Individually Pivoted Vanes Patents (Class 415/160)
  • 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: 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: 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: 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: 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: 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: 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: 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: 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: 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
  • Patent number: 10508660
    Abstract: An apparatus and method of controlling the position of a variable vane in a compressor and a kit for adding such apparatus to the compressor are disclosed. The vane is coupled to a unison ring, a cam is secured to a torque tube, a cam follower is secured to the unison ring. The cam follower is secured such that a wall of the cam follower is in contact with the cam. Rotation of the torque tube causes movement of the cam, and movement of the cam moves the cam follower, thereby moving the unison ring and the variable vane coupled thereto.
    Type: Grant
    Filed: October 20, 2017
    Date of Patent: December 17, 2019
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Christopher Hall, Russell White, Jonathan Acker, Lyle Helvie
  • Patent number: 10502077
    Abstract: A vane retainer for a gas turbine engine includes a retainer body, an inner surface of the retainer body to engage complimentary threads of a mating component, and a plurality of castellations located at an end of the retainer body for engagement with complementary installation tool features during installation of the vane retainer to the mating component. A gas turbine engine includes a combustor and a plurality of vane assemblies in fluid communication with the combustor. Each vane assembly includes a vane having an airfoil portion and a vane stem extending from the airfoil portion. The vane stem is inserted into a bushing. A vane retainer is engaged with the bushing and includes a retainer body, an inner surface of the retainer body to engage complimentary threads of the bushing, and a plurality of castellations located at an end of the retainer body for engagement with complementary installation tool features.
    Type: Grant
    Filed: March 17, 2016
    Date of Patent: December 10, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Edward Torres
  • Patent number: 10393146
    Abstract: A flexible metal foil can be fixed on the inside part of a variable pitch vane control ring of a turbojet compressor, so as to close all through holes in which lever pins and their surrounding bushes are housed. As a result, the foil can retain the shank of the bush if the bush breaks. The use of such foil does not impose the development of a new model of control ring and its impact on the mass is small enough so that it does not affect engine performances. Therefore it avoids problems related to the breakage of bushes without having to make major changes to the existing system.
    Type: Grant
    Filed: July 3, 2017
    Date of Patent: August 27, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Olivier Bazot, Jérémy Philippe Pierre Edynak
  • Patent number: 10364827
    Abstract: An adjustable guide vane ring of a turbomachine having an inner ring, the guide vanes of which each have a radially inner vane disk with disk thickness increasing in the direction of flow and acting as a bearing pin; a guide vane, as well as an inner ring for such a guide vane ring, as well as a turbomachine are disclosed.
    Type: Grant
    Filed: March 30, 2015
    Date of Patent: July 30, 2019
    Assignee: MTU Aero Engines AG
    Inventors: Werner Humhauser, Hermann Klingels
  • Patent number: 10287902
    Abstract: A variable stator vane includes airfoil mounted to a button centered about a rotational axis and having cylindrical portion supporting airfoil and a button undercut extending away from cylindrical portion and radially inwardly from circumference of cylindrical portion. Conical portion of button circumscribed about conical axis of revolution extends away from cylindrical portion. Conical axis of revolution may be tilted with respect to and may intersect rotational axis. Airfoil may include airfoil overhang extending radially outwardly beyond circular trailing edge of button. Variable stator vane may include airfoil disposed between spaced apart outer and inner buttons centered about a rotational axis, inner button having a cylindrical portion supporting airfoil and circumscribed about rotational axis, and button undercut extending away from cylindrical portion and radially inwardly from a circumference of cylindrical portion with respect to rotational axis.
    Type: Grant
    Filed: January 6, 2016
    Date of Patent: May 14, 2019
    Assignee: General Electric Company
    Inventors: Wojciech Sak, Timothy William Taylor, Walter Glen Crosby, IV
  • Patent number: 10240519
    Abstract: At least one of a variable turbine geometry and a variable compressor geometry for an exhaust gas turbocharger may include a housing including a first housing wall and a blade bearing ring having at least one guide blade rotatably mounted thereon. A control lever may be included for adjusting the at least one guide blade between a closing position and an opening position. An actuating shaft may be connected to the control lever in a rotationally fixed manner along a rotation axis. The actuating shaft may be rotatably mounted on the housing via a passage opening disposed in the first housing wall. The actuating shaft may directly support itself on the first housing wall in the passage opening.
    Type: Grant
    Filed: September 11, 2015
    Date of Patent: March 26, 2019
    Assignee: BMTS Technology GmbH & Co. KG
    Inventors: Anatolij Martens, Volkhard Ammon
  • Patent number: 10240518
    Abstract: A variable-geometry turbocharger (1) with a vane lever (11) that provides a stop function at full open position of the guide vanes (8). The integrated vane-open stop controls the full open position of the VTG mechanism. A vane lever (11) preferably has an integrated protrusion (50) that functions as a vane-open stop that contacts an adjacent vane lever (11), an integrated bolt (56), or the upper vane ring (16) at the full open position to regulate maximum exhaust gas flow to the turbine wheel (5).
    Type: Grant
    Filed: March 12, 2014
    Date of Patent: March 26, 2019
    Assignee: BorgWarner Inc.
    Inventors: Vahidin Alajbegovic, Daniel J. Van Saun, Robert S. Lerosen, Daniel N. Ward
  • Patent number: 10221711
    Abstract: In an integrated strut and turbine vane nozzle (ISV) configuration, lug/slot or tag/groove arrangements may be provided between an interturbine duct (ITD) of the ISV and a vane ring of the ISV such that struts of the ITD and associated vanes are angularly positioned to form integrated strut-vane airfoils, reducing mismatch at the integration.
    Type: Grant
    Filed: October 30, 2017
    Date of Patent: March 5, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Vincent Paradis, John Walter Pietrobon, Richard L. Bouchard
  • Patent number: 10215047
    Abstract: An actuator includes a pump including a first cavity and a diaphragm coupled in flow communication with the first cavity. The diaphragm is configured to pressurize a fluid contained in the first cavity. The pump further includes a first valve coupled in flow communication with the first cavity. The first valve is configured to release fluid from the first cavity when the first cavity is pressurized. The actuator also includes a piston assembly operatively coupled to the pump.
    Type: Grant
    Filed: December 28, 2015
    Date of Patent: February 26, 2019
    Assignee: General Electric Company
    Inventors: Thomas Ory Moniz, Joseph George Rose, Robert Joseph Orlando, Chenyu Jack Chou
  • Patent number: 10145264
    Abstract: An example variable vane actuation system of a gas turbine engine includes, among other things, an actuation ring, a plurality of variable vanes circumferentially disposed about an engine axis, a plurality of vane arms configured to actuate the plurality of variable vanes, and a plurality of press fit members coupling the vane arms to the actuation ring.
    Type: Grant
    Filed: July 2, 2014
    Date of Patent: December 4, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: James F. McGuire, II
  • Patent number: 10094391
    Abstract: A compressor housing includes an intake port, a scroll, and a shroud. The shroud includes a shroud surface facing the impeller, a sliding member in an annular shape, and a sliding-member fixing portion in an annular shape. An inner circumferential surface of the sliding member defines the shroud surface. The sliding-member fixing portion includes contact portions that are configured to such that an inner circumferential surface of the sliding-member fixing portion and an outer circumferential surface of the sliding member at least partially come into contact with each other. The sliding member is fastened to the sliding-member fixing portion at the contact portions by the fastening members. The sliding member is fastened by the fastening members configured to extend through the sliding-member fixing portion. The fastening members are fastened from an outer circumferential surface of the sliding-member fixing portion to the sliding member.
    Type: Grant
    Filed: February 23, 2016
    Date of Patent: October 9, 2018
    Assignee: TOYOTA JIDOSHA KABUSHIKI KAISHA
    Inventors: Tomoki Miyoshi, Tomoyuki Isogai, Koichi Yonezawa
  • Patent number: 10066668
    Abstract: The present invention provides a split inner ring for an adjustable guide blade arrangement, having a ring segment arrangement with at least two ring segments (1, 2) and a bearing bush arrangement with at least one bearing bush (5) for mounting an adjustable guide blade (4) of the guide blade arrangement, in which a ring segment and another ring segment of the ring segment arrangement can be joined together by the bearing bush arrangement.
    Type: Grant
    Filed: May 15, 2014
    Date of Patent: September 4, 2018
    Assignee: MTU AERO ENGINES AG
    Inventor: Georg Zotz
  • Patent number: 10046424
    Abstract: Methods are provided for improving performance of a gas turbine engine comprising a component having a rotor mounted in a rotor casing and having rotor blades. A tip sweep is applied to a leading edge of one or more rotor blades each having a pressure sidewall and a circumferentially opposing suction sidewall extending in a radial direction between a root and a tip and in an axial direction between the leading edge and a trailing edge. One or more blade geometric design parameters are adjusted. A rotor casing treatment is applied to the rotor casing over at least one of the one or more rotor blades. The applying and adjusting steps are performed during design of the rotor and cause a measured stall margin to substantially match a required stall margin with an increase in efficiency of the component.
    Type: Grant
    Filed: August 28, 2014
    Date of Patent: August 14, 2018
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Bruce David Reynolds, John A. Gunaraj, Timothy Gentry
  • Patent number: 10030576
    Abstract: A bottom surface of a housing recess of a turbine housing includes a close attachment portion in a continuous annular land shape, which is located radially outside a fitting recess. The close attachment portion is closely attached to a portion radially outside first support holes in a surface of a shroud ring opposite from its facing surface, by a fastening force of attachment bolts. The first support holes in the shroud ring communicate with an outlet side of a turbine impeller through a connection path and a cutout.
    Type: Grant
    Filed: January 16, 2015
    Date of Patent: July 24, 2018
    Assignee: IHI Corporation
    Inventors: Takafumi Ueda, Akira Iwakami, Yoshinari Yoshida, Naoki Tokue, Masaru Nishioka, Mikito Ishii
  • Patent number: 10024186
    Abstract: A variable stator vane for a compressor guide vane is provided. The vane includes a blade and a pivot. The pivot includes an internal pivot element and a pivot cap. The blade and the internal pivot element are each made from a composite material. At least one contact surface of the pivot cap is metallic.
    Type: Grant
    Filed: December 11, 2014
    Date of Patent: July 17, 2018
    Assignee: SNECMA
    Inventors: Stephane Pierre Roger Hennequin, Julien Prevost, Ziyad Karmy
  • Patent number: 10018069
    Abstract: The present disclosure includes vane assemblies having a vane lever arm with an inclined profile. The inclined profile may engage with a complementary end of a vane shaft to locate, retain, and prevent rotation of the vane shaft and vane.
    Type: Grant
    Filed: August 28, 2015
    Date of Patent: July 10, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Christopher Osborne, Adam Nicholas Hart
  • Patent number: 10006355
    Abstract: An object is to provide a variable-geometry exhaust turbine whereby it is possible to prevent deformation and damage to a nozzle support under a high temperature. A variable-geometry exhaust turbine includes: a nozzle mount, a nozzle support including a first end portion joined to the first surface of the nozzle mount, a nozzle plate including the first surface joined to the second end portion of the nozzle support 6 and supported so as to face the nozzle mount at a distance, and the opposite second surface facing an exhaust—as channel through which exhaust gas flows, and a plurality of nozzle vanes supported rotatably between the nozzle mount and the nozzle plate. The nozzle support is capable of tilting along a radial direction so as to absorb a relative displacement in the radial direction between the nozzle mount and the nozzle plate due to thermal expansion.
    Type: Grant
    Filed: February 21, 2013
    Date of Patent: June 26, 2018
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Noriyuki Hayashi, Takamitsu Himeno, Takashi Arai, Yukihide Nagayo, Mitsuru Aiba, Takao Yokoyama, Toru Hoshi, Hiroyuki Arimizu, Toshio Sakon