And Fixed Vane Patents (Class 415/161)
  • Patent number: 10837307
    Abstract: The invention relates to a system of vanes with adjustable orientation, also called a system of variable stator vanes, for a low-pressure compressor of an axial turbine engine. The system comprises vanes, each having a vane extending radially in a flow of the turbine engine and a spindle having a cylindrical portion connected to a telescopic actuating lever. The cylindrical portion comprises radially extending slot, and the actuating lever comprises a pivot joint housed in the slot, that is configured to communicate a rotary movement to the vane about its spindle. The invention also proposes a compressor and a turbine engine.
    Type: Grant
    Filed: July 13, 2018
    Date of Patent: November 17, 2020
    Assignee: SAFRAN AERO BOOSTERS SA
    Inventor: Rafael Perez
  • Patent number: 10808721
    Abstract: An intake structure of a compressor includes an intake duct forming an intake port opening in a direction away from a central axis of the compressor and a bellmouth forming an annular channel expanding from an inlet of the compressor toward an inner space of the intake duct. The bellmouth includes a plurality of struts connecting an inner casing positioned inside the annular channel and an outer casing positioned outside the annular channel. At least one of a plurality of transverse struts, of the plurality of struts, which are located on both sides of a center plane passing through the central axis of the compressor and the center of the intake port has a trailing edge positioned on a virtual plane passing through the central axis of the compressor and a leading edge positioned on a side of the intake port with respect to the virtual plane.
    Type: Grant
    Filed: October 7, 2016
    Date of Patent: October 20, 2020
    Assignee: KAWASAKI JUKOGYO KABUSHIKI KAISHA
    Inventors: Takuya Ikeguchi, Koji Terauchi, Keiji Oikaze, Naoto Sakai, Kazuhiko Tanimura
  • Patent number: 10662782
    Abstract: An airfoil includes an airfoil section that defines an airfoil profile. The airfoil section includes first and second airfoil pieces. The first airfoil piece defines a portion of the airfoil profile and has a first slot. The second airfoil piece defines a different portion of the airfoil profile and has a second slot. The first slot and the second slot together form a seal slot, and a seal is disposed in the seal slot.
    Type: Grant
    Filed: November 17, 2016
    Date of Patent: May 26, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventor: Tracy A. Propheter-Hinckley
  • Patent number: 10563541
    Abstract: A securing device having a radial pin which is inserted into a through-hole having an outside hole and an inside hole and penetrating an outside member in the radial direction of a rotary machine, the outside hole being open to the outside of the outside member in the radial direction of the rotary machine, the inside hole communicating with the outside hole, having a smaller diameter than the outside hole, and being open to the inside in the radial direction of the rotary machine, the radial pin having a portion on the inside in the radial direction of the rotary machine inserted into a recess formed in an inside member, and including a flange portion having an outer diameter larger than a diameter of the inside hole; and a pin support unit which is inserted into the outside hole on the outside in the radial direction of the rotary machine.
    Type: Grant
    Filed: March 22, 2016
    Date of Patent: February 18, 2020
    Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.
    Inventors: Akihiko Shirota, Taichi Ozaki
  • Patent number: 10393143
    Abstract: A compressor includes an impeller having a rotational axis. An annular diffuser is provided around the rotational axis to surround the impeller in order to decelerate the fluid discharged from the impeller in a centrifugal direction with respect to the rotational axis. The annular diffuser includes first vanes and second vanes. The first vanes are arranged in a first blade row extending in a circumferential direction around the rotational axis such that two adjacent vanes among the first vanes do not define a throat therebetween viewed along the rotational axis. The second vanes are arranged in a second blade row which extends in the circumferential direction and which is provided farther than the first blade row in the centrifugal direction from the rotational axis. A number of the second vanes is two times or more as large as a number of first vanes.
    Type: Grant
    Filed: April 19, 2017
    Date of Patent: August 27, 2019
    Assignee: HONDA MOTOR CO., LTD.
    Inventors: Naoki Kuno, Naoki Itoh
  • Patent number: 10151322
    Abstract: A tandem tip blade includes a main blade body, a front blade and a rear blade. The front blade extends from a main body end. Each of a front blade pressure and a front blade suction side extends between a front blade leading edge and a front blade trailing edge and a front blade tip extending from the front blade pressure side to the front blade suction side. The rear blade extends from the main body end. Each of a rear blade pressure side and a rear blade suction side extends between a rear blade leading edge and a rear blade trailing edge, and a rear blade tip extending from the rear blade pressure side to the rear blade suction side.
    Type: Grant
    Filed: May 20, 2016
    Date of Patent: December 11, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Dmytro Mykolayovych Voytovych, Alexander Staroselsky, Eric D. Gray
  • Patent number: 9784133
    Abstract: A turbine frame for a turbine engine having an axial centerline, the turbine frame comprising an inner hub, an outer hub encircling the inner hub, a plurality of struts extending between the inner and outer hubs and having a maximum width portion relative to the axial centerline and an airfoil comprising at least first and second fairings mounted to the inner and outer hubs and encircling one of the struts.
    Type: Grant
    Filed: April 1, 2015
    Date of Patent: October 10, 2017
    Assignee: General Electric Company
    Inventors: Apostolos Pavlos Karafillis, Martin Wayne Frash, Schuyler Javier Ortega, Angelo Parisi
  • Patent number: 9617968
    Abstract: The invention relates to a hydraulic machine having an impeller wheel that comprises a plurality of impeller blades; having a spiral housing that encloses the impeller wheel and that is open toward said impeller wheel by a circumferential slit formed by two circumferential edges; having a traverse ring, comprising two traverse ring decks that are connected to one another by tension anchors; wherein the spiral housing is composed of segments that meet in the flow direction and that are welded to each other, the ends of which segments stand on the respective traverse ring deck and are welded to said deck; wherein at the meeting point between two segments that are adjacent to one another and one traverse ring deck a stiffening element is provided that protrudes into the inner space of the spiral housing; and wherein the extension of the stiffening element into the inner space of the spiral housing is so small that the flow is not affected in a significant manner.
    Type: Grant
    Filed: July 26, 2012
    Date of Patent: April 11, 2017
    Assignee: Voith Patent GmbH
    Inventors: Sebastian Hyneck, Gerhard Wengert
  • Patent number: 9464533
    Abstract: An inlet guide vane actuation apparatus is provided. The inlet guide vane actuation apparatus comprises an actuation ring with a first connector for connecting an actuator rod, wherein the first connector positions the actuator rod over the rotational axial center of the actuation ring, a plurality of crank rods with a first end connected respectively to a plurality of second connectors located on the rotational axial center of the actuation ring; and a plurality of cranks with each having a third connector connected respectively to a second end of the plurality of crank rods and respectively to vanes associated with a nozzle, wherein the third connector located on the rotational axial center of the actuation ring.
    Type: Grant
    Filed: August 31, 2012
    Date of Patent: October 11, 2016
    Assignee: Nuovo Pignone S.p.A
    Inventors: Giacomo Landi, Antonio Asti, Paolo Del Turco
  • Patent number: 9249736
    Abstract: Inlet guide vanes and gas turbine engine systems involving such vanes are provided, In this regard, a representative an inlet guide vane for a gas turbine engine includes: a fixed strut; and a variable flap located downstream of the fixed strut and being movable with respect thereto; the fixed strut having a leading edge, a trailing edge and side surfaces extending between the leading edge and the trailing edge, the side surfaces being asymmetric with respect to each other.
    Type: Grant
    Filed: December 29, 2008
    Date of Patent: February 2, 2016
    Assignee: United Technologies Corporation
    Inventor: Christian A. Carroll
  • Patent number: 9188138
    Abstract: A device for adjusting variable guide vanes of an axial-flow machine includes a control rod that adjusts an angular position of the variable guide vanes and is pivotably connected to a shaft. Each of a first and a second bracket has a first end connectable to a casing of the machine. A first joint is fixed to a second end of the first bracket and provides adjustable positioning of a first end of the shaft. A second joint is fixed to a second end of the second bracket and provides adjustable positioning of a second end of the shaft. The two joints are spatially positioned to each other solely via a first fixed connection between the first end of the first bracket to the casing and via a second fixed connection between the first end of the second bracket to the casing.
    Type: Grant
    Filed: November 17, 2010
    Date of Patent: November 17, 2015
    Assignee: SIEMENS AKTIENGESELLSCHAFT
    Inventors: Colm Keegan, Michael Tibenham
  • Patent number: 8919119
    Abstract: Various systems and methods are described for a variable geometry turbine. In one example, a turbine nozzle comprises a central axis and a nozzle vane. The nozzle vane includes a stationary vane and a sliding vane. The sliding vane is positioned to slide in a direction substantially tangent to an inner circumference of the turbine nozzle and in contact with the stationary vane.
    Type: Grant
    Filed: August 16, 2011
    Date of Patent: December 30, 2014
    Assignee: Ford Global Technologies, LLC
    Inventors: Harold Huimin Sun, Jizhong Zhang, Liangjun Hu, Dave R. Hanna
  • Patent number: 8718975
    Abstract: A method and system for accepting or rejecting a curved surface of a body under evaluation involves conducting a comparison between the curvature of a surface profile for the surface under evaluation and higher and lower curvature tolerance boundaries. The higher and lower curvature tolerance boundaries are determined from a desired surface profile. The curvature at a plurality of locations on the curve profile under evaluation may be defined with reference to a geometric variable for said curved surface and may be plotted on a graph. The higher and lower curvature tolerance boundaries may also be plotted on the graph so as to determine whether the plot of curvature for the surface under evaluation falls within the bounds of the higher and lower tolerance boundaries.
    Type: Grant
    Filed: February 24, 2010
    Date of Patent: May 6, 2014
    Assignee: Rolls-Royce, PLC
    Inventors: Hugo M P Lobato, Ian R Gower, Christopher A Powell, Nicholas B Orchard
  • Patent number: 8632302
    Abstract: A compressor performance adjustment system includes a compressor chassis defining an inlet passageway, a diffuser passageway coupled to the inlet passageway, and a return passageway extending from the diffuser passageway. At least one inlet vane is located in the inlet passageway. At least one diffuser vane is located in the diffuser passageway. At least one return vane is moveably coupled to the compressor chassis and located in the return passageway. The return vanes may be adjusted without disassembling the compressor chassis in order to adjust the flow incident on compressor components and adjust the performance of a compressor.
    Type: Grant
    Filed: December 7, 2009
    Date of Patent: January 21, 2014
    Assignee: Dresser-Rand Company
    Inventors: James M. Sorokes, William C. Maier
  • Patent number: 8573929
    Abstract: A turbocharger includes an annular bypass passage to allow exhaust gas to bypass the turbine wheel. An annular bypass valve is disposed in the bypass passage. The bypass valve comprises a fixed annular valve seat and a rotary annular valve member arranged coaxially with the valve seat. The valve member is disposed against the valve seat and is rotatable about the axis for selectively varying a degree of alignment between respective orifices in the valve seat and valve member. The turbine includes a nozzle having a vane assembly. In one embodiment the vane assembly has only fixed vanes. In another embodiment the vane assembly includes both fixed vanes and variable vanes, and the variable vanes are part of a rotor that rotates together with the rotary valve member.
    Type: Grant
    Filed: April 30, 2010
    Date of Patent: November 5, 2013
    Assignee: Honeywell International Inc.
    Inventors: Alain Lombard, Michel Thirion, Nicolas Serres
  • Publication number: 20130223974
    Abstract: A gas turbine engine includes a shaft and a turbine configured to drive the shaft. The turbine has at least one stage comprising a plurality of turbine vanes interspersed with a plurality of turbine blades. The plurality of vanes includes at least one variable vane movable between a closed position to reduce air flow and an open position to increase air flow. Movement of the at least one variable vane is controlled based on an engine limiting condition.
    Type: Application
    Filed: February 28, 2012
    Publication date: August 29, 2013
    Inventors: Frederick M. Schwarz, Daniel Bernard Kupratis
  • Patent number: 8435000
    Abstract: A variable vane actuation system is disclosed herein. The variable vane actuation system includes a ring member disposed for pivoting movement about a centerline axis. The ring member is engaged with a plurality of vanes in a turbine engine such that the plurality of vanes pivot in response to the pivoting movement of the ring member. The variable vane actuation system also includes a ring moving device engaged with the ring member at first and second positions spaced from one another about the centerline axis. The ring moving device is operable to apply first and second forces, respectively, at the first and second positions to pivot the ring member.
    Type: Grant
    Filed: March 7, 2008
    Date of Patent: May 7, 2013
    Assignee: Rolls-Royce Corporation
    Inventors: Albert Wong, Lucas Perez, Anthony F. Tommasone
  • Patent number: 8215902
    Abstract: A variable vane arm has a hook portion comprising a radially inner leg connected to a radially outer leg by an arcuate connection, and an actuation lever extending from the hook portion. The hook portion and actuation lever are formed from a singular piece of material.
    Type: Grant
    Filed: October 15, 2008
    Date of Patent: July 10, 2012
    Assignee: United Technologies Corporation
    Inventors: Daniel W. Major, Bernard W. Pudvah
  • Patent number: 8202043
    Abstract: Gas turbine engines and related systems involving variable vanes are provided. In this regard, a representative vane assembly for a gas turbine engine includes: a first inner diameter platform; a first outer diameter platform spaced from the first inner diameter platform; and a variable vane airfoil rotatably attached to and extending between the first inner diameter platform and the first outer diameter platform such that at least a portion of the vane airfoil extends beyond a periphery of at least one of the first inner diameter platform and the first outer diameter platform.
    Type: Grant
    Filed: October 15, 2007
    Date of Patent: June 19, 2012
    Assignee: United Technologies Corp.
    Inventor: Michael G. McCaffrey
  • Patent number: 8100639
    Abstract: An improved actuating rod end connector is connected with an actuating rod that extends from a turbocharger assembly actuator mechanism. The rod end connector has a body with an opening at one longitudinal end, and the actuator rod is disposed through the opening. An adjustment member is rotatably disposed within the body and has a threaded inside cavity in communication with the opening. The inside cavity is threadably engaged with a threaded outside surface of the actuator rod. The body includes an actuator rod opening disposed therethrough adjacent the adjustment member to receive a section of the actuator rod therein to facilitate contacting the actuator rod disposed within the body from outside of the rod end connector. An attachment opening is disposed through the body to facilitate attachment of the rod end connector with a linkage member, e.g., a linkage member connected with a movable member of the turbocharger.
    Type: Grant
    Filed: October 13, 2005
    Date of Patent: January 24, 2012
    Assignee: Honeywell International Inc.
    Inventors: Emeric Genin, Emmanuel Severin, Alexis Lavez, Frederic Gerard, Muller Philippe, Francois Grandjean
  • Patent number: 8061975
    Abstract: A bushing assembly for a turbine vane includes a bushing and a housing. The bushing includes a bore for receiving a trunnion of the vane, a first electrical contact carried on an outer surface thereof, and a first conductor extending from the first electrical contact. The first electrical contact is adapted to be connected to a heater element disposed on the vane. The housing is positioned over the bushing and rotatable relative to the bushing. The housing includes a second electrical contact disposed in contact with the first electrical contact and a second conductor extending from the second electrical contact for connection to an electrical power source.
    Type: Grant
    Filed: August 31, 2007
    Date of Patent: November 22, 2011
    Assignee: General Electric Company
    Inventors: Brian Michael Davis, Billy T. Wood, Kent Gerhard Huber, Louis Bruno Lorenzi
  • Patent number: 8007229
    Abstract: A ring vane nozzle for a gas turbine engine according to an exemplary aspect of the present disclosure includes a multiple of fixed turbine vanes between an inner vane ring and an outer vane ring and a multiple of rotational turbine vanes between the inner vane ring and the outer vane ring, each of the rotational turbine vanes rotatable about an axis of rotation.
    Type: Grant
    Filed: May 11, 2010
    Date of Patent: August 30, 2011
    Assignee: United Technologies Corporation
    Inventors: Michael G. McCaffrey, John R. Farris, Eric A. Hudson, George T. Suljak, Jr.
  • Patent number: 7982323
    Abstract: There is provided an apparatus 2 for generating electrical charge from a motive power source 3. The apparatus 2 comprises an alternator 3a and a worm drive assembly 4 connectable to the motive power source 3. The worm drive assembly 4 comprises a drive shaft 14 a worm gear 20; and, a worm wheel 32 configured so as to mesh with the worm gear 20 and as is further arranged so as to be operatively associated with the alternator 3a. During use, rotation of the drive shaft 14 by the motive power source 3 effects generation of electrical charge by the alternator 3a.
    Type: Grant
    Filed: December 15, 2008
    Date of Patent: July 19, 2011
    Inventor: Frank Seghezzi
  • Patent number: 7850422
    Abstract: A device is for adjusting guide blades of a gas turbine. The guide blades are each connected to an adjusting ring via an adjusting lever, so as to be able to swivel, a first end of the, or each, adjusting lever engaging with the adjusting ring, and a second end of the, or each, adjusting lever, opposite to the first end, engaging with an end of a shaft or shank of the respective guide blade. The adjusting ring is assigned a rotor of a torque motor, a stator of the torque motor concentrically surrounding the rotor of the torque motor.
    Type: Grant
    Filed: January 28, 2005
    Date of Patent: December 14, 2010
    Assignee: MTU Aero Engines GmbH
    Inventor: Hubert Herrmann
  • Patent number: 7850420
    Abstract: The present invention broadly comprises a blade for a torque converter stator including a first blade segment connected to inner and outer circumferential sections of the stator and a second blade segment, separately formed from the first blade segment, and connected to the circumferential sections. In some aspects, the blade segments are: in contact along edges, overlapped, circumferentially misaligned, at least partially folded, stamped, or cast. Configurations of the blade segments can be selected to modify performance characteristics of the stator such as torque ratio, efficiency, and capacity. In some aspects, the blade segments are in a circumferential alignment, and the stator includes an alignment element operatively arranged to control the circumferential alignment, for example, in response to pressure from fluid in the stator upon the blade. In some aspects, the stator includes axial halves, separately formed and fixedly connected and the blade segments are connected to respective halves.
    Type: Grant
    Filed: March 23, 2007
    Date of Patent: December 14, 2010
    Assignee: Schaeffler Technologies GmbH & Co. KG
    Inventors: William Brees, Christopher Shamie, Aliihsan Karamavruc
  • Patent number: 7828518
    Abstract: A securing arrangement 32 for securing an actuating lever 20 to a spindle 14, for example a spindle 14 of a variable inlet guide vane 10 in a gas turbine engine, comprises a fastening formation 38 rotatably co-operable, in use, with a corresponding fastening formation 30 on the spindle 14. The securing arrangement 32 is rotatable relative to the spindle 14 to a securing position in which the respective fastening formations 30, 38 co-operate so that the securing arrangement 32 secures the actuating lever 20 to the spindle 14. The securing arrangement 32 includes anti-rotation means 42, preferably in the form of anti-rotation tabs 44, for preventing rotation of the securing arrangement 32 from the securing position.
    Type: Grant
    Filed: August 5, 2008
    Date of Patent: November 9, 2010
    Assignee: Rolls-Royce plc
    Inventors: Dale E Evans, Ben Williams
  • Patent number: 7661925
    Abstract: A variable-setting stator blade guidance device of an axial turbomachine is provided. The blade includes an airfoil, a platform and a pivot mounted in the casing of the turbomachine. The device includes a bearing integrated into the platform. In particular, the device includes a bush sandwiched between the platform and the casing, and the integrated bearing is formed between the bush and the platform. In particular, the bush includes a cylindrical surface portion on the side of the platform cooperating with a matching cylindrical surface portion on the platform to form the integrated bearing.
    Type: Grant
    Filed: October 13, 2006
    Date of Patent: February 16, 2010
    Assignee: SNECMA
    Inventors: Claude Robert Louis Lejars, Thierry Jean Maurice Niclot, Didier Raymond Charles Riby, Richard Staessen
  • Patent number: 7614846
    Abstract: The invention relates to a ceramic-based bushing for mounting in a turbomachine casing to provide a smooth bearing for a pivot of a variable-pitch vane. The bushing is constituted by a metal jacket and a ceramic ring secured to the inside wall of said jacket by brazing. The invention also provides a turbomachine compressor having variable-pitch stator vanes with pivots mounted in the casing by means of such bushings.
    Type: Grant
    Filed: April 4, 2005
    Date of Patent: November 10, 2009
    Assignee: Snecma
    Inventors: Christelle Foucher, Claude Robert Louis Lejars, Didier Riby
  • Patent number: 7594794
    Abstract: A variable geometry inlet guide vane assembly that reduces stress placed on downstream compressor blades in gas turbine engines. The invention circumferential leans upstream guide vanes, pushing engine core air flow radially. This allows for aerodynamic stresses on the downstream blades to be reduced. The invention overcomes the difference in movement between a unison ring and a vane arm by providing a hinge in conjunction with a spherical bearing that couples to the unison ring.
    Type: Grant
    Filed: August 24, 2006
    Date of Patent: September 29, 2009
    Assignee: United Technologies Corporation
    Inventors: Brian D. Merry, Om Parkash Sharma, Gabriel L. Suciu, William E. Alford
  • Patent number: 7549839
    Abstract: An inlet guide vane provides improved, smooth airflow and avoids separation of flow even at high incidence angles. The inlet guide vane includes a strut having opposite side surfaces that are continuously curved to provide a controlled velocity distribution at the trailing edge of the strut. The inlet guide vane further includes a flap having a leading edge aligned behind the trailing edge of the strut. Generally, the strut and the flap are designed together so that low momentum air in the gap between the strut and the flap will be energized and entrained in the boundary layer of the flap. The airflow from the gap will remain attached to the flap to improve the flow from the flap.
    Type: Grant
    Filed: October 25, 2005
    Date of Patent: June 23, 2009
    Assignee: United Technologies Corporation
    Inventors: Christian A. Carroll, James Allen Eley, Carl Brian Klinetob
  • Publication number: 20090104024
    Abstract: Disclosed is an air intake for a turbocharger for an internal combustion engine, said air intake including a series of variable position guide vanes for directing the air such that it is swirling in a rotational sense on reaching the impeller of the compressor of the turbocharger. The variable position guide vanes are made comprised of sound absorbent material such as to achieve a substantial reduction in turbocharger noise at the air intake.
    Type: Application
    Filed: May 24, 2006
    Publication date: April 23, 2009
    Applicants: Siemens Aktiengesellschaft, Napier Turbochargers Limited
    Inventor: Peter Kay
  • Patent number: 7520716
    Abstract: A vane system for a centrifugal compressor (10), comprising two rows (15, 20) of vanes (15?, 20?) installed in series inside a suction duct (14), the first row (15) of fixed vanes (15?) being suitable for homogenizing the gas flow that passes through them and sending it to the second row (20) of adjustable vanes (20?) equipped with a guiding mechanism comprising a mechanical system (30) suitable for varying the orientation of the vanes (20?).
    Type: Grant
    Filed: December 22, 2004
    Date of Patent: April 21, 2009
    Assignee: Nuovo Pignone Holding S.p.A.
    Inventors: Remo Tacconelli, Stefano Mantellassi
  • Publication number: 20090087305
    Abstract: The invention is an Exit Stay Apparatus with Intermediate Flange for Francis and propeller hydraulic turbines. The purpose of the invention is to improve the effectiveness of known Exit Stay Apparatus (U.S. Pat. No. 6,918,744, July 2005, for Hydraulic Turbine and Exit Stay Apparatus therefor) in eliminating the axial central vortex and, therefore, in increasing the efficiency and decreasing the flow pressure pulsations in draft tube cone at off optimum operating regimes. The new Exit Stay Apparatus has an intermediate flange between exit stay crown and periphery and two sets of exit stay vanes: crown exit stay vanes secured to the exit stay crown and the intermediate flange and peripheral exit stay vanes secured to the intermediate flange and following to the periphery. When installed in the turbine the peripheral exit stay vanes are secured at the periphery.
    Type: Application
    Filed: September 28, 2007
    Publication date: April 2, 2009
    Inventor: Alexander Gokhman
  • Patent number: 7491030
    Abstract: A variable inlet guide vane assembly in a turbomachine in which the vanes can vary in angle to control the flow through into the turbomachine, each guide vane having a leading edge portion and a trailing edge portion, and where the entire vane can pivot or the trailing edge portion can pivot about the leading edge portion. The leading edge and trailing edge portions each have a magnetic field generating material located within the portion of the vane or one a surface of the vane. The vanes are offset in the shroud such that the trailing edge portion of a first vane is located closer to the leading edge portion of an adjacent vane than to the trailing edge portion of the adjacent vane. An electric current is passed through at least one of the trailing edge and leading edge portions to produce a magnetic field. The magnetic field causes the trailing edge portion to move toward the leading edge portion of the adjacent vane.
    Type: Grant
    Filed: August 25, 2006
    Date of Patent: February 17, 2009
    Assignee: Florida Turbine Technologies, Inc.
    Inventors: Alex Pinera, Gabriel L Johnson
  • Patent number: 7448847
    Abstract: There is provided an adjustable vane turbine and turbine generator using the same, in which hydrodynamic properties are employed to adjust adjustable vanes automatically in response to flow condition such as the flow rate of the working fluid, thereby simplifying the system using the adjustable vanes and reducing cost. In the adjustable vane turbine, a turbine wheel is installed in a turbine housing and rotatably supported by a shaft, and a plurality of adjustable vanes are movably installed between the turbine housing and the turbine wheel, wherein each of the adjustable vanes includes an adjustable vane member having one end portion rotatably fixed to the turbine housing, a vane control element attached on one side of the adjustable vane member at a set angle, and a guide element attached on the other side of the adjustable vane member, the plurality of adjustable vanes being connected using links between neighboring vanes.
    Type: Grant
    Filed: July 1, 2005
    Date of Patent: November 11, 2008
    Assignee: Samsung Techwin Co., Ltd.
    Inventor: Chan-sun Lim
  • Patent number: 7448848
    Abstract: An attachment system for use with a variable incidence vane is disclosed. The attachment system includes a vane arm for joining a unison ring to a vane spindle. The vane arm has an arm portion and a bushing connected to the arm portion. The attachment system further has a pin for joining the vane arm to the unison ring. The pin fits within an interior bore in the bushing and is joined to the unison ring by a dual swage.
    Type: Grant
    Filed: August 2, 2005
    Date of Patent: November 11, 2008
    Assignee: United Technologies Corporation
    Inventors: Phillip Alexander, John Pickens
  • Patent number: 7438521
    Abstract: A stay ring of a hydraulic turbine has: a ring-shaped upper wall, a ring-shaped lower wall arranged below the upper wall forming a ring-shaped flow channel between the upper wall and the lower wall; and stay vanes arranged in array with spaces in a peripheral direction in the ring-shaped flow channel and rigidly secured to the upper and lower walls. The upper wall and the lower wall are inclined so as to reduce height of the ring-shaped flow channel toward outlet at least near inlet end thereof. The straightening bodies are arranged along inner surfaces of the upper wall and the lower wall at least near inlet end to reduce inclination of water flow in the stay ring.
    Type: Grant
    Filed: July 7, 2006
    Date of Patent: October 21, 2008
    Assignee: Kabushiki Kaisha Toshiba
    Inventors: Yasuyuki Enomoto, Toshiaki Suzuki, Kazuyuki Nakamura, Taizo Inagaki
  • Publication number: 20080025837
    Abstract: The present invention relates to a variable-setting stator blade guidance device of an axial turbomachine, the blade comprising an airfoil (22), a platform (23) and a pivot (24) mounted in the casing of the turbomachine. The device is characterized in that it comprises a bearing integrated into the platform. In particular, the device comprises a bush (26b) between the platform and the casing, and the integrated bearing is formed between the bush and the platform. In particular, the bush comprises a cylindrical surface portion (26b1) on the side of the platform interacting with a matching cylindrical surface portion (23b1) on the platform to form said integrated bearing.
    Type: Application
    Filed: October 13, 2006
    Publication date: January 31, 2008
    Applicant: SNECMA
    Inventors: Claude Robert Louis LEJARS, Thierry Jean Maurice Niclot, Didier Raymond Charles Riby, Richard Staessen
  • Patent number: 7234914
    Abstract: A compressor or pump employs principles of unsteady delayed stall to enhance the head increase produced by the compressor or pump. Plural airfoil-shaped lifting elements are spaced from each other in a cascade and the fluid is directed into the cascade by a device that varies a parameter of the flow relative to each lifting element in repeating cycles to cause the flow relative to each lifting element to begin to separate from the lifting element and then reattach thereto during each cycle. The cascade can comprise an axial flow impeller with plural impeller blades arranged around a hub capable of rotating on an axis. The device for varying the flow parameter can be a stator with a plurality of stator blades upstream of the impeller, or a second, counter-rotating axial flow impeller. In either case, the parameter is a flow angle at which the flow is directed to the downstream impeller.
    Type: Grant
    Filed: July 25, 2003
    Date of Patent: June 26, 2007
    Assignee: Continum Dynamics, Inc.
    Inventors: William J. Usab, Jr., Alan J. Bilanin
  • Patent number: 6918744
    Abstract: The invention is an Exit Stay Apparatus for Francis and propeller hydraulic turbines. The purpose of the invention is to eliminate the loss of turbine efficiency and strong pulsations in draft tube caused by the axial circular vortex in all turbine operating regimes other than optimum without a noticeable decrease in maximum efficiency. It can be incorporated not only into newly fabricated hydraulic turbines, but also retrofitted into existing turbines. The Exit Stay Apparatus has a crown and exit stay vanes secured to the the crown. When installed in the turbine, the exit stay crown is located immediately after the runner crown, which is truncated at the bottom by a plane perpendicular to the central axis of the turbine. The exit stay crown together with the truncated runner crown forms water passages after the runner blade crown profile exit.
    Type: Grant
    Filed: August 21, 2002
    Date of Patent: July 19, 2005
    Inventor: Alexander Gokhman
  • Publication number: 20040037698
    Abstract: The invention is an Exit Stay Apparatus for Francis and propeller hydraulic turbines. The purpose of the invention is to eliminate the loss of turbine efficiency and strong pulsations in draft tube caused by the axial circular vortex in all turbine operating regimes other than optimum without a noticeable decrease in maximum efficiency. It can be incorporated not only into newly fabricated hydraulic turbines, but also retrofitted into existing turbines. The Exit Stay Apparatus has a crown and exit stay vanes secured to the the crown. When installed in the turbine, the exit stay crown is located immediately after the runner crown, which is truncated at the bottom by a plane perpendicular to the central axis of the turbine. The exit stay crown together with the truncated runner crown forms water passages after the runner blade crown profile exit.
    Type: Application
    Filed: August 21, 2002
    Publication date: February 26, 2004
    Inventor: Alexander Gokhman
  • Patent number: 6619916
    Abstract: A method for assembling an articulated fan front frame for a gas turbine engine facilitates improving engine performance. The method includes forming a strut including a pair of sidewalls connected at a leading edge and a trailing edge, forming a flap including a first sidewall and a second sidewall connected at a leading edge and a trailing edge, and extending in radial span between a root endwall and a tip endwall, wherein each endwall extends between the first and second sidewalls, and wherein at least one of the root endwall and the tip endwall is contoured in a radial direction extending between the flap leading and trailing edges, and pivotally coupling the flap downstream from the strut such that a gap is defined between the flap and the strut.
    Type: Grant
    Filed: February 28, 2002
    Date of Patent: September 16, 2003
    Assignee: General Electric Company
    Inventors: Joseph Capozzi, Ruby Lasandra Zenon, Alan Glen Turner, Carol Vaczy Wallis, Peter Nicholas Szucs
  • Publication number: 20030161724
    Abstract: A method for assembling an articulated fan front frame for a gas turbine engine facilitates improving engine performance. The method includes forming a strut including a pair of sidewalls connected at a leading edge and a trailing edge, forming a flap including a first sidewall and a second sidewall connected at a leading edge and a trailing edge, and extending in radial span between a root endwall and a tip endwall, wherein each endwall extends between the first and second sidewalls, and wherein at least one of the root endwall and the tip endwall is contoured in a radial direction extending between the flap leading and trailing edges, and pivotally coupling the flap downstream from the strut such that a gap is defined between the flap and the strut.
    Type: Application
    Filed: February 28, 2002
    Publication date: August 28, 2003
    Inventors: Joseph Capozzi, Ruby Lasandra Zenon, Alan Glen Turner, Carol Vaczy Wallis, Peter Nicholas Szucs
  • Patent number: 6607353
    Abstract: The centrifugal compressor of the present invention is equipped with a plurality of vane groups (A, B) comprised of a plurality of vanes (16A, 16B) disposed in the peripheral direction of an impeller (12) so as to be concentric about the center of an axis of rotation (15) of the impeller, and the individual vanes (16A) belonging to vane group (A) nearest to the impeller are able to rotate. Since diffuser efficiency decreases if the intake flow volume of the impeller changes and the flow of gas is unable to easily continue from the vanes (16A) to vanes (16B), the vanes (16A) are rotated to change the inclination of the direction of a wing center line on their front edges so as to coincide with the direction of the flow of gas discharged from the impeller. As a result, diffuser efficiency is maintained at a high level even if the intake flow volume of the impeller is changed.
    Type: Grant
    Filed: July 26, 2001
    Date of Patent: August 19, 2003
    Assignee: Mitsubishi Heavy Industries, Ltd.
    Inventor: Joo Masutani
  • Publication number: 20030021677
    Abstract: The centrifugal compressor of the present invention is equipped with a plurality of vane groups (A, B) comprised of a plurality of vanes (16A, 16B) disposed in the peripheral direction of an impeller (12) so as to be concentric about the center of an axis of rotation (15) of the impeller, and the individual vanes (16A) belonging to vane group (A) nearest to the impeller are able to rotate. Since diffuser efficiency decreases if the intake flow volume of the impeller changes and the flow of gas is unable to easily continue from the vanes (16A) to vanes (16B), the vanes (16A) are rotated to change the inclination of the direction of a wing center line on their front edges so as to coincide with the direction of the flow of gas discharged from the impeller. As a result, diffuser efficiency is maintained at a high level even if the intake flow volume of the impeller is changed.
    Type: Application
    Filed: July 26, 2001
    Publication date: January 30, 2003
    Applicant: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventor: Joo Masutani
  • Patent number: 6435821
    Abstract: A vane having a trunnion portion and an airfoil portion is provided with a stress reducing undercut on the trunnion portion proximate to the transition zone defined between the trunnion portion and the airfoil portion of the vane.
    Type: Grant
    Filed: December 20, 2000
    Date of Patent: August 20, 2002
    Assignee: United Technologies Corporation
    Inventors: Matthew Nicolson, Paul Duesler
  • Patent number: 6334757
    Abstract: A water turbine comprises a runner, guide vanes formed of a plurality of vanes arranged outside the runner in a peripheral direction, each of the vanes being rotatable about a center axis thereof parallel with a rotation shaft of the runner, stay vanes formed of a plurality of vanes outside the guide vanes in a peripheral direction, and a casing covering the outside of the stay vanes, wherein sections of each vane of the guide vanes perpendicular to the center axis are displaced to the rotation direction of the runner from an upper side of the runner to a lower side, under the condition that the guide vanes are shutdown.
    Type: Grant
    Filed: October 13, 1999
    Date of Patent: January 1, 2002
    Assignee: Hitachi, Ltd.
    Inventors: Ryuichiro Iwano, Katsumasa Shinmei
  • Patent number: 6270309
    Abstract: A low drag ducted ram air turbine generator and cooling system is provided. The ducted ram air turbine generator and cooling system has reduced drag while extracting dynamic energy from the air stream during the complete range of intended flight operating regimes. A centerbody/valve tube having an aerodynamically shaped nose is slidably received in a fairing and primary structure to provide a variable inlet area. An internal nozzle control mechanism attached to the valve tube positions nozzle control doors to provide variable area nozzles directing air flow to the turbine stator and rotor blades to maintain optimum generator efficiency. An alternate embodiment includes an annular internal nozzle having interleaved panels to modulate the air flow to the turbine.
    Type: Grant
    Filed: December 14, 1999
    Date of Patent: August 7, 2001
    Assignee: Ghetzler Aero-Power Corporation
    Inventors: Richard Ghetzler, Jerome F. Wojtalik, Jr., Neils Kruse, Kendal R. Stephens, Harold Schmulenson
  • Patent number: 6179559
    Abstract: A variable camber vane for the inlet of a gas turbine engine has a pivoting trailing section behind a fixed leading section. In order to accommodate a wide range of flow conditions the trailing section is movable through a wide angle about its upstream edge. The surrounding casing profile and the radially outer edges of the vane trailing sections are matching part-spherical surfaces. As a result of the large angle of movement the trailing section is subjected to substantial turning forces. To contain the forces the curved radially outer edges of each trailing section is formed with a broad flange which tapers in the direction of the vane trailing edge, and for aerodynamic efficiency the flange is smoothly blended into the vane aerodynamic surfaces.
    Type: Grant
    Filed: June 10, 1999
    Date of Patent: January 30, 2001
    Assignee: Rolls-Royce PLC
    Inventor: Kevin J Weaver
  • Patent number: 6050775
    Abstract: A radial-flow exhaust-gas turbocharger turbine is provided with a row of adjustable guide blades which are rotatable via adjusting shafts mounted in a casing. The guide blades are each provided with sealing discs on their longitudinal sides running at right angles to the adjusting-shaft axes. The diameter of the sealing discs is a multiple of the thickness of the guide blades. The sealing discs which are located on the side remote from the adjusting shafts form bearing points for the guide blades in the casing.
    Type: Grant
    Filed: November 25, 1998
    Date of Patent: April 18, 2000
    Assignee: DaimlerChrysler AG
    Inventors: Wolfgang Erdmann, Siegfried Sumser