Blade Making Patents (Class 29/889.7)
  • Publication number: 20140050573
    Abstract: A turbocharger (15) with variable turbine geometry, having a blade bearing ring arrangement (1) which has a blade bearing ring (2) and a disk (3) which is fixed to the blade bearing ring (2) so as to create a flow duct (4), having guide blades (5?) mounted in the blade bearing ring (2), and having a spacer device (5) which is arranged between the blade bearing ring (2) and the disk (3) so as to set a defined width (B) of the flow duct (4). The spacer device (5) is formed as an inlet guide grate (6) which has movable inlet guide blades (8) which are arranged in each case on a spacer pin (7) which is fixed with its first end (7A) to the blade bearing ring (2). Also, a method for producing a blade bearing ring arrangement (1).
    Type: Application
    Filed: April 30, 2012
    Publication date: February 20, 2014
    Applicant: BORGWARNER INC.
    Inventor: Leif Heidingsfelder
  • Publication number: 20140044526
    Abstract: Disclosed is an adjustable stationary blade ring of a turbomachine, whose stationary blades are each supported in a bearing body onto which an inner ring, which is divided into two half rings and acts as a seal carrier, is pushed without deformation, viewed in the circumferential direction, as well as a method for assembling a stationary blade ring of this type and a turbomachine having a stationary blade ring of this type.
    Type: Application
    Filed: August 2, 2013
    Publication date: February 13, 2014
    Applicant: MTU Aero Engines AG
    Inventor: Werner Humhauser
  • Publication number: 20140041224
    Abstract: A method of post processing a laser peened component to remove a laser remelt layer is proposed. The post processing includes a series of steps including grit blasting, chemical etching and mechanical finishing the component. This will ensure that the mechanical property (i.e., damage tolerance) benefit of laser peening is restored to the surface of the component.
    Type: Application
    Filed: August 13, 2012
    Publication date: February 13, 2014
    Inventor: David S. Murphy
  • Publication number: 20140044532
    Abstract: Disclosed is a process for producing a blade or vane ring segment for a gas turbine, in particular for an aero engine, and also to a correspondingly produced blade or vane ring segment, the process comprising: forging at least two blanks made of a TiAl material, joining the blanks to form a blade or vane ring by means of an integral connection process, and remachining of the blank composite by material-removing processes.
    Type: Application
    Filed: August 8, 2013
    Publication date: February 13, 2014
    Applicant: MTU AERO ENGINES AG
    Inventor: Karl-Hermann RICHTER
  • Publication number: 20140030093
    Abstract: A wind turbine blade 2 comprises a profiled contour including a leading edge 34 and a trailing edge 33 as well as a pressure side and a suction side. The profiled contour is formed by a first shell part 10 and a second shell part 15 being bonded together in a bonding region between the first and the second shell part by a curable bonding means 40. The first and the second shell part 10; 15 are formed in a fibre-reinforced polymer. The wind turbine blade further comprises resistive heating means 50 being arranged in thermal connection with the bonding means 40 such that the resistive heating means 50 supplies heat for curing of the curable bonding means 40 during assembling of the wind turbine blade.
    Type: Application
    Filed: April 11, 2012
    Publication date: January 30, 2014
    Inventors: Martin Dahl, Bjarne Krab Mortensen, Benjamin Hornblow
  • Publication number: 20140030095
    Abstract: A wind turbine blade for a wind turbine is a shell structure of a fiber-reinforced composite and comprises a root region and an airfoil region. The root region has ring-shaped cross section and comprises a plurality of elongated bushings 7 with an inner thread 22 and embedded interspaced in the fiber-reinforced polymer so as to substantially follow the circumference of the root region and allow access from the outside to the inner threads. Each fastening member 7 is provided with a notch 60? in the periphery 11 thereof. A rod-shaped locking element 61 passes through the notch 60? in engagement therewith. The locking element 61 is fixedly and tightly fitting arranged in a through-going circular bore 65 extending through the wall of the root region.
    Type: Application
    Filed: April 11, 2012
    Publication date: January 30, 2014
    Applicant: LW WP Patent Holding A/S
    Inventor: Martin Dahl
  • Publication number: 20140030076
    Abstract: A method for fabricating turbine engine blade or vane made of composite material includes: performing three-dimensional weaving to make a single-piece fiber blank; shaping the fiber blank to obtain a single-piece fiber preform having a first portion forming a preform for at least a blade/vane airfoil, at least one second portion forming a preform for an inner part of a blade/vane inner platform or for an outer part of a blade/vane outer platform, and at least one third portion forming a preform for an outer part of a blade/vane inner platform or for an inner part of a blade/vane outer platform; and densifying the fiber preform with a matrix to obtain a composite material blade, and forming a single piece with an inner and/or outer platform(s) incorporated therein.
    Type: Application
    Filed: September 7, 2012
    Publication date: January 30, 2014
    Applicants: HERAKLES, SNECMA
    Inventors: ROMAIN NUNEZ, Stephane Blanchard, Guillaume Renon, Dominique Coupe, Clement Roussille, Antoine Jean-Philippe Beaujard, Elric Georges Andre Fremont
  • Patent number: 8635772
    Abstract: A method for the milling machining of components is disclosed. The method produces recesses with one or more lateral walls, in particular for the production of integrally bladed rotors for gas turbines, the recesses forming flow channels and the lateral walls forming blade surfaces of an integrally bladed rotor. The component to be machined by milling is clamped in a locating device for the milling machining. To adjust the vibrational properties of the component to be machined by milling, areas of the component are embedded in and/or filled with a machinable plastic.
    Type: Grant
    Filed: January 12, 2007
    Date of Patent: January 28, 2014
    Assignee: MTU Aero Engines GmbH
    Inventors: Stefan Heinrich, Arndt Glaesser, Goetz Lebkuechner
  • Patent number: 8631578
    Abstract: A balancing weight clip with a mass adapted to balance a rotor assembly of a gas turbine engine, includes a weight portion, a first flange engaging portion and a second flange engaging portion extending from the weight portion, each being engageable with a sidewall of at least one recess located on an edge of a flange of a disc of the rotor assembly. Each flange engaging portion is provided with a hook engageable with a mating groove provided on a face of the flange. At least one of the first and second flange engaging portions is resiliently biased so that the first and second flange engaging portions are elastically moveable away from one another to removably secure the balancing weight clip to the flange and engage each hook with the mating groove.
    Type: Grant
    Filed: October 1, 2009
    Date of Patent: January 21, 2014
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: David F. Glasspoole, Francois Caron
  • Patent number: 8631577
    Abstract: A method of fabricating an integrally bladed rotor of a gas turbine engine according to one aspect, includes a 3-dimensional scanning process to generate a 3-dimensional profile of individual blades before being welded to the disc of the rotor. A blade distribution pattern on the disc is then determined in a computing process using data of the 3-dimensional profile of the individual blades such that the fabricated integrally bladed rotor is balanced.
    Type: Grant
    Filed: July 22, 2011
    Date of Patent: January 21, 2014
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Visal Ing
  • Publication number: 20140010663
    Abstract: A method of manufacturing a fan blade includes providing a metallic fan blade body, and applying at least a 200 volt potential to the fan blade body in a solution to produce a crystalline oxidation layer. A fan blade for a gas turbine engine includes a metallic fan blade body having a tip with a crystalline oxidation layer. A fan blade for a gas turbine engine includes a metallic fan blade body having a tip with a titanium dioxide layer.
    Type: Application
    Filed: June 28, 2012
    Publication date: January 9, 2014
    Inventors: Joseph Parkos, JR., James O. Hansen
  • Publication number: 20140003953
    Abstract: A method and manufacturing unit for producing a rotor blade (5) of a wind turbine (1) from at least a first rotor blade element (11, 11?, 12, 12?) and a second rotor blade element (11, 11?, 12, 12?). The first rotor blade element (11, 11?, 12, 12?) and the second rotor blade element (11, 11?, 12, 12?) are positioned in the desired relative arrangement with respect to each other such that a joint gap (13) remains between the first rotor blade element (11, 11?, 12, 12?) and the second rotor blade element (11, 11?, 12, 12?). Adhesive is introduced into the joint gap (13) for joining the first rotor blade element (11, 11?, 12, 12?) and the second rotor blade element (11, 11?, 12, 12?).
    Type: Application
    Filed: October 5, 2011
    Publication date: January 2, 2014
    Applicant: REPOWER SYSTEMS SE
    Inventors: Lenz Simon Zeller, Maik Gunther
  • Patent number: 8616852
    Abstract: A method of repairing a rotor blade, for example on an integrally bladed rotor, includes preparing a surface on a damaged area of the blade. The blade has first and second airfoil surfaces adjoining the prepared surface that are spaced apart a distance. An edge of a patch abuts the prepared surface to provide a weld interface defining a welding plane. First and second cover sheets respectively overlap the first and second airfoil surfaces. The first and second cover sheets adjoin the edge and the first and second airfoil surfaces. The blade, patch and first and second cover sheets are welded along the welding plane providing a welded joint at the weld interface. The first and second cover sheets are substantially unsecured to the first and second airfoil surfaces subsequent to the welding operation.
    Type: Grant
    Filed: November 25, 2009
    Date of Patent: December 31, 2013
    Assignee: United Technologies Corporation
    Inventors: Wangen Lin, Robert W. Jackson, Andrew L. Haynes, John E. Matz, Adam Quagliaroli, Samuel T. Davidson, Herbert A. Chin
  • Patent number: 8615875
    Abstract: A method of manufacturing a metal blading sector for low-pressure guide vanes of a turbomachine of which at least one blade includes an internal cavity configured to accept or communicate with a gas detection probe and at least one hole formed in the wall constituting a passage for gas from a low-pressure zone of the turbomachine toward the cavity and the probe through the fitting, into a casting mold, of a core corresponding to the cavity and the casting of a molten metal in the cavity of the casting mold. The core includes, for each hole for communication with the cavity, a protrusion penetrating the internal surface of the mold and constituting the only element holding the core in position in the casting mold.
    Type: Grant
    Filed: July 16, 2009
    Date of Patent: December 31, 2013
    Assignee: Snecma
    Inventors: Damien Alquier, Sebastien Digard Brou De Cuissart
  • Publication number: 20130343897
    Abstract: A sheet metal blank is formed into a helical turbine blade by stretching an outer portion of the blank by creating indents and detents thereon. Then the stretched side is flattened and the stretched structure is formed into a helical shape.
    Type: Application
    Filed: March 4, 2013
    Publication date: December 26, 2013
    Inventor: David A. Collins
  • Publication number: 20130333214
    Abstract: A method for producing a metal component such as a metal turbomachine blade reinforcement, includes positioning a plurality of metal staples in a forming tool having a die and a punch; and hot isostatic pressing the plurality of metal staples causing the agglomeration of the metal staples so as to obtain a solid component.
    Type: Application
    Filed: February 29, 2012
    Publication date: December 19, 2013
    Applicant: SNECMA
    Inventors: Thierry Godon, Bruno Jacques Gérard Dambrine, Alain Robert Yves Perroux
  • Publication number: 20130333213
    Abstract: A method for producing, on the surface of a wall capable of being swept by a fluid, raised elements forming disruptions of the boundary layer is disclosed. The method includes applying laser shocks to the surface so as to create peaks on the edge of the impact zones such that the peaks form the disruptive raised elements.
    Type: Application
    Filed: August 9, 2012
    Publication date: December 19, 2013
    Applicant: SNECMA
    Inventors: Yann Pascal Raymond René LEBRET, Claude Marcel Mons
  • Publication number: 20130336785
    Abstract: A rotor assembly includes a first rotor having first tabs and a second rotor that is arranged coaxial with the first rotor and that includes second tabs that are interlocked with the first tabs. A retainer locks the first tabs and the second tabs together.
    Type: Application
    Filed: June 14, 2012
    Publication date: December 19, 2013
    Inventors: Raymond S. Hummel, Matthew P. Ricker, Scott D. Virkler, Virginia L. Ross
  • Publication number: 20130336789
    Abstract: A wind turbine blade (10) for a rotor of a wind turbine (2) having a substantially horizontal rotor shaft is disclosed. The rotor comprises a hub (8), from which the blade (10) extends substantially in a radial direction when mounted to the hub (8), the blade having a longitudinal direction (r) with a tip end (16) and a root end (14) and a transverse direction. The wind turbine blade comprises a blade shell defining a profiled contour of the blade and having an inner shell wall, wherein the blade is provided with a bulkhead mounted to the inner shell wall at the root end of the blade via an attachment part, the bulkhead comprising a first side and a second side. The attachment part is integrally formed with or connected to the bulkhead, and the attachment part comprises an elastomeric material.
    Type: Application
    Filed: March 2, 2012
    Publication date: December 19, 2013
    Applicant: LM WP PATENT HOLDING A/S
    Inventor: Kore Bjarke Berg
  • Patent number: 8607456
    Abstract: A method for producing, on the surface of a wall capable of being swept by a fluid, raised elements forming disruptions of the boundary layer is disclosed. The method includes applying laser shocks to the surface so as to create peaks on the edge of the impact zones such that the peaks form the disruptive raised elements.
    Type: Grant
    Filed: August 9, 2012
    Date of Patent: December 17, 2013
    Assignee: SNECMA
    Inventors: Yann Pascal Raymond Rene Lebret, Claude Marcel Mons
  • Patent number: 8607455
    Abstract: A method for producing a coated turbine blade, with which the frequency property thereof can be particularly easily adjusted to the required boundary conditions is provided. Recesses are introduced into a blade tip of the blade leaf of the turbine blade after coating of turbine blade. In one aspect a plurality of bores are made which are distributed along the blade leaf center line.
    Type: Grant
    Filed: April 10, 2008
    Date of Patent: December 17, 2013
    Assignee: Siemens Aktiengesellschaft
    Inventor: Fathi Ahmad
  • Patent number: 8611732
    Abstract: A device and method for locally heat treating at least one airfoil in an integrally bladed rotor device. A pair of IR heat sources are positioned to direct IR heat rays in the direction where local heat treatment is required. A pair of parabolic mirrors are positioned to direct the IR heat rays on to the metal component. The heat treating is useful after welding the airfoil on to the rotor device.
    Type: Grant
    Filed: July 18, 2011
    Date of Patent: December 17, 2013
    Assignee: United Technologies Corporation
    Inventors: Thomas DeMichael, James J. Moor, Herbert A. Chin, Wangen Lin
  • Publication number: 20130330197
    Abstract: A blade for a wind turbine comprising a blade root portion is described. The blade root portion defines an mounting surface for coupling to a hub or extender of the wind turbine and comprises a plurality of first holes provided with an insert, the blade root portion further comprises a mounting flange arranged in the periphery of the mounting surface and provided with second holes, wherein the inserts comprise a first end embedded in the blade root portion and a second end opposite to said first end, the second end protruding beyond the mounting surface of the blade root portion, and wherein the second ends are fitted in the second holes of the mounting flange and the mounting flange is attached to the blade by means of the inserts. Furthermore, a wind turbine rotor comprising such a blade is described. Methods of manufacturing half a wind turbine blade and a whole wind turbine blade are also described.
    Type: Application
    Filed: June 6, 2013
    Publication date: December 12, 2013
    Inventor: Luca Feigl
  • Publication number: 20130323070
    Abstract: A wind turbine rotor blade for a wind turbine having a length extending from a first end, a leading edge and a trailing edge, where a pressure side and a suction side extend between the leading edge and the trailing edge and thus define an airfoil shaped cross section. At least along a part of the length of the wind turbine rotor blade, the trailing edge comprises a trailing edge part having a first and a second installation flange, each of which has a width. The installation flanges are arranged in connection with a trailing edge extender, the first and second installation flanges both having an inner surface for installation on the pressure side and the suction side of the wind turbine blade. Also, method for fitting a wind turbine rotor blade with a trailing edge part is provided.
    Type: Application
    Filed: May 23, 2013
    Publication date: December 5, 2013
    Applicant: Envision Energy (Denmark) ApS
    Inventor: Peter Grabau
  • Publication number: 20130318787
    Abstract: A method of manufacturing a family of airfoils includes providing a plurality of airfoil blanks of identical geometry, selecting a first airfoil geometry from a family of airfoil geometries, selecting a second, different airfoil geometry from the family of airfoil geometries, machining a first one of the plurality of airfoil blanks to the first airfoil geometry to produce a first airfoil of the family of airfoil geometries, and machining a second, different one of the plurality of airfoil blanks to the second airfoil geometry to produce a second, different airfoil of the family of airfoil geometries
    Type: Application
    Filed: June 5, 2012
    Publication date: December 5, 2013
    Inventors: Seth J. Thomen, Wieslaw A. Chlus
  • Publication number: 20130323073
    Abstract: A method of making a platform of a blade includes the steps of creating two platform sections by solidifying a material with a fabric in a mold and positioning a band of fabric around the two platform sections to retain an airfoil and define a blade. The method further includes the step of bonding the two platform sections together by solidifying the material to define a platform of a solid material. The platform is not bonded to the airfoil.
    Type: Application
    Filed: June 5, 2012
    Publication date: December 5, 2013
    Inventors: Michael G. McCaffrey, Gregory H. Hasko, Michael G. Abbott
  • Publication number: 20130318788
    Abstract: The invention provides a manufacturing method of a component of a split blade of a wind turbine (such as an inboard shell or an inboard spar) having joining elements with its complementary component (i.e. an outboard shell or an outboard spar). The method comprises the following steps: a) manufacturing a joint laminate of a composite material having embedded into it the joining elements, said joint laminate being configured for becoming a part of the component; b) manufacturing the component using as a preform said joint laminate. The invention also refers to a split blade comprising components manufactured by said manufacturing method.
    Type: Application
    Filed: March 27, 2013
    Publication date: December 5, 2013
    Inventors: Ion AROCENA DE LA RUA, Eneko SANZ PASCUAL
  • Publication number: 20130318789
    Abstract: A method and system is provided for assembling or disassembling a blade of a wind turbine. The wind turbine includes a tower resting on a base, a rotor including at least one rotor blade having a blade connection flange and a nacelle mounted atop the tower, a hub rotatably connected to the nacelle and including a hub connection flange adapted to be detachably connected to a blade connection flange of a rotor blade. Thy wind turbine further includes a first positioning element adapted to be attached to the nacelle or to the tower in a top area and a second positioning element adapted to be joined to the blade in a root blade area, where the first and second positioning elements are configured to cooperate to provide an accurate position of the blade connection flange prior to connection to the hub connection flange.
    Type: Application
    Filed: June 4, 2013
    Publication date: December 5, 2013
    Inventors: Teresa Arlaban Gabeiras, José Miguel Garcia Sayés, Ander Gastón Lujambio, Miguel Núñez Polo, Alvaro Gorostidi Martinez de Lecea
  • Publication number: 20130315746
    Abstract: A method of producing a pre-bent wind blade, includes: obtaining a pre-bent curve of a straight wind blade; and producing a bent wind blade according to the pre-bent curve, in such a manner that under a rating wind speed, the wind blade extends to be straight, so as to increase energy yield annually.
    Type: Application
    Filed: May 26, 2012
    Publication date: November 28, 2013
    Inventors: Zaiman Huang, Suo Ding, Xingbo Wang, Chengliang Li, Shiqiang Zhang, Jinqian Tang
  • Patent number: 8591191
    Abstract: A film cooling hole for a turbine airfoil having a diffusion section with a convergent wall and two divergent side walls, and with a thin exit slot that opens onto the airfoil surface. The divergent side walls have an expansion of 15 to 25 degrees and the convergent wall converges up to 15 degrees. The film hole is formed by an electrode than is pushed into the metal surface to form the divergent side walls and then pivoted to form the convergent wall.
    Type: Grant
    Filed: November 22, 2010
    Date of Patent: November 26, 2013
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: George Liang
  • Patent number: 8584357
    Abstract: The invention relates to a device for the production or repair of a blade for a gas turbine, said device comprising: a holding device for holding a blade or an aerofoil of a blade; a lowering mechanism for lowering the blade or the aerofoil; a container for receiving power and/or for receiving the blade or the aerofoil; a heating device; and a radiation source, wherein the heating device is formed as an induction coil.
    Type: Grant
    Filed: December 5, 2007
    Date of Patent: November 19, 2013
    Assignee: MTU Aero Engines AG
    Inventors: Karl-Hermann Richter, Herbert Hanrieder, Christoph Ader, Christoph Over
  • Publication number: 20130298401
    Abstract: Provided are a manufacturing method for a blade material and a manufacturing device for a blade material, by which a long blade material can be manufactured without using a large-sized press forging machine. A manufacturing method for a blade material, in which hot forging is sequentially performed by molds from the root side to a blade (vane) tip, wherein when a root-side portion is grasped and a material to be forged is restrained by a mold, twisting is performed on a region between the grasped portion and the restrained portion. A manufacturing method for a blade material, in which hot forging and twisting are repeated, is preferable, and a manufacturing method for a blade material, in which hot forging is performed while molds are sequentially changed, is more preferable.
    Type: Application
    Filed: September 22, 2011
    Publication date: November 14, 2013
    Applicant: HITACHI METALS, LTD.
    Inventors: Koji Sato, Takashi Toga, Yoshihiro Wakazono, Hideki Matsumoto, Yusuke Shigihara
  • Patent number: 8579181
    Abstract: A method of forming an internal structure in a hollow component that includes the steps of forming an assembly having first, second, and third plates the first and second plates each with a substantially planar surface and a surface that includes at least one protrusion and is on the exterior facing surfaces of the assembly. The third plate is sandwiched between the first and second plates. The method also includes the steps of selectively bonding portions of the third plate to sections of the first and second plates substantially opposite the at least one protrusions of the first and second plates; and forming the assembly against a die such that the at least one protrusions of the first and second plates are transferred from the exterior facing surfaces to the interior facing surfaces of the first and second plates.
    Type: Grant
    Filed: March 9, 2010
    Date of Patent: November 12, 2013
    Assignee: Rolls-Royce PLC
    Inventors: Oliver Michael Strother, Keith Christopher Goldfinch
  • Publication number: 20130294891
    Abstract: The invention provides a method for the generative manufacture of a component (1) with integrated damping for a turbomachine, in particular a gas turbine, having the following method steps: building up the component (1) in a generative manner, and introducing a damping material (2) into the component (1) during the method step of the generative building up of the component (1). The invention further provides a component (1) with integrated damping for a turbomachine, in particular a gas turbine, wherein the component (1) is built up in a generative manner, and the component (1) has a damping material (2) which is introduced into the component (1) during the generative building up of the component (1). The invention further provides a turbomachine, in particular a gas turbine, comprising such a component (1).
    Type: Application
    Filed: January 10, 2012
    Publication date: November 7, 2013
    Inventors: Stefan Neuhaeusler, Wilhelm Satzger, Siegfried Sikorski, Karl-Heinz Dusel, Hans-Christian Melzer, Erwin Bayer
  • Patent number: 8572844
    Abstract: A turbine engine airfoil includes an airfoil structure having an exterior surface that provides a leading edge. A first cooling passage includes radially spaced legs extending laterally from one side of the leading edge toward another side of the leading edge and interconnecting to form a loop with one another. A trench extends radially in the exterior surface along the leading edge. The trench intersects one of the first and second legs to provide at least one first cooling hole in the trench.
    Type: Grant
    Filed: August 29, 2008
    Date of Patent: November 5, 2013
    Assignee: United Technologies Corporation
    Inventor: Justin D. Piggush
  • Patent number: 8572845
    Abstract: A mold system for manufacturing wind turbine blades includes two mold halves shaped for molding respective mold halves. A first mold is supported by a hinge system which is capable of moving the mold from a first position wherein the mold faces upwards to a position wherein the first mold faces the second mold. A final linear displacement of the first mold is carried out by actuators which may be integrated with the first or the second mold. The actuators are engaged with the hinge system so that the first mold is displaceable or the hinge system holding the first mold is displaceable. In both alternatives the actuators merely transfer the load of the first mold to a support via the hinge system.
    Type: Grant
    Filed: September 28, 2010
    Date of Patent: November 5, 2013
    Assignee: Vestas Wind Systems A/S
    Inventor: Damien Rajasingam
  • Publication number: 20130276303
    Abstract: A resinous blade-supporting rotator is prepared to rotate around a rotational axis. The blade-supporting rotator has rotator weld parts including rotator weld surfaces formed on one side surface in the axial direction. A plurality of resinous blades are disposed annularly around the axis. The plurality of resinous blades have hollow spaces formed in the blade interiors, and blade weld parts with blade weld surfaces. The blade weld surfaces and the rotator weld surfaces are inclined with respect to each other when facing each other in the axial direction. An axial pressure load is applied to opposite axial ends of the blade-supporting rotator so as to compress the blades in the axial direction such that the blade weld surfaces and the rotator weld surfaces are no longer inclined with respect to each other. The blade weld surfaces are fixed to the rotator weld surfaces by laser welding.
    Type: Application
    Filed: June 14, 2013
    Publication date: October 24, 2013
    Inventor: Hisanori NISHINO
  • Publication number: 20130280092
    Abstract: An airfoil includes a body that includes leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface. A cooling passage is arranged interiorly of the exterior airfoil surface and provides an interior surface. The interior cooling surface includes micro-bumps that protrude from the interior cooling surface into the cooling passage. The micro-bumps are discrete from and noncontiguous relative to one another in multiple directions along the interior cooling surface. The micro-bumps may be provided while forming the airfoil or using correspondingly shaped micro-depressions on an airfoil core.
    Type: Application
    Filed: April 24, 2012
    Publication date: October 24, 2013
    Inventor: JinQuan Xu
  • Publication number: 20130280083
    Abstract: In a moving blade system for a turbomachine, in particular a gas turbine, having at least one moving blade (1), the moving blade system having at least one cavity (3) in which at least one tuning mass (2) is movably situated, the tuning mass and/or the cavity is/are adapted in such a way that the tuning mass rests against an inner wall (3.1) of the cavity in a predefined first operating state of the turbomachine and at least temporarily moves away from the inner wall in a second predefined operating state of the turbomachine.
    Type: Application
    Filed: November 5, 2011
    Publication date: October 24, 2013
    Applicant: MTU AERO ENGINES GMBH
    Inventor: Andreas Hartung
  • Publication number: 20130276460
    Abstract: An airfoil includes an airfoil body that defines a longitudinal axis. The airfoil body includes a leading edge and a trailing edge and a first side wall and a second side wall that is spaced apart from the first side wall to define a camber line there between. The first side wall and the second side wall join the leading edge and the trailing edge and at least partially define a cavity in the airfoil body. Multiple ribs extend longitudinally in the cavity and are laterally spaced apart from each other relative to the longitudinal axis. In at least one plane that is perpendicular to the longitudinal axis, each of the ribs connects the first side wall and the second side wall along respective minimum distance directions that are perpendicular to the camber line. At least two of the respective minimum distance directions are non-parallel.
    Type: Application
    Filed: April 24, 2012
    Publication date: October 24, 2013
    Inventors: Tracy A. Propheter-Hinckley, Benjamin T. Fisk, Steven Taffet, Gregory M. Dolansky, Anita L. Tracy
  • Publication number: 20130280088
    Abstract: A method of making a wind turbine component of composite construction with enhanced radar absorbing properties is described. The method comprises making the component and then modifying the component by applying circuit analogue elements to a surface of the component.
    Type: Application
    Filed: October 26, 2011
    Publication date: October 24, 2013
    Applicant: VESTAS WIND SYSTEMS A/S
    Inventor: Steve Appleton
  • Publication number: 20130280086
    Abstract: A fan impeller structure and a manufacturing method thereof. The fan impeller structure includes a base seat, multiple blades and a ring member. Each blade has a main body made of plastic material and at least one fixing member made of metal material. The base seat and the ring member are made of metal material. The base seat and the ring member are respectively disposed on two sides of the blades. By means of the manufacturing method, the blades can be diversified and the universality of the blades is greatly increased to lower the manufacturing cost.
    Type: Application
    Filed: April 24, 2012
    Publication date: October 24, 2013
    Inventor: Chu-Hsien Chou
  • Patent number: 8562295
    Abstract: A turbine rotor blade formed from three pieces with a pressure wall side piece and a suction wall side piece bonded to an intermediate piece so that a pressure side cooling circuit can be formed as a separate cooling circuit from a suction side cooling circuit. The intermediate piece has film cooling holes and blade tip cooling holes and trailing edge exit slots formed in it that are enclosed when the outer two pieces are boded to it.
    Type: Grant
    Filed: December 20, 2010
    Date of Patent: October 22, 2013
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: George Liang
  • Patent number: 8561298
    Abstract: A method for welding superalloy components at ambient temperature conditions while reducing the propensity of the superalloy material to crack as a result of the weld. A root pass region of the weld is formed using a filler material that exhibits ductility that is higher than that of the base superalloy material. The ductile material mitigates stress in the root region, thereby preventing the formation of cracks. A remaining portion of the weld is formed using a filler material that essentially matches the base superalloy material. The method may utilize a pre-weld heat treatment to grow a gamma prime precipitate phase in the superalloy material, a chill fixture to remove heat during welding, a relief cut to reduce stress in the root region, and a conventional post-weld heat treatment.
    Type: Grant
    Filed: February 29, 2008
    Date of Patent: October 22, 2013
    Assignee: Siemens Energy, Inc.
    Inventors: James A. Morin, Lucian Iordache, Ovidiu Timotin, Sooyeum Oh
  • Publication number: 20130269189
    Abstract: In a method and a device for machining an elongate workpiece that is not rotationally symmetrical in the form of turbine blades, the workpiece is supported by a steady rest that has clamping elements for clamping the workpiece on the cross-section thereof that is not rotationally symmetrical. After clamping the workpiece, the steady rest moves with its open clamping elements along the longitudinal axis of the workpiece into a supporting position. During movement of the steady rest into the supporting position and/or while the supporting position of the steady rest is being changed, a collision between the open clamping elements of the steady rest and the workpiece is prevented by a program-controlled rotation of a rotary part of the steady rest.
    Type: Application
    Filed: September 20, 2011
    Publication date: October 17, 2013
    Applicant: STARRAGHECKERT AG
    Inventors: Horst Keller, Roland Geiger
  • Publication number: 20130272890
    Abstract: When a distance from a front edge along a blade chord line is represented by X and a distance from the blade chord line to a blade back side is represented by Y, a blade back shape of a wind turbine blade includes a first region extending from the maximum blade thickness position toward the rear edge with dY/dX as a primary derivative amount of Y to X decreasing by a first amount of change, a second region on a side of the rear edge of the first region and extending toward the rear edge with dY/dX having a second amount of change smaller than the first amount of change, and a third region on the side of the rear edge of the second region and connected to the rear edge with dY/dX decreasing by a third amount of change larger than the second amount of change.
    Type: Application
    Filed: October 13, 2011
    Publication date: October 17, 2013
    Applicant: MITSUBISHI HEAVY INDUSTRIES, LTD
    Inventor: Koji Fukami
  • Patent number: 8555501
    Abstract: A method of manufacturing a blade comprising: applying a stop-off material in a first predetermined pattern between a first layer and a membrane so as to prevent a diffusion bond from forming between the first layer and the membrane across said first predetermined pattern; and applying the stop-off material in a second predetermined pattern between a second layer and the membrane; wherein the first and second predetermined patterns are arranged to allow a diffusion bond to be formed along the blade tip edge, the diffusion bond along the blade tip edge extending across the blade in a chord-wise direction; applying the first and second predetermined patterns so that over at least a first portion of the blade chord at the blade tip, a greater portion of the first layer at the tip edge, extending in a span-wise direction, is diffusion bonded to the membrane than the opposing second layer.
    Type: Grant
    Filed: February 3, 2010
    Date of Patent: October 15, 2013
    Assignee: Rolls-Royce plc
    Inventor: Phillip Brennand
  • Publication number: 20130259681
    Abstract: An enhanced performance rotorcraft rotor blade system and methods are presented. A rotor blade comprises an inboard blade portion, and at least one controllable surface coupled to the inboard blade portion. The at least one controllable surface is operable to improve a lift of the inboard blade portion by altering an angle of attack of the inboard blade portion independent of the rotor blade.
    Type: Application
    Filed: March 27, 2012
    Publication date: October 3, 2013
    Inventor: David L. Perlman
  • Publication number: 20130259691
    Abstract: An airfoil with a tip cover surface treatment for reducing leakage flows, minimizing tip vortex size and penetration into main flow that will improve turbine efficiency. The surface treatment for the airfoil tip covers includes a series of concave shapes, such as grooves or holes. These grooves and holes will cause the leakage flow into separate flow paths within the cavities and generate more resistance to leakage flows through the airfoil tip clearance, thereby reducing the leakage mass flow and weakening tip vortex and its interaction with turbine main flows. The material removed from the tip cover provides the additional benefit of reducing the weight of the tip cover, thereby enhancing blade reliability.
    Type: Application
    Filed: July 17, 2009
    Publication date: October 3, 2013
    Inventors: Xiaoyue Liu, Joseph A. Cotroneo, Jonathon E. Slepski, Zekai Ceylan, Hiteshkumar R. Mistry
  • Publication number: 20130251572
    Abstract: A method for manufacturing a stator for a progressive cavity motor or pump comprises (a) forming an elastomeric stator insert. In addition, the method comprises (b) exposing the elastomeric stator insert to ionizing radiation. Further, the method comprises (c) positioning the elastomeric stator insert in a stator housing to form a stator.
    Type: Application
    Filed: November 22, 2011
    Publication date: September 26, 2013
    Applicant: NATIONAL OILWELL VARCO, L.P.
    Inventor: Stefan M. Butuc