Individually Pivoted Vanes Patents (Class 415/160)
  • 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
  • Patent number: 10006374
    Abstract: An engine that has, in axial flow series, booster compressor, core compressor, combustion equipment, core turbine, and low-pressure turbine. Core turbine drives core compressor via an interconnecting high-pressure shaft. Low-pressure turbine drives booster compressor via an interconnecting low-pressure shaft. Low-pressure turbine also drives external load having a defined speed characteristic that dictates speed of the low-pressure turbine and booster compressor. Booster compressor has one or more rows of variable stator vanes. The method includes: scheduling variation in the angle of variable stator vanes as a function of speed of the booster compressor wherein the vanes open as booster compressor speed increases; measuring or setting one or more operational parameters which are determinative of temperature at entry to core turbine; and biasing scheduling of angle variation of variable stator vanes as a function of operational parameter(s) to reduce variation in temperature at entry to core turbine.
    Type: Grant
    Filed: April 16, 2015
    Date of Patent: June 26, 2018
    Assignee: ROLLS-ROYCE plc
    Inventors: Alasdair Gardner, Arthur Laurence Rowe, Mark David Taylor, Nicholas Howarth
  • Patent number: 9988926
    Abstract: An exemplary variable vane actuation system includes, among other things, a vane arm with a vane stem contact surface and a radially outward facing surface. The vane stem contact surface is to contact a vane stem of a variable vane and thereby actuate the variable vane about a radially extending axis. The vane stem contact surface is angled relative to both the radially extending axis and the radially outward facing surface.
    Type: Grant
    Filed: February 18, 2014
    Date of Patent: June 5, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Eugene C. Gasmen, Bernard W. Pudvah, Christopher St. Mary, Stanley Wiecko
  • Patent number: 9988975
    Abstract: An exhaust-gas turbocharger (1) having a turbine (2) which has a turbine wheel (3) surrounded by an inflow duct (4), and having a VTG cartridge (5), which VTG cartridge has a disk (6) and a vane bearing ring (7), which delimit the inflow duct (4), and which VTG cartridge has a multiplicity of vanes (8) which are arranged in the inflow duct (4) and which are mounted in the vane bearing ring (7) by way of rotatable vane shafts (9), which vane shafts are connected to vane levers (10), the lever heads (11) of which engage into associated grooves (12) in an adjusting ring (13) which surrounds the vane bearing ring (7) on the outside. At least one min-flow stop (25, 26) has, on an outer surface (31), a laser-cut portion (32).
    Type: Grant
    Filed: February 28, 2014
    Date of Patent: June 5, 2018
    Assignee: BorgWarner Inc.
    Inventor: Dietmar Metz
  • Patent number: 9981739
    Abstract: A structure (10) for aircrafts, includes a part (20) including a metal leading edge (30), the leading edge (30) being covered by a coating (40) having a thickness which is less than or equal to ten micrometers and having a hardness higher than six hundred in the Vickers hardness test (HV). According to a mode of embodiment, the coating (40) is a multilayer stainless steel coating consisting of a superposition of layers with a low nitrogen gradient and layers with a high nitrogen gradient, the layers having a thickness essentially equal to a micrometer. An aircraft including such a structure is also described.
    Type: Grant
    Filed: March 13, 2014
    Date of Patent: May 29, 2018
    Assignees: AIRBUS GROUP SAS, EUROCOPTER
    Inventors: Benjamin Luiset, Thomas Navarre, Patrick Boschet, Alain Billard
  • Patent number: 9976438
    Abstract: A stator vane adjusting device of a gas turbine having a plurality of stator vanes each swivellable about a radial axis and arranged in at least one radial plane, as well as at least one stator vane adjusting ring which is connected to the respective stator vanes and rotatable in the circumferential direction by means of an actuating device, where the stator vane adjusting ring is braced on a centrally arranged casing in the radial direction by means of several spacers distributed about the circumference and mounted on the stator vane adjusting ring, characterized in that a bush on which the spacer is mounted is fastened to the stator vane adjusting ring for each spacer, the bush being made from a plastic material with a high thermal expansion coefficient.
    Type: Grant
    Filed: September 22, 2015
    Date of Patent: May 22, 2018
    Assignee: Rolls-Royce Detschland Ltd & Co KG
    Inventor: Thomas Klauke
  • Patent number: 9970314
    Abstract: An inner ring for forming a guide blade ring for a turbomachine is disclosed, composed of at least two one-part ring segments having a plurality of openings, closed on the peripheral side, for accommodating journal bearings on the blade side, the outer diameter of the inner ring being at least 12 times larger than its height. Also disclosed are a guide blade ring having this type of inner ring and a turbomachine having this type of guide blade ring.
    Type: Grant
    Filed: May 1, 2012
    Date of Patent: May 15, 2018
    Assignee: MTU Aero Engines GmbH
    Inventor: Frank Stiehler
  • Patent number: 9932988
    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: December 16, 2013
    Date of Patent: April 3, 2018
    Assignee: United Technologies Corporation
    Inventors: David Maliniak, Nathan F. Champion, Kenneth A. Frisk
  • Patent number: 9915267
    Abstract: A fan structure comprising a base, a fan inlet funnel coupled to the base, the fan inlet funnel having an inner surface for conducting air flow into a fan inlet and an outer surface and a plurality of external ribs coupled to the outer surface of the fan inlet funnel.
    Type: Grant
    Filed: June 8, 2015
    Date of Patent: March 13, 2018
    Assignee: Air Distribution Technologies IP, LLC
    Inventor: Timothy A. Schrand
  • Patent number: 9915158
    Abstract: The disclosure relates to a vane arrangement with a vane carrier, an array of rocking first stage vanes, and an array of frame segments for axially receiving aft ends of a combustor transition pieces. The frame segments comprise an I-beam with an upper horizontal element, a lower horizontal element, a vertical web, a radially outer fixation to the vane carrier, and an arm extending from the lower horizontal element in axial direction below the inner rim segment for supporting the inner platform of the vane and for sealing a gap between the inner platform and the lower horizontal element. Besides the vane arrangement the disclosure relates to a method for assembly of such an arrangement as well as to a gas turbine comprising such a vane arrangement.
    Type: Grant
    Filed: November 24, 2015
    Date of Patent: March 13, 2018
    Assignee: ANSALDO ENERGIA SWITZERLAND AG
    Inventors: Frank Graf, Hans-Christian Mathews, Fabien Fleuriot, Urs Benz
  • Patent number: 9909435
    Abstract: An apparatus for sealing a gap between a stator vane platform including a seal slot, and a rotatable stator vane including a shaft connected to a vane end. The apparatus includes a substantially flat, semi-annular seal body, a first tab and a second tab. The seal body extends circumferentially between a first body end and a second body end, and radially between a radial inner body side and a radial outer body side. The inner body side wraps partially around the shaft, and the outer body side mates with the seal slot. The first tab extends axially from the first body end, and the second tab extends axially from the second body end. The first tab and the second tab engage the vane end and cause the seal body to move within the seal slot during rotation of the stator vane.
    Type: Grant
    Filed: July 1, 2015
    Date of Patent: March 6, 2018
    Assignee: United Technologies Corporation
    Inventor: Tracy A. Propheter-Hinckley
  • Patent number: 9896957
    Abstract: An exhaust-gas turbocharger (1) having a turbine (2) which has a turbine wheel (3) surrounded by an inflow duct (4), and having a VTG cartridge (5), which VTG cartridge has a disc (6) and a vane bearing ring (7), which delimit the inflow duct (4), and which VTG cartridge has a multiplicity of vanes (8) which are arranged in the inflow duct (4) and which are mounted in the vane bearing ring (7) by way of rotatable vane shafts (9), which vane shafts are connected to vane levers (10), the lever heads (11) of which engage into associated grooves (12) in an adjusting ring (13) which surrounds the vane bearing ring (7) on the outside; and having a radial bearing between the adjusting ring (13) and the vane bearing ring (7). Two min-flow stops (25, 26) are arranged, with a selectable angular spacing (?) with respect to one another, on the vane bearing ring (7).
    Type: Grant
    Filed: November 14, 2013
    Date of Patent: February 20, 2018
    Assignee: BorgWarner Inc.
    Inventor: Dietmar Metz
  • Patent number: 9890795
    Abstract: A cooling fan structure includes a housing, a multistage fan wheel, and a stator-blade unit set. The housing is integrally formed and includes a first and a second frame, and a connecting spacer set connected to between the first and the second frame to define an open space therebetween. The multistage fan wheel is located in the housing and has a hub, around which a group of first and a group of second rotor blades are formed and axially spaced to define a bladeless zone on the hub between the first and the second rotor blades. The stator-blade unit set includes a first and a second stator-blade unit, which are assembled into the open space of the housing to circumferentially close the open space. The stator-blade unit set is exchangeable according to different high impedance systems to achieve different levels of high static pressure without increasing any mold-making cost.
    Type: Grant
    Filed: May 6, 2015
    Date of Patent: February 13, 2018
    Assignee: Asia Vital Components Co., Ltd.
    Inventors: Bor-Haw Chang, Chung-Shu Wang
  • Patent number: 9890793
    Abstract: A vane for a variable diffuser includes a body with an inlet end and an outlet end, a leading surface extending from the inlet end to the outlet end, a trailing surface opposite the leading surface and extending from the inlet end to the outlet end, a first surface extending from the inlet end to the outlet end, and a second surface opposite the first surface and extending from the inlet end to the outlet end. The vane further includes a first cavity on the first surface of the vane adjacent the inlet end, a second cavity on the first surface of the vane adjacent the outlet end, a third cavity on the second surface of the vane adjacent the inlet end, and a fourth cavity on the second surface of the vane adjacent the outlet end.
    Type: Grant
    Filed: September 23, 2014
    Date of Patent: February 13, 2018
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Craig M. Beers, Murtuza Lokhandwalla, Kevin M. Rankin, David A. Dorman, Seth E. Rosen, John M. Beck, Paul E. Hamel, Clarence J. Wytas, Jr.
  • Patent number: 9856744
    Abstract: A variable geometry turbocharger includes a vane pack having rotatable vanes constrained by a pair of vane rings connected by a plurality of spacer connectors. The spacer connectors can include a spacer body for maintaining a minimum spacing between the vane rings. The spacer connectors are configured for bayonet mounting to at least one of the vane rings. To that end, the spacer connectors can include shaft portions extending from opposing sides of the spacer body. A plurality of transverse protrusions can extend outwardly from each shaft portion. Each shaft portion can be received in a respective in a vane ring. The spacer connectors can be rotated such that the transverse protrusions are offset from aperture portions that allow passage of the transverse portions, thereby retaining the vane rings in place in spaced relation. Such a system avoids close tolerances, press fits, expensive bolted joints or weld processes.
    Type: Grant
    Filed: April 22, 2013
    Date of Patent: January 2, 2018
    Assignee: BorgWarner Inc.
    Inventor: George E. Heddy, III
  • Patent number: 9835045
    Abstract: An exhaust gas turbocharger may include a turbine housing and a turbine wheel. The turbine wheel may include a first quantity of a plurality of moving blades. The turbine wheel may be rotatable relative to the turbine housing about a turbine wheel center of rotation and have a turbine wheel radius. A variable turbine geometry may include a blade bearing ring on which a second quantity of a plurality of guide blades are rotatably mounted in each case about a guide blade center of rotation. The plurality of guide blades may be adjustable between a closed position, in which a flow cross section between the guide blades for an exhaust gas to flow through is at a minimum, and an opened position, in which the flow cross section is at a maximum.
    Type: Grant
    Filed: December 1, 2014
    Date of Patent: December 5, 2017
    Assignee: Bosch Mahle Turbo Systems GmbH & Co. KG
    Inventors: Jochen Laubender, Marcus Schneider
  • Patent number: 9784285
    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 includes a local forward sweep at the root, a local aft sweep at the tip, or both, thereby forming a locally swept leading edge thereat. The button forward edge portion of one or both of the inner and outer buttons is substantially coextensive with the locally swept leading edge. Methods are also provided for minimizing endwall leakage in the variable stator vane assembly using the same.
    Type: Grant
    Filed: September 12, 2014
    Date of Patent: October 10, 2017
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Bruce David Reynolds, Timothy Gentry, Richard David Conner
  • Patent number: 9784178
    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 5, 2012
    Date of Patent: October 10, 2017
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Naoto Tashiro, Yasuaki Jinnai, Hiroyuki Arimizu
  • Patent number: 9771939
    Abstract: It is intended to achieve weight reduction and production reduction of a nozzle mount for pivotably supporting a drive ring constituting a variable nozzle mechanism, and is characterized by: providing on an end face of a guide part 5a a nail pin 20 having a flange portion and being positioned so as to hold a drive ring 3 of a variable nozzle mechanism 100 to the guide part 5a of a nozzle mount 5 in the thrust direction, and setting the thrust-directional width of the drive ring 3 smaller than the width of the guide part 5a, and providing an adjusting member 20c between the flange portion of the nail pin 20 and the end face of the guide part 5a to adjust a distance between the side face of the nozzle mount and the flange portion of the nail pin 20.
    Type: Grant
    Filed: September 5, 2012
    Date of Patent: September 26, 2017
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Naoto Tashiro, Yasuaki Jinnai, Hiroyuki Arimizu
  • Patent number: 9695822
    Abstract: A turbocharger is provided herein. The turbocharger includes a housing and an adjustable core at least partially circumferentially surrounded by the housing, the adjustable core having a turbine rotor coupled to a compressor rotor via a shaft. The turbocharger further includes an adjustment mechanism coupled to the adjustable core configured to adjust an axial position of the housing relative to the adjustable core in response to adjustment commands.
    Type: Grant
    Filed: September 17, 2014
    Date of Patent: July 4, 2017
    Assignee: Ford Global Technologies, LLC
    Inventors: James Douglas Ervin, August Thomas Vaught
  • Patent number: 9611751
    Abstract: A number of variations may include a product comprising: a vane lever comprising a first end; a second end; a top surface; and a bottom surface; and an opening defined by an inner surface which extends through the top surface and the bottom surface of the second end, and wherein at least a portion of the inner surface comprises a non-cylindrical, multi-lobed shape.
    Type: Grant
    Filed: September 18, 2015
    Date of Patent: April 4, 2017
    Assignee: BorgWarner Inc.
    Inventors: John Zagone, Eli Morgan, Greg Williams
  • Patent number: 9587557
    Abstract: A vane pack for a VTG turbocharger is provided. The vane pack includes a plurality of vanes pivotably positioned between an inner surface of an upper vane ring and an inner surface of a lower vane ring. Clearances are defined between opposing cheek surfaces of the vanes and the inner surfaces of the vane rings. The vane pack is configured to minimize these clearances by applying an abradable coating is to the inner surface of the upper vane ring, the inner surface of the lower vane ring and/or cheek surface(s) of one or more of the vanes. In this way, an essentially zero clearance can be established without interfering with the proper function of the vanes. As a result, there can be gains in efficiency. Further wearing of the abradable coating may occur during turbocharger operation.
    Type: Grant
    Filed: April 19, 2013
    Date of Patent: March 7, 2017
    Assignee: BorgWarner Inc.
    Inventors: Luke Barron, Steve Birnie, Alan Wint
  • Patent number: 9556882
    Abstract: A turbocharger (15) with variable turbine geometry, having a blade bearing ring arrangement (1) which has a blade bearing ring (2) and a disk (3) which is fixed to the blade bearing ring (2) so as to create a flow duct (4), having guide blades (5?) mounted in the blade bearing ring (2), and having a spacer device (5) which is arranged between the blade bearing ring (2) and the disk (3) so as to set a defined width (B) of the flow duct (4). The spacer device (5) is formed as an inlet guide grate (6) which has movable inlet guide blades (8) which are arranged in each case on a spacer pin (7) which is fixed with its first end (7A) to the blade bearing ring (2). Also, a method for producing a blade bearing ring arrangement (1).
    Type: Grant
    Filed: April 30, 2012
    Date of Patent: January 31, 2017
    Assignee: BorgWarner Inc.
    Inventor: Leif Heidingsfelder
  • Patent number: 9534501
    Abstract: An inlet guide vane assembly is disclosed, which comprises: a housing, configured with a first penetration part and a plurality of first grooves; at least one fixing ring, each configured with a second penetration part and a plurality of second grooves; at least one rotary ring, each configured with a third penetration part and a plurality of sliding chutes, wherein the first, the second and the third penetration parts are arranged in communication with one another; a plurality of vane units, each vane unit is composed of a vane, a linkage and a sliding block; and at least one driving unit, for driving one vane of the plural vanes to swing, thus driving the rotary ring to rotate simultaneously, bringing along the other vanes to swing, enabling the sliding blocks to slide inside corresponding sliding chutes, and consequently flipping the vane from a first state to a second state.
    Type: Grant
    Filed: May 1, 2014
    Date of Patent: January 3, 2017
    Assignee: INDUSTRIAL TECHNOLOGY RESEARCH INSTITUTE
    Inventors: Kuo-Shu Hung, Jenn-Chyi Chung, Chung-Che Liu
  • Patent number: 9533485
    Abstract: A variable vane assembly for a gas turbine engine compressor and method of manufacturing same is described. A plurality of projections the inner and/or outer shroud which protruded into the annular gas path such as to ensure that a radial clearance gap, defined between the projections and a vane airfoil overhang portion, remains substantially constant throughout a substantial portion of the vane pivot arc of the variable vane. The method includes forming one cavities within the shroud, the cavities isolated from the annular gas path and disposed radially beneath at least each of the projections, and providing one or more structural reinforcing elements within the cavities.
    Type: Grant
    Filed: March 28, 2014
    Date of Patent: January 3, 2017
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Andrew R. Marshall, David Menheere
  • Patent number: 9452832
    Abstract: The invention relates to compensation for the torque which is produced by the main rotor (110) of a helicopter (100). The apparatus according to the invention for torque compensation is intended for a helicopter whose main rotor rotates about a rotation axis (RH) during operation and thus produces a torque, which acts on the fuselage (120) of the helicopter and would cause it to rotate. The apparatus comprises a lateral flow fan (200) having a housing (210) and having a rotor (220) which is mounted in the housing, wherein the lateral flow fan is arranged on the tail boom (130) of the helicopter such that it produces a thrust effect (F) during operation which compensates for the torque of the main rotor.
    Type: Grant
    Filed: April 5, 2011
    Date of Patent: September 27, 2016
    Assignee: Siemens Aktiengesellschaft
    Inventor: Oliver Heid
  • Patent number: 9435352
    Abstract: A drive lever arrangement is provided. The drive lever arrangement includes a unison ring which has a groove; a drive lever having connection means for connecting the drive lever to the unison ring; a drive lever pin having a transversal throughbore hole; and a clip, wherein the drive lever pin connects the drive lever to the unison ring, and wherein the clip is inserted in the groove through the throughbore hole of the drive lever pin, and engages with the groove of the unison ring.
    Type: Grant
    Filed: April 24, 2012
    Date of Patent: September 6, 2016
    Assignee: SIEMENS AKTIENGESELLSCHAFT
    Inventor: Philip Twell
  • Patent number: 9394804
    Abstract: Actuation systems and methods for varying the angle of small turbine engine inlet guide vanes (IGV) and/or compressor stator vanes (CSV). Such systems and methods may employ a piezoelectric inchworm actuator (or a piezo stack actuator or magnetostrictive actuator, depending upon actuation requirements) to actively modify the angle of attack of a single or a cascade of inlet guide vanes or compressor stator vanes. The change in angle of attack is necessary due to large variations in engine operating envelope including but not limited to air density, velocity, temperature, and the like. The present invention is especially suitable to actuate small inlet guide vanes and compressor stator vanes found in small turbine jet engines including but not limited to those under ten (10) inches in diameter.
    Type: Grant
    Filed: January 24, 2013
    Date of Patent: July 19, 2016
    Assignee: Florida Institute of Technology
    Inventor: Razvan Rusovici
  • Patent number: 9353643
    Abstract: A stator assembly for a turbine engine includes a support structure, such as an outer case, providing a bore. A non-metallic bushing is arranged in the bore and extends radially between inner and outer diameters providing a one-piece structure. The outer diameter of the bushing engages the bore in a press-fit relationship, in one example. A stator includes a trunnion arranged within and engaging the bushing inner diameter. In one example, the non-metallic bushing is constructed from an electrographitic carbon. The bushing is installed into the bore such that an end of the bushing is generally flush with or recessed from a wall on the support structure.
    Type: Grant
    Filed: April 10, 2007
    Date of Patent: May 31, 2016
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Daniel W. Major
  • Patent number: 9309778
    Abstract: A turbomachine includes a variably positioned vane, an outer spindle integral with a vane outer button, where the vane is coupled to the vane outer button, an annular sleeve defining the spindle, where the annular sleeve contacts the vane outer button at a radially inward extent and contacts a turbine casing at a radially outward extent. The annular sleeve includes a wall portion having an aperture and the spindle extends through the aperture. A nut engages spindle threads, where the nut applies force to the wall portion toward the radially inward extent. An end of the spindle extends through the turbine casing, and a cantilever rotation actuator is coupled to the end of the spindle. A first bearing and second bearing engage the annular sleeve. A vane inner button is coupled to the vane, and a third bearing engages the vane inner button.
    Type: Grant
    Filed: December 30, 2011
    Date of Patent: April 12, 2016
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventor: Robert A. Ress, Jr.
  • Patent number: 9303524
    Abstract: A gas turbine engine (100) variable nozzle (460) includes an outer shroud (461), an inner shroud (462), a variable nozzle airfoil (463), and a position selector (470). The inner shroud (462) is located radially inward from the outer shroud (461). The variable nozzle airfoil (463) extends radially between the outer shroud (461) and the inner shroud (462). The variable nozzle airfoil (463) includes a vane shaft (464) extending radially outward from the variable nozzle airfoil (463) through the outer shroud (461). The position selector (470) is coupled with the variable nozzle airfoil (463) to fixedly lock the variable nozzle airfoil (463) into one of a plurality of preselected positions.
    Type: Grant
    Filed: October 25, 2012
    Date of Patent: April 5, 2016
    Assignee: Solar Turbines Incorporated
    Inventors: John James Hensley, Ulrich Edmund Stang
  • Patent number: 9249732
    Abstract: A support hanger is provided for a turbine engine. The support hanger includes a pin with a pin head, a retainer and a flexible seal. The retainer is pivotally connected to the pin head. The retainer includes a seal bearing surface facing towards the pin head. The seal includes a retainer bearing surface sealingly engaging the seal bearing surface.
    Type: Grant
    Filed: November 8, 2012
    Date of Patent: February 2, 2016
    Assignee: United Technologies Corporation
    Inventors: Timothy J. McAlice, Carlos G. Figueroa
  • Patent number: 9103222
    Abstract: An apparatus for sealing a gap between a stator vane platform including a seal slot, and a rotatable stator vane including a shaft connected to a vane end. The apparatus includes a substantially flat, semi-annular seal body, a first tab and a second tab. The seal body extends circumferentially between a first body end and a second body end, and radially between a radial inner body side and a radial outer body side. The inner body side wraps partially around the shaft, and the outer body side mates with the seal slot. The first tab extends axially from the first body end, and the second tab extends axially from the second body end. The first tab and the second tab engage the vane end and cause the seal body to move within the seal slot during rotation of the stator vane.
    Type: Grant
    Filed: June 22, 2012
    Date of Patent: August 11, 2015
    Assignee: United Technologies Corporation
    Inventor: Tracy A. Propheter-Hinckley
  • Patent number: 9097137
    Abstract: An actuator module for a gas turbine engine includes a multiple of actuators mounted within a common actuator housing.
    Type: Grant
    Filed: December 15, 2011
    Date of Patent: August 4, 2015
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Gabriel L. Suciu, Brian D. Merry, Christopher M. Dye, James S. Elder
  • Patent number: 9033654
    Abstract: One embodiment of the present invention is a unique variable geometry vane system. Another embodiment is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and turbomachinery variable geometry vane systems. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.
    Type: Grant
    Filed: December 28, 2011
    Date of Patent: May 19, 2015
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies, Inc.
    Inventors: Brian Peck, Edward Claude Rice
  • Publication number: 20150132113
    Abstract: In an adjustable guide vane mechanism for a turbine, comprising a bearing ring with a plurality of guide vanes rotatably supported on the bearing ring by means of guide vane shafts provided with actuating levers which are engaged by a rotatable ring, the rotatable ring comprises axially spaced radial inner and outer sections with a radially inclined center section joining the spaced radial inner and outer sections, the radially inner section being rotatably supported and the radially outer section extending around the actuating levers and having recesses in which the actuating levers are received for pivoting the actuating levers and the guide vanes upon rotation of the rotatable ring.
    Type: Application
    Filed: January 1, 2015
    Publication date: May 14, 2015
    Inventor: Lorenz JAENIKE
  • Publication number: 20150118030
    Abstract: A variable geometry turbo system that controls a flow of exhaust gas introduced into a turbine of a turbo charger may include a vane base ring in which the turbine may be positioned at a center thereof, a fixed vane which may be fixed onto a first surface of the vane base ring to guide the exhaust gas introduced into the turbine, a variable vane which may be pivotally positioned on the first surface of the vane base ring and adjacent to the fixed vane so as to vary a flow path of the exhaust gas introduced into the turbine, a vane cover ring fixed to the vane base ring with the fixed vane and the variable vane interposed therebetween, and an actuating module coupled to the variable vane and selectively actuating the variable vane.
    Type: Application
    Filed: June 20, 2014
    Publication date: April 30, 2015
    Applicants: Hyundai Motor Company, Hyundai Wia Corporation
    Inventors: Kyung-Jae Jung, Seung Yeon Lee, Kwang Hwan Kim, Gil-Beom Lee, Jun Gwan Park, Sung-Jin Yang, Ui Yeon Park, Kyung-Wook Jin
  • Patent number: 9017017
    Abstract: A variable-vane assembly for a variable nozzle turbine comprises a nozzle ring supporting a plurality of vanes affixed to vane arms that are engaged in recesses in the inner edge of a unison ring. The unison ring is rotatable about the axis of the nozzle ring so as to pivot the vane arms, thereby pivoting the vanes in unison. A plurality of guide pins for the unison ring are inserted into apertures in the nozzle ring and are rigidly affixed therein such that the guide pins are non-rotatably secured to the nozzle ring with a guide portion of each guide pin projecting axially from the face of the nozzle ring. Each guide portion defines a shoulder radially overlapping the inner edge of the unison ring such that the unison ring is restrained by the guide pins against excessive movement in both radial and axial directions.
    Type: Grant
    Filed: April 10, 2009
    Date of Patent: April 28, 2015
    Assignee: Honeywell Internatonal Inc.
    Inventors: Lorrain Sausse, Pierre Barthelet, Francis Abel, Olivier Espasa, Mohamed Tahyry, Emmanuel Bouvier
  • Patent number: 8992166
    Abstract: The invention relates to a turbocharger (1) with variable turbine geometry (VTG), having a turbine housing (2) with a supply duct (9) for exhaust gases, having a turbine rotor (4) which is rotatably mounted in the turbine housing (2); and having a guide grate (18), which surrounds the turbine rotor (4) radially at the outside, which has a blade bearing ring (6), which has a multiplicity of guide blades (7) which have in each case one blade shaft mounted in the blade bearing ring (6), which has an adjusting ring (5) which is operatively connected to the guide blades (7) by means of associated blade levers (20) fastened to the blade shafts (8) at one of their ends, with each blade lever (20) having, at the other end, a lever head (23) which can be placed in engagement with an associated engagement recess (24) of the adjusting ring (5), and which has a stop (25) at least for setting the minimum throughflow through the nozzle cross sections formed by the guide blades (7), wherein the stop (25) is formed as a part
    Type: Grant
    Filed: November 16, 2010
    Date of Patent: March 31, 2015
    Assignee: BorgWarner Inc.
    Inventor: Thomas Ramb
  • Publication number: 20150071768
    Abstract: A variable pitch rectifier for a compressor includes a plurality of radial vanes having respectively, at outer and inner ends of same, outer and inner pivots, the inner pivots being received between two upstream and downstream inner rings, which are assembled by a link device. The link device includes only a set of angular sectors of elastically deformable stirrups, arranged to grip together the inner peripheral edges of the upstream and downstream rings by clamping one against the other.
    Type: Application
    Filed: March 28, 2013
    Publication date: March 12, 2015
    Applicant: SNECMA
    Inventors: Nadege Hugon, Jacques Rene Bart
  • Patent number: 8974175
    Abstract: A turbomachine compressor including variable-pitch vanes including an aerofoil section connected by a mounting plate of circular outline to a pivot guided in rotation in an orifice in a casing is disclosed. The mounting plate of the vane includes at least one notch for bleeding air from the compressor stream. The notch is intended to communicate with a hole in the casing in order to remove the air bled off when the vanes are in a first position, and to be closed off by this casing when the vanes are in a second position, so that the flow rate of bled air depends on the pitch angle of the vanes.
    Type: Grant
    Filed: June 15, 2009
    Date of Patent: March 10, 2015
    Assignee: SNECMA
    Inventors: Olivier Stephane Domercq, Vincent Paul Gabriel Perrot