Individually Pivoted Vanes Patents (Class 415/160)
  • Patent number: 11448086
    Abstract: The present disclosure relates to a variable stator vane and a method of fabricating the variable stator vane of a gas turbine engine. The method includes providing at least one fibre sheet. The method further includes rolling the at least one fibre sheet around a mandrel to form a spindle section of the variable stator vane. An excess of material of the at least one fibre sheet remains after forming the spindle section. The method further includes using the excess of material of the at least one fibre sheet to form the at least one aerofoil section of the variable stator vane.
    Type: Grant
    Filed: February 8, 2021
    Date of Patent: September 20, 2022
    Assignee: Rolls-Royce PLC
    Inventors: Christopher D. Jones, Robert C. Backhouse, Adam J. Bishop
  • Patent number: 11428243
    Abstract: An assembly is provided for a variable vane arrangement of a turbine engine. A platform extends circumferentially about a centerline and radially relative to the centerline between a first platform side and a second platform side. The platform includes a plurality of variable vane receptacles arranged in an annular array about the axial centerline, which variable vane receptacles include a first variable vane receptacle. The first variable vane receptacle is configured with a recess, a bore and a shelf. The recess extends longitudinally along a variable vane pivot axis into the platform from the first platform side to the shelf. The bore extends longitudinally along the variable vane pivot axis into the platform from the shelf. An insert includes a sleeve and a plate. The sleeve lines at least a portion of the bore. The plate is located within the recess adjacent the shelf.
    Type: Grant
    Filed: September 9, 2019
    Date of Patent: August 30, 2022
    Assignee: Raytheon Technologies Corporation
    Inventors: Robert R. Mayer, Peter F. Gero, Tracy A. Propheter-Hinckley
  • Patent number: 11371380
    Abstract: A variable guide vane (VGV) assembly for a gas turbine engine has: vanes distributed about a central axis and having airfoils between stems at respective ends of the airfoils; a unison ring; sliders protruding from the unison ring; and vane arms engaged to first stems and defining respective slots, each of the slots extending in a direction having a radial component relative to a respective one of the spanwise axes, the sliders received within respective ones of the slots, a slot extending from a proximal end to a distal end along a slot axis, the vane arm defining the slot having an end wall at the distal end, the end wall extending in a direction having a component transverse to the slot axis such that a slider abuts against the end wall when the slider is at the distal end to prevent the sliders from moving out of the slots.
    Type: Grant
    Filed: December 1, 2020
    Date of Patent: June 28, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Daniel Poick
  • Patent number: 11359509
    Abstract: A gas turbine engine has: a first component and a second component defining a respective first gaspath surface and a second gaspath surface of an annular gaspath, the first and second gaspath surfaces axially spaced apart from one another by an annular recess in the first component; a bushing ring disposed within the annular recess and defining stem pockets therein; variable guide vanes pivotable about respective vane axes extending between first and second stems; and a biasing member received within the annular recess and disposed axially between the bushing ring and one of the first component and the second component, the biasing member exerting a force against the bushing ring in an axial direction relative to the central axis and towards the other of the first component and the second component.
    Type: Grant
    Filed: November 23, 2020
    Date of Patent: June 14, 2022
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: James O'Brien
  • Patent number: 11339670
    Abstract: A blade airfoil including a platform, concave pressure sidewall and convex suction sidewall extending axially between corresponding leading and trailing edges and radially between a root and outboard tip. The blade further includes at least one part-span shroud positioned on the airfoil defined by a nominal profile in accordance with at least a portion of Cartesian coordinate values of X, Y and Z set forth in at least one of TABLE I and TABLE II. The Cartesian coordinate values are non-dimensional values of from 0% to 100% convertible to distances by multiplying values by a length of the at least one part-span shroud. X and Y values are connected by continuing arcs to define part-span shroud profile sections at each distance Z along at least a portion of the at least one part-span shroud, profile sections at Z distances being joined with one another to form the nominal profile.
    Type: Grant
    Filed: October 13, 2020
    Date of Patent: May 24, 2022
    Assignee: General Electric Company
    Inventors: Neil Devin Ristau, Michael Anthony Wondrasek
  • Patent number: 11333167
    Abstract: To provide a method of designing a blade of an axial flow fluid machine that has a blade surface whose radius of curvature is continuous at a leading edge thereof and has a high aerodynamic performance. The method includes a step of determining a pressure surface curve and a suction surface curve as curves capable of first to third order differentiations at respective connection points to a leading edge curve, that is, a pressure surface connection point and a suction surface connection point, and a step of forming the leading edge curve as a fifth order Bezier curve that is defined by a first control point, a second control point, a third control point, a fourth control point, a fifth control point and a sixth control point. The first control point is the suction surface connection point. The sixth control point is the pressure surface connection point.
    Type: Grant
    Filed: September 30, 2019
    Date of Patent: May 17, 2022
    Assignee: IHI CORPORATION
    Inventors: Ryuichi Okada, Tomonori Enoki, Takeshi Murooka, Dai Kato
  • Patent number: 11326514
    Abstract: A turbocharger includes a turbine, a bearing housing, and a variable capacity mechanism. The variable capacity mechanism includes first and second plates and a connecting pin connecting the first and second plates to each other. The connecting pin includes a main body portion disposed between the first plate and the second plate, a first shaft portion disposed in a first through-hole of the first plate, and a second shaft portion disposed in a second through-hole of the second plate. The first plate is disposed on the side opposite to the bearing housing with respect to the second plate. The thickness of the first plate is larger than the thickness of the second plate and the length of the first shaft portion is equal to the length of the second shaft portion.
    Type: Grant
    Filed: December 24, 2020
    Date of Patent: May 10, 2022
    Inventor: Takao Asakawa
  • Patent number: 11236634
    Abstract: The invention relates to a turbine engine (2) compressor shroud, comprising: first and second sections (130, 230) and respective flanges (131, 231), the flanges (131, 231) making it possible to hold the two sections (130, 230) together, the first section (130) comprising a cylindrical surface (137) forming a seat for an actuating device (136, 140, 166, 168, 170) for orienting stator blades (126), characterised in that the first shroud (130) comprises a tubular wall (132) axially overlapping both flanges (131, 231) and said cylindrical surface (137) is an outer surface of the tubular wall (132). The invention also relates to an assembly with the shroud (130, 230), the blade (126) and means (140) for actuating the orientation of the blade (126), the shroud being produced using the kit described above. The invention finally relates to a method for assembling a compressor with such an assembly.
    Type: Grant
    Filed: June 20, 2019
    Date of Patent: February 1, 2022
    Assignee: SAFRAN AERO BOOSTERS SA
    Inventor: Morgan Vyvey
  • Patent number: 11187101
    Abstract: A variable geometry turbocharger (VGT) is provided. The VGT includes a unison ring that rotates a plurality of vanes disposed in a nozzle ring and a sagging prevention mechanism. The sagging prevention mechanism is installed to support the unison ring in a direction opposite to a direction in which a self-weight of the unison ring acts. In particular, the sagging prevention mechanism includes a support pulley that is installed to provide an elastic pressure on an outer circumferential surface of the unison ring in rolling contact therewith.
    Type: Grant
    Filed: November 18, 2019
    Date of Patent: November 30, 2021
    Assignees: Hyundai Motor Company, Kia Motors Corporation
    Inventors: Jang Sin Lee, Jun Hee Lee
  • Patent number: 11168579
    Abstract: A turbocharger device includes an annular spring element for axially clamping a guide device of a variable turbine geometry against a turbine housing. The annular spring element rests radially outwardly on the bearing housing and radially inwardly on a component of the guide device. The spring element has an annular radial outer flange in contact with the bearing housing, and a plurality of tabs which extend from the outer flange radially inwardly in the direction of the guide device and come into contact with a component thereof. An annular spring element for such a turbocharger is also provided.
    Type: Grant
    Filed: September 10, 2018
    Date of Patent: November 9, 2021
    Assignee: Vitesco Technologies GmbH
    Inventors: Jan Ehrhard, Holger Faeth, Daniel Kraus, Lukasz Przada, Benjamin Adler, Hildegard Lang, Simon Pflaum
  • Patent number: 11162376
    Abstract: A guide vane according to the invention for a guide vane ring of a turbomachine has a vane element as well as a guide vane plate for its support on an inner ring. The guide vane plate has a cover surface facing the vane element, a base surface lying opposite to the cover surface, and an edge surface joining the cover and base surfaces. In a first region, the edge surface forms a chamfer of the vane plate, and in a second region, which forms the edge of a sector of the guide vane plate that is different from that of the first region, the edge surface runs along a cylindrical surface. A method comprises inserting a plurality of guide vanes according to the invention into respective uptakes in an inner ring.
    Type: Grant
    Filed: March 7, 2017
    Date of Patent: November 2, 2021
    Assignee: MTU Aero Engines AG
    Inventor: Frank Stiehler
  • Patent number: 11125115
    Abstract: Described is a connecting device (50) for a variable vane (51) of a gas turbine (10), in particular of an aircraft gas turbine, the connecting device including a trunnion element (52) connected to a respective vane (51); a lever element (54) connected to the trunnion element (52), the lever element (54) and the trunnion element (52) being movable together about a trunnion axis of rotation (ZD). It is provided that the lever element (54) and the trunnion element (52) be aligned with each other by a positioning element (68), the positioning element (68) being received in a trunnion receptacle (60) and a lever receptacle (66, 66a, 66b).
    Type: Grant
    Filed: February 4, 2019
    Date of Patent: September 21, 2021
    Assignee: MTU Aero Engines AG
    Inventor: Werner Humhauser
  • Patent number: 11118468
    Abstract: One exemplary embodiment of this disclosure relates to a system having a static segment with a circumferentially extending slot. The system further includes a retention clip partially received in the slot, and partially contacting a circumferential end of the static segment.
    Type: Grant
    Filed: January 20, 2020
    Date of Patent: September 14, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Michael G. McCaffrey
  • Patent number: 11105207
    Abstract: A blade wheel of a turbomachine, which blade wheel has a multiplicity of blades which are suitable and provided for extending radially in a flow path of the turbomachine, wherein the blades form a blade entry angle and a blade exit angle. Provision is made whereby the blade wheel forms N blocks of blades, where N?2, wherein the blades of a block have in each case the same blade entry angle and the same blade exit angle, and the blades of at least two mutually adjacent blocks have a different blade entry angle and/or a different blade exit angle. According to a further aspect of the invention, partial gaps that the blades form in relation to an adjacent flow path boundary are varied in mutually adjacent blocks.
    Type: Grant
    Filed: August 13, 2019
    Date of Patent: August 31, 2021
    Assignees: Rolls-Royce Deutschland Ltd & Co KG, Rolls-Royce
    Inventors: Sven Schrape, Bernhard Mück, Jens Nipkau, Thomas Giersch, Frank Heinichen, John Dodds
  • Patent number: 11092032
    Abstract: A variable guide vane (VGV) apparatus has a variable guide vane (VGV) rotatable about a vane rotation axis. An actuating arm is mounted to the VGV. The actuating arm has a fork defining a slot for receiving a drive pin. The slot is profiled to accommodate angular misalignment between the pin and the fork throughout a range of motion of the associated pin along the slot.
    Type: Grant
    Filed: August 19, 2019
    Date of Patent: August 17, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Tibor Urac, Esther Leung
  • Patent number: 11092167
    Abstract: A variable guide vane (VGV) apparatus has a variable guide vane (VGV) rotatable about a vane rotation axis. An actuating arm is mounted to the VGV. The actuating arm has a fork defining a slot for receiving a drive pin. The slot has a curved contour configured to act as a vane angle schedule adjustment.
    Type: Grant
    Filed: August 19, 2019
    Date of Patent: August 17, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Tibor Urac, Esther Leung
  • Patent number: 11022145
    Abstract: A variable area vane arrangement includes a stator vane, a bushing and a vane platform with an aperture. The stator vane rotates about an axis, and includes a shaft that extends along the axis into the aperture. The bushing is connected to the shaft, and is arranged within the aperture between the vane platform and the shaft.
    Type: Grant
    Filed: August 20, 2018
    Date of Patent: June 1, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: David Maliniak, Nathan F. Champion, Kenneth A. Frisk
  • Patent number: 11002142
    Abstract: A variable vane assembly including a variable stator vane disposed in a main flow gaspath, the variable stator vane having a vane stem. The assembly also includes a case located at a radially outward location of the variable stator vane, the vane stem extending through a port of the case, the port defined by a port wall, a clearance defined by the vane stem and a port wall to allow gas from the main flow gaspath to pass therethrough. The assembly further includes a synchronization ring spaced from the case to define a gap. The assembly yet further includes a vane arm operatively coupled to a synchronization ring and to the vane stem, the vane arm redirecting gas from the main flow gaspath to the synchronization ring.
    Type: Grant
    Filed: January 21, 2019
    Date of Patent: May 11, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Tristan Thomas Peirce
  • Patent number: 10968748
    Abstract: A turbine section includes a pair of adjacent turbine airfoils and an endwall extending between the airfoils. The endwall includes a first feature spanning approximately thirty percent pitch and having a first depression with a maximum depression located between twenty percent and eighty percent of the axial chord length of the first airfoil, a second feature spanning approximately thirty percent pitch and having a first peak with a maximum height located between sixty percent and ninety percent of the axial chord length of the first airfoil, and a third feature spanning approximately thirty percent pitch and having a second depression with a maximum depression located between twenty percent and fifty percent of the axial chord length of the second airfoil.
    Type: Grant
    Filed: April 8, 2019
    Date of Patent: April 6, 2021
    Assignee: United Technologies Corporation
    Inventor: Loubriel Ramirez
  • Patent number: 10961865
    Abstract: A casing assembly for a gas turbine engine includes a case having an outer case wall extending around a central axis, an inner case wall radially offset from the outer case wall, and one or more hydraulic fluid passages embedded in the case between the outer case wall and the inner case wall. A variable pitch stator vane system includes a plurality of stator vanes are located radially inboard of the inner case wall. Each stator vane is rotatable about a central vane axis. An actuation unit is operably connected to the plurality of stator vanes and driven by hydraulic fluid through the one or more hydraulic fluid passages to urge rotation of the plurality of stator vanes about their respective central vane axes.
    Type: Grant
    Filed: November 6, 2018
    Date of Patent: March 30, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Gary D. Roberge
  • Patent number: 10934869
    Abstract: In a variable stator vane structure of an axial compressor, each stator vane (70) is provided with a shaft (72) rotatably supported by the cylindrical outer peripheral portion (14B) around an axial center line (T) of the shaft, and a vane member (74) supported by the shaft, and the axial center line of the shaft is tilted with respect to a radial line (R) extending radially from a center of the annular fluid passage (34) in a circumferential direction and/or in an axial direction of the annular fluid passage.
    Type: Grant
    Filed: March 18, 2019
    Date of Patent: March 2, 2021
    Assignee: HONDA MOTOR CO., LTD.
    Inventor: Yuuri Tsukioka
  • Patent number: 10934884
    Abstract: An assembly (50) for a turbine engine includes an annular row of stator blades with a longitudinal axis (B) having variable pitch blades each comprising a radial vane (6), at least one of its ends of which is connected to a radially extending pivot (14) and being engaged in rotation around its axis (A) in a ring (16), characterised in that a tubular component (26) is mounted coaxially around the pivot (14), wherein said tubular component (26) comprises a first annular zone (26a) mounted tightly on the pivot (14) and a second annular zone (26b) comprising an annular bulge (28) extending substantially radially outwards in relation to the axis (A) of the pivot (14), wherein the annular bulge (28) and the pivot (14) define an annular space (30).
    Type: Grant
    Filed: March 29, 2019
    Date of Patent: March 2, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Rémi Philippe Guy Onfray, Benoit André Pierre Frossard, Clément Miraton
  • Patent number: 10927699
    Abstract: Variable-pitch blade control ring (44) for a turbine engine, including an annular body (42) configured to be mounted so as to be rotatable about an annular casing (16) of the turbine engine. The body links to levers (34) for connecting to the vanes. The ring has a mechanism for guiding in an axial and/or helical direction, supported by the body. The mechanism includes at least one substantially radial finger (60, 62) for axial abutment on at least one first surface (72, 74) of the casing and for sliding on the surface.
    Type: Grant
    Filed: June 27, 2016
    Date of Patent: February 23, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Alain Marc Lucien Bromann, Kamel Benderradji, Lilian Yann Dumas, Blaise Bergon, Suzanne Madeleine Coustillas
  • Patent number: 10914190
    Abstract: A variable nozzle unit includes a variable nozzle vane which is disposed between a hub wall surface and a shroud wall surface and is rotatable around a rotation axis parallel to a rotation axis of a turbine impeller inside a gas flow passage. The variable nozzle vane includes a leading edge, a trailing edge, a hub end surface facing a hub wall surface, and a shroud end surface facing a shroud wall surface. The variable nozzle vane is twisted around a twist center located between the trailing edge and the rotation axis so that the hub end surface protrudes to a radial outside of a rotation axis in relation to the shroud end surface at the leading edge side and the hub end surface protrudes to a radial inside of the rotation axis in relation to the shroud end surface at the trailing edge side.
    Type: Grant
    Filed: October 31, 2017
    Date of Patent: February 9, 2021
    Assignee: IHI Corporation
    Inventor: Natsuko Motoda
  • Patent number: 10876411
    Abstract: A turbine section includes a pair of adjacent turbine airfoils and an endwall extending between the airfoils. The endwall includes a first feature spanning approximately twenty percent pitch and having a first depression with a first maximum depression located between twenty percent and sixty percent of an axial chord length of the first airfoil, a second feature adjacent the first feature with the second feature spanning approximately forty percent pitch and having a first peak with a maximum height located between twenty percent and sixty percent of the axial chord length of the first airfoil, and a third feature adjacent the second feature and first side of the second airfoil with the third feature spanning approximately forty percent pitch and having a second depression with a second maximum depression located between thirty percent and sixty percent of an axial chord length of the second airfoil.
    Type: Grant
    Filed: April 8, 2019
    Date of Patent: December 29, 2020
    Assignee: United Technologies Corporation
    Inventor: Loubriel Ramirez
  • Patent number: 10876425
    Abstract: Disclosed is a lever connection for a guide vane adjustment for connecting a guide vane of a turbomachine to an adjusting ring of an actuator, which is arranged in such a way that an adjusting lever of the lever connection is pushed radially from a first mounting direction, in relation to a machine longitudinal axis of the turbomachine, onto a vane shaft of the guide vane, and is locked with the vane shaft in a form-fitting and, in particular, rotationally rigid manner by a movement in a second mounting direction; a mounting method; and a turbomachine.
    Type: Grant
    Filed: February 10, 2019
    Date of Patent: December 29, 2020
    Assignee: MTU Aero Engines AG
    Inventor: Werner Humhauser
  • Patent number: 10858959
    Abstract: An axially divided inner ring is provided for fastening to, in particular adjustable, guide vanes (50) of a turbomachine, in particular a compressor or turbine stage of a gas turbine, which includes a first partial ring (10) and a second partial ring (20), which is supported in the axial direction directly or indirectly on two axially facing support surfaces (11, 12) of the first partial ring (10) and is fixed on the first partial ring (10) in the radial direction with the aid of multiple alignment pins (40) distributed in the circumferential direction.
    Type: Grant
    Filed: May 30, 2018
    Date of Patent: December 8, 2020
    Assignee: MTU Aero Engines AG
    Inventor: Karl Maar
  • Patent number: 10851706
    Abstract: A variable nozzle mechanism includes: a nozzle mount having an annular shape; a plurality of nozzle vanes supported rotatably at a plurality of respective locations along a circumferential direction of the nozzle mount; and a drive ring disposed rotatably with respect to the nozzle mount, the drive ring being configured to transmit a driving force to the nozzle vanes so that a vane angle of the nozzle vanes is variable and to rotate the nozzle vanes. The drive ring includes: a low-rigidity region; and a high-rigidity region including an uneven portion in a thickness direction of the drive ring, and having a greater cross-sectional secondary moment than the low-rigidity region in a cross section along a radial direction of the drive ring. The low-rigidity region and the high-rigidity region are disposed alternately in the circumferential direction.
    Type: Grant
    Filed: February 24, 2015
    Date of Patent: December 1, 2020
    Assignee: MITSUBISHI HEAVY INDUSTRIES ENGINE & TURBOCHARGER, LTD.
    Inventors: Yukihide Nagayo, Yuki Ishii, Takaki Sato, Yosuke Dammoto, Youji Akiyama
  • Patent number: 10837308
    Abstract: A device for controlling variable-pitch turbomachine members such as stator vanes, wherein the movement of a control mechanism is imparted to a ring that rotates the levers for pivoting the vanes about a stator, and takes place with a possible change in the length of the bottle screw connecting the ring to the control mechanism, thereby allowing the blade pitch angle law to be changed according to the extension of the control device. A greater freedom of adjustment is thus obtained. The device can be useful when a single control mechanism is used for multiple rings arranged side by side, making it possible to have different control laws for the rings.
    Type: Grant
    Filed: May 23, 2017
    Date of Patent: November 17, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Olivier Bazot, Jeremy Philippe Pierre Edynak
  • Patent number: 10830090
    Abstract: A lever assembly forming part of a vane actuating mechanism and serving to connect a stator vane of a turbomachine to an actuating ring of an actuator is provided. The lever assembly is adapted such that an actuating lever of the lever assembly is moved in a first mounting direction transversely to a vane stem of the stator vane extending radially relative to a longitudinal machine axis of the turbomachine and is thereby positioned laterally against the vane stem, and that the actuating lever is radially form-fittingly locked to the vane stem by a locking piece in a second mounting direction. An assembly method and a turbomachine is also provided.
    Type: Grant
    Filed: November 29, 2017
    Date of Patent: November 10, 2020
    Assignee: MTU Aero Engines AG
    Inventor: Vitalis Mairhanser
  • Patent number: 10815813
    Abstract: An active clearance control system for a gas turbine engine includes an annular piston with a multiple of piston lift lugs. A method of active blade tip clearance control for a gas turbine engine includes translating axial movement of an annular piston to radial movement of a multiple of blade outer air seal segments.
    Type: Grant
    Filed: May 9, 2014
    Date of Patent: October 27, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Ken F. Blaney, Christopher M. Jarochym
  • Patent number: 10815876
    Abstract: A method for operating an internal combustion engine is provided, wherein the internal combustion engine has at least one combustion engine and a fresh gas line and wherein a compressor, to which a trim adjuster is assigned, is integrated into the fresh gas line, said trim adjuster by which an edge section of the inlet cross section of a compressor wheel can be covered to a variable extent. In this case, the edge section of the inlet cross section is covered relatively little in a release position of the trim adjuster and covered relatively greatly in a covering position of the trim adjuster. It is provided that the trim adjuster is adjusted between the release position and the covering position, when substantially the same compressor pressure ratio and substantially the same fresh gas mass flow and substantially the same compressor efficiency are achieved in both operating positions.
    Type: Grant
    Filed: July 5, 2019
    Date of Patent: October 27, 2020
    Assignee: Volkswagen Aktiengesellschaft
    Inventors: Sebastian Heinken, Javier Bartolome, Manuel Vahldiek, Dirk Hagelstein, Arne Staats
  • Patent number: 10794219
    Abstract: The bearing surface between a thrust bushing and a boss/or face is increased with the addition of a ring or tab that extends radially into a casing bore configured to receive a bushing and cooperating spindle of a variable stator/guide vane. The addition of the ring adds additional bearing surface area without increasing the size of the vane penny, reducing spindle diameter or reducing the bushing bore diameter.
    Type: Grant
    Filed: September 14, 2017
    Date of Patent: October 6, 2020
    Assignee: Rolls-Royce Corporation
    Inventors: Grace Aker, Alex Ertman, Jonathan Acker
  • Patent number: 10794392
    Abstract: A hub for a propeller having variable-pitch blades for a turbomachine with longitudinal rotation axis, including a plurality of blade platforms, each one being designed to receive a blade root, the platforms being distributed around the annular outer periphery of the hub concentrically with the longitudinal rotation axis, wherein each blade platform has the general geometric shape of a spherical cap, and wherein, between two adjacent blade platforms around the longitudinal rotation axis, the transverse dimension, in particular the diameter, of the hub can vary axially and radially.
    Type: Grant
    Filed: February 20, 2017
    Date of Patent: October 6, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Paul Antoine Foresto, Vivien Mickaël Courtier, Christophe Paul Jacquemard
  • Patent number: 10774674
    Abstract: A variable vane adjustment system for a gas turbine engine including: a vane platform having a recess, a vane opening within the recess, and a set screw opening originating at a first wall of the recess and extending into the vane platform; a trunnion carrier having a base portion located at least partially within the recess, a bushing attached to the base portion, and an orifice that extends through the base portion and bushing, wherein the orifice is aligned with the vane opening; a variable vane having a vane stem, the vane stem extending through the vane opening and the orifice; and a set screw located at least partially within the set screw opening, the set screw being configured to longitudinally traverse the set screw opening as the set screw is rotated, wherein the set screw is configured to move the trunnion carrier and variable vane.
    Type: Grant
    Filed: September 13, 2018
    Date of Patent: September 15, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: David M. Dyer
  • Patent number: 10746057
    Abstract: A method for constructing a variable nozzle assembly within a turbine engine that includes: constructing a variable nozzle sub-assembly; attaching the variable nozzle sub-assembly to a casing; and linking segments of a segmented shaft via an opening. Constructing the variable nozzle sub-assembly may include: attaching a downstream inner platform to a upstream inner platform; inserting an outer stem of a first segment through an outer stem opening formed through the downstream outer platform; connecting the first segment to the downstream outer platform by loading a first bearing about a protruding spherical shaped section of the outer stem; inserting the inner stem through an opening formed through the downstream inner platform while aligning sidewalls of the downstream and upstream outer platforms; mechanically securing the aligned sidewalls; and connecting the first segment to the downstream inner platform by loading a second bearing about a protruding spherical shaped section of the inner stem.
    Type: Grant
    Filed: August 29, 2018
    Date of Patent: August 18, 2020
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Zachary John Snider, Gary Charles Liotta
  • Patent number: 10746034
    Abstract: An airfoil assembly for a turbo machine, the airfoil assembly including an airfoil defining a leading edge and a trailing edge, and further defining ends separated along a span of the airfoil; a shaft extended from the end of the airfoil; and a button surrounding at least a portion of the end of the airfoil, the button comprising a composite material.
    Type: Grant
    Filed: June 13, 2018
    Date of Patent: August 18, 2020
    Assignee: General Electric Company
    Inventors: Mark Joseph Mielke, Heidi Stegemiller
  • Patent number: 10731488
    Abstract: A turbine housing of a turbocharge can include a surface that defines a portion of a volute, an annular surface that extends radially inwardly to define a portion of a pressure chamber that is in fluid communication with the volute, a substantially annular plate that defines a portion of the pressure chamber, an annular component, at least one spacer that defines a minimum axial distance between the substantially annular plate and the annular component to define a nozzle that is in fluid communication with the volute and in fluid communication with a turbine wheel space where, responsive to fluid flow in the volute and through the nozzle to the turbine wheel space, the pressure chamber has a fluid pressure that exceeds a fluid pressure of the nozzle to apply a biasing force to the substantially annular plate in an axial direction toward a center housing.
    Type: Grant
    Filed: February 4, 2018
    Date of Patent: August 4, 2020
    Assignee: Garrett Transportation I Inc.
    Inventors: Emeric Genin, Giorgio Figura, Daniel Frank
  • Patent number: 10718230
    Abstract: A unison ring assembly for a gas turbine engine has a unison ring and a plurality of levers extending from the unison ring. Each lever has a pin at one end that inserts through a bore of a respective bush mounted in the unison ring. Each bush is formed as separate first and second parts which are mounted to their through-hole by inserting the first part into the through-hole from one side of the unison ring and the second part into the through-hole from the opposing side of the unison ring. Each part has a respective stop which prevents that part from inserting into the through-hole by more than a predetermined amount. When both parts are inserted by their predetermined amounts, their ends join together to form the bush and prevent the parts being retracted from the through-hole.
    Type: Grant
    Filed: July 16, 2018
    Date of Patent: July 21, 2020
    Assignee: ROLLS-ROYCE PLC
    Inventor: Graham Littler
  • Patent number: 10711630
    Abstract: A retention and control system includes a rotor configured to rotate about an axis. A shroud ring has a peripheral groove and surrounds the rotor with a clearance defined between the rotor and the ring. A support ring engages the shroud ring in the peripheral groove and axially locates the shroud ring. The support ring includes a series of tabs, each with an aperture, projecting radially outward from the support ring. A retention spring engages the support ring radially outward from the shroud ring and includes a series of openings, one of which registers with each of the apertures. An alignment pin extends through each of the registered openings and apertures to locate the support ring and the engaged shroud ring concentrically with the turbine about the axis.
    Type: Grant
    Filed: March 20, 2018
    Date of Patent: July 14, 2020
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: David R. Waldman, Donald W. Tillman, Ryon James Stanley, Edwin Martinez
  • Patent number: 10704563
    Abstract: A compressor apparatus includes: an upstream portion comprising an axial-flow compressor; a downstream portion comprising a centrifugal-flow compressor; and a row of variable-stagger-angle outlet guide vanes disposed between the upstream and downstream portions.
    Type: Grant
    Filed: August 11, 2015
    Date of Patent: July 7, 2020
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: David Vickery Parker, Wilhelm Ramon Hernandez, Basuki Srivastava, Paul Trimby
  • Patent number: 10677148
    Abstract: A variable displacement exhaust turbocharger is provided with a plurality of nozzle vanes that are rotatably supported by a nozzle mount, a drive ring that is interlocked with an actuator and fits to a guide part of the nozzle mount, a lever plate having one end coupled to the drive ring and the other end coupled to the nozzle vane, and a variable nozzle mechanism that varies the vane angle of the nozzle vane by rotating the drive ring. A bulge suppressing portion is provided for absorbing bulging occurring on an outer peripheral surface of the guide part, the bulging being caused by the press-fitting of a nail pin into a press-fitting hole in a direction slightly toward the rotational axis with respect to the guide section and following the axial direction of the nozzle mount.
    Type: Grant
    Filed: September 1, 2017
    Date of Patent: June 9, 2020
    Assignee: MITSUBISHI HEAVY INDUSTRIES ENGINE & TURBOCHARGER, LTD.
    Inventors: Naoto Tashiro, Yasuaki Jinnai, Hiroyuki Arimizu
  • Patent number: 10605254
    Abstract: A bearing element for at least one adjustable guide vane of a turbomachine, in particular an aircraft engine, is provided. The bearing element comprising a porous matrix made of carbon and/or graphite and at least one metallic phase or a metal salt that is at least partially arranged inside the pores of the matrix, so that what results is a metal-infiltrated or a metal-salt-infiltrated material.
    Type: Grant
    Filed: June 16, 2017
    Date of Patent: March 31, 2020
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Bjorn Ulrichsohn, Susanne Schruefer, Karl Schreiber
  • Patent number: 10590904
    Abstract: A vane body of a guide vane includes a leading edge, and a trailing edge which is located closer to a runner than the leading edge, when located radially outside the runner. A projection extending in a direction from the trailing edge toward the leading edge is provided on an internal-diameter side blade face of the vane body, at least in any one of one side area of the internal-diameter side blade face and the other side area thereof in an axial direction of a guide vane rotation shaft, the internal-diameter side blade face being disposed on a side of the runner. The projection has a projection rear end of an arcuate shape, which projection rear end is formed to extend along a rotation trajectory which is drawn by the trailing edge when the vane body is rotated about the guide vane rotation shaft.
    Type: Grant
    Filed: October 11, 2016
    Date of Patent: March 17, 2020
    Assignee: KABUSHIKI KAISHA TOSHIBA
    Inventors: Madoka Narikawa, Hideyuki Kawajiri, Norio Ohtake, Koichi Kubo, Toshifumi Kurokawa, Nobuaki Noda
  • Patent number: 10563513
    Abstract: An inlet guide vane is disclosed. The inlet guide vane includes a strut and a flap having a radial length in a radial direction. The flap includes a radially inner portion having a first angular orientation with respect to the strut, a radially outer portion having a second angular orientation with respect to the strut, and a transition portion intermediate the radially inner portion and the radially outer portion, wherein the first angular orientation transitions to the second angular orientation along a portion of the radial length.
    Type: Grant
    Filed: December 19, 2017
    Date of Patent: February 18, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Georgi Kalitzin, Gorazd Medic
  • Patent number: 10557371
    Abstract: A variable vane assembly for a gas turbine engine includes a case having a bore and a recess. The case provides a first portion of a flow path surface. A vane includes a journal that extends along an axis from a vane end and received in the bore. An insert is arranged in the recess and provides a second portion of the flow path surface adjacent to the first flow path surface. The insert includes a pocket that slidably receives the vane end. The vane end is configured to move axially relative to the insert.
    Type: Grant
    Filed: July 14, 2017
    Date of Patent: February 11, 2020
    Assignee: United Technologies Corporation
    Inventor: Jose E. Ruberte Sanchez
  • Patent number: 10539024
    Abstract: A gas turbine engine airflow member is disclosed having spherical interface shapes at a tip end and a hub end. In one embodiment, the airflow member is a fan blade. The spherical interface shapes can be convex or concave. In one form, the tip end spherical shape is axially shifted aft relative to a hub end. The tip end can include relatively little forward portion in an expanding flow path with predominant portion of the tip end in a contracting flow path. Such a configuration can occur with a midpoint and trailing edge located in the contracting flow path. A center of gravity of a swept airflow member having spherical end shape can be located on a pivot axis of the airflow member. Divot depressions can be provided to permit concave flow path shapes.
    Type: Grant
    Filed: July 7, 2017
    Date of Patent: January 21, 2020
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Roy D. Fulayter, Daniel K. Vetters, Bronwyn Power
  • Patent number: 10526911
    Abstract: A synchronization ring for a variable vane assembly of a gas turbine engine may include a first ring portion and a second ring portion. The first ring portion and the second ring portion may be detachably coupled together to jointly define a plurality of cylindrical bores circumferentially distributed around the synchronization ring and extending radially through the synchronization ring.
    Type: Grant
    Filed: June 22, 2017
    Date of Patent: January 7, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: William S. Pratt, David Maliniak, Christopher St. Mary
  • Patent number: 10527060
    Abstract: Variable stator vane assemblies and stator vanes thereof having a local swept leading edge are provided. The variable stator vane comprises an airfoil disposed between spaced apart inner and outer buttons centered about a rotational axis. The inner and outer buttons each have a button forward edge portion. The airfoil includes leading and trailing edges, pressure and suction sides, and a root and a tip. The leading edge, at least a portion of which extends forward of the buttons, includes a local forward sweep at the root, thereby forming a locally swept root of the leading edge thereat. The button forward edge portion of the inner button is substantially vertically aligned with the locally swept leading edge root. Methods are also provided for minimizing endwall leakage in the variable stator vane assembly using the same.
    Type: Grant
    Filed: August 24, 2017
    Date of Patent: January 7, 2020
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Bruce David Reynolds, Timothy Gentry, Richard David Conner
  • Patent number: 10518395
    Abstract: A cuff-blade attachment bushing removal tool system includes an alignment plate comprising alignment holes defined through the alignment plate in a pattern of a plurality of bushing holes of a blade root, a bladder plate connected to the alignment plate, and a bladder positioned on the bladder plate such that a gap is formed between the bladder and the alignment plate to receive a blade root to align the alignment holes and the bushing holes of the blade root, wherein the bladder is transitionable between an uninflated position where the blade root can be inserted into the gap and an inflated position where the blade root is clamped between the bladder and the alignment plate.
    Type: Grant
    Filed: January 14, 2019
    Date of Patent: December 31, 2019
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventors: Scott O. Smith, Sven R. Lofstrom, Philip Petering