Assembling Individual Fluid Flow Interacting Members, E.g., Blades, Vanes, Buckets, On Rotary Support Member Patents (Class 29/889.21)
  • Patent number: 11066944
    Abstract: There is disclosed a shroud for a compressor stator, including: shroud segments extending circumferentially around an axis along portions of a circumference of the shroud. At least one of the shroud segments extending from a first lateral edge to a second lateral edge. The shroud segment has an inner face oriented toward the axis and an opposed outer face oriented away from the axis. At least one opening extends from the inner face to the outer face for receiving a vane of the compressor. A tab protrudes circumferentially from the second lateral edge and away from the first lateral edge. A slot extends circumferentially from the first lateral edge toward the second lateral edge. The tab is matingly received within a slot of an adjacent one of the shroud segments.
    Type: Grant
    Filed: February 8, 2019
    Date of Patent: July 20, 2021
    Assignee: PRATT & WHITNEY CANADA CORP
    Inventors: Tibor Urac, Barry Barnett
  • Patent number: 11053804
    Abstract: A shroud for a turbine blade includes a shroud body having an outer side and opposite first and second Z-shaped side edges; a first sealing fin and a second sealing fin extending outwardly from the outer side and spaced apart from each other in a streamwise direction, the first and second sealing fins extending between the first and second side edges of the shroud body; a first ridge extending radially outwardly from the outer side, the first ridge extending from and connecting the first and second sealing fins along the first side edge and having a radial height which varies; and a second ridge extending radially outwardly from the outer side, the second ridge extending from and connecting the first and second sealing fins along the second side edge and having a radial height which varies.
    Type: Grant
    Filed: May 8, 2019
    Date of Patent: July 6, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Niloofar Moradi, John Pietrobon
  • Patent number: 11028697
    Abstract: A fan section for a gas turbine engine is disclosed herein. The fan may include a rotor disk and a plurality of airfoils fixedly attached to and supported by the rotor disk as a single unitary piece. The airfoils may extend radially outward from the rotor disk with respect to an engine axis. The rotor disk may be made of metal and the airfoils may each be made at least partially of an organic matrix composite.
    Type: Grant
    Filed: December 19, 2013
    Date of Patent: June 8, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Gary D. Roberge
  • Patent number: 11021971
    Abstract: A blade for a gas turbine engine includes a fiber reinforced ceramic matrix composite structure that provides an airfoil with an exposed exterior airfoil surface and a refractory structure that provides at least an outer portion of a root secured relative to the airfoil.
    Type: Grant
    Filed: September 17, 2014
    Date of Patent: June 1, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: John E. Holowczak, Michael G. McCaffrey
  • Patent number: 11008888
    Abstract: A turbine vane assembly adapted for use in a gas turbine engine includes a vane support and a vane heat shield comprising ceramic matrix composite materials to insulate the metallic materials of the vane support. The turbine vane assembly further includes an aero-load transfer rib located outside of a primary gas path and configured to carry loads applied to the vane heat shield to the vane support.
    Type: Grant
    Filed: July 17, 2018
    Date of Patent: May 18, 2021
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Aaron D. Sippel, Ted J. Freeman, David J. Thomas, Adam L. Chamberlain
  • Patent number: 11002247
    Abstract: A wind turbine blade and method of manufacture, the blade extending between root and tip ends on a longitudinal axis and having root, transition, and airfoil regions. The blade has a profiled contour with a chord extending between the leading and trailing edges; a blade shell with a first blade shell part with a pressure side and a second blade shell part with a suction side, the blade shell parts extending between root and tip ends and are joined on a primary glue joint; first and second main spar caps integrated in the first and the second blade shell parts, respectively, and have one or more shear webs there between. A third blade shell part may be present and joined to the first blade shell part along a first secondary glue joint and to the second blade shell part along a second secondary glue joint.
    Type: Grant
    Filed: July 12, 2017
    Date of Patent: May 11, 2021
    Assignee: LM WIND POWER US TECHNOLOGY APS
    Inventors: David Roberts, Allan Riber
  • Patent number: 10982555
    Abstract: A root extending from a platform of an airfoil is disclosed. The root may include a first portion having a generally cylindrical shape, and a second portion extending from the first portion to the platform. The second portion may have a circumference larger than a circumference of the first portion.
    Type: Grant
    Filed: February 27, 2014
    Date of Patent: April 20, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Nicholas Aiello, John C. Duong
  • Patent number: 10975703
    Abstract: A gaspath component includes a body having at least one internal cooling passage and a metering feature integral to the internal cooling passage. The metering feature and the body are a unitary structure.
    Type: Grant
    Filed: October 27, 2016
    Date of Patent: April 13, 2021
    Assignee: Raytheon Technologies Corporation
    Inventor: Mark T. Ucasz
  • Patent number: 10954796
    Abstract: A rotor assembly includes a plurality of rotor disks that each have a rim portion. The plurality of rotor disks includes a first rotor disk and at least one first bleed air passage that extends through a forward rim portion of the first rotor disk. At least one second bleed air passage that extends through an aft rim portion of the first rotor disk.
    Type: Grant
    Filed: August 13, 2018
    Date of Patent: March 23, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Christopher J. Knortz, William W. Frank, Erica J. Harvie, Conor Lee
  • Patent number: 10876412
    Abstract: A gas turbine engine 10 is provided in which a fan having fan blades 139 in which the camber distribution relative to covered passage of the fan 13 allows the gas turbine engine to operate with improved efficiency when compared with conventional engines, whilst retaining an acceptable flutter margin.
    Type: Grant
    Filed: October 25, 2018
    Date of Patent: December 29, 2020
    Inventors: Mark J. Wilson, Stephane M M Baralon, Benedict Phelps
  • Patent number: 10876405
    Abstract: A removal device includes a base, a push rod, a rod-moving mechanism and a rod guide. The base is restrained immovably in a first direction. The push rod can protrude from a front surface of the base toward a front side. The rod-moving mechanism is installed on the base. The rod-moving mechanism moves the push rod toward the front side. The rod guide is attached to the base. The rod guide guides movement of the push rod by the rod-moving mechanism in a second direction that forms an acute angle with respect to the first direction.
    Type: Grant
    Filed: December 27, 2016
    Date of Patent: December 29, 2020
    Assignee: MITSUBISHI POWER, LTD.
    Inventors: Shinji Yoshida, Tadakazu Sakaguchi, Shouhei Ooba
  • Patent number: 10876410
    Abstract: An airfoil array for a turbomachine, in particular a turbine or compressor stage of a gas turbine.
    Type: Grant
    Filed: July 11, 2018
    Date of Patent: December 29, 2020
    Assignee: MTU Aero Engines AG
    Inventors: Inga Mahle, Markus Brettschneider, Fadi Maatouk
  • Patent number: 10864585
    Abstract: Various embodiments include a system for machining a hole in a turbine blade. The system can include: a mount for engaging a first side of a turbine rotor, the mount including: a drill plate for coupling with the first side of the turbine rotor, the drill plate having: a body; a feed opening on a first side of the body; a passage extending from the feed opening through the body; and a second opening on a second side of the body, the second opening coupled with the passage and positioned to align with the pre-formed hole in the turbine rotor; an alignment bushing for engaging the pre-formed hole in the rotor at a second side of the rotor; and a cutting device for extending through the body and alignment bushing, the cutting device for machining the hole in the blade, the cutting device aligned along a chamfer axis relative to a primary axis of the turbine rotor.
    Type: Grant
    Filed: March 13, 2017
    Date of Patent: December 15, 2020
    Assignee: General Electric Company
    Inventors: Phillip Charles Johnson, Robert Charles Malison, John Matthew Sassatelli
  • Patent number: 10844868
    Abstract: A free-tipped axial fan assembly features a shroud barrel comprising an inlet, the radius of said inlet at its upstream end being greater than the radius of said inlet at its downstream end. An angle, in a plane including the fan axis, between the surface of said inlet and the direction of the fan axis varies non-monotonically with respect to a surface coordinate which increases with distance along the surface of the inlet.
    Type: Grant
    Filed: April 15, 2016
    Date of Patent: November 24, 2020
    Assignee: Robert Bosch GmbH
    Inventors: Robert J. Van Houten, Yoonshik Shin
  • Patent number: 10767502
    Abstract: A turbine vane made from ceramic matrix composite material and adapted for use in a gas turbine engine. The turbine vane is made from ceramic matrix composite materials with three-dimensionally woven or braided reinforcing tows and includes an inner band, an outer band, and an airfoil that extends between the inner band and the outer band.
    Type: Grant
    Filed: March 17, 2017
    Date of Patent: September 8, 2020
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc., Rolls-Royce High Temperature Composites Inc.
    Inventors: Tara G. Schetzel, Ted J. Freeman, Jun Shi, Jeffrey A. Walston, Steven Clarke, Sean Kroszner
  • Patent number: 10767496
    Abstract: A turbine blade assembly adapted for use in a gas turbine engine is disclosed in this paper. A primary member of the turbine blade assembly shaped to form an airfoil and comprises ceramic matrix composite materials. A independent platform of the turbine blade assembly is coupled to the primary member of the turbine blade assembly such that the primary member need not be shaped to provide the platform.
    Type: Grant
    Filed: March 23, 2018
    Date of Patent: September 8, 2020
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Ted J. Freeman, Michael A. Kowalkowski
  • Patent number: 10738626
    Abstract: A turbine engine including: rotor blades circumferentially arrayed about a rotor wheel; a connection assembly by which each of the rotor blades connects to the rotor wheel, the connection assembly including: an axially oriented slot formed through a perimeter face of the rotor wheel; a root of the rotor blade installed within the slot, the root being shaped in relation to the slot such that the installation therein forms an axially extending shim cavity between opposing exterior surfaces of the root and the slot; and a shim installed within the shim cavity for restraining movement of the rotor blade relative to the rotor wheel in a radial direction.
    Type: Grant
    Filed: October 24, 2017
    Date of Patent: August 11, 2020
    Assignee: General Electric Company
    Inventors: Steven Sebastian Burdgick, Thomas Joseph Farineau, Timothy Scott McMurray, John James Ligos
  • Patent number: 10738640
    Abstract: A shroud (22) comprises shroud bodies (22) fixed to blade tips of blades (18) mounted to a rotor body to extend in a radial direction, the shroud bodies (22) being disposed adjacent to one another in a circumferential direction, wherein each of the shroud bodies (22) includes a circumferential end surface (27, 28) that includes an abutting end surface where adjacent shroud bodies (22) abut, and an opposing surface (34) where adjacent shroud bodies (22) face one another with a clearance (32) therebetween, the opposing surface (34) being contiguous with the abutting end surface; and an outer surface (24) that includes a radially outward protruding protrusion (40) formed to extend along the opposing surface (34).
    Type: Grant
    Filed: March 11, 2015
    Date of Patent: August 11, 2020
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Hitoshi Kitagawa, Takashi Hiyama, Daigo Fujimura
  • Patent number: 10718223
    Abstract: A turbomachine airfoil element includes an airfoil that has pressure and suction sides spaced apart from one another in a thickness direction and joined to one another at leading and trailing edges. The airfoil extends in a radial direction a span that is in a range of 1.13-1.23 inch (28.7-31.2 mm). A chord length extends in a chordwise direction from the leading edge to the trailing edge at 50% span and is in a range of 0.64-0.74 inch (16.3-18.8 mm). The airfoil element includes at least two of a first mode with a frequency of 1634±10% Hz, a second mode with a frequency of 5611±10% Hz, a third mode with a frequency of 19027±10% Hz, a fourth mode with a frequency of 29268±10% Hz, a fifth mode with a frequency of 33103±10% Hz, a sixth mode with a frequency of 34908±10% Hz and a seventh mode with a frequency of 41277±10% Hz.
    Type: Grant
    Filed: January 11, 2018
    Date of Patent: July 21, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Charles H. Warner, William R. Edwards, Mark David Ring, Sean Nolan, Ernest D. Casparie
  • Patent number: 10711636
    Abstract: A system for coating a component is provided. The system includes a feedstock supply, a carrier fluid supply, and a thermal spray gun coupled in flow communication with the feedstock supply and the carrier fluid supply. The feedstock supply contains a substantially homogeneous powder mixture of a first powder and a second powder. The second powder is softer than the first powder and has a percentage by mass of the powder mixture of between about 0.1% and about 3.0%.
    Type: Grant
    Filed: December 22, 2015
    Date of Patent: July 14, 2020
    Assignee: General Electric Company
    Inventors: Eklavya Calla, Joydeep Pal, Krishnamurthy Anand
  • Patent number: 10669859
    Abstract: A turbine stator vane or turbine rotor vane has a body, a channel being adapted for leading a cooling fluid through the body, and a flow adaption feature protruding from the body to the channel in such a manner as to reduce a cross-sectional area of the channel.
    Type: Grant
    Filed: July 6, 2016
    Date of Patent: June 2, 2020
    Assignee: Siemens Aktiengesellschaft
    Inventor: Stephen Batt
  • Patent number: 10655482
    Abstract: A vane ring for a gas turbine engine includes an outer end wall and a plurality of spars coupled to the outer end wall. The vane ring further includes an inner end wall positioned radially inward of the outer end wall and coupled to the spars. The outer and inner end walls cooperate to form a flowpath.
    Type: Grant
    Filed: February 4, 2016
    Date of Patent: May 19, 2020
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Ted J. Freeman, Jeffrey A. Walston, Jun Shi, Tara G. Schetzel
  • Patent number: 10641113
    Abstract: An airfoil cluster includes an inner diameter platform and an outer diameter platform. A plurality of airfoils extend radially from the inner diameter platform to the outer diameter platform. Each airfoil has a leading edge and a trailing edge, and pressure and suction sides between the leading and trailing edges. At least one of the airfoils includes a recessed portion on the pressure side adjacent to the trailing edge.
    Type: Grant
    Filed: April 8, 2015
    Date of Patent: May 5, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Takao Fukuda, Scott D. Hartmann
  • Patent number: 10625370
    Abstract: The present disclosure provides a rotary friction welding process including: providing an outer axisymmetric workpiece having a front first annular weld surface at a radially inward extent and a rear first annular weld surface at a radially inward extent; providing a front inner axisymmetric workpiece, the front inner workpiece having a front second annular weld surface at a radially outward extent of the front inner workpiece; providing a rear inner axisymmetric workpiece, the rear inner workpiece having a rear second annular weld surface at a radially outward extent of the rear inner workpiece; and rotary welding the workpieces together.
    Type: Grant
    Filed: July 19, 2017
    Date of Patent: April 21, 2020
    Assignee: ROLLS-ROYCE PLC
    Inventors: Simon E. Bray, Andrew R. Walpole
  • Patent number: 10612402
    Abstract: One aspect of the present disclosure includes a turbine vane assembly comprising a vane made from ceramic matrix composite material having an outer wall extending between a leading edge and a trailing edge and between a first end and an opposing second end; an endwall made at least partially from a ceramic matrix composite material configured to engage the first end of the vane; and a retaining region including corresponding bi-cast grooves formed adjacent the first end of the vane and a receiving aperture formed in the endwall; wherein a bond is formed in the retaining region to join the vane and endwall together.
    Type: Grant
    Filed: September 21, 2017
    Date of Patent: April 7, 2020
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Ted J. Freeman, Robert F. Proctor, Sean E. Landwehr, Adam L. Chamberlain
  • Patent number: 10590949
    Abstract: The invention relates to a ventilator wheel which is produced in the form of a radial or a diagonal ventilator wheel, and comprises a bottom disc and a plurality of ventilator blades arranged, on said bottom disc, so as to be distributed about an axial rotational axis, said bottom disc comprising a circumferential radial outer edge section that, when viewed in cross-section, extends in a curved shape in at least some sections and thus forms an elliptical transition of said bottom disc from a radial extension into an axial extension.
    Type: Grant
    Filed: December 30, 2015
    Date of Patent: March 17, 2020
    Assignee: ebm-papst Mulfingen GmbH & Co. KG
    Inventors: Daniel Gebert, Jens Mueller, Alexander Konzal, Michael Strehle
  • Patent number: 10584603
    Abstract: A method of manufacturing a composite material vane with a covering element, the vane including a platform and a profile extending perpendicularly to the platform, comprises the following steps: providing a covering element and a preform of the vane, the preform comprising a platform portion and a profile portion extending substantially perpendicularly to the platform portion; positioning the covering element against the platform portion so as to obtain an assembly; placing said assembly in a mold; injecting a first resin into the mold so that said resin impregnates and covers the preform and covers at least a portion of the covering element; and carrying out a heat treatment so as to harden the first resin.
    Type: Grant
    Filed: August 17, 2016
    Date of Patent: March 10, 2020
    Assignee: Safran Aircraft Engines
    Inventors: Virginie Guilbert, Xavier Durand, Lise Lacroix
  • Patent number: 10549520
    Abstract: A structure includes a first body section that has a wall that spans in a vertical direction. The wall has a relatively thin thickness with respect to a length and a width of the wall. A second body section is arranged next to, but spaced apart from, the first body section. A gusset connects the first body section and the second body section. The gusset extends obliquely from the wall of the first body section with respect to the vertical direction such that the gusset is self-supporting. The first body section has a geometry that corresponds to an end-use component exclusive of the gusset.
    Type: Grant
    Filed: October 7, 2016
    Date of Patent: February 4, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Sergey Mironets, Lyutsia Dautova, Joseph Ott, Christopher F. O'Neill, Robert P. Delisle, Jesse R. Boyer, Agnes Klucha, Louis Porretti
  • Patent number: 10480333
    Abstract: A blade for a gas powered turbine includes a platform having a leading edge and a trailing edge. The leading edge is connected to the trailing edge by a suction side mateface and by a pressure side mateface. A blade extends outward from the platform. The blade has a foil shaped cross section and a suction side of the blade faces the suction side mateface and a pressure side of the blade faces the pressure side mateface. A radial height of the suction side mateface is different from a radial height of the pressure side mateface at a first axial position.
    Type: Grant
    Filed: May 30, 2017
    Date of Patent: November 19, 2019
    Assignee: United Technologies Corporation
    Inventors: Evan P. Molony, Carey Clum, Wolfgang Balzer
  • Patent number: 10458244
    Abstract: A rotor disk assembly may include a rotor disk and a retention ring coupled to the rotor disk. Generally, the retention ring is tuned to adjust a modal frequency response of the rotor disk/rotor disk assembly. In various embodiments, dimensions of the retention ring vary circumferentially. In various embodiments, the retention ring includes an axially extending flange and a radially extending flange. A radial thickness of the axially extending flange may vary circumferentially and/or an axial thickness of the radially extending flange may vary circumferentially.
    Type: Grant
    Filed: October 18, 2017
    Date of Patent: October 29, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Peter V. Tomeo, Carney R. Anderson
  • Patent number: 10436062
    Abstract: An article includes a ceramic wall that defines at least a side of a passage. The ceramic wall includes a flow turbulator that projects into the passage. The flow turbulator is formed of ceramic matrix composite. A gas turbine engine is also disclosed. The gas turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor. At least one of the turbine section or the compressor section including the article.
    Type: Grant
    Filed: November 17, 2016
    Date of Patent: October 8, 2019
    Assignee: United Technologies Corporation
    Inventor: Tracy A. Propheter-Hinckley
  • Patent number: 10415401
    Abstract: An airfoil retention assembly for a gas turbine engine includes, among other things, a disk, a coverplate, and a retaining ring. The disk defines a disk axis and an array of slots for receiving airfoil blades. The coverplate is dimensioned to radially overlap the array of slots relative to the disk axis. The retaining ring includes a ring body extending circumferentially about the disk axis between first and second ring ends to define a ring length. First and second retaining features continue along first and second circumferential faces of the ring body, respectively, to define first and second lengths, respectively. At least one of the first and second lengths is less than the ring length.
    Type: Grant
    Filed: September 8, 2016
    Date of Patent: September 17, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Noah Wadsworth, Elizabeth F. Vinson
  • Patent number: 10384302
    Abstract: A workpiece for use with a flash producing welding process comprises a revolute body, a plurality of first attachment portions, a plurality of second attachment portions. The revolute body has an axis of rotation. Each of the first attachment portions has a first radially outer weld joint surface, and each of the second attachment portions has a second radially outer weld joint surface. The revolute body comprises a plurality of first and second stub portions, with each of the first stub portions having a first radially inner weld joint surface, and each of the second stub portions having a second radially inner weld joint surface.
    Type: Grant
    Filed: February 23, 2018
    Date of Patent: August 20, 2019
    Assignee: ROLLS-ROYCE plc
    Inventor: Richard N. March
  • Patent number: 10352331
    Abstract: An airfoil of a turbine engine includes pressure and suction sides and extends in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a camber angle and span position that defines a curve with the camber angle having a positive slope from 0% span to 100% span.
    Type: Grant
    Filed: February 12, 2015
    Date of Patent: July 16, 2019
    Assignee: United Technologies Corporation
    Inventors: Edward J. Gallagher, Lisa I. Brilliant, Joseph C. Straccia, Stanley J. Balamucki, Mark A. Stephens, Kate Hudon
  • Patent number: 10352178
    Abstract: A locking element for a row of blades of a turbomachine includes a number of blades that are inserted by their roots in an anchoring groove on the rotor side and are thereby held in the radial direction in form-fitting manner in the anchoring groove. The locking element has a basic body that has a front bearing surface and a back bearing surface for form-fitting with opposite-lying groove surfaces, a front lock projection and a back lock projection for engaging in opposite-lying recesses of the anchoring groove, and a threaded region for interacting with a tightening element. Access to the threaded region for the tightening element is blocked on one side.
    Type: Grant
    Filed: February 15, 2016
    Date of Patent: July 16, 2019
    Assignee: MTU Aero Engines AG
    Inventors: Werner Humhauser, Hermann Klingels
  • Patent number: 10344603
    Abstract: A vane pack for a gas turbine engine includes an annular arrangement of vanes. A ring is secured around the vanes and extends proud of an axial end of the vanes.
    Type: Grant
    Filed: June 19, 2014
    Date of Patent: July 9, 2019
    Assignee: United Technologies Corporation
    Inventors: John T. Ols, Steven D. Porter
  • Patent number: 10301945
    Abstract: A turbine rotor blade that includes: an airfoil defined between a pressure face and a suction face; a tip shroud that includes a seal rail projecting from an outboard surface and, formed thereon, a cutter tooth; and a cooling configuration that includes a cooling channel for receiving and directing a coolant through an interior of the rotor blade. The cooling channel may include fluidly connected segments, in which: a supply segment extends radially through the airfoil; a cutter tooth segment is formed within the cutter tooth of the seal rail; and branching segments formed within at least one of the tip shroud and an outboard region of the airfoil. Each of the branching segments may extend between an upstream port, which connects to the cutter tooth segment, and an outlet port, which is formed on a target surface area, so that the branching segment bisects a target interior region.
    Type: Grant
    Filed: December 18, 2015
    Date of Patent: May 28, 2019
    Assignee: General Electric Company
    Inventors: Rohit Chouhan, Randall Richard Good, Hiteshkumar Rameshchandra Mistry, Shashwat Swami Jaiswal
  • Patent number: 10267166
    Abstract: A turbomachine assembly is shown, including a rotor and a ring of blades mounted on the rotor. Each blade includes an airfoil portion and a root portion inserted in a circumferential blade-retaining groove of the rotor. The blade-retaining groove includes an enlarged groove portion. The blades in the enlarged groove portion are rotatable around a respective, generally radial axis, to take a position of minimum tangential dimension. At least one removable insert is arranged along the enlarged groove portion, between the root portions of the blades located in the enlarged groove portion and a side wall of the blade-retaining groove, to force and lock the blades in a final assembled arrangement.
    Type: Grant
    Filed: May 19, 2014
    Date of Patent: April 23, 2019
    Assignee: NUOVO PIGNONE SRL
    Inventors: Lorenzo Cosi, Damaso Checcacci
  • Patent number: 10202859
    Abstract: A stator blades of an axial turbomachine intended to be fitted on a ferrule in an annular row of identical blades. Each blade includes a platform with opposed lateral edges and a screw to the ferrule. The contour of the platform has, at each of the lateral edges, an angular profile designed to mate with the contiguous edge of the platform of an adjacent blade. This feature enables the angular position or pitch of the blade to be set. In a blade row fixed on a stator, mechanical clearances J1, J2, J3 and the fixation screws cause an average angular orientation error. The blades are made with a compensatory angle to offset the angular orientation error.
    Type: Grant
    Filed: November 27, 2013
    Date of Patent: February 12, 2019
    Assignee: SAFRAN AERO BOOSTERS SA
    Inventor: Guy Biemar
  • Patent number: 10190497
    Abstract: A gas turbine engine comprises a compressor section, a combustor section downstream of the compressor section, and a turbine section downstream of the combustor section. A mid-turbine frame includes an outer case portion and is configured to support the turbine section. At least one shaft defines an axis of rotation, and the turbine section comprises an inner rotor directly driving the shaft. The inner rotor includes an inner set of blades. An outer rotor is positioned immediately adjacent to the outer case portion and has an outer set of blades interspersed with the inner set of blades. The outer rotor is configured to rotate in an opposite direction about the axis of rotation from the inner rotor. A gear system is positioned downstream of the combustor section, is mounted to the mid-turbine frame, and is coupled to the outer rotor to drive the at least one shaft.
    Type: Grant
    Filed: October 20, 2015
    Date of Patent: January 29, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Gabriel L. Suciu, Brian D. Merry
  • Patent number: 10132291
    Abstract: A wind turbine blade having a circular root portion and provided with root bushings for mounting the blade to a wind turbine hub, and the root bushings comprise an elongated cross-sectional profile with a first dimension oriented along a radius of the circular root portion being larger than a second dimension oriented along a circumferential direction of the circular root section.
    Type: Grant
    Filed: September 16, 2013
    Date of Patent: November 20, 2018
    Assignee: LM WP PATENT HOLDING A/S
    Inventor: Jesper Hasselbalch Garm
  • Patent number: 10072746
    Abstract: A stator of a hydrokinetic torque converter comprises a stator hub having an axis, a stator belt coaxial to the axis and a plurality of stator blades extending radially outwardly between the stator hub and the stator belt. Each of the stator blades has radially inner and outer mounting pins. The stator hub has hub slots, and the stator belt has belt slots. The radially inner mounting pin of one of the stator blades is disposed in one of the hub slots of the stator hub and the radially outer mounting pin of one of the stator blades is disposed in one of the belt slots of the stator belt.
    Type: Grant
    Filed: May 5, 2015
    Date of Patent: September 11, 2018
    Assignee: Valeo Embrayages
    Inventor: Alexandre Depraete
  • Patent number: 10054206
    Abstract: A torque converter having an input means and an output means, comprising a cover non-rotatably connected to the input means, an impeller having an impeller shell non-rotatably connected to the cover, the impeller also having at least one blade fixedly secured to the impeller shell, a stator having at least one blade fixedly secured thereto, and, a turbine having a turbine shell non-rotatably connected to the output means, the turbine shell comprising a first profile having at least one blade fixedly secured thereto, and a second profile arranged concentrically within the first profile, the second profile comprising at least one integrated stiffening element.
    Type: Grant
    Filed: March 12, 2015
    Date of Patent: August 21, 2018
    Assignee: SCHAEFFLER TECHNOLOGIES AG & CO. KG
    Inventor: Nigel Gurney
  • Patent number: 10047615
    Abstract: A method for mounting rotor blades on a rotor disk along a predetermined pitch circle diameter in such a way that adjacent rotor blades, when properly mounted on the rotor disk and in the cold state, are clamped against each other with a predetermined preload. A clamping device which performs such a method has a plurality of clamping elements which are arranged in a uniformly distributed manner around a central axis, the number of which corresponds to the number of rotor blades to be mounted on the rotor disk and which in each case are designed for the locating of a rotor blade, wherein the clamping elements are moveable radially, exerting a radially inwardly directed force.
    Type: Grant
    Filed: December 8, 2015
    Date of Patent: August 14, 2018
    Assignee: Siemens Aktiengesellschaft
    Inventor: Daniel Hofsommer
  • Patent number: 10041471
    Abstract: Provided are a wind turbine blade, with which effective reinforcement against possible flexural deformation in a longitudinal direction is realized, and a reinforcing method for the wind turbine blade. The wind turbine blade includes a hollow blade main body having a cylindrical blade root portion and extending from the blade root portion along a blade length direction, and a reinforcing plate provided in contact with an inside surface of the blade root portion and formed of an elongated member having a dimension along the blade length direction that is larger than a dimension along a circumferential direction of the blade root portion.
    Type: Grant
    Filed: September 7, 2017
    Date of Patent: August 7, 2018
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Yasutaka Kimura, Takao Kuroiwa, Kouji Esaki, Toshiyuki Hirano, Kentaro Shindo, Takeshi Fujita, Keisuke Ota
  • Patent number: 10018058
    Abstract: A propulsion unit having reduced noise employs a rotor having a plurality of variable pitch blades. A tensioning joint mechanism is carried within each blade and a tension element is engaged by the tension joint mechanism. The tension element is configured to maintain tension between the blades in the rotor and the tensioning joint mechanism adapted to allow variation of pitch of the blades without altering tension in the tension element.
    Type: Grant
    Filed: July 14, 2015
    Date of Patent: July 10, 2018
    Assignee: The Boeing Company
    Inventors: Sina Golshany, Todd W. Erickson
  • Patent number: 10006296
    Abstract: A method and a blade for a turbine or, more generally a turbomachine, are described with the blade having at a top end a shroud segment designed to engage with shroud segments of adjacent blades in an ring-shaped assembly at least partly by means of assembling the blades with the shroud segment having a central indentation along an engaging face.
    Type: Grant
    Filed: May 23, 2013
    Date of Patent: June 26, 2018
    Assignee: GENERAL ELECTRIC TECHNOLOGY GMBH
    Inventors: Dilli Prasad Ramannagari, Pierre-Alain Masserey, Ross Brian Fleming, Christina Calcagni
  • Patent number: 9958046
    Abstract: A torque converter turbine core ring is provided. The turbine core ring includes a plurality of arc sections having an inner circumference and an outer circumference and a plurality of weakened sections connecting the arc sections to each other. The weakened sections each having a lesser strength than each of the arc sections. A torque converter turbine, a torque converter and a method of forming a torque converter turbine are also provided.
    Type: Grant
    Filed: February 11, 2015
    Date of Patent: May 1, 2018
    Assignee: Schaeffler Technologies AG & Co. KG
    Inventor: Scott Schrader
  • Patent number: 9932833
    Abstract: A method for building centrifugal radial stages of turbines, in which the first and the second end of each blade (4) are connected to respective two support rings (2, 3) joining, by means of laser welding, at least a first semi-portion (10) belonging to the respective end of the blade (4) to a respective second semi-portion (10) belonging to the respective support ring (2, 3) so as to form a resilient yielding connecting portion (10, 15) along a radial direction, and providing at least a stop portion (11) belonging to the end of the blade (4) facing, along the radial direction, at least a stop element (14) of the respective support ring (2, 3). The resilient yielding connecting portion (10, 15) enables the stop portion (11) to enter into contact with the stop element (14) when the stage (1) is subjected to the functioning loads of the turbine.
    Type: Grant
    Filed: October 10, 2013
    Date of Patent: April 3, 2018
    Assignee: EXERGY S.P.A.
    Inventors: Claudio Spadacini, Marco Rizzi
  • Patent number: 9919392
    Abstract: A method for manufacturing a turbine rotor blade wherein warping, bending and twisting of the entire rotor blade, which is provided with an excess thickness portion after a forging step, can be suppressed. In the forging step in a process for manufacturing a rotor blade (23), the forging is hot-forged such that the distance (the excess thickness amount) from the blade surface of the blade section (23) to the surface of the excess thickness section is substantially uniform along the entire periphery of a cross section of the blade section (23) and the excess thickness section (31) perpendicular to the blade length direction, and such that the amount of the excess thickness in the blade length direction, which is the thickness of the excess thickness section (31), gradually increases toward the blade tip from a prescribed position.
    Type: Grant
    Filed: December 18, 2013
    Date of Patent: March 20, 2018
    Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.
    Inventors: Kohei Hatano, Hiroharu Oyama, Motonari Machida, Hidetaka Haraguchi, Ken Ishii, Keisuke Kamitani, Takumi Matsumura, Takahiro Ota