grant
    Filed: December 4, 2013
    Date of Patent: March 28, 2017
    Assignee: General Electric Company
    Inventors: Bruce Clark Busbey, Edward McBeth Stewart
  • Patent number: 9587497
    Abstract: A turbine blade having a root and a tip and an airfoil with a core section made of composite material and a protective sheath or layer joined to the composite core at a location or locations exposed to erosion is described with the composite core of the airfoil being continuous from a location in vicinity of the root to a location in vicinity of the tip of the blade and including a section which widens with distance from the rotational axis along the length of the airfoil and which ends at the location in vicinity of the tip of the blade. The protective sheath or layer is secured by interference fit with widening section of the core.
    Type: Grant
    Filed: December 4, 2015
    Date of Patent: March 7, 2017
    Assignee: General Electric Technology GmbH
    Inventors: Rolf Hunziker, Said Havakechian
  • Patent number: 9488056
    Abstract: According to one embodiment, a propeller blade includes a foam core and a structural layer formed of multiple layers that surrounds at least a portion of the foam core. The structural layer includes a mid-thickness location defined between the foam core and an outer edge of the structural layer and the multiple layers include at least one unidirectional layer and at least one biased layer disposed asymmetrically about the mid-thickness location.
    Type: Grant
    Filed: April 30, 2013
    Date of Patent: November 8, 2016
    Assignees: RATIER-FIGEAC SAS, HAMILTON SUNDSTRAND CORPORATION
    Inventors: David P. Nagle, Patrice Brion, Ludovic Prunet
  • Patent number: 9470243
    Abstract: A guide vane attachment structure including a first fitting portion formed in a vane joint surface of a guide vane, a support member whose constituent material is a metal is integrally connected to a fan frame, and a second fitting portion to be fitted to the first fitting portion formed in a support joint surface of the support member.
    Type: Grant
    Filed: March 8, 2012
    Date of Patent: October 18, 2016
    Assignee: IHI Corporation
    Inventors: Tadahiro Ishigure, Yukihiro Kondo, Takaomi Inada
  • Patent number: 9376917
    Abstract: A fan rotor blade includes a blade body constructed of a composite material, a blade root constructed of the composite material, and a sheath attached to a leading edge of the blade body. The sheath includes a sheath main body and a pair of joint flanges, and is segmented into a sheath base segment and a sheath top segment. The sheath top segment has a longer length than a length of the sheath base segment along a span direction. A sheath length of the sheath main body at an assumed impact position with an obstacle is not shorter than 10% chord and not longer than 60% chord. A sheath length of the sheath along an end edge of the fan rotor blade is not shorter than 40% chord. The fan rotor blade possesses sufficient impact resistance and can be simplified and light-weighted.
    Type: Grant
    Filed: July 12, 2011
    Date of Patent: June 28, 2016
    Assignee: IHI Corporation
    Inventors: Takeshi Murooka, Hiroshi Kuroki, Rintaro Kajiwara, Kenro Obuchi
  • Patent number: 9328614
    Abstract: A metal reinforcing piece for mounting on a leading edge or trailing edge of a composite blade for a turbine engine is made by shaping two metal sheets, positioning them on either side of a core, assembling the two sheets together around the core under a vacuum, shaping them on the core by hot isostatic compression, and cutting them to separate the reinforcing piece and release the core. A predetermined roughness is given to at least a portion of the surface of the core and is transferred to a corresponding portion of an inside surface of the reinforcing piece by the hot isostatic compression.
    Type: Grant
    Filed: January 10, 2012
    Date of Patent: May 3, 2016
    Assignee: SNECMA
    Inventors: Gilles Charles Casimir Klein, Jean-Michel Patrick Maurice Franchet, Gilbert Michel Marin Leconte, Dominique Magnaudeix
  • Patent number: 9222362
    Abstract: A leading edge for use as a leading edge reinforcement on a blade or airfoil part. The leading edge has a main body that includes two leg sections. A metal deposition layer is applied to the main body to form the outer end portion of the leading edge. The main body can be formed of one or more pieces.
    Type: Grant
    Filed: November 3, 2011
    Date of Patent: December 29, 2015
    Assignee: Barnes Group Inc.
    Inventors: Jeffery L. Ford, Benjamin Adams, Michael Schroder, Eric Cutiongco
  • Patent number: 9157454
    Abstract: A flow straightener device for a turbomachine including an inner shell ring and an outer shell ring surrounding the inner shell ring, at least one out of the inner shell ring and outer shell ring having first orifices; at least two flow straightener vanes each including, at least at one same first end, an attachment platform having second orifices positioned facing the first orifices; the at least two vanes being assembled with at least one of the inner shell ring and outer shell ring by at least one first device of attachment introduced into the first orifices and the second orifices. The flow straightener device includes a covering platform covering the at least one first device of attachment.
    Type: Grant
    Filed: April 4, 2011
    Date of Patent: October 13, 2015
    Assignee: SNECMA
    Inventor: Jean Marc Claude Perrollaz
  • Publication number: 20150147185
    Abstract: Turbine buckets include a pressure side, a suction side opposite the pressure side, and a bucket squealer tip attached to the pressure side and the suction side. The bucket squealer tip includes a plurality of high hot hardness shroud-cutting deposits deposited on its exterior surface that have a hardness of at least about 1100 kg mm?2 and a melting temperature of at least about 1500° C.
    Type: Application
    Filed: November 26, 2013
    Publication date: May 28, 2015
    Applicant: General Electric Company
    Inventors: Srikanth Chandrudu Kottilingam, Surinder Singh Pabla, Brian Lee Tollison
  • Patent number: 9032622
    Abstract: An elongate web is attached to the root end of a spar of a wind turbine rotor blade to provide additional support along the width of the blade. The root end is formed by a winding operation, and a recess is then cut into the surface of the spar. The recess is defined by a relatively large first, cylindrical surface, which is coaxial with the longitudinal axis of the root end, and a relatively small second, conical surface. A tapered end of the elongate web is attached within the recess of the root end using a layer of suitable adhesive and an array of pins. Resilient spacer elements are arranged within the recess so as to surround the pins. The large area of the cylindrical surface causes the tensile and compressive stresses which arise along the elongate web in use to be transmitted to the spar as shear stresses.
    Type: Grant
    Filed: December 12, 2011
    Date of Patent: May 19, 2015
    Assignee: Vestas Wind Systems A/S
    Inventors: Mark Hancock, Anton Bech, Rens Christiaan Verhoef, Adrian Gill, Karl Gregory
  • Patent number: 9032621
    Abstract: A method for manufacturing a work piece is provided. The method includes preparing fiberglass in a mold, preparing a closed mold cavity around the fiberglass, flushing the closed mold cavity with an oxygen-free gas, injecting resin in the closed mold cavity, and curing the casted work piece. Furthermore, a work piece manufactured by the above method is provided.
    Type: Grant
    Filed: June 24, 2011
    Date of Patent: May 19, 2015
    Assignee: SIEMENS AKTIENGESELLSCHAFT
    Inventor: Karsten Schibsbye
  • Patent number: 9011085
    Abstract: A Ceramic Matrix Composites (CMC) airfoil for a gas turbine engine includes at least one CMC ply which defines a suction side, an outer platform, a pressure side and an inner platform with a continuous “I”-shaped fiber geometry.
    Type: Grant
    Filed: May 26, 2011
    Date of Patent: April 21, 2015
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Ioannis Alvanos
  • Patent number: 8998581
    Abstract: An impeller for a turbo-machine and is provided. The impeller includes a metallic base having a central hole, a back surface and a front surface opposite to the back surface; at least one blade extending on the front surface of the metallic base; a composite shroud attached to the at least one blade such that plural closed paths or vanes are formed by the front surface of the metallic base, the at least one blade and the composite shroud; and a connector configured to attach the composite shroud to the metallic base or the at least one blade.
    Type: Grant
    Filed: May 7, 2010
    Date of Patent: April 7, 2015
    Assignee: Nuovo Pignone S.p.A.
    Inventors: Iacopo Giovannetti, Massimo Giannozzi, Dino Bianchi, Leonardo Tognarelli, Manuele Bigi, Andrea Massini
  • Publication number: 20150093249
    Abstract: Disclosed is a blade for a gas turbine, in particular for an aircraft engine, wherein the blade comprises at least one internal and/or external supporting structure of a metallic and/or intermetallic material. Also disclosed are a blade cluster having at least one such blade for a gas turbine, a method for producing such a blade cluster and a gas turbine.
    Type: Application
    Filed: September 26, 2014
    Publication date: April 2, 2015
    Inventors: Christine LANG, Guenter RAMM
  • Publication number: 20150093250
    Abstract: In one aspect, a rotor blade for a wind turbine may include a body extending between a root end and a tip end. The body may include a root portion extending from the root end. The root portion may include an inner surface defining an inner circumference. In addition, the rotor blade may include a root stiffener assembly disposed within the root portion of the body. The root stiffener assembly may include a plurality of stiffening ribs coupled to the root portion so as to extend along the inner surface.
    Type: Application
    Filed: September 30, 2013
    Publication date: April 2, 2015
    Applicant: General Electric Company
    Inventors: Bruce Clark Busbey, Darren John Danielsen
  • Publication number: 20150082634
    Abstract: A method of assembling a rotor blade assembly includes determining a first spanwise moment of a first component of the rotor blade assembly and comparing the first spanwise moment to a target first spanwise moment. The first spanwise moment of the first component is adjusted based on a result of the comparison. A second spanwise moment of a second component of the rotor blade assembly is determined and compared to a target second spanwise moment. The second spanwise moment of the second component is adjusted based on a result of the comparison. The first component is assembled to the second component, resulting in a rotor blade assembly meeting a target spanwise moment of the rotor blade assembly.
    Type: Application
    Filed: September 23, 2013
    Publication date: March 26, 2015
    Applicant: Sikorsky Aircraft Corporation
    Inventors: Kevin P. Leahy, Frank Caputo
  • Publication number: 20150086377
    Abstract: A method of making a metal reinforcing member that is to be mounted on a leading edge or a trailing edge of a composite blade of a turbine engine, the method including: shaping two metal sheets, positioning them on either side of a core including at least one recess that is to form a mold for a spacer for positioning the reinforcing member, assembling them together under a vacuum, conforming them against the core by hot isostatic compression, and cutting them to separate the reinforcing member and release the core.
    Type: Application
    Filed: May 31, 2013
    Publication date: March 26, 2015
    Applicant: SNECMA
    Inventors: Gilbert Michel Marin Leconte, Gilles Charles Casimir Klein, Jean-Michel Patrick Maurice Franchet, Dominique Magnaudeix
  • Patent number: 8985962
    Abstract: The invention relates to a stirrer organ (1) in composite construction comprised of a metallic part (4) and a hybrid casting (9), with the hybrid casting (9) being fixed to the metallic part (4) by means of at least one anchoring element which forms at least one back-cutting in the hybrid casting (9). Furthermore, the present invention relates to a method for rehabilitating a damaged metallic stirrer organ which when applied provides a rehabilitated stirrer organ (1) in composite construction. The invention tackles the task of creating a stirrer organ (1) in hybrid construction which features a largest possible metallic part (4) because higher strength can hereby be achieved. This task is inventively solved in that the anchoring element is provided with a perforated plate (5) which is spot-wise fastened to the metallic part (4) and which is arranged at least partly at a small distance to the surface of the metallic part (4) so as to configure the at least one back-cutting.
    Type: Grant
    Filed: December 22, 2010
    Date of Patent: March 24, 2015
    Assignees: SICcast Mineralguss GmbH & Co. KG, EKATO Ruehr- und Mischtechnik GmbH
    Inventor: Frank Hoffmann
  • Publication number: 20150064013
    Abstract: A composite assembly has an outer spar component having an outer spar component inner profile, an inner spar component having an inner spar component outer profile substantially complementary to the outer spar component inner profile, and an adhesive disposed between the outer spar component and the inner spar component.
    Type: Application
    Filed: August 30, 2013
    Publication date: March 5, 2015
    Applicant: Bell Helicopter Textron Inc.
    Inventors: Ronald J. Measom, Mitchell Elvin Rains
  • Patent number: 8967974
    Abstract: A composite blade assembly for mounting on a turbine wheel includes a ceramic airfoil and an airfoil platform. The ceramic airfoil is formed with an airfoil portion, a blade shank portion and a blade dovetail tang. The metal platform includes a platform shank and a radially inner platform dovetail. The ceramic airfoil is captured within the metal platform, such that in use, the ceramic airfoil is held within the turbine wheel independent of the metal platform.
    Type: Grant
    Filed: January 3, 2012
    Date of Patent: March 3, 2015
    Assignee: General Electric Company
    Inventor: Andres Jose Garcia-Crespo
  • Patent number: 8961143
    Abstract: A rotor blade of a wind power plant in which the rotor blade has a longitudinal extension that extends from a rotor blade root substantially to a rotor blade tip. At least in one region of the rotor blade, an aerodynamic cross-sectional profile is provided, which has a leading edge (nose) and a trailing edge, which are connected via a suction side and a pressure side of the cross-sectional profile. The rotor blade is subdivided at least in a longitudinally extended section into a front rotor blade section with the leading edge and a rear rotor blade section with the trailing edge. The rear region of the front rotor blade section and the adjacent front region of the rear rotor blade section are connected through an I-beam.
    Type: Grant
    Filed: June 15, 2010
    Date of Patent: February 24, 2015
    Assignee: Repower Systems AG
    Inventors: Jens Kulenkampff, Claus Weegen, Mario Kontis
  • Publication number: 20150044054
    Abstract: A retention feature for use in a gas turbine engine is disclosed herein. The retention feature includes a ceramic post, an insert, and a braze layer coupling the insert to the ceramic post. The ceramic post includes a body adapted to be coupled to a turbine engine component and a head coupled to the body. The insert is arranged in a space formed in the head and the braze layer extends from the ceramic post to the insert to bond the insert to the ceramic post.
    Type: Application
    Filed: December 2, 2013
    Publication date: February 12, 2015
    Inventors: Peter Loftus, Adam L. Chamberlain, Ted J. Freeman
  • Publication number: 20150040396
    Abstract: Multilayer weaving is used to form a fiber blank having a longitudinal direction corresponding to the longitudinal direction of the vane to be made and comprising across its thickness a first woven portion with a plurality of layers of yarns interlinked by weaving, and also a second and third woven portions. The first portion is situated between the second and third portions and interlinked thereto by weaving over only a fraction of its longitudinal dimension. A preform for the vane is formed by folding out, on either side of the first portion, segments of the second and third portions not interlinked with the first portion, by shaping the first portion to form a preform portion for the airfoil of the vane, and by shaping the folded-out segments of the second and third portions to form preform portions for the inner and outer platforms of the vane to be fabricated.
    Type: Application
    Filed: November 26, 2012
    Publication date: February 12, 2015
    Applicants: HERAKLES, SNECMA
    Inventors: Elric Fremont, Romain Nunez, Max Massot
  • Publication number: 20150037165
    Abstract: A turbine blade is provided and includes pressure and suction surfaces connected to define an interior through which coolant is passable and first and second pedestal arrays, each of the first and second pedestal arrays including pedestals respectively coupled to radially outboard portions of respective interior faces of one of the pressure and suction surfaces. The pedestals of the first pedestal array are separated from pedestals of the second pedestal array by gaps respectively defined therebetween.
    Type: Application
    Filed: July 31, 2013
    Publication date: February 5, 2015
    Applicant: General Electric Company
    Inventors: Mark Andrew Jones, Bradley Taylor Boyer, Robert Alan Brittingham, Gregory Thomas Foster, Christopher William Kester
  • Publication number: 20150033561
    Abstract: A method for hardfacing a surface including: depositing a powder (68) having alloy particles onto a surface (70) of a substrate (66); rastering a laser beam (60) across the surface to melt the powder and to form a weld pool (78) having a width (64); directing particles (74) of a material exhibiting a different property than the substrate into the weld pool in a spray pattern having a width less than the width of the weld pool; and establishing the rastering and directing steps such that material circulation within the weld pool is effective to distribute the particles in the weld pool into a pattern having a width greater than the width of the spray pattern prior to re-solidification of the weld pool.
    Type: Application
    Filed: August 1, 2013
    Publication date: February 5, 2015
    Inventors: Gerald J. Bruck, Ahmed Kamel
  • Publication number: 20150017009
    Abstract: A blade of an impeller has a blade surface made up of line elements. The line elements forming the blade surface are not parallel to each other. A relationship between a twist angle of the line elements and a distance between the origin and an intersection of a central line of the impeller and an extension line of a Z-axis projection line obtained by projecting each of the line elements onto a Z-axis projection plane is represented by a curve.
    Type: Application
    Filed: July 9, 2014
    Publication date: January 15, 2015
    Inventor: Shinji OKUDA
  • Publication number: 20150017018
    Abstract: A turbine component is provided. The turbine component includes an airfoil having a first surface and a second surface. A thermal barrier coating is coupled to the second surface, wherein the thermal barrier coating includes a first portion, a second portion and a trench defined between the first and second portions. A channel is coupled in flow communication to the first surface and the trench, wherein the channel includes a first sidewall and a second sidewall opposite of the first sidewall. The first and second sidewalls extend from the first surface and toward the trench at an angle. The turbine component includes a cover coupled to the second surface, wherein the cover includes a first end coupled to the first portion and a second end extending into the trench and spaced from the second portion.
    Type: Application
    Filed: July 12, 2013
    Publication date: January 15, 2015
    Inventors: Benjamin Paul Lacy, Brian Gene Brzek, Srikanth Chandrudu Kottilingam, David Edward Schick
  • Publication number: 20150017003
    Abstract: A gas turbine engine bladed component, such as a turbine blade, is shown as including a shroud located above a blade portion and a stiffener located above the shroud. The stiffener is generally located in a central interior region of the shroud and includes a raised portion that extends above a top surface of the shroud. In one non-limiting form the stiffener can have a central ridge that is oriented in an axial direction. Seal members can be included in the shroud that can be used to interact with corresponding seal members in static gas turbine engine structure to discourage a flow of fluid. In one form the shroud includes an upturned leading edge portion.
    Type: Application
    Filed: December 31, 2013
    Publication date: January 15, 2015
    Inventor: Don L. Shaffer
  • Publication number: 20150010405
    Abstract: A manufacturing method for a wind turbine blade is described which utilises a post-moulding station in the manufacturing process. A blade shell forming part of a wind turbine blade is initially moulded in a blade mould, the blade shell subsequently transferred to a post-moulding station which allows for various post-moulding operations to be carried out on the blade shell away from the mould, thereby increasing the productivity of the blade mould in the manufacturing process. The post-moulding station may be operable to perform the closing of first and second blade shells to form a wind turbine blade, and may be formed from an adjustable structure which can provide relatively easy access to the contained blade shell for working thereon. Accordingly, the manufacturing equipment may be of reduced cost, combined with an increase in the overall productivity of the manufacturing system.
    Type: Application
    Filed: January 31, 2013
    Publication date: January 8, 2015
    Inventor: Bernard Willem De Waal Malefijt
  • Publication number: 20150010396
    Abstract: A device such as a drum for positioning at least one guide blade row from a plurality of guide blade groups in a turbomachine, the device on the outer circumferential side including at least one flange for attachment to a housing section of the turbomachine and on the inner circumferential side including a plurality of uniformly distributed receptacles for accommodating holding elements of the guide blade groups and a plurality of recesses, the device having a depth-reduced inner circumferential section, relative to the accommodating grooves, between at least two adjoining receptacles, which extends in each case from the one receptacle to the other receptacle; a blade-device combination; a method for assembling such a blade-device combination; and a turbomachine.
    Type: Application
    Filed: July 3, 2014
    Publication date: January 8, 2015
    Inventors: Hans STRICKER, Stefan Rauscher, Willem Bokhorst
  • Publication number: 20150003994
    Abstract: A wind turbine blade is provided. The wind turbine blade includes a root region, a tip region, and a body extending from the root region to the tip region. The tip region includes a first winglet and a second winglet that extend arcuately away from one another.
    Type: Application
    Filed: June 27, 2013
    Publication date: January 1, 2015
    Inventors: Mark Edward Braaten, Anurag Gupta, Arathi Kamath Gopinath
  • Publication number: 20150004000
    Abstract: A method for making a gas turbine engine ceramic matrix composite airfoil is disclosed. The method includes fabricating an airfoil preform that has a slotted forward end and a continuous trailing end. The slotted forward end of the airfoil preform is coupled to an airfoil core insert. A ceramic matrix composite covering is applied to cover the slots of the airfoil perform. The continuous trailing end of the airfoil preform is removed to expose the slots. A gas turbine engine airfoil is also disclosed.
    Type: Application
    Filed: December 26, 2013
    Publication date: January 1, 2015
    Inventors: Ted J. Freeman, Richard C. Uskert
  • Publication number: 20150003997
    Abstract: A monolithic composite turbine component includes at least one first region of a first material and one second region of a second material formed by solid freeform fabrication (SFF). The first material may be a metal and the second material may be a ceramic or a ceramic matrix composite. Transition regions between the metal region and ceramic region are functionally graded regions to minimize internal stress during temperature fluctuations.
    Type: Application
    Filed: July 1, 2014
    Publication date: January 1, 2015
    Inventors: Sergey Mironets, Alexander Staroselsky, Thomas J. Martin, Thomas N. Slavens
  • Patent number: 8918997
    Abstract: A method provides for assembling a wind turbine blade from at least two blade segments, with each of the blade segments having a pressure side shell member, a suction side shell member, internal support structure, and ends with joint sections that are offset span-wise from the pressure side shell member to the suction side shell member. The blade segments are aligned in an end-to-end orientation and moved into a mating configuration with relative movement that includes overlapping the respective joint sections of adjacent blade segments. The overlapped joint sections are subsequently moved into engagement with each other and joined along respective joint profiles at a chord-wise joint.
    Type: Grant
    Filed: October 13, 2011
    Date of Patent: December 30, 2014
    Assignee: General Electric Company
    Inventors: Steven Alan Kyriakides, Scott Gabell Riddell, Alan Majors Walker