Blade Making Patents (Class 29/889.7)
  • Patent number: 10669856
    Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 0.75-0.85 inch (19.1-21.6 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 0.56-0.66 inch (14.2-16.8 mm). The airfoil element includes at least two of a first mode with a frequency of 2740±10% Hz, a second mode with a frequency of 5956±10% Hz, a third mode with a frequency of 6554±10% Hz and a fourth mode with a frequency of 31959±10% Hz.
    Type: Grant
    Filed: January 12, 2018
    Date of Patent: June 2, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Charles H. Warner, William R. Edwards, Mark David Ring, Sean Nolan, Ernest D. Casparie
  • Patent number: 10598158
    Abstract: A method for detaching or installing a rotor blade from or to a hub of a wind turbine includes positioning the rotor blade toward a ground location between a three o'clock position and a nine o'clock position. The method also includes mounting a mechanical arm to an uptower location of the wind turbine. Further, the mechanical arm includes a torqueing tool at a distal end thereof. Thus, the method also includes removing or installing, via the torqueing tool, each of the plurality of hub fasteners so as to detach or attach the rotor blade from or to the hub.
    Type: Grant
    Filed: July 20, 2017
    Date of Patent: March 24, 2020
    Assignee: General Electric Company
    Inventors: Paul Howard Davidson, Stephanie Lohberg Willman, Santiago Murcia, Joshua Adam Klinghagen, Gregory Clarence Thomas, Michael Royce Johnson, Don Conrad Johnson, Ulrich Werner Neumann, Adam Sean Davis, Dean Thomas Roney, Kathleen Lynne Bentzel
  • Patent number: 10584598
    Abstract: A cantilevered airfoil includes, among other things, an airfoil having a body section and a tip, the body section extending in a first direction that is angled relative to a radial direction, the tip of the airfoil angled radially in a second direction relative to the body section.
    Type: Grant
    Filed: March 14, 2013
    Date of Patent: March 10, 2020
    Assignee: United Technologies Corporation
    Inventors: Matthew E. Bintz, Peter T. Schutte, Brian J. Schuler, Anthony R. Bifulco
  • Patent number: 10436044
    Abstract: The invention relates to a guide vane cluster for a turbomachine, in particular for a turbojet engine, having at least two vanes that are joined together by way of at least one common platform for the radial delimiting of a flow channel of the turbomachine, wherein each vane has a vane element with a suction side and a pressure side that are joined together by a leading edge and a trailing edge, wherein the at least two vanes have different trailing edge wall thicknesses at least in a corresponding radial lengthwise extension region.
    Type: Grant
    Filed: December 2, 2016
    Date of Patent: October 8, 2019
    Assignee: MTU Aero Engines AG
    Inventors: Markus Schlemmer, Martin Pernleitner, Nina Wolfrum, Markus Brettschneider, Inga Mahle
  • Patent number: 10400611
    Abstract: The invention relates to a blade for a turbomachine a shroud for such a blade, and a turbomachine having at least one such blade. The blade comprises a shroud which is positioned on the blade tip side of the blade and is stiffened in the region of its surface by means of a stiffening structure having at least one longitudinal stiffening element such as a rib. The height of the longitudinal stiffening element varies in the circumferential direction.
    Type: Grant
    Filed: January 28, 2016
    Date of Patent: September 3, 2019
    Assignee: MTU AERO ENGINES AG
    Inventors: Marcin Kozdras, Krzysztof Skura, Piotr Lebiedowicz, Marek Szponar
  • Patent number: 10280781
    Abstract: An exemplary shroud milling method includes milling a convex side of a shroud, milling a concave side of the shroud, and holding a shroud within a common fixture when milling the convex side and when milling the concave side.
    Type: Grant
    Filed: December 19, 2013
    Date of Patent: May 7, 2019
    Assignee: Pratt & Whitney Services PTE LTD.
    Inventor: Kim Wei Cheah
  • Patent number: 10280758
    Abstract: A composite vane for a low-pressure compressor of an axial-flow turbomachine, wherein the vane comprises a platform and an aerodynamic airfoil having a leading edge and a trailing edge. The airfoil extends into the primary flow of the turbomachine. The airfoil includes a body extending from the leading edge to the trailing edge and a reinforcement of the leading edge of the airfoil. The reinforcement comprises a reinforcing sheet, which extends from the leading edge to the trailing edge, and which is arranged in the thickness of the body in such a way as to reinforce it. In addition, the reinforcement comprises a shell forming the leading edge and which is integral with the sheet. The sheet is a titanium sheet, and the body includes a composite material having an organic matrix charged with fibers. This configuration improves the rigidity and the resistance to corrosion while lightening the airfoil.
    Type: Grant
    Filed: February 25, 2016
    Date of Patent: May 7, 2019
    Assignee: SAFRAN AERO BOOSTERS SA
    Inventor: Jean-François Cortequisse
  • Patent number: 10245678
    Abstract: A management method of a powder supply head in which supplied cladding metal is stabilized, and a method and apparatus for forming an erosion shield. The powder supply head has a double tube that supplies the cladding metal to a cladding portion and includes an inner tube that sprays a cladding metal used for cladding by welding and an outer tube that concentrically overlaps the inner tube and sprays a shielding air. The method including: spraying the cladding metal from the powder supply head to a test region; measuring a width of the cladding metal sprayed onto the test region; in a case where the measured width of the cladding metal is an allowance or smaller, determining that the powder supply head is usable, and in a case where the measured width of the cladding metal is greater than the allowance, determining that the powder supply head is unusable.
    Type: Grant
    Filed: April 1, 2015
    Date of Patent: April 2, 2019
    Assignee: MITSUBISHI HITACHI POPOWER SYSTEM, LTD.
    Inventors: Takehisa Okuda, Motonari Machida, Yasuo Matsunami
  • Patent number: 10208602
    Abstract: A film cooled component may comprise a cooling chamber and a first ligament centered about a first axis. The first ligament may be in fluid communication with the cooling chamber. A first meter may be disposed at an end of the first ligament. A first diffuser may extend from the first meter to a surface of the film cooled component. The first diffuser may comprise a first tapered sidewall oriented at an angle of between 5 degrees to 15 degrees relative to the first axis. The first diffuser may further comprise a first non-tapered sidewall oriented at an angle less than 5 degrees relative to the first axis.
    Type: Grant
    Filed: April 27, 2015
    Date of Patent: February 19, 2019
    Assignee: United Technologies Corporation
    Inventors: Lane Thornton, Ryan Alan Waite, Peter Balawajder, Benjamin F. Hagan
  • Patent number: 10211126
    Abstract: This invention relates to a method of manufacturing an object with microchannels provides therethrough, and more particularly, but not exclusively, to a method of manufacturing a micro heat exchanger with microchannels provided therethrough. The method includes the steps of providing a metal base layer made from a first metal; forming a plurality of spaced apart ridges, made from a second metal, on the base layer; depositing more of the first metal onto the ridges in order to cover the ridges; and removing the ridges using a chemical etching process so as to produce microchannels in a body made of the first metal.
    Type: Grant
    Filed: October 13, 2015
    Date of Patent: February 19, 2019
    Assignee: UNIVERSITY OF THE WITWATERSRAND, JOHANNESBURG
    Inventors: Agripa Hamweendo, Ionel Botef
  • Patent number: 10066492
    Abstract: A turbomachine blade having a metal coupling root, and a metal airfoil-shaped oblong member cantilevered projecting from the coupling root; the airfoil-shaped oblong member being divided into: a lower connecting fin cantilevered projecting from and formed in one piece with the coupling root; an upper connecting fin cantilevered projecting from a coupling head towards the coupling root and formed in one piece with the coupling head; and a main plate-like body which is shaped and positioned between the two connecting fins to form an extension of the fins, and is butt-welded to the same connecting fins to form one piece with the fins.
    Type: Grant
    Filed: March 7, 2017
    Date of Patent: September 4, 2018
    Assignee: Pietro Rosa T.B.M. S.r.l.
    Inventor: Andrea Maurizio
  • Patent number: 10060277
    Abstract: A turbine wheel for use in a gas turbine engine having a plurality of blades attached to a rotor disk. Each blade is formed from a composite comprising ceramic matrix material. The blades each include a root that fits within dovetail slots of the rotor disk and cooperates with a blade retention assembly to couple the blades to the rotor disk.
    Type: Grant
    Filed: December 18, 2015
    Date of Patent: August 28, 2018
    Assignees: Rolls-Royce North American Technologies, Inc., Rolls-Royce Corporation
    Inventors: Todd Z. Engel, Ted J. Freeman, Robert J. Shinavski, Ian Thomson
  • Patent number: 10046482
    Abstract: A method of fabricating a turbine engine blade out of composite material including fiber reinforcement densified by a matrix, the method including using multilayer weaving to make a first fiber that has a first portion forming a blade root preform and extended by a second portion, the second portion forming a tenon preform; using multilayer weaving to make a second fiber preform, the second preform including a first portion made up of two skins defining between them an internal housing, the first portion forming an airfoil preform, and a second portion extending from an outside surface of the skins, the second portion forming a platform preform; assembling the first preform with the second preform in the non-consolidated state by engaging the second portion of the first preform in the internal housing; and co-densifying the first and second preforms as assembled together in this way to obtain a turbine engine blade.
    Type: Grant
    Filed: February 9, 2016
    Date of Patent: August 14, 2018
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: David Marsal, Clément Roussille, Jérémy Blachier
  • Patent number: 10047612
    Abstract: A method and device for manufacturing turbine blades (5; 7; 28; 33) made of a metal alloy. Starting with aluminum and titanium alloy bar (10; 34) having a simple and/or axisymmetric shape, at least two mutually interlocking blanks (2; 3; 4; 8; 11) are produced in the bar (10; 34) by waterjet cutting (16) and then each one of the blanks (2; 3; 4; 8; 11) thus obtained is machined separately in order to obtain the blades (5; 7; 28; 33) having a final profile.
    Type: Grant
    Filed: November 8, 2013
    Date of Patent: August 14, 2018
    Assignee: Mechachrome France
    Inventors: Arnaud De Ponnat, Olivier Martin
  • Patent number: 10012976
    Abstract: A method for manufacturing a turbine engine blade including an airfoil with a profile defined by a theoretical digital model, the method including: manufacturing a blank having a thickened portion along a trailing edge of the airfoil relative to the theoretical profile; removing the thickened portion by adaptive machining, including: positioning the blank in a reference frame; acquiring, by probing at a predetermined number of points on a first surface of the blank along the trailing edge, positions of the points in the reference frame; determining differences, in one direction, in position from corresponding points of the theoretical model; producing machining grids on the blank surface, peaks of the grids determined from the points; determining an amount of material to be removed from the surface of the grids, based on the position of the points relative to the peaks and the deviations in position; and machining the airfoil.
    Type: Grant
    Filed: April 22, 2013
    Date of Patent: July 3, 2018
    Assignee: SNECMA
    Inventors: Yvon Marie-Joseph Louesdon, Florian Le Merdi, Joseph Tami, Daniel Quach, Fadoua Cisse, Sabine Maltaverne, Damien Alquier
  • Patent number: 9938833
    Abstract: Methods, systems, and devices for designing and manufacturing flank millable components. In one embodiment, devices, systems, and methods for designing a flank millable component are provided, in which a user is notified when a component geometry option is selected that will result in the component not being flank millable. In another embodiment, the user is prevented from selecting a geometry option that would result in the component not being flank millable. In yet another embodiment, devices, systems, and methods are provided for manufacturing a component with a flank milling process, in which optimized machine instructions are determined that minimize milling machine motion.
    Type: Grant
    Filed: September 29, 2016
    Date of Patent: April 10, 2018
    Assignee: Concepts NREC, LLC
    Inventors: Derek J. Cooper, Alexander Plomp, David Japikse
  • Patent number: 9932661
    Abstract: Disclosed is a process for producing a high-temperature protective coating for metallic components, in particular components of turbomachines which are subjected to thermal loading. The process comprises producing a slip from MCrAlY powder, in which M is at least one metal, and from a Cr powder, applying the slip to the component to be coated and subsequently alitizing the component provided with the slip.
    Type: Grant
    Filed: April 23, 2014
    Date of Patent: April 3, 2018
    Assignee: MTU AERO ENGINES AG
    Inventor: Heinrich Walter
  • Patent number: 9919457
    Abstract: A method for forming a preform for a hollow turbomachine component is provided. The method includes positioning a sheet made of woven fibers on a base equipped with a longitudinal impression; positioning a mandrel in the longitudinal impression to clamp the sheet between the base and the mandrel, the mandrel having a thickness that increases between a proximal end and a distal end; locking the distal end of the mandrel into position; placing a proximal block resting on the base; forming two flaps of the sheet around the flanks of the mandrel; resting two lateral blocks on the base on either side of the mandrel; locking the lateral blocks into position to form an assembly; drying the assembly to form a preform including a flat base, from which two flaps extend perpendicularly; and adjusting the flaps to the dimensions of the mandrel by trimming excess material.
    Type: Grant
    Filed: August 14, 2013
    Date of Patent: March 20, 2018
    Assignee: SNECMA
    Inventors: Richard Mathon, Dominique Magnaudeix, Noemie Souhaite, Yann Marchal, Matthieu Gimat
  • Patent number: 9863254
    Abstract: A turbine airfoil for a gas turbine engine including an outer peripheral wall having an external surface, the outer peripheral wall enclosing an interior space and including a concave pressure sidewall and a convex suction sidewall joined together at a leading edge and at a trailing edge; wherein the outer peripheral wall has a varying wall thickness which incorporates a locally-thickened wall portion; and a film cooling hole having a shaped diffuser exit passing through the outer peripheral wall within the locally-thickened wall portion.
    Type: Grant
    Filed: April 23, 2013
    Date of Patent: January 9, 2018
    Assignee: General Electric Company
    Inventors: Christopher Michael Ceglio, Randall Charles Bauer, Stephen Mark Molter, Mark Edward Stegemiller
  • Patent number: 9835114
    Abstract: A method is provided for fabricating a coolant channel closeout jacket on a structure having coolant channels formed in an outer surface thereof. A line of tangency relative to the outer surface is defined for each point on the outer surface. Linear rows of a metal feedstock are directed towards and deposited on the outer surface of the structure as a beam of weld energy is directed to the metal feedstock so-deposited. A first angle between the metal feedstock so-directed and the line of tangency is maintained in a range of 20-90°. The beam is directed towards a portion of the linear rows such that less than 30% of the cross-sectional area of the beam impinges on a currently-deposited one of the linear rows. A second angle between the beam and the line of tangency is maintained in a range of 5-65°.
    Type: Grant
    Filed: June 6, 2017
    Date of Patent: December 5, 2017
    Assignee: The United States of America as Represented by the Administrator of NASA
    Inventors: Paul R. Gradl, David Christopher Reynolds, Bryant H. Walker
  • Patent number: 9752445
    Abstract: Coupled turbine vanes having an axis are produced by arranging a plurality of first fabrics of ceramic fibers in radial directions relative to the axis to constitute a plurality of vane sections, arranging a second fabric of the ceramic fibers in a circumferential direction relative to the axis, connecting the first fabrics with the second fabric by bending first ends of the first fabrics to lay them on the second fabric in parallel, and impregnating the plurality of first fabrics connected with the second fabric with the matrix.
    Type: Grant
    Filed: September 8, 2014
    Date of Patent: September 5, 2017
    Assignee: IHI Corporation
    Inventor: Fumiaki Watanabe
  • Patent number: 9624783
    Abstract: A turbomachine blade of the type having a metal lower coupling root, a metal upper coupling head, and a metal airfoil-shaped oblong member designed to connect the coupling root rigidly to the coupling head; the airfoil-shaped oblong member having a substantially airfoil-shaped main plate-like element connected to the coupling root and to the coupling head, and which is divided into: a lower connecting fin cantilevered from and formed in one piece with the coupling root; an upper connecting fin cantilevered from and formed in one piece with the coupling head; and a center plate-like body, which is located between the lower and upper connecting fins, is shaped/designed to form an extension of the lower and upper connecting fins, and is butt-welded to, to form one piece with, the lower and upper connecting fins.
    Type: Grant
    Filed: February 28, 2014
    Date of Patent: April 18, 2017
    Assignee: PIETRO ROSA T.B.M. S.R.L.
    Inventor: Andrea Maurizio
  • Patent number: 9556745
    Abstract: A plate closes the main part of a vane in two parts. An internal cavity is closed by the plate. Around a bearing surface of the plate, a groove receives an elastic seal, and the outer edge of the plate extends over the groove to compress the seal and to establish excellent leak proofing. The position of the plate may be guaranteed by centring pins penetrating into holes adjacent to the seal and which it fills when the pins have been removed, which completes the closing of the cavity. The plate has application in particular to stationary gas guide vanes in turbine engines.
    Type: Grant
    Filed: July 17, 2012
    Date of Patent: January 31, 2017
    Assignee: SNECMA
    Inventors: Thierry Georges Paul Papin, Lise Lacroix, Dominique Raulin
  • Patent number: 9534498
    Abstract: A vane includes a platform with a fixture overmolded by a sheath.
    Type: Grant
    Filed: December 14, 2012
    Date of Patent: January 3, 2017
    Assignee: United Technologies Corporation
    Inventor: David R. Lyders
  • Patent number: 9479028
    Abstract: An automotive rotary electric machine has a cooling fan including a flat ring-shaped mounting base plate fixed to a rotor, and a plurality of fan blades arranged in a row circumferentially such that each stands on a surface of the mounting base plate, the fan blades having an S-shaped cross-sectional shape that displaces gradually forward in a direction of rotation from a trailing edge that is an outer circumferential edge toward a leading edge that is an inner circumferential edge, and in which an arc shape near the trailing edge that is convex forward in the direction of rotation and an arc shape near the leading edge that is convex rearward in the direction of rotation are connected smoothly.
    Type: Grant
    Filed: June 26, 2013
    Date of Patent: October 25, 2016
    Assignee: Mitsubishi Electric Corporation
    Inventors: Masao Akiyoshi, Yuzuru Kobayashi, Kazunori Tanaka, Yoshihiro Shinosaka, Yoshiro Imazawa
  • Patent number: 9346141
    Abstract: A joining device for arranging a component on a component carrier is disclosed. The joining device includes an application system for positioning the component in the joining device and a receptacle for clamping the component carrier in the joining device. The component is arranged on the component carrier by an adapter. A method for arranging the component on the component carrier is also disclosed.
    Type: Grant
    Filed: July 7, 2010
    Date of Patent: May 24, 2016
    Assignee: MTU Aero Engines GmbH
    Inventors: Martin Fessler-Knobel, Roland Huttner
  • Patent number: 9291151
    Abstract: The present invention provides a wind turbine blade of hybrid material composition, wherein the blade comprises a structural box mainly made of a epoxy based prepreg and a shell manufactured by resin infusion technique using polyester or vinylester, and the box and the shell are bonded using an adhesive that is not a polyester, a vinylester and an epoxy. The present invention also provides a method for producing such a blade.
    Type: Grant
    Filed: September 20, 2010
    Date of Patent: March 22, 2016
    Assignee: SUZHOU RED MAPLE WIND BLADE MOULD CO., LTD.
    Inventor: Gabriel Mironov
  • Patent number: 9266166
    Abstract: Plural saddle shape patches are formed on a blank material for forming a blade using a manufacturing apparatus provided with a punch support having punches each with a holder attached to be opposite with one another at a predetermined interval corresponding to a thickness of the blank material. The punch support is mounted to a second ram via a second rotational mechanism which is rotatable in a direction in which the ram moves. The die is attached to the first ram via the first rotational mechanism. The actuator controls the rotating angles of both the rotational mechanisms.
    Type: Grant
    Filed: December 13, 2012
    Date of Patent: February 23, 2016
    Assignee: HITACHI, LTD.
    Inventors: Tetsuya Yagami, Toshiya Teramae, Koji Hayashi, Kazutoshi Yanagihara, Ryouichi Kataoka
  • Patent number: 9228445
    Abstract: Hybrid turbine airfoil components containing a ceramic material, in which detailed features of the components are formed of materials other than ceramic materials. The components include a first component formed of a ceramic-based material and a second component formed of a metallic material. The first component comprises an airfoil portion and a nub, and the second component is separately formed and attached to the first component by casting the metallic material around the nub of the first component. The second component includes a platform portion between the airfoil portion and the nub of the first component and a dovetail portion on the nub of the first component. Each of the platform and dovetail portions has at least one off-axis geometric feature that results in the second component having a more complex geometry than the first component.
    Type: Grant
    Filed: December 23, 2010
    Date of Patent: January 5, 2016
    Assignee: General Electric Company
    Inventors: Toby George Darkins, Jr., John Peter Heyward, Eric Alan Estill, Joshua Brian Jamison, James Herbert Deines, Mark Willard Marusko, James Thomas Hawkins
  • Patent number: 9091277
    Abstract: Multipart shrouded impellers and methods for manufacturing multi-part shrouded impellers are described. Components of the shrouded impeller include alignment features that, when brought into contact, provide concentric and spatial alignment of the component parts. Upon alignment a gap remains between portions of the components, which permits the introduction of a filler material that joins the components into a unitized whole.
    Type: Grant
    Filed: April 25, 2014
    Date of Patent: July 28, 2015
    Assignee: Computer Assisted Manufacturing Technology Corporation
    Inventor: Lance A. Young
  • Publication number: 20150147180
    Abstract: Aerodynamic root adapters for rotor blades include an interior support section having a first end that connects to a root end of the rotor blade and a second end that connects to a rotor hub of the wind turbine, and, an aerodynamic exterior section supported by the interior support section. The aerodynamic exterior section thereby extends an aerodynamic profile of the rotor blade beyond the root end of the rotor blade to at least partially between the root end of the rotor blade and the rotor hub when the aerodynamic root adapter is connected thereto.
    Type: Application
    Filed: November 22, 2013
    Publication date: May 28, 2015
    Applicant: General Electric Company
    Inventors: Saravakota Sambamurty, Mohan Muthu Kumar Sivanantham, Afroz Akhtar
  • Publication number: 20150143696
    Abstract: An apparatus for assembling blade sections for forming a blade is provided. The apparatus comprises at least two members (1, 2) movable with respect to each other, said members having respective opposing surfaces (2A, 2B) forming a pressing space for pressing outer surfaces of preassembled blade sections in a transition between the sections.
    Type: Application
    Filed: May 28, 2013
    Publication date: May 28, 2015
    Applicant: youWINenergy GmbH
    Inventor: Rolf Rohden
  • Publication number: 20150139789
    Abstract: An array of flow-directing elements for a compressor of a gas turbine including at least one first flow-directing element and at least one second flow-directing element different from the first flow-directing element; the flow-directing elements each having a leading edge facing the gas turbine inlet, a trailing edge, a pressure side connecting them and located ahead in the direction of rotation, a suction side located opposite thereof, as well as successive chords along a stacking axis; the flow-directing elements each extending between an airfoil root proximate to the rotor and an airfoil tip remote from the rotor. The trailing edge of the first flow-directing element is, at least in a portion thereof, axially offset from the trailing edge of the second flow-directing element in a direction toward the leading edge at least in a half proximate to the airfoil tip.
    Type: Application
    Filed: October 7, 2014
    Publication date: May 21, 2015
    Inventor: Harald Schoenenborn
  • Publication number: 20150139810
    Abstract: Rotor blade assemblies and methods for constructing rotor blade assemblies are provided. A rotor blade assembly may include a rotor blade having exterior surfaces defining a pressure side, a suction side, a leading edge and a trailing edge each extending between a tip and a root, the rotor blade defining a span and a chord. The rotor blade assembly further includes an extension plate mounted to one of the pressure side or the suction side, the extension plate extending in the chord-wise direction between a first end and a second end, the second end extending beyond the trailing edge. The rotor blade assembly further includes a filler substrate provided on an inner surface of the extension plate and the trailing edge, the filler substrate tapering from the trailing edge towards the second end.
    Type: Application
    Filed: November 20, 2013
    Publication date: May 21, 2015
    Applicant: General Electric Company
    Inventor: Kevin Wayne Kinzie
  • 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: 9027245
    Abstract: A method for producing a solid component which in succession includes deforming a metal bar by forging using two dies in order to obtain an intermediate component including two fins one on each side of a solid part capable of forming the base of the metal reinforcement, the two fins being at a divergent angle ?; deforming the two fins of the intermediate component, altering the divergent angle ?, so as to obtain the final shape of the turbomachine blade leading edge or trailing edge metal reinforcement.
    Type: Grant
    Filed: June 23, 2011
    Date of Patent: May 12, 2015
    Assignee: Snecma
    Inventors: Christine Hottier, Bertrand Lamaison, Jacques Abousefian
  • Publication number: 20150125308
    Abstract: A method of manufacturing a filled aerofoil component (100) for a gas turbine engine (10) comprises using a capping panel (200) to cover a pocket (310) in a pocketed aerofoil body (300). During manufacture, a pre-formed filler insert (400) is provided to support the capping panel (200) in the correct position. This ensures that the outer surface of the capping panel (200) is located as accurately as possible. This means that the capping panel (200) can be made to be as thin as possible, which in turn reduces weight and material wastage. The pre-formed filler insert (400) provides a lightweight core for the finished aerofoil component in use.
    Type: Application
    Filed: September 2, 2014
    Publication date: May 7, 2015
    Inventor: Steven Aleksy RADOMSKI
  • Publication number: 20150113779
    Abstract: The present invention provides a method for installing at least one sensor device within a rotor blade of a wind turbine. A first substantially planar light beam is emitted in the interior of the rotor blade. Finally, at least one second substantially planar light beam is emitted in the interior of the rotor blade, wherein the plane of the first planar light beam is oriented at a predetermined angle to the plane of the second planar light beam. Further, the planes of the first and second planar light beams are aligned on the blade flange of the rotor blade. At least one sensor device is subsequently aligned in reference to the planar light beams.
    Type: Application
    Filed: June 4, 2013
    Publication date: April 30, 2015
    Inventors: Thorbjörn Buck, Lars Hoffmann, Mathias Müller, Rolf Wojtech
  • Patent number: 9015942
    Abstract: A method of imparting deep compressive residual stress to an aerofoil, the method involves determining a stress map for the aerofoil for stress generated by Foreign Object (FOD) impact, a stress map for the aerofoil of high cycle fatigue, a stress map for the aerofoil of low cycle fatigue and determining a combined stress map by combining the stress map of FOD impact, the stress map of high cycle fatigue and the stress map of low cycle fatigue. A zone is then defined on the aerofoil from the combined stress map for receiving the deep residual compressive stress, and compressive residual stress imparted to the defined zone.
    Type: Grant
    Filed: June 28, 2012
    Date of Patent: April 28, 2015
    Assignee: ROLLS-ROYCE plc
    Inventor: Ian C. D. Care
  • Publication number: 20150110632
    Abstract: A blade assembly for a wind turbine rotor is provided, the blade assembly comprising at least two blade sections (1, 2) being longitudinally joinable at respective joining end portions (10, 20) for forming a blade. One of said blade sections has at least one cavity (11) in its joining end portion (10) and the other of said blade sections has at least one protrusion (21) at its joining end portion (20). Said cavity (11) is contractible to a contracted position in a direction which is substantially perpendicular to a longitudinal direction of the blade.
    Type: Application
    Filed: May 28, 2013
    Publication date: April 23, 2015
    Applicant: youWINenergy GmbH
    Inventor: Rolf Rohden
  • Patent number: 9003657
    Abstract: A manufacturing method includes providing a substrate with an outer surface and at least one interior space and machining the substrate to selectively remove a portion of the substrate and define one or more cooling supply holes therein. Each of the one or more cooling supply holes is in fluid communication with the at least one interior space. The method further includes disposing an open cell porous metallic layer on at least a portion of the substrate. The open cell porous metallic layer is in fluid communication with the one or more cooling supply holes. A coating layer is disposed on the open cell porous metallic layer. The coating layer having formed therein one or more cooling exit holes in fluid communication with the open cell porous metallic layer. The substrate, the one or more cooling supply holes, the open cell porous metallic layer and the cooling exit holes providing a cooling network for a component.
    Type: Grant
    Filed: December 18, 2012
    Date of Patent: April 14, 2015
    Assignee: General Electric Company
    Inventors: Ronald Scott Bunker, Scott Andrew Weaver, Wayne Charles Hasz
  • Publication number: 20150098832
    Abstract: A system for relieving stress on a turbine rotor blade dovetail in a gas turbine is provided. At least one turbine rotor blade includes a dovetail that is axially insertable into a correspondingly-shaped slot defined in a turbine disk. At least one axially-extending tang is defined on the dovetail. At least one stress relief surface is defined in the at least one tang. The at least one stress relief surface extends along a central portion of a length of the tang. Accordingly, contact between the at least one tang and an inner surface of the slot is precluded, along the central portion, such that stresses generated by radially-directed forces along the central portion are reduced.
    Type: Application
    Filed: October 9, 2013
    Publication date: April 9, 2015
    Applicant: General Electric Company
    Inventors: Bradley Scott Carter, Michael Anthony Wondrasek
  • Publication number: 20150089809
    Abstract: A method of engineering a turbomachine airfoil may include providing a master airfoil configuration having a preset outer and inner radius relative to an axis of rotation thereof. The master airfoil configuration may be radially scaled to a custom-sized turbomachine airfoil having an outer radius different than the preset outer radius of the master airfoil configuration, and/or an inner radius different than the preset inner radius of the master airfoil configuration. Tuning a frequency of the custom-sized turbomachine airfoil by changing a parameter of at least one of a part span shroud and a tip shroud may then be performed. Axial scaling may also be performed. The custom-sized turbomachine airfoil may be employed in the turbomachine without performing wheel box testing, and may exhibit substantially similar operational characteristics as the master airfoil configuration.
    Type: Application
    Filed: September 27, 2013
    Publication date: April 2, 2015
    Applicant: General Electric Company
    Inventors: Tao Guo, Michael Ernest Boisclair, Joseph Anthony Cotroneo, Carl Douglas Hofer, Amir Mujezinovic, Vsevolod Yuriyevich Ostrovskiy
  • Patent number: 8991021
    Abstract: A method for machining at least one aircraft gas turbine engine rotor blade wear indicator is provided. The method includes machining the wear indicator using a laser so as to melt part of the blade, and collecting the molten material of the blade. The method further includes fitting a plug into the bathtub squealer. The plug includes at least one cavity for receiving the molten blade material.
    Type: Grant
    Filed: June 1, 2011
    Date of Patent: March 31, 2015
    Assignee: Snecma
    Inventors: Damien Hebuterne, Janvier Lecomte
  • Publication number: 20150075178
    Abstract: A turbine rotor blade is provided. The turbine rotor blade includes a root, a platform coupled to the root, and an airfoil extending from the platform. The platform has a leading edge, a trailing edge, a suction side edge, and a pressure side edge. The pressure side edge includes a first concave portion.
    Type: Application
    Filed: September 17, 2013
    Publication date: March 19, 2015
    Inventors: Steve Halfmann, Mark C. Morris, Jason Smoke, Brandan Wakefield, Bob Mitlin
  • Publication number: 20150078913
    Abstract: An arrangement to reduce noise emission generated by a wind turbine rotor blade is provided. The arrangement includes the rotor blade and a noise reduction device attached thereto. The rotor blade has a suction side and pressure side, leading and trailing edge sections with a trailing edge. The noise reduction device has an inner surface facing the rotor blade trailing edge section, and an outer surface opposite to the inner surface. The noise reduction device has a leading and trailing edge, both connecting the inner and outer surface. The noise reduction device is connected at the rotor blade trailing edge section by a connector. The inner surface has a pre-defined distance to at least one side of the rotor blade chosen so acoustic waves generated at the rotor blade trailing edge section are reflected by the inner surface to reduce noise emission generated by the wind turbine rotor blade.
    Type: Application
    Filed: August 11, 2014
    Publication date: March 19, 2015
    Applicant: Siemens Aktiengesellschaft
    Inventors: Peder Bay Enevoldsen, Stefan Oerlemans
  • Patent number: 8978249
    Abstract: A method for repairing a gas turbine component includes: identifying on the gas turbine component (10) a worn out location, where the gas turbine component (10) is damaged; removing the damaged location, thereby creating a missing zone (18); manufacturing an insert, which fits into the missing zone (18); putting the insert into the missing zone (18); adjusting the insert in the gas turbine component (10); and joining the adjusted insert to the gas turbine component (10).
    Type: Grant
    Filed: October 29, 2010
    Date of Patent: March 17, 2015
    Assignee: Alstom Technology Ltd.
    Inventors: Simone Hövel, Günter Ambrosy, Matthias Höbel
  • Patent number: 8955206
    Abstract: A method for creating a layup of reinforcing fibers comprises mounting a face sheet to a spindle of a mandrel tool support, the face sheet having a layup surface for the reinforcing fibers, and counterbalancing the mounted face sheet for stiffness and center of balance.
    Type: Grant
    Filed: October 6, 2011
    Date of Patent: February 17, 2015
    Assignee: The Boeing Company
    Inventor: Jeffrey L. Miller
  • Patent number: 8956487
    Abstract: A rotor blade of a turbine engine comprising a body made of composite material consisting of a fiber-reinforced thermosetting resin and a connecting yoke designed to be attached to a fastener of a rotor disc of the said turbine engine, the said blade characterized in that the connecting yoke comprises a metal reinforcement and a casing made of composite material encasing the said reinforcement.
    Type: Grant
    Filed: July 20, 2011
    Date of Patent: February 17, 2015
    Assignee: SNECMA
    Inventor: Francois Gallet