Blade Making Patents (Class 29/889.7)
  • Publication number: 20130239379
    Abstract: An apparatus (60) is provided for forming a trailing edge (52) of a wind turbine blade having first and second shells (40, 42). The first and second shells define a gap therebetween, and the apparatus has a first mold component (62) that is adapted to form the first or second shell, and an engaging element (77). The engaging element is configured to securely support a trailing edge component to be coupled to the first and second shells. The engaging element is coupled to the first mold component. The apparatus may additionally include a second mold component (64) that is adapted to form the other of the first or second shells and which is coupled to the first mold component. In this embodiment, the first and second mold components have a closed position in which the first and second shells are closed over one another so as to define a generally closed profile of the wind turbine blade.
    Type: Application
    Filed: August 4, 2011
    Publication date: September 19, 2013
    Applicant: VESTAS WIND SYSTEMS A/S
    Inventors: Damien Rajasingam, Richard Evans, Olav Davis, Stephen Sandercock
  • Patent number: 8533949
    Abstract: A method of manufacturing a component is provided. The method includes forming one or more grooves in an outer surface of a substrate. Each groove extends at least partially along the surface of the substrate and has a base, a top and at least one discharge point. The method further includes forming a run-out region adjacent to the discharge point for each groove and disposing a coating over at least a portion of the surface of the substrate. The groove(s) and the coating define one or more channels for cooling the component. Components with cooling channels are also provided.
    Type: Grant
    Filed: February 14, 2011
    Date of Patent: September 17, 2013
    Assignee: General Electric Company
    Inventor: Ronald Scott Bunker
  • Publication number: 20130236326
    Abstract: An airfoil includes a blade having a pocket recess therein and one or more features disposed within the pocket recess. The one or more features are configured to disrupt pressure oscillations within the pocket recess. In another embodiment, a blade is disclosed having a first wall and a second wall. The first wall is disposed on a suction side of the blade and the second wall is disposed on a pressure side of the blade. The second wall is connected to the first wall at a leading edge of the blade. Together the first wall and the second wall form a portion of a pocket recess and the pocket recess is disposed asymmetrically with respect to a camber line of the blade.
    Type: Application
    Filed: March 8, 2012
    Publication date: September 12, 2013
    Applicant: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Loc Quang Duong, Xiaolan Hu, Nagamany Thayalakhandan, Gao Yang
  • Patent number: 8522417
    Abstract: Vibration damping is important with regard to such components as hollow turbine blades in gas turbine engines. Traditionally damping has occurred through damping elements secured at the root or tip of such blades. Such damping is not optimised and results in potential problems with wear in operational life. By providing a tube of deformable material which can be located within a hollow cavity it is possible to provide an element which through friction engagement can absorb vibration energy and therefore damp such vibration. The tube incorporates a number of cuts and/or grooves in an appropriate pattern in order to define a deformation profile once the tube is expanded in location. The tube is secured in position internally upon an expandable element which is typically an inflatable device. Once in position the tube is retained in its expanded deformable profile and the engagement between the tube and the hollow cavity wall surface results in energy absorption through vibration episodes.
    Type: Grant
    Filed: January 26, 2010
    Date of Patent: September 3, 2013
    Assignee: Rolls-Royce, PLC
    Inventor: David Miller
  • Patent number: 8522435
    Abstract: A vertical axis turbine and method of making same is disclosed. The device and method comprise a plurality of blades rotatably disposed around an axis of rotation at a plurality of blade locations, each blade being twisted at a first angle about its longitudinal axis, each blade having its distal ends located a predetermined distance from the axis of rotation, each blade being bent at one or more central locations along the longitudinal axis so the one or more central locations are the same predetermined distance from the axis of rotation as the distal ends, each blade having a foil cross section perpendicular to the axis of rotation for maintaining unidirectional rotation of that blade about the axis of rotation in a fluid flow, and each blade having its longitudinal axis tilted at a second angle with respect to the axis of rotation.
    Type: Grant
    Filed: November 22, 2011
    Date of Patent: September 3, 2013
    Assignee: Seab Energy Ltd.
    Inventor: Nicolas W. Sassow
  • Publication number: 20130219717
    Abstract: A method for producing a metal reinforcement for the leading edge or trailing edge of a turbomachine blade, the method including cutting a plurality of metal foils from a flexible metal sheet, corresponding substantially to the developed length of the leading or trailing edge metal reinforcement; producing a plurality of metal pockets, each pocket being produced from two of the metal foils obtained during the cutting; stacking the metal pockets one inside the other, such as to form a preform of the leading or trailing edge metal reinforcement; and hot isostatic pressing the preform, causing the metal pockets to bond to one another, so as to produce the leading or trailing edge metal reinforcement.
    Type: Application
    Filed: October 5, 2011
    Publication date: August 29, 2013
    Applicant: SNECMA
    Inventors: Bruno Jacques Gérard Dambrine, Thierry Godon, Alain Robert Yves Perroux
  • Publication number: 20130225910
    Abstract: A pump assembly 1, 33, 200 adapted for continuous flow pumping of blood. In a particular from the pump 1, 200 is a centrifugal pump wherein the impeller 100, 204 is entirely sealed within the pump housing 2, 201 and is exclusively hydrodynamically suspended therein as the impeller rotates within the fluid 105 urged by electromagnetic means external to the pump cavity 106, 203. Hydrodynamic suspension is assisted by the impeller 100, 204 having deformities therein such as blades 8 with surfaces tapered from the leading edges 102, 223 to the trailing edges 103, 224 of bottom and top edges 221, 222 thereof.
    Type: Application
    Filed: February 4, 2013
    Publication date: August 29, 2013
    Applicant: Thoratec Corporation
    Inventor: Thoratec Corporation
  • Patent number: 8516676
    Abstract: A method of fixturing a plurality of dissimilar blade assemblies, wherein each assembly undergoes one or more manufacturing steps to bring it to a finished form, the method comprising the step of providing on each of the articles a datum feature, wherein each datum feature is of identical form and dimension, in turn a) locating the datum feature of a first one of the articles in a complimentary fixture to secure the dissimilar article, b) performing at least one manufacturing step on the secured dissimilar article, c) removing the dissimilar article from the fixture, d) locating the datum feature of another of the articles in the complimentary fixture to secure the dissimilar article, e) performing at least one manufacturing step on the secured dissimilar article, f) removing the dissimilar article from the fixture.
    Type: Grant
    Filed: May 19, 2008
    Date of Patent: August 27, 2013
    Assignee: Rolls-Royce PLC
    Inventor: Colin J. High
  • Patent number: 8516674
    Abstract: A method for bonding airfoil sections includes aligning upper and stub airfoil sections having upper airfoil pressure and suction sides and stub airfoil pressure and suction sides respectively, pressing together upper and stub airfoil cross sections at upper and stub airfoil distal ends of the upper and stub airfoil sections respectively, and then resistance welding, preferably solid state resistance welding, the upper and stub airfoil sections together along the upper and stub airfoil cross sections by passing electrical current across the upper and stub airfoil cross sections. The upper and stub airfoil sections may be clamped between pressure and suction side upper airfoil electrodes and between the stub airfoil pressure and suction sides respectively. The method may be performed while the stub airfoil section is attached to an airfoil carrier such as a rotor disk rim, a gas turbine engine drum, or a gas turbine engine blade platform.
    Type: Grant
    Filed: June 30, 2010
    Date of Patent: August 27, 2013
    Assignee: General Electric Company
    Inventors: Gary Edward Trewiler, Stephen Joseph Ferrigno, Melvin Howard Wilkins, Timothy Joseph Trapp, Matthew Stewart, Gregory Christopher Firestone
  • Patent number: 8510947
    Abstract: A method includes joining an integral bulkhead and a blade shell to form a blade and separating the blade into two blade segments at a location including the integral bulkhead such that each blade segment comprises a portion of the integral bulkhead and a portion of the blade shell.
    Type: Grant
    Filed: November 14, 2008
    Date of Patent: August 20, 2013
    Assignee: General Electric Company
    Inventors: Bowden Kirkpatrick, Peggy Lynn Baehmann, Shu Ching Quek, Grama Narasimhaprasad Praveen, Youdong Zhou
  • Patent number: 8510925
    Abstract: A system and method for repairing a hollow fan blade. In one aspect the blade includes a hollow portion having a plug disposed therein, wherein the plug is smaller than the opening. During processing the blade is located under a vacuum box and the gap is sealed between the plug and the opening using a fiber laser.
    Type: Grant
    Filed: September 2, 2009
    Date of Patent: August 20, 2013
    Assignee: Rolls-Royce Corporation
    Inventor: Gregory Thomas Krause
  • Publication number: 20130209257
    Abstract: A blade for a wind turbine comprising a blade root portion for attachment to a mounting flange of the wind turbine, the blade root comprising a plurality of first holes provided with an internal bushing wherein the bushings comprise a first end at or near a mounting surface of the blade root and an opposite second end embedded in their corresponding first holes, and wherein one or more internal bushing being guiding bushings, the guiding bushings comprising a first end that is adapted to guide the blade root with respect to a mounting flange.
    Type: Application
    Filed: November 10, 2011
    Publication date: August 15, 2013
    Applicant: ALSTOM WIND, S.L.U.
    Inventor: Luca Feigl
  • Publication number: 20130209260
    Abstract: A method of balancing a gas turbine engine rotor comprises the step of obtaining a rotor disc with a circumferential array of balance tabs projecting from a peripheral rim of the disc. Stress shielding scallops are defined in the rotor disc between the tabs. The balancing is achieved by removing material from at least one of the tabs.
    Type: Application
    Filed: February 9, 2012
    Publication date: August 15, 2013
    Inventor: Paul Stone
  • Publication number: 20130209263
    Abstract: A blade for a wind turbine comprising a blade root portion, the blade root portion defining an annular mounting surface for coupling to a hub or extender of the wind turbine and comprising a plurality of first holes provided with an internal bushing, wherein at least one first internal bushing comprises at least one first securing member, and at least one second internal bushing comprises at least one second securing member, the first and second bushings being located in or near substantially opposite positions of the annular mounting surface, and wherein said first and second securing members are adapted to receive connecting means for connecting the first securing member with the second securing member.
    Type: Application
    Filed: October 13, 2011
    Publication date: August 15, 2013
    Applicant: ALSTOM WIND, S.L.U.
    Inventor: Luca Feigl
  • Publication number: 20130209271
    Abstract: Gas turbine blades which simplify the formation of cooling channels provided inside the turbine blades while simultaneously avoiding loss of turbine blade strength and rigidity due to forming of the cooling channels. Cooling channels provided in the interior of a gas turbine blade include a plurality of straight channel-like base-side elongated holes extending in a longitudinal direction at a base side of the turbine blade, a plurality of straight channel-like tip-side elongated holes extending in a longitudinal direction at a tip side of the turbine blade, and a plurality of communicating hollow portions interposed at connection portions between the two types of elongated holes to allow the two types of elongated holes to communicate with each other, and have larger cross-sectional areas than the channel cross-sectional areas of both elongated holes. The communicating hollow portions are formed to match the position of a platform portion of the turbine blade.
    Type: Application
    Filed: March 15, 2013
    Publication date: August 15, 2013
    Applicant: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventor: MITSUBISHI HEAVY INDUSTRIES, LTD.
  • Patent number: 8505202
    Abstract: A process for manufacturing a single-piece blisk, including: using an abrasive water jet to cut a block of material, so as to create blade preforms extending radially outwards from a disk, while keeping material to form a connecting mechanism between directly consecutive blade preforms, the cutting being done such that the connecting mechanism approximately forms a ring at a radial spacing from the disk, connecting the blade preforms together at a radially inwards distance from their tips, and then removing the connecting mechanism.
    Type: Grant
    Filed: March 25, 2009
    Date of Patent: August 13, 2013
    Assignee: Snecma
    Inventors: Serge Berlanger, Sebastien Bordu, Thierry Jean Maleville, Christophe Charles Maurice Roca
  • Patent number: 8499449
    Abstract: A turbine blade growth pocket provides a feature to measure blade growth due to engine operation while maintaining dynamic characteristics of the turbine blade within acceptable limits by providing a variable radius fillet between the pocket and a side rail of the pocket.
    Type: Grant
    Filed: April 3, 2012
    Date of Patent: August 6, 2013
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Marc Tardif, Harris Shafique, Mario Guerra
  • Publication number: 20130195673
    Abstract: A turbine component for a turbine of an engine is provided. The turbine component includes a blade portion of a first material; and an attachment portion coupled to the blade portion, the attachment portion being a second material.
    Type: Application
    Filed: January 27, 2012
    Publication date: August 1, 2013
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Donald G. Godfrey, Mark C. Morris, Mamballykalathil Menon
  • Patent number: 8496440
    Abstract: A method of manufacturing an aerofoil structure capable of being diffusion bonded and superplastically formed to create a substantially hollow cavity within the aerofoil structure, the method comprising: providing a metallic plate for forming the aerofoil structure; joining mounting elements to opposing end surfaces of said metallic plate; dividing said plate along a plane extending substantially in a span-wise direction so as to produce two metallic panels each with one of said mounting elements joined thereto; assembling the two metallic panels so that the surfaces of the panels opposite to the surfaces which have been divided are facing each other; and joining the two metallic panels to one another to form the aerofoil structure; wherein the mounting elements are joined to one another to form the root of the aerofoil.
    Type: Grant
    Filed: February 9, 2010
    Date of Patent: July 30, 2013
    Assignee: Rolls-Royce PLC
    Inventor: Michael J. Wallis
  • Patent number: 8495810
    Abstract: A process for manufacturing a metal part reinforced with ceramic fibers, in which: a housing is formed for an insert in a main metal body having an upper face; an insert formed from a bundle of fibers with a metal matrix is placed in the housing; a metal cover is placed on the main body so as to cover the insert; the cover is welded onto the metal body; a hot isostatic pressing operation is carried out; and the part obtained is machined to the desired shape. The housing has the shape of a notch of L-shaped cross section with a face perpendicular to the upper face and a face parallel to the upper face, the cover having an internal notch of L-shaped cross section, this having a shape complementary to that of the metal body with said insert, the cover being shaped on the outside so that the pressure forces are exerted perpendicular to said faces of the notch.
    Type: Grant
    Filed: December 24, 2008
    Date of Patent: July 30, 2013
    Assignee: Messier-Bugatti-Dowty
    Inventors: Richard Masson, Dominique Ducos
  • Publication number: 20130189108
    Abstract: The present invention relates to a blade rim segment for a turbomachine with at least one shroud band which extends along a segment of a circle and is connected in single-piece fashion with at least three blades, which extend radially from the shroud band and are configured to be hollow with at least one channel, wherein the blade rim segment is manufactured in a single piece by casting and directional solidification, and wherein at the outlet openings of the channels of the blades, the shroud band exhibits first reinforcement ribs that surround the opening and run axially, as well as at least one second reinforcement rib between at least the first reinforcement ribs, as well as a corresponding method for manufacturing a blade rim segment.
    Type: Application
    Filed: January 11, 2013
    Publication date: July 25, 2013
    Applicant: MTU AERO ENGINES GMBH
    Inventor: MTU Aero Engines GmbH
  • Publication number: 20130189112
    Abstract: A method of fabricating a composite joint from a first cured composite component (13) and a second cured composite component (14), the first and second cured composite components (13, 14) comprising fibre elements embedded in a thermoset resin matrix; the method comprising the steps of providing an adhesive (15) on at least one of the first and/or second composite components (13, 14); forming a joint region between the first and second composite component by bringing the first and second composite component into contact with each other with the adhesive (15) therebetween; applying a force to the joint region (16, 17); and heating the first composite component in the joint region to a temperature above the glass transition temperature of the thermoset resin matrix of the first composite component.
    Type: Application
    Filed: January 7, 2011
    Publication date: July 25, 2013
    Applicant: VESTAS WIND SYSTEMS A/S
    Inventors: Andrew Hedges, Kim Sylvester Nielsen
  • Publication number: 20130189114
    Abstract: The invention relates to a method for manufacturing a wind turbine blade, comprising the steps of pre-manufacturing a first blade member, positioning said pre-manufactured first blade member in a joining mold and bonding said first blade member with a second blade member using a vacuum assisted infusion process so as to form an integrated blade part.
    Type: Application
    Filed: December 9, 2011
    Publication date: July 25, 2013
    Applicants: EUROS ENTWICKLUNGSGESELLSCHAFT FUR WINDKRAFTAN- LAGEN MBH, MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Dominique Jenzewski, Andreas Cremer
  • Patent number: 8490281
    Abstract: A method of manufacturing a metal component from metal powder comprises preparing (12) a metal powder, providing (14) gallium on at least part of the surface of at least some of the metal powder particles, encapsulating (16) the metal powder in a container, evacuating (18) the container to remove air and/or gas from the container, sealing (20) the container, hot isostatically pressing (22) the container to consolidate the metal powder particles to produce the metal component and removing (24) the container from the metal component. The process is used to produce gas turbine engine metal components, for example turbine discs with improved fatigue properties.
    Type: Grant
    Filed: August 23, 2010
    Date of Patent: July 23, 2013
    Assignee: Rolls-Royce PLC
    Inventor: Wayne E. Voice
  • Publication number: 20130183159
    Abstract: A wind turbine blade includes a blade body whose chord length increases from a blade tip toward a blade root. The blade body includes a blade tip region located near the blade tip and whose chord length increases gradually toward the blade root, the blade tip region having a substantially constant first design lift coefficient, a maximum-chord-length position located near the blade root and having a maximum chord length, the maximum-chord-length position having a second design lift coefficient higher than the first design lift coefficient, and a transition region located between the blade tip region and the maximum-chord-length position. The transition region has a design lift coefficient increasing gradually from the first design lift coefficient to the second design lift coefficient in a direction from the blade tip toward the blade root.
    Type: Application
    Filed: October 20, 2011
    Publication date: July 18, 2013
    Applicant: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventor: Koji Fukami
  • Publication number: 20130174420
    Abstract: An equipment for coating an airfoil of a turbine blade of a turbine engine in a coating block, including a base on which a molding block is positioned for flow of the coating metal, the molding block including a cavity defining a reference plane on the block for positioning the block in space, wherein the base also includes a cradle supporting the blade via six bearing points defining an orientation plane representative of an angular position of the airfoil relative to a root of the blade. The cradle is rotatably movable relative to the base about an axis oriented so as to be substantially parallel to a direction of a leading edge of the blade, to enable a modification in an angle formed between the reference and orientation planes.
    Type: Application
    Filed: October 14, 2011
    Publication date: July 11, 2013
    Applicant: SNECMA
    Inventors: Jose Chacon, Jean-Jacques Michel Roussel
  • Publication number: 20130177401
    Abstract: A stator subassembly includes an array of circumferentially arranged stator vanes. A damper spring is provided between the array and an outer case, which supports the array. The damper spring is configured to bias the array radially inwardly from the outer case.
    Type: Application
    Filed: January 5, 2012
    Publication date: July 11, 2013
    Inventor: Mark David Ring
  • Publication number: 20130167337
    Abstract: A method for adjusting a predetermined contour of a turbine blade root including a main salient edge defined by a determined interior angle. The method includes: chamfering the main edge of the contour to obtain two auxiliary salient edges, associated interior angles of which are respectively greater than the interior angle of the main edge; and blunting the auxiliary edges obtained to fine-tune the contour of the blade root.
    Type: Application
    Filed: September 15, 2011
    Publication date: July 4, 2013
    Applicant: SNECMA
    Inventors: Olivier Dupouy, Christian Defrocourt, Thomas Marquoin, Pascal Paul
  • Patent number: 8474137
    Abstract: A method for repairing turbine blades by replacing at least a part of the blade profile, the method having: a) manufacture of a replacement blade part; b) separation of the damaged area with a standardized cutting plane, leaving behind a remaining blade; c) matching of the replacement blade part to the actual geometry of the remaining blade; d) connecting or joining of the replacement blade part to the remaining blade by soldering of at least one web and welding of an outer contour.
    Type: Grant
    Filed: July 11, 2007
    Date of Patent: July 2, 2013
    Assignee: MTU Aero Engines GmbH
    Inventors: Karl-Hermann Richter, Klaus Emiljanow
  • Publication number: 20130164141
    Abstract: A blade with an aerodynamic blade body having a leading edge and a trailing edge is provided. The blade includes at least one flexible adaptor component having a first side coupled to the trailing edge. Further, the blade includes at least one rigid acoustic segment attached to an opposing second side of the at least one flexible adapter component for mitigating noise during fluid flow over the blade.
    Type: Application
    Filed: December 22, 2011
    Publication date: June 27, 2013
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Wendy Wen-Ling Lin, Roger Drobietz
  • Publication number: 20130164488
    Abstract: An airfoil and method of fabricating an airfoil including a first and a second side coupled together at a leading and a trailing edge and extending there between. The airfoil includes a plurality of first chord sections having a first chord length and extending outward from one of the first side or second side of the airfoil at the leading edge and a plurality of second chord sections having a second chord length and extending outward from the one of the first side or the second side of the airfoil at the leading edge. The leading edge including spaced-apart wave-shaped projections defining a waveform. The configuration defining a three-dimensional crenulated airfoil configured to facilitate desensitization of an airfoil unsteady pressure response to at least one impinging upstream generated wake or vortex by decorrelating spatially and temporally and reducing in amplitude an unsteady pressure caused by interaction of the airfoil with the upstream generated wake or vortex.
    Type: Application
    Filed: December 22, 2011
    Publication date: June 27, 2013
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Trevor Howard Wood, Kishore Ramakrishnan, Umesh Paliath
  • Publication number: 20130164144
    Abstract: A bulkhead (22) of a wind turbine (10) to be arranged on a rotor blade connection of a rotor blade (14), especially on a rotor hub (9). The bulkhead (22) has a core body (30). A layer (31, 32) of fiberglass-reinforced plastic (31, 32) is arranged on the core body (30) on both sides respectively and a metal layer body (33) is arranged on one side of the layer of fiberglass-reinforced plastic (31). A method for producing a bulkhead (22) of a wind turbine (9), which is arranged on a rotor blade connection of a rotor blade (14) and a use of a bulkhead (22) of a wind turbine (10).
    Type: Application
    Filed: October 10, 2011
    Publication date: June 27, 2013
    Applicant: REPOWER SYSTEMS SE
    Inventor: Urs Bendel
  • Publication number: 20130156583
    Abstract: An airfoil, a fan assembly and an unducted contra-rotating fan engine include fabricating at least one airfoil including a suction and a pressure side coupled together at a leading and a trailing edge and extending therebetween. The airfoil includes a plurality of chord sections having a chord length. The airfoil including a tip profile defining a reducing slope extending from the leading edge at the tip portion along at least a portion of the chord length. The tip profile is configured to reduce the high unsteady pressure near the tip portion of the airfoil.
    Type: Application
    Filed: December 20, 2011
    Publication date: June 20, 2013
    Applicant: GENERAL ELECTRIC COMPANY
    Inventor: Trevor Howard Wood
  • Patent number: 8464425
    Abstract: A process for manufacturing a single-piece bladed disk, including: using an abrasive water jet to cut a block of material, so as to create blade preforms extending radially outwards from a disk, while keeping material forming a connecting mechanism between at least two directly consecutive blade preforms, the connecting mechanism being at a radial spacing from the disk; then removing the connecting mechanism; then milling the blade preforms.
    Type: Grant
    Filed: March 25, 2009
    Date of Patent: June 18, 2013
    Assignee: SNECMA
    Inventors: Serge Berlanger, Sebastien Bordu, Thierry Jean Maleville, Christophe Charles Maurice Roca
  • Publication number: 20130149163
    Abstract: A turbine engine component has an airfoil portion with a tip portion and the tip portion has at least one chamfered edge on one side. If desired, the tip portion may have a first chamfered edge on a first side and a second chamfered edge on a second side opposed to the first side. A flattened tip portion may extend between the first and second chamfered edges. A tip treatment may be applied to the flattened tip portion.
    Type: Application
    Filed: December 13, 2011
    Publication date: June 13, 2013
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Joseph Parkos, JR., Michael A. Weisse, Christopher S. McKaveney, James R. Murdock, Scott C. Billings
  • Patent number: 8459955
    Abstract: Composite aerofoils for gas turbine engines are commonly provided with a metal protection strip along the leading edge, to prevent erosion of the leading edge in use and to protect against impacts from foreign bodies. A problem with such strips is that they can cause serious damage to other parts of the engine if they become detached from the aerofoil. The invention provides an aerofoil having such a protection strip, characterized in that the protection strip includes one or more weakening features to reduce the ability of the protection member to withstand a compressive force applied along its length. The weakening features encourage the protection member to break up under impact, or if it becomes detached from the aerofoil, so that damage to other parts of the engine is minimized.
    Type: Grant
    Filed: July 22, 2009
    Date of Patent: June 11, 2013
    Assignee: Rolls-Royce PLC
    Inventors: Alison J McMillan, Ian C D Care
  • Publication number: 20130142660
    Abstract: An airfoil for a gas turbine engine includes an aft trailing edge support between a pressure side and a suction side.
    Type: Application
    Filed: December 1, 2011
    Publication date: June 6, 2013
    Inventor: Michael G. McCaffrey
  • Publication number: 20130136621
    Abstract: A blading for a turbomachine, particularly for a gas turbine, wherein thickened areas and depressions are formed and disposed on a lateral wall having a plurality of blades such that at least one depression or thickened area is disposed at a blade pressure side and at least one thickened area or depression is disposed at a blade suction side for each blade of the plurality of blades.
    Type: Application
    Filed: November 21, 2012
    Publication date: May 30, 2013
    Applicant: MTU AERO ENGINES GMBH
    Inventor: MTU AERO ENGINES GMBH
  • Publication number: 20130136612
    Abstract: A turbine is described for deriving energy from a fluid flow. The turbine has a plurality of generally arcuate blades that are rotatable about a rotational axis transverse to the direction of fluid flow. Each blade comprises a plurality of separately formed straight sections that are straight when unstressed, and that are joined to form a blade in which at least some adjacent sections are inclined at an angle to one another.
    Type: Application
    Filed: November 25, 2011
    Publication date: May 30, 2013
    Applicant: CLEAN GREEN ENERGY LLC
    Inventors: Rupert Stephen Tull de Salis, Brian Joseph Zaplitny
  • Publication number: 20130136619
    Abstract: A blading for a turbomachine, particularly for a gas turbine, wherein thickened areas and depressions formed and disposed on a lateral wall having a plurality of blades such that at least one depression is disposed on a blade pressure side and at least one thickened area is disposed on a blade suction side for each blade of the plurality of blades.
    Type: Application
    Filed: November 21, 2012
    Publication date: May 30, 2013
    Applicant: MTU AERO ENGINES GMBH
    Inventor: MTU Aero Engines GmbH
  • Publication number: 20130129517
    Abstract: Aerogenerator blade and method of manufacturing thereof, the aerogenerator blade comprising an intrados shell, an extrados shell and a structural beam, the structural beam comprising a root spar, a transitional spar and a box spar, wherein the root spar has a substantially circular cross section configured to support the connection of the blade to the aerogenerator hub; the transitional spar tapers from the root spar towards the box spar; and the box spar tapers towards the blade tip; and wherein the aerogenerator blade is characterized by comprising: a first section of the structural beam including at least a root spar portion, a transitional spar portion and a box spar portion, the portions forming a first integral structural beam section; a second section including at least the counterparts of the root spar portion, the transitional spar portion and the box spar portion, said counterpart portions forming a second integral structural beam section; and wherein the first section of the structural beam is join
    Type: Application
    Filed: May 20, 2010
    Publication date: May 23, 2013
    Applicant: TECSIS TECNOLOGIA E SISTEMAS AVANCADOS S.A.
    Inventors: Phillips Antonio Da Costa Lemos, Hely Ricardo Savii, Leo Ossanai, Tomaz Schmidt Cavalcante, Bruno Dal Medico Hirsch, Lúcio Corrêa Oliveira De Oliveira
  • Publication number: 20130115103
    Abstract: An article is disclosed that comprises a thermal material having a first surface and a second surface. The thermal material defines a film hole between the first surface and the second surface, and the film hole includes a metering portion adjacent the first surface and a diffuser portion adjacent the second surface. The metering portion defines a metering hole axis, and the diffuser portion defines a trench. The trench extends substantially parallel to a metering hole axis.
    Type: Application
    Filed: November 9, 2011
    Publication date: May 9, 2013
    Applicant: General Electric Company
    Inventors: Sandip Dutta, Gary Michael Itzel, Benjamin Paul Lacy
  • Publication number: 20130111752
    Abstract: A method of manufacturing a root section of a rotor blade of a wind turbine is disclosed. The method includes assembling a plurality of supporting rods with an interface section to a hub interface of the wind turbine in an essentially circular shape such that there are gaps between the supporting rods; arranging first fibres in the gaps which first fibres are physically and/or chemically compatible with an injection material; placing a first molding tool along an outer surface of the circular shape and a second molding tool along an inner surface of the circular shape, treating the injection material so that it bonds with the first fibres. The invention also concerns a supporting rod holding arrangement for such purpose and a root section of a rotor blade manufactured by such method.
    Type: Application
    Filed: October 30, 2012
    Publication date: May 9, 2013
    Inventors: Kristian Lehmann Madsen, Karsten Schibsbye
  • Publication number: 20130111751
    Abstract: A process for forming a turbine blade comprises the step of forming an as-cast turbine blade having an airfoil portion and a tip shroud, wherein the forming step comprises forming at least one as-cast cooling circuit within the tip shroud.
    Type: Application
    Filed: October 8, 2012
    Publication date: May 9, 2013
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventor: Eric A. Hudson
  • Patent number: 8434224
    Abstract: A method to manufacture an integrally bladed rotor, including: cutting a block of material by an abrasive waterjet, undertaken so as to reveal blade preforms extending radially from a disk, while retaining the material forming a linking mechanism between at least two preforms of directly consecutive blades, wherein the linking mechanism is spaced radially from the disk; followed by removal of the linking mechanism.
    Type: Grant
    Filed: March 25, 2009
    Date of Patent: May 7, 2013
    Assignee: SNECMA
    Inventors: Serge Berlanger, Sebastien Bordu, Thierry Jean Maleville, Christophe Charles Maurice Roca
  • Patent number: 8437628
    Abstract: A process for heat treating selected portions of an integrally bladed rotor (IBR) having a plurality of blades, the process using an IBR on a fixture having a rotor engaging portion that moves the IBR into an environmental chamber. An IR heater is placed on one of the IBR blades and heat treated after air has been removed from the chamber and an inert gas is added. The IR heater is lifted from the blade and indexed to position another blade on the IBR. The process is repeated until all the IBR blades are heat treated.
    Type: Grant
    Filed: January 30, 2012
    Date of Patent: May 7, 2013
    Assignee: United Technologies Corporation
    Inventors: Wangen Lin, James J. Moor, Thomas DeMichael, Herbert A. Chin, Melissa R. Hill, Michael J. Labbe
  • Publication number: 20130108446
    Abstract: A turbine rotor disk includes a row of buckets secured about a radially outer periphery of the rotor disk, each bucket having an airfoil, a platform, a shank and a mounting portion, the mounting portion received in a radial slot formed in the rotor disk such that adjacent buckets in adjacent radial slots are separated by a rotor disk post located between adjacent mounting portions and a shank cavity between adjacent shanks, radially outward of the rotor disk post and radially inward of adjacent platforms. The shank cavity is substantially filled with at least one discrete thermal plug.
    Type: Application
    Filed: October 28, 2011
    Publication date: May 2, 2013
    Applicant: GENERAL ELECTRIC COMPANY
    Inventor: Jeffrey John BUTKIEWICZ
  • Publication number: 20130108448
    Abstract: A turbine bucket includes a radially inner mounting portion; a shank radially outward of the mounting portion; at least one radially outer airfoil having a leading edge and a trailing edge; a substantially planar platform radially between the shank and the at least one radially outer airfoil; at least one axially-extending angel wing seal flange on a leading end of the shank thus forming a circumferentially extending trench cavity along the leading end of the shank, radially between an underside of the platform leading edge and a radially outer side of the angel wing seal flange; and slash faces along opposite, circumferentially-spaced side edges of the platform. At least one of the slash faces is formed with a dog-leg shape, a leading end of the at least one of slash face terminating at a location circumferentially offset from the leading edge of the at least one radially outer airfoil.
    Type: Application
    Filed: October 26, 2011
    Publication date: May 2, 2013
    Applicant: GENERAL ELECTRIC COMPANY
    Inventor: Clint Luigie INGRAM
  • Patent number: 8429817
    Abstract: A process for manufacturing a single-piece blisk, including: using an abrasive water jet to cut a block of material, so as to create blade preforms extending radially outwards from a disk, while keeping material forming a connecting mechanism between at least two directly consecutive blade preforms; then milling on the blade preforms so as to obtain profiled blade blanks; then a finishing by milling of the blade blanks, so as to obtain blades with a final profile; then removing the connecting mechanism.
    Type: Grant
    Filed: March 25, 2009
    Date of Patent: April 30, 2013
    Assignee: SNECMA
    Inventors: Serge Berlanger, Sebastien Bordu, Thierry Jean Maleville, Christophe Charles Maurice Roca
  • Patent number: 8429810
    Abstract: There is disclosed a method of manufacturing a rotor for a dynamoelectric machine. The rotor includes a rotating shaft, a rotor core fixed on the rotating shaft, and a cooling fan fixed to an axial end face of the rotor core. The method includes the step of fixing the cooling fan to the axial end face of the rotor core by resistance welding. The method is characterized in that in the resistance welding, both a positive electrode and a negative electrode are first brought into contact with the cooling fan to have the cooling fan held between the axial end face of the rotor core and both the positive and negative electrodes, and then weld current is supplied to flow from the positive electrode to the negative electrode.
    Type: Grant
    Filed: September 17, 2009
    Date of Patent: April 30, 2013
    Assignee: Denso Corporation
    Inventors: Ryotaro Kojima, Yuji Sugiyama, Keigo Moriguchi, Koji Kondo