Having Wear Liner, Sheathing Or Insert Patents (Class 416/224)
  • Patent number: 10704402
    Abstract: A gas turbine engine having a combustor, turbine and transition duct to channel hot gas from combustor to turbine. The transition duct has an internal surface on which the hot gas impinges causing a varying temperature profile. A thermal barrier coating is located on the internal surface having a first and second thermal barrier coating patch. The first patch having a first thickness located on the internal surface and within a first area subject to a higher temperature than an uncoated part and bounded by a first isotherm of a first temperature. The second patch having a second thickness located on the internal surface and within a second area subject to a higher temperature than the uncoated part and bounded by a second isotherm of a second temperature. The second temperature is higher than the first temperature and the second thickness is thicker than the first thickness.
    Type: Grant
    Filed: June 1, 2015
    Date of Patent: July 7, 2020
    Assignee: Siemens Aktiengesellschaft
    Inventors: Steven Brewer, Ghenadie Bulat, Robert Parke
  • Patent number: 10677067
    Abstract: A method of assembling an airfoil includes depositing a bonding material on a first end of the tip portion and shaping the bonding material to form a first plurality of features. The first plurality of features correspond to a second plurality of features on a second end of the body portion. The method also includes positioning the first end relative to the second end such that the first plurality of features and the second plurality of features interlock. The method further includes coupling the first end of the tip portion to the second end of the body portion.
    Type: Grant
    Filed: September 29, 2016
    Date of Patent: June 9, 2020
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Scott Andrew Weaver, Scott Michael Oppenheimer, Thomas Robert Raber, Scott McCulloch
  • Patent number: 10648451
    Abstract: A method for manufacturing a rotor blade of a wind power plant which has an area close to the blade root in which the rotor blade has an obtuse rear edge. The method includes manufacturing a half-shell on the pressure side and a half-shell on the suction side, introducing and adhesively bonding filler bodies into at least one section of the area of the obtuse rear edge of the pressure-side half-shell and the suction-side half-shell, wherein the sections with the filler bodies lie opposite one another in the assembled rotor blade, assembling and positioning the half-shells relative to one another, wherein an adhesive gap which is delimited by the first adhesive surfaces of the filler bodies remains between the filler bodies, and introducing an adhesive medium into the adhesive gap. Also a rotor blade manufactured according to the method, and a wind power plant including such a rotor blade.
    Type: Grant
    Filed: September 1, 2016
    Date of Patent: May 12, 2020
    Assignee: Senvion GmbH
    Inventors: Urs Bendel, Enno Eyb, Tilman Richers, Christian Flach, Hendrik Mester
  • Patent number: 10626884
    Abstract: A method of making a fan blade may include the steps of forming a core comprising fibrous material, and placing a first layer of dry fiber tows over the core using a robot. The first layer of dry fiber tows may be substantially un-crimped and may have a thermoplastic coating. A second layer of dry fiber tows may be placed over the first layer of dry fiber tows using the robot. The second layer may be un-crimped and coated similar to the first layer. The core, the first layer, and the second layer may be molded using resin transfer molding. The first layer may be placed over the core in a curved configuration. The core may include a three-dimensionally woven core formed on a loom and/or a plurality of layers of dry fiber tows placed by the robot.
    Type: Grant
    Filed: December 9, 2016
    Date of Patent: April 21, 2020
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventor: Daniel Ursenbach
  • Patent number: 10612393
    Abstract: A turbine airfoil includes a turbine component that includes a leading edge, a trailing edge, a pressure side wall extending between the leading edge and the trailing edge, a suction side wall extending between the leading edge and the trailing edge, a near wall source cavity disposed within the turbine component, and the near wall source cavity receives cooling air, and a second near wall cooling cavity disposed within the turbine component. The turbine airfoil further includes a first circuit completion plate disposed on a first end of the turbine component, and the first circuit completion plate fluidly couples the near wall source cavity to the second near wall cooling cavity.
    Type: Grant
    Filed: June 15, 2017
    Date of Patent: April 7, 2020
    Assignee: General Electric Company
    Inventors: Zachary John Snider, Allison Christine Gose, Daniel Burnos, Gregory Thomas Foster
  • Patent number: 10598025
    Abstract: An airfoil includes an airfoil section defining an airfoil profile, the airfoil section including a core structure and a plurality of rods disposed adjacent the core structure.
    Type: Grant
    Filed: November 17, 2016
    Date of Patent: March 24, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Raymond Surace
  • Patent number: 10570917
    Abstract: A fan blade includes a metallic body, a first composite cover, and a second composite cover. The metallic body may have a first side, a second side, a plurality of first retention slots, and a plurality of second retention slots, in accordance with various embodiments. The first and second retention slots may extend from the first side to the second side of the metallic body. The first composite cover may be coupled to the first side of the metallic body and may include a plurality of first fingers that extend through the first retention slots and are coupled to the second side of the metallic body. The second composite cover may be coupled to the second side of the metallic body and may include a plurality of second fingers that extend through the second retention slots and are coupled to the first side of the metallic body.
    Type: Grant
    Filed: August 1, 2016
    Date of Patent: February 25, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Michael A. Weisse
  • Patent number: 10562241
    Abstract: The application describes methods of making composite bodies including fibre-reinforced composite material with carbon fibre reinforcement and also a metal-containing portion (4). The metal-containing portion (4) is formed by laying up metal reinforcement elements, such as tapes of titanium alloy, among the carbon fibre reinforcement tapes which make up the composite body. The proportion of metal reinforcement may increase progressively towards the surface and/or towards an edge (14) of the composite body. In an example, metal leading and trailing edges (14,15) of a fan blade (1) are integrally formed in this way.
    Type: Grant
    Filed: March 29, 2017
    Date of Patent: February 18, 2020
    Assignee: ROLLS-ROYCE plc
    Inventor: Robert C Backhouse
  • Patent number: 10563636
    Abstract: A joint assembly for joining rotor blade segments of a wind turbine rotor blade includes a female structural member secured within a first rotor blade segment. The female structural member includes first bore holes on opposing sides thereof that are aligned in a chord-wise direction. Further, the joint assembly includes a male structural member extending longitudinally from an end face of a second rotor blade segment. As such, the male structural member is received within the female structural member of the first rotor blade segment such that the first and second rotor blade segments are aligned and connected. The male structural member includes second bore holes on opposing sides thereof. Further, the second bore holes are aligned with the first bore holes. Moreover, the joint assembly includes at least one chord-wise extending pin extending through the first and second bore holes so as to join the first and second rotor blade segments.
    Type: Grant
    Filed: August 7, 2017
    Date of Patent: February 18, 2020
    Assignee: General Electric Company
    Inventors: Aaron A. Yarbrough, Christopher Daniel Caruso, Scott Jacob Huth, Andrew Mitchell Rodwell
  • Patent number: 10557353
    Abstract: A fan blade having a damping system is provided. The fan blade comprising: a fan blade body having one or more compartments within the fan blade body; a damping material located within at least one of the one or more compartments; one or more partial ribs originating at the fan blade body and extending into at least one of the one or more compartments, wherein each of the one or more partial ribs terminate at a distal end; and one or more damping plates, wherein each of the one or more damping plates are attached to a distal end of a partial rib, wherein the damping material is located between the damping plate and the fan blade body.
    Type: Grant
    Filed: October 18, 2017
    Date of Patent: February 11, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Eric W. Malmborg, Thomas A. Pollack
  • Patent number: 10550823
    Abstract: A method for balancing segmented rotor blades for a wind turbine may include determining a weight for each of a plurality of blade segments, wherein each blade segment extends between a first end and a second and is configured to form a common spanwise section of a segmented rotor blade between the first and second ends. The method may also include determining an initial static moment for each blade segment based on the weight of the blade segment, wherein the initial static moment of at least one of the blade segments differing from the initial static moments of the remainder of the blade segments. Additionally, the method may include adding mass to each of the blade segments to increase the initial static moment for each blade segment to a predetermined static moment, wherein the predetermined static moment is greater than each of the initial static moments of the blade segments.
    Type: Grant
    Filed: August 10, 2016
    Date of Patent: February 4, 2020
    Assignee: General Electric Company
    Inventors: Aaron A. Yarbrough, Donald Joseph Kasperski, Daniel Alan Hynum, Christopher Daniel Caruso
  • Patent number: 10539025
    Abstract: An airfoil assembly including a composite body having a mounting edge and a trailing edge which is secured to a leading edge element defining a 3-D leading edge geometry with both chord and camber variation.
    Type: Grant
    Filed: February 10, 2016
    Date of Patent: January 21, 2020
    Assignee: General Electric Company
    Inventors: Nicholas Joseph Kray, Trevor Howard Wood, Dong-Jin Shim, Pranav Dhoj Shah
  • Patent number: 10539019
    Abstract: A set of stationary blades for a steam turbine is provided. At least one of the stationary blades includes a suction side and an opposite pressure side, and a plurality of ejection channels defined in the at least one stationary blade. Each of the plurality of ejection channels extends through an outer surface of the pressure side, and each of the plurality of ejection channels is coupled in flow communication to a blade inlet aperture.
    Type: Grant
    Filed: August 8, 2017
    Date of Patent: January 21, 2020
    Assignee: General Electric Company
    Inventors: Saeid Havakeshian, Krzysztof Cherek
  • Patent number: 10533574
    Abstract: The invention relates to a blade made of composite material, provided with a reinforcement (17) made of a stronger material with regard to a leading edge (5) likely to be struck by solid objects, which comprises, under the aerodynamic portion of the blade, extensions (18, 19) attached to the blade root. According to the invention, the extensions (18, 19) are dissymmetric, the extension (18) located on the suction side being generally further back from the leading edge (5) than the extension (19) on the pressure side.
    Type: Grant
    Filed: April 28, 2016
    Date of Patent: January 14, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Alexandre Damiens, Frédéric Jean-Bernard Pouzadoux, Gilles Pierre-Marie Notarianni
  • Patent number: 10508657
    Abstract: The present invention provides a stator component of a vacuum pump, which is suitable for reducing the fracture energy (energy of fracture that occurs when a rotor of the pump is damaged during its rotation) and the size of the pump, and also provides a vacuum pump having this stator component. In the vacuum pump, a spacer or of a thread groove pump stator, which is a stator component forms a gap satisfying the following <<condition>> between an outer circumferential surface of each of housed in a pump case of the vacuum pump, and an inner circumferential surface of the pump case, with the stator component being housed in the pump case. <<Condition>> 2d/D??max, where D is the outer diameter of the stator component (spacer or thread groove pump stator), d is the width of the gap, and ?max is the breaking elongation of the stator component.
    Type: Grant
    Filed: November 20, 2018
    Date of Patent: December 17, 2019
    Assignee: Edwards Japan Limited
    Inventor: Yoshiyuki Sakaguchi
  • Patent number: 10472971
    Abstract: A method for manufacturing a component having a defined geometry includes: a) defining a pre-component geometry including interim shape elements and additional, sacrificial elements for supporting interim elements; b) on a base plate, depositing multiple layers of a powder including a material from which the pre-component will be manufactured; c) sintering the powder to form the pre-component to the defined geometry; d) removing at least some of the sacrificial elements from the pre-component; e) subjecting the remaining pre-component from step d) to a HIP step; and f) removing remaining sacrificial elements from the pre-component product of step e) to provide a component to the defined component geometry. In the definition of the pre-component geometry, the interim elements differ from the corresponding final shape elements in the defined component geometry such that during the HIP step, the interim shape elements adjust to form final shape elements in the defined component geometry.
    Type: Grant
    Filed: August 9, 2016
    Date of Patent: November 12, 2019
    Assignees: ROLLS-ROYCE plc, ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Adrian L Harding, Jens Taege
  • Patent number: 10465528
    Abstract: Turn caps for airfoils of gas turbine engines including cavity sidewalls, a first turn cap divider extending between the cavity sidewalls and defining a turning cavity between the first turn cap divider and the cavity sidewalls, and a second turn cap divider disposed radially inward within the turning cavity. A first turning path is defined between the first turn cap divider and the second turn cap divider and a second turning path is defined radially inward of the second turn cap divider and a merging chamber is formed in the turn cap wherein fluid flows through the first turning path and the second turning path are merged, the merging chamber, the first turning path, and the second turning path forming the turning cavity.
    Type: Grant
    Filed: February 7, 2017
    Date of Patent: November 5, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Brandon W. Spangler, Dominic J. Mongillo, Jr.
  • Patent number: 10458428
    Abstract: An airfoil member (100) comprising has a substrate (120) along at least a portion of an airfoil (102) of the airfoil member. A sheath (122) has a channel (144) receiving a portion (160) of the substrate. A plurality of separate spacers (320; 380; 400) are between the sheath and the substrate and have a plurality of gaps between the spacers.
    Type: Grant
    Filed: August 4, 2014
    Date of Patent: October 29, 2019
    Assignee: United Technologies Corporation
    Inventors: Lee M. Drozdenko, James O. Hansen, Jesse C. Meyer, John J. Marcin, Jr., Robert M. Shemenski, Scot A. Webb, Brandon A. Gates, Michael A. Morden
  • Patent number: 10443612
    Abstract: An airfoil for a turbine engine includes an airfoil body with a cover mounting support, a first cover, and a second cover. The airfoil body includes a solid perimeter portion surrounding a recess formed into at least one of a suction side and a pressure side of the airfoil body, while the cover mounting support extends through the recess. The first cover can be engaged with a first edge of the recess and joined to a first portion of the cover mounting support by a first stir weld. The second cover can be engaged with a second edge of the recess, and joined to a second portion of the cover mounting support by a second stir weld.
    Type: Grant
    Filed: December 16, 2014
    Date of Patent: October 15, 2019
    Assignee: United Technologies Corporation
    Inventors: Frederick M. Schwarz, Michael A. Weisse
  • Patent number: 10436040
    Abstract: An airfoil with dual wall cooling for a gas turbine engine comprises a spar having pressure and suction side walls that meet at leading and trailing edges of the airfoil, with a tip extending therebetween. An interior of the spar includes a coolant cavity, and each of the pressure and suction side walls includes an arrangement of pedestals on an outer surface thereof and a plurality of cooling holes in fluid communication with the coolant cavity. A pressure side coversheet overlies the pressure side wall and terminates in a radial direction short of the tip of the spar to form a shelf extending along a chordal direction. Flow channels between the pressure side wall and coversheet are configured to direct coolant from the cooling holes to radial flow outlets adjacent to the shelf. A suction side coversheet overlies the suction side wall, and a coolant circuit between the suction side wall and coversheet does not include radial coolant outlets.
    Type: Grant
    Filed: October 11, 2017
    Date of Patent: October 8, 2019
    Assignee: Rolls-Royce Corporation
    Inventors: Jeffery F. Rhodes, Tyler C. Gillen, Christopher Nash, Brian Shoemaker, Brett J. Barker
  • Patent number: 10415588
    Abstract: A lightweight fan blade for use in turbofan gas turbine engines is disclosed. The fan blade includes a metallic body having a pressure side and a suction side. The suction side of the body includes one or more cavities. A cover is then attached to the suction side of the body to cover or enclose the one or more cavities. The cover includes one or more transverse weakened areas, such as a transverse slit so that the cover separates into one or more smaller segments in the event of a foreign object damage (FOD) or fan blade out (FBO) event occurs. The smaller segments of the cover are less likely to do damage to downstream components such as the low and high-pressure compressors. A single smaller segment of the cover may allow for continued operation of the engine because the imbalance created by the event may be tolerated by the engine.
    Type: Grant
    Filed: September 29, 2014
    Date of Patent: September 17, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Charles H. Roche
  • Patent number: 10344772
    Abstract: A fan blade for a turbofan gas turbine engine is disclosed. The fan blade includes a body having a pressure side and a suction side and a cover. The suction side of the body includes an opening and at least one cavity for purposes of reducing the weight of the fan blade. The cover overlays the opening and includes a peripheral edge that is received in a slot defined by the body. The cavities are filled with a sacrificial material.
    Type: Grant
    Filed: September 29, 2014
    Date of Patent: July 9, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Charles H. Roche
  • Patent number: 10337521
    Abstract: A fan blade for a turbofan gas turbine engine is disclosed. The fan blade includes a body having a pressure side and a suction side. The body also includes a leading edge, a trailing edge, a distal tip and a base that is coupled to a hub. The suction side of the body includes at least one cavity for purposes of reducing the weight of the fan blade. The at least one body is surrounded by a slot that extends outwardly away from the cavity. A lip that extends inwardly towards the body further defines the slot. A cover is provided that overlays the cavity and includes a peripheral edge that is received in the slot and that is at least partially covered by the lip for a robust connection between the fan blade body and the cavity cover.
    Type: Grant
    Filed: September 29, 2014
    Date of Patent: July 2, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Charles H. Roche
  • Patent number: 10316818
    Abstract: The present disclosure is directed to a method for manufacturing a thermoset component having a weldable thermoplastic interface. The method includes forming a polymerized thermoplastic component having a removable protective layer on a portion thereof. Another step includes placing a plurality of dry plies and the thermoplastic component into a mold of the thermoset component with the removable protective layer facing an outer surface of the thermoset component mold. Thus, the method further includes co-infusing the dry plies and thermoplastic component with a resin material so as to form the thermoset component having a weldable thermoplastic interface.
    Type: Grant
    Filed: March 21, 2016
    Date of Patent: June 11, 2019
    Assignee: General Electric Company
    Inventors: Christopher Daniel Caruso, Aaron A. Yarbrough, Daniel Alan Hynum
  • Patent number: 10293424
    Abstract: The disclosure describes techniques for joining a first part including a ceramic or a CMC and a second part including a ceramic or a CMC using brazing. A technique may include positioning a filler material in a joint region between the first and second parts and a metal or alloy on a bulk surface of the filler material. The metal or alloy may be locally heated to melt the metal or alloy, which may infiltrate the filler material. A constituent of the molten metal or alloy may react with a constituent of the filler material to join the first and second parts. Another technique may include depositing a powder that includes the filler material and the metal or alloy in the joint region. Substantially simultaneously with depositing the powder, the powder may be locally heated. A constituent of the molten metal or alloy may react with a constituent of the filler material to join the first and second parts.
    Type: Grant
    Filed: May 2, 2016
    Date of Patent: May 21, 2019
    Assignee: Rolls-Royce Corporation
    Inventors: Sean E. Landwehr, Scott Nelson, Jacque Sue Bader
  • Patent number: 10266247
    Abstract: A device for protecting an airfoil element made of a complex comprising a polymer film, a metal strip deposited on a part of the polymer film and an adhesive element to attach the polymer film on the airfoil element. The polymer film forms a protection against sand abrasion. The metal strip forms a protection against water abrasion of the airfoil element on which the complex is attached.
    Type: Grant
    Filed: February 28, 2015
    Date of Patent: April 23, 2019
    Assignees: Airbus SAS, Airbus Helicopters
    Inventors: Daniel Aliaga, Marie-Paule Guillou, Elisa Campazzi, Thomas Navarre
  • Patent number: 10259574
    Abstract: Sounds are generated by an aerial vehicle during operation. For example, the motors and propellers of an aerial vehicle generate sounds during operation. Disclosed are systems, methods, and apparatus for actively adjusting the position of one or more propeller blade treatments of a propeller blade of an aerial vehicle during operation of the aerial vehicle. For example, the propeller blade may have one or more propeller blade treatments that may be adjusted between two or more positions. Based on the position of the propeller blade treatments, the airflow over the propeller is altered, thereby altering the sound generated by the propeller when rotating. By altering the propeller blade treatments on multiple propeller blades of the aerial vehicle, the different sounds generated by the different propeller blades may effectively cancel, reduce, and/or otherwise alter the total sound generated by the aerial vehicle.
    Type: Grant
    Filed: December 18, 2015
    Date of Patent: April 16, 2019
    Assignee: Amazon Technologies, Inc.
    Inventors: Brian C. Beckman, Gur Kimchi, Allan Ko
  • Patent number: 10259138
    Abstract: An injection mold system for injecting slurry into an internal portion of an injection mold component core is disclosed. The system may include a fill clip for injecting slurry into an internal portion of an injection mold component core including a fill member for injecting slurry into the internal portion of the injection mold component core, and a latch member for removably coupling the fill member with the injection mold component core. The system may also include a fill reservoir for collecting excess slurry from the internal portion of the injection mold component core. The fill reservoir may also redistribute the excess slurry back into the internal portion of the injection mold component core.
    Type: Grant
    Filed: January 27, 2017
    Date of Patent: April 16, 2019
    Assignee: General Electric Company
    Inventors: Dillon Mathew Smith, Travis J Packer, James Stuart Pratt
  • Patent number: 10260515
    Abstract: The present invention provides a stator component of a vacuum pump, which is suitable for reducing the fracture energy (energy of fracture that occurs when a rotor of the pump is damaged during its rotation) and the size of the pump, and also provides a vacuum pump having this stator component. In the vacuum pump, a spacer or of a thread groove pump stator, which is a stator component forms a gap satisfying the following <<condition>> between an outer circumferential surface of each of housed in a pump case of the vacuum pump, and an inner circumferential surface of the pump case, with the stator component being housed in the pump case. <<Condition>> 2d/D??max, where D is the outer diameter of the stator component (spacer or thread groove pump stator), d is the width of the gap, and ?max is the breaking elongation of the stator component.
    Type: Grant
    Filed: June 6, 2014
    Date of Patent: April 16, 2019
    Assignee: Edwards Japan Limited
    Inventor: Yoshiyuki Sakaguchi
  • Patent number: 10260351
    Abstract: An airfoil for a gas turbine engine includes a substrate and a sheath providing an edge. A cured adhesive secures the sheath to the substrate. The cured adhesive has a fillet that extends beyond the edge that includes a mechanically worked finished surface. A method of manufacturing the airfoil includes the steps of securing a sheath to a substrate with adhesive, curing the adhesive, and mechanically removing a portion of the adhesive extending beyond the sheath.
    Type: Grant
    Filed: March 16, 2012
    Date of Patent: April 16, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Michael Parkin, James O. Hansen, Christopher J. Hertel, David R. Lyders
  • Patent number: 10196907
    Abstract: A turbomachine rotor blade includes an outer part at its distal end. The outer part includes a platform defining an outside surface of a passage for gas passing through a turbomachine and presenting first and second opposite side edges; and upstream and downstream sealing wipers extending outwards from the platform, each wiper extending between two lateral faces situated respectively at the first and second side edges. The two lateral faces of the upstream or the downstream wiper are covered at least in part in an anti-wear material.
    Type: Grant
    Filed: January 16, 2013
    Date of Patent: February 5, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Slim Bensalah, Arnaud Negri, Sebastien Digard Brou De Cuissart, Guillaume Klein, Ba-Phuc Tang, David Mathieu, Sibylle Doremus
  • Patent number: 10174626
    Abstract: A partially coated blade for a gas turbine engine, including a fillet surface surrounding the airfoil section and connecting it to the platform section. A radially outermost portion of the pressure side and leading edge is covered by a thermal barrier coating. This portion extends radially from a first limit to the blade tip. The first limit is located at a radial distance from the platform of at most 21% of the maximum span. The fillet surface is free or substantially free of the thermal barrier coating. In another embodiment, a second portion of the pressure side and of the leading edge is free or substantially free of the thermal barrier coating, extending radially from the platform section to a second limit located a radial distance from the platform section corresponding to at least 5% of the maximum span. A method of applying a thermal barrier coating is also discussed.
    Type: Grant
    Filed: October 15, 2014
    Date of Patent: January 8, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Michael Papple, Daniel Lecuyer
  • Patent number: 10125616
    Abstract: A fan blade for an aircraft engine, including a leading edge, a trailing edge, a suction side, a pressure side and a blade tip, is provided. The fan blade has a large-area elastomer layer which takes up at least 20% of the surface of the suction side of the fan blade.
    Type: Grant
    Filed: February 12, 2016
    Date of Patent: November 13, 2018
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Knut Rosenau
  • Patent number: 10094220
    Abstract: A method for patching a damaged polymeric erosion coating (250) on a gas turbine engine component. The method comprises removing a portion of the coating around a damage site (200; 202; 204) and applying a pre-formed coating patch (220).
    Type: Grant
    Filed: December 2, 2013
    Date of Patent: October 9, 2018
    Assignee: United Technologies Corporation
    Inventors: John H. Vontell, Sr., Charles R. Watson
  • Patent number: 10072505
    Abstract: A turbine blade having a root and a tip and an airfoil with a core section made of composite material and a protective sheath or layer joined to the composite core at a location or locations exposed to erosion is described with the composite core of the airfoil being continuous from a location in vicinity of the root to a location in vicinity of the tip of the blade and including a section which widens with distance from the rotational axis along the length of the airfoil and which ends at the location in vicinity of the tip of the blade. The protective sheath or layer is secured by interference fit with widening section of the core.
    Type: Grant
    Filed: June 15, 2012
    Date of Patent: September 11, 2018
    Assignee: General Electric Technology GmbH
    Inventors: Rolf Hunziker, Said Havakechian
  • Patent number: 10047613
    Abstract: A gas turbine component is provided. The gas turbine component includes an airfoil having a leading edge, a trailing edge, a suction side extending from the leading edge to the trailing edge, and a pressure side extending from the leading edge to the trailing edge opposite the suction side. The gas turbine component also includes a thermal barrier coating applied to the airfoil pressure side such that an uncoated margin is defined on the pressure side at the trailing edge.
    Type: Grant
    Filed: August 31, 2015
    Date of Patent: August 14, 2018
    Assignee: General Electric Company
    Inventors: Cody Jermaine Ford, Brad Wilson VanTassel
  • Patent number: 9938838
    Abstract: A composite turbine blade for high-temperature applications such as gas turbines or the like includes a root for mounting the blade in a corresponding circumferential assembly groove of a rotor and an airfoil connected to said root. An inner carrying structure is provided extending at least over a portion of the root as well as at least a portion of said airfoil. The inner carrying structure is made of a high strength eutectic ceramic and the airfoil is made of a ceramic matrix composite (CMC) material.
    Type: Grant
    Filed: January 21, 2015
    Date of Patent: April 10, 2018
    Assignee: ANSALDO ENERGIA IP UK LIMITED
    Inventors: Gregoire Etienne Witz, Michael Stuer, Hans-Peter Bossmann
  • Patent number: 9926798
    Abstract: A method of making a fan annulus filler for use in a fan assembly of a gas turbine engine may include an annulus filler body formed of a polymer. The annulus filler body may include a surface coated with a nanocrystalline coating to form a flow surface.
    Type: Grant
    Filed: August 7, 2015
    Date of Patent: March 27, 2018
    Assignee: Rolls-Royce Corporation
    Inventor: Wade A. Vest
  • Patent number: 9908124
    Abstract: A scroll conveyor tile protection or any other material subject to wear with a weldable support and a wear resistant insert, not necessary weldable. The support is fit with a flat surface and shoulder allowing for precise positioning of tile on a scroll flight to be protected. At least one opening, preferably at its center, allows for insertion and assembly of a complementary shaped insert. The unit setting up on the scroll flight and the contact between the flight faces and the unit faces allows for creating a dove tail locking system. Welding of the support permanently insures locking of the system and insert being maintained without being otherwise fixed beyond this mechanical clamping.
    Type: Grant
    Filed: May 15, 2013
    Date of Patent: March 6, 2018
    Assignee: ANDRITZ S.A.S.
    Inventors: Denis Lamy, Jean-Marc Huyghe
  • Patent number: 9896936
    Abstract: A fan assembly for gas assembly engine is disclosed. The fan assembly includes a rotor that is coupled to at least one fan blade. The fan assembly also includes a spinner that extends towards the rotor and the fan blades so that an edge of the spinner engages the fan blades. The edge of the spinner thereby serves as a grounding element for the fan blade. If the spinner is fabricated from a composite or a plastic material that is not sufficiently conductive for grounding purposes, the edge may be coated with a conductive material. Alternatively, the spinner may be fabricated from a metallic material, which would eliminate the need for a conductive coating on the edge that engages the fan blades.
    Type: Grant
    Filed: October 15, 2014
    Date of Patent: February 20, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Sean A. Whitehurst, Patrick James McComb
  • Patent number: 9890641
    Abstract: An integrally bladed rotor includes a rim integral with a web that extends radially inward to a bore. The rim provides an end wall from which integral blades extend radially outward to a tip. The blades have an airfoil that extends in a chord-wise direction from a leading edge to a trailing edge. A fillet circumscribes the airfoil and joins the airfoil to the end wall. The fillet is at one of the leading edge and the trailing edge is truncated at least 50% in an axial direction to provide a face of the rim.
    Type: Grant
    Filed: January 15, 2015
    Date of Patent: February 13, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Christopher L. Potter, Michael Espinoza
  • Patent number: 9885244
    Abstract: A metallic leading edge protective strip adapted to provide impact protection for a leading edge of an airfoil of a turbomachine. The protective strip is formed of a stainless steel or a nickel-based alloy and is denser and provides increased strength and elasticity characteristics as compared to an identical protective strip formed of a titanium-based alloy. The protective strip is particularly suitable for use with composite blades and allows for thinner airfoils, thereby improving engine efficiency.
    Type: Grant
    Filed: June 28, 2013
    Date of Patent: February 6, 2018
    Assignee: General Electric Company
    Inventors: Nicholas Joseph Kray, Dong-Jin Shim, Tod Winton Davis
  • Patent number: 9752443
    Abstract: A ceramic matrix composite member used as a turbine blade includes a principal part forming a blade part and a dovetail part, and a subordinate part forming a platform part. A principal fiber in a ceramic fiber fabric forming the principal part is a continuous fiber. An extension direction of the principal fiber is in parallel with a direction in which stress is applied. The ceramic fiber fabrics respectively forming the principal part and the subordinate part are joined together and formed into an integrated three-pronged fiber fabric. The ceramic fiber fabric forming the principal part and the ceramic fiber fabric forming the subordinate part are integrated together by being set into a mold with the ceramic fiber fabric forming the subordinate part folded at a desired angle to the ceramic fiber fabric forming the principal part. Then, a ceramic matrix is formed in the obtained molded body.
    Type: Grant
    Filed: April 10, 2014
    Date of Patent: September 5, 2017
    Assignee: IHI Corporation
    Inventor: Fumiaki Watanabe
  • Patent number: 9726192
    Abstract: Fans having fan blades with lightweight blade tips are disclosed herein. In one embodiment, for example, each fan blade includes a blade tip attached to an end portion of a main airfoil. The blade tip includes a shaped body that is molded over a support structure to form the shape and exterior surface of the blade tip.
    Type: Grant
    Filed: March 31, 2015
    Date of Patent: August 8, 2017
    Assignee: ASSA ABLOY Entrance Systems AB
    Inventors: L. Blake Whitley, Richard K. Hoofard
  • Patent number: 9702257
    Abstract: A fan rotor blade includes a blade body made from a composite material of a resin and fibers, and having a pressure surface facing one side in a rotation direction and a suction surface facing the other side in the rotation direction. The blade body is provided with a sheath which is more rigid than the blade body and is fixed to the blade body in a state where the sheath covers a leading edge portion of the blade body, which is located on an upstream side in the direction of intake of external air, and the vicinity thereof. A tip end portion of the sheath extends from the leading edge portion side of the blade body to a trailing edge portion side of the blade body. An end portion of the tip end portion of the sheath is flush with the trailing edge portion of the blade body.
    Type: Grant
    Filed: July 28, 2014
    Date of Patent: July 11, 2017
    Assignee: IHI Corporation
    Inventors: Hiroyuki Yagi, Hiroshi Kuroki, Kenro Obuchi
  • Patent number: 9689269
    Abstract: A component of a gas turbine engine is provided. The component has a leading edge with two air-washed surfaces extending rearwardly therefrom to define opposing sides of the component. The component has a leading edge protector formed as a plurality of protector segments which succeed in a line along the leading edge. Each protector segment includes a sheath which covers the leading edge and the air-washed surfaces at regions adjacent the leading edge. Each protector segment overlaps with the neighboring sheath of the succeeding segment.
    Type: Grant
    Filed: January 14, 2015
    Date of Patent: June 27, 2017
    Assignee: ROLLS-ROYCE plc
    Inventor: Kristofer John Bottome
  • Patent number: 9664051
    Abstract: A root section of a rotor blade for interacting with working fluid upon rotating the rotor blade is provided. The root section includes a curved cooling passage for guiding a cooling fluid within the root section. A cooling fluid entry plenum has an entry aperture for introducing the cooling fluid into the cooling passage. A platform is located at a radially outer end of the root section. The curved cooling passage penetrates through the platform, and the following condition is satisfied at least in a portion of a radial extent of the cooling passage: 0.25*dr<rc<1.5*dr, where dr is a radial distance in the radial direction between the platform of the root section and the aperture of the entry plenum and rc is the radius of curvature of the curved cooling passage.
    Type: Grant
    Filed: May 30, 2012
    Date of Patent: May 30, 2017
    Assignee: SIEMENS AKTIENGESELLSCHAFT
    Inventors: Richard Bluck, Carlos Felipe Favaretto, Stuart Stott
  • Patent number: 9556742
    Abstract: A composite airfoil includes a core that has a three-dimensional network of fibers. The core defines an airfoil section and a root section. A composite skin covers a portion of the core excluding the root section.
    Type: Grant
    Filed: November 29, 2010
    Date of Patent: January 31, 2017
    Assignee: United Technologies Corporation
    Inventors: Michael Parkin, Phillip Alexander, Carl Brian Klinetob
  • Patent number: 9470095
    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. 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. A lattice network connects the first side and the second side. The lattice network includes at least one enlarged node spaced apart from the first side wall and the second side wall and ribs that extend from the at least one enlarged node. Each of the ribs connects to one of the first side wall and the second side wall.
    Type: Grant
    Filed: April 24, 2012
    Date of Patent: October 18, 2016
    Assignee: United Technologies Corporation
    Inventors: Tracy A. Propheter-Hinckley, Sergio M. Loureiro, Agnes Klucha, Benjamin T. Fisk, Anita L. Tracy
  • Patent number: RE47696
    Abstract: A composite aerofoil, the aerofoil having a leading edge, a trailing edge a pressure side and a suction side and comprising an outer erosion protection layer along one or both of the pressure side or suction side, a structural core having a plurality of resin impregnated plies of unidirectional fibers, and between the outer erosion protection layer and the structural core a woven composite impregnated with a resin having a modulus of elasticity greater lower than that of the resin impregnating the plies in the structural core.
    Type: Grant
    Filed: May 31, 2017
    Date of Patent: November 5, 2019
    Assignee: Rolls-Royce, PLC
    Inventors: Simon Read, Bijoysri Khan