Removably Secured Or Mounted In Casing Patents (Class 415/189)
  • Patent number: 10337352
    Abstract: The invention relates to a method for manufacturing a turbine engine casing (1), characterized in that said method includes the steps of: manufacturing (E1) a plurality of sectors (2), at least one portion of the sectors (2) being manufactured by casting and including, on the surface thereof, fastening elements (3) produced during the casting step, assembly bands (8) being produced at the ends of the sectors (2) during the step of manufacturing the sectors (2) by casting, by means of which the sectors (2) can be assembled; and assembling (E2) the sectors (2) end-to-end such as to form a ring (5) of the casing (1). The invention also relates to a turbine engine casing (1).
    Type: Grant
    Filed: July 25, 2014
    Date of Patent: July 2, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Margaux Justine Emma Dubois, Erwan Pierre Antoine Perse, Valentine Bader, Jean-Pierre Trzebski
  • Patent number: 10329950
    Abstract: A nozzle guide vane for a gas turbine engine is disclosed herein. The nozzle guide vane includes an inner endcap, an outer endcap, and at least one airfoil that extends from the inner endcap to the outer endcap. The nozzle guide vane further includes at least one composite heat shield component adapted to shield metallic components from high temperature gasses.
    Type: Grant
    Filed: March 23, 2016
    Date of Patent: June 25, 2019
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: Ted J. Freeman, Jeffrey A. Walston, Jun Shi, Tara G. Schetzel
  • Patent number: 10323652
    Abstract: A pump intake device comprising a main body which includes a side wall section having an inner side and an outer side, an intake section extending from the outer side of the side wall section and an intake passage extending through the intake section, the intake passage having an inner surface and an entry end and an exit end with a central axis extending between the entry and exit ends, a first portion of the inner surface having one or more first guides thereon for directing fluid passing through the intake passage so that in use said fluid leaves the exit end at the first portion with an exit angle which is inclined relative to the central axis.
    Type: Grant
    Filed: August 22, 2016
    Date of Patent: June 18, 2019
    Assignee: Weir Minerals Australia Ltd.
    Inventor: Craig Ian Walker
  • Patent number: 10294816
    Abstract: A turbine exhaust case has an outer housing to be secured within a gas turbine engine and a central hub. Struts extend between the outer housing and the central hub. The struts are formed at least in part of a first material. The central hub is formed at least in part of a second material.
    Type: Grant
    Filed: November 13, 2014
    Date of Patent: May 21, 2019
    Assignees: United Technologies Corporation, GKN Aerospace Sweden AB
    Inventors: Daryl B. Mountz, Theodore W. Kapustka, Glenn Levasseur, Marcus Borg, Joakim Berglund, Anders Svahn, Johan Ockborn, Bengt Pettersson
  • Patent number: 10190427
    Abstract: A turbine nozzle box includes an annular outer ring plate, an annular nozzle unit, and an annular inner ring plate. The annular outer ring plate is operable to be disposed in a turbine such that an outer peripheral surface thereof is adjacent to an inner peripheral surface of an inner casing of the turbine. The annular nozzle unit is disposed adjacent to an inner peripheral surface of the outer ring plate. The annular inner ring plate is disposed such that an outer peripheral surface thereof is adjacent to an inner peripheral surface of the nozzle unit. The nozzle unit includes a plurality of segment blocks circumferentially installed at an arc angle. The segment blocks are disposed at an inlet end of a first-stage nozzle unit, and an outlet end of the first-stage nozzle unit is open.
    Type: Grant
    Filed: March 30, 2016
    Date of Patent: January 29, 2019
    Assignee: Doosan Heavy Industries Construction Co., Ltd
    Inventors: Dong Woo Kang, Hae Sang Jeong, Cheol Hong Kim
  • Patent number: 10180145
    Abstract: A fan salt-fog-resistant structure and a fan frame thereof. The fan salt-fog-resistant structure includes a base seat having a bearing cup and at least one flow guide body. Multiple connection bodies outward extend from the base seat. The flow guide body is disposed at a junction between the base seat and the connection bodies. The fan frame includes a main body having a first open side and a second open side and a flow passage defined therebetween. One end of the connection body is connected with the second open side. When airflow entraining moisture and salt fog flows through the junction between the base seat and the connection bodies, the flow guide body serves to guide the airflow and prevent the airflow from forming eddy, whereby the salt fog entrained by the airflow will not crystallize to form sediments at the junction between the base seat and the connection bodies.
    Type: Grant
    Filed: November 7, 2013
    Date of Patent: January 15, 2019
    Assignee: Asia Vital Components Co., Ltd.
    Inventor: Bor-Haw Chang
  • Patent number: 10125623
    Abstract: Various embodiments of the invention include turbine nozzles and systems employing such nozzles. Various particular embodiments include a turbine nozzle having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; and at least one endwall connected with the airfoil along the suction side, pressure side, trailing edge and the leading edge, the at least one endwall including an axisymmetric contour.
    Type: Grant
    Filed: February 9, 2016
    Date of Patent: November 13, 2018
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Craig Allen Bielek, Pradeep Jagannath Ghute
  • Patent number: 10047763
    Abstract: A rotor assembly for use in a turbofan engine is provided. The rotor assembly includes an annular spool including a first blade opening defined therein, a first rotor blade configured to be radially inserted through the first blade opening, and a fairing positioned on a radially outer side of the annular spool. The first rotor blade includes a blade portion and a flange portion that extends substantially perpendicularly relative to the blade portion such that the flange portion is positioned on a radially inner side of the annular spool. The fairing is configured to receive a fastener radially inserted through the flange portion and the annular spool such that the first rotor blade is secured to the annular spool.
    Type: Grant
    Filed: December 14, 2015
    Date of Patent: August 14, 2018
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Todd Alan Anderson, Nicholas Joseph Kray, Bryant Edward Walker
  • Patent number: 10036264
    Abstract: A component according to an exemplary aspect of the present disclosure includes, among other things, a shell defining an interior, a spar extending into the interior and a first flange attached to the spar. The spar is configured to pivot to change a positioning of the shell.
    Type: Grant
    Filed: June 6, 2014
    Date of Patent: July 31, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Michael G. McCaffrey, Tracy A. Propheter-Hinckley, Raymond Surace
  • Patent number: 9920655
    Abstract: A gas turbine having a guide vane assembly (2) and a securing ring (1) for axially locking the guide vane assembly in position that has a radially outer rim (1A) which is configured in a housing-side groove (3.1), a radially inner rim (1B) which is configured outside of the groove, and a slot (10) which extends from the radially outer rim to the radially inner rim, and a first flank having a radially inner rim section (12) and an undercut portion (11), the radially inner rim section forming an angle (?) of at least 50° with the radially inner rim.
    Type: Grant
    Filed: November 12, 2014
    Date of Patent: March 20, 2018
    Assignee: MTU Aero Engines AG
    Inventors: Hans Stricker, Stefan Rauscher
  • Patent number: 9863259
    Abstract: An airfoil for a gas turbine engine includes a first airfoil. A first chordal seal is located adjacent a first end of the airfoil. A second chordal seal is located adjacent a second end of the airfoil. The first chordal seal includes a first edge parallel to a first edge on the second chordal seal.
    Type: Grant
    Filed: May 11, 2015
    Date of Patent: January 9, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Mark A. Boeke, Kevin Rajchel, Mosheshe Camara-khary Blake, Vincent E. Simms
  • Patent number: 9850774
    Abstract: An assembly for a gas turbine engine, comprises a fairing assembly extending generally axially through a portion of the gas turbine engine, a first component disposed radially inward of the fairing assembly, a second component disposed axially adjacent to the first component, a flow diverter, and a finger seal. The flow diverter includes a mounting portion securing the flow diverter to the first component, and an arm extending in an axial direction from the mounting portion toward the second component. The finger seal includes a fixed end secured between the flow diverter mounting portion and the first component.
    Type: Grant
    Filed: December 16, 2013
    Date of Patent: December 26, 2017
    Assignee: United Technologies Corporation
    Inventor: Tuan David Vo
  • Patent number: 9850809
    Abstract: An inlet duct, an induction system, and a system are disclosed for directing an inlet flow into an inlet compressor for use in an internal combustion engine. An example inlet duct may include one or more relief features disposed on an inner surface of the inlet duct. The one or more relief features may be made integral with the inlet duct. The one or more relief features may be disposed to protrude into the inlet flow to cause the inlet flow to swirl before reaching the inlet compressor.
    Type: Grant
    Filed: November 12, 2013
    Date of Patent: December 26, 2017
    Assignee: Ford Global Technologies, LLC
    Inventors: Erik Henry Hermann, Randall Alan Stec, Douglas White, Jacqueline Tomlin, William C. Ronzi, Roger Khami, Robert Bruce Bonhard, Bhaskara Rao Boddakayala
  • Patent number: 9845692
    Abstract: A turbine component assembly for a gas turbine engine includes: a first component having a first coefficient of thermal expansion and including an end face; a second component including a mating surface abutting the end face; and a fastener having a second coefficient of thermal expansion different from the first coefficient of thermal expansion, the fastener including a shank engaging the second component and an enlarged head engaging a mounting slot in the first component; wherein the mating surface and the end face shaped to permit relative pivoting movement between the first and second components.
    Type: Grant
    Filed: May 5, 2015
    Date of Patent: December 19, 2017
    Assignee: General Electric Company
    Inventor: Joshua Brian Jamison
  • Patent number: 9835174
    Abstract: The present invention relates to a system and method for joining adjacent sections of a compressor diaphragm. A splitline jumper is positioned within a recessed portion of a seal ring segment of the adjacent compressor diaphragms. The splitline jumper is sized and oriented so as to prevent axial movement of the compressor diaphragms relative to each other and also to prevent rotational movement of the seal ring relative to the diaphragm.
    Type: Grant
    Filed: February 20, 2014
    Date of Patent: December 5, 2017
    Assignee: ANSALDO ENERGIA IP UK LIMITED
    Inventors: Douglas James Dietrich, Kevin Damian Carpenter
  • Patent number: 9777744
    Abstract: An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in a scalable TABLE 1, wherein the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y, and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.
    Type: Grant
    Filed: September 4, 2015
    Date of Patent: October 3, 2017
    Assignee: General Electric Company
    Inventors: Paul Griffin Deivernois, Jeremy Peter Latimer
  • Patent number: 9551224
    Abstract: The turbine includes: a shaft body supported rotatably; a plurality of turbine blade members; a casing covering the shaft body and the turbine blade row; an outer ring member that is provided on an inner periphery of the casing and includes an inner peripheral portion in which a cross-section having a uneven shape is continuous in a circumferential direction; a plurality of turbine vane members that each has a shroud fitted into the inner peripheral portion of the outer ring member and a turbine vane main body extending from the shroud to a radially inward side; and a plate member that connects at least some of the plurality of turbine vane members and covers one side of the shrouds in the axial direction, thereby sealing a shroud gap formed between the shrouds adjacent to each other in the circumferential direction.
    Type: Grant
    Filed: October 28, 2011
    Date of Patent: January 24, 2017
    Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.
    Inventors: Tomoyuki Onishi, Yuichiro Waki, Shoki Yamashita, Takaaki Matsuo, Asaharu Matsuo
  • Patent number: 9534500
    Abstract: A seal arrangement for segmented turbine components comprises a sealing strip and a resilient cord element compressed against the strip to provide positive loading of the strip against the segment sealing faces. The sealing strip and the resilient cord element are engaged in confronting cavities defined in the end faces of adjacent segments. The resilient cord element is commonly held by both segments in a compressed state against the sealing strip.
    Type: Grant
    Filed: April 27, 2011
    Date of Patent: January 3, 2017
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Richard Bouchard, John Pietrobon
  • Patent number: 9494039
    Abstract: The invention refers to a stationary gas turbine arrangement with at least one turbine stage that includes at least a first row of vanes being mounted at a stationary component arranged radially outside of the first row of vanes and extending radially into an annular entrance opening of the turbine stage facing a downstream end of a combustor. Further a method for performing maintenance work on a stationary gas turbine is described. The invention is characterized in that the stationary component provides for each vane a radially orientated through-hole designed and arranged for a radial insertion and removal of the vane, and each of said vanes comprises an airfoil having at its one end directed radially outwards a contour being adapted to close the through-hole airtight by a detachable fixation means.
    Type: Grant
    Filed: July 25, 2013
    Date of Patent: November 15, 2016
    Assignee: GENERAL ELECTRIC TECHNOLOGY GMBH
    Inventors: Beat Von Arx, Herbert Brandl
  • Patent number: 9388704
    Abstract: A vane array adapted to be coupled to a vane carrier within a gas turbine engine is provided comprising: a plurality of elongated airfoils comprising at least a first airfoil and a second airfoil located adjacent to one another; a U-ring; first connector structure for coupling a radially inner end section of each of the first and second airfoils to the U-ring; second connector structure for coupling a radially outer end section of each of the first and second airfoils to the vane carrier; a platform extending between the first and second airfoils; and platform connector structure for coupling the platform to one of the U-ring and the vane carrier.
    Type: Grant
    Filed: November 13, 2013
    Date of Patent: July 12, 2016
    Assignee: Siemens Energy, Inc.
    Inventors: Andrew S. Lohaus, Christian Xavier Campbell, Samuel R. Miller, Jr., John J. Marra
  • Patent number: 9382809
    Abstract: A sealing arrangement for a turbomachine for sealing a radial gap between a rotor and a stator, with a plurality of sealing segments each comprising a honeycomb element and a base body for holding the honeycomb element, and with at least one support for arranging the sealing segments on a rotor section or stator section, wherein the base bodies can be arranged on the at least one support by a radial movement and by a plastic deformation of at least one body section, a generative method for the integral production of the sealing segments, and a turbomachine are disclosed.
    Type: Grant
    Filed: January 24, 2013
    Date of Patent: July 5, 2016
    Assignee: MTU AERO ENGINES GMBH
    Inventors: Erwin Bayer, Thomas Hess, Manfred Feldmann, Sven Hiller, Peter Geiger
  • Patent number: 9366149
    Abstract: A compressor case assembly according to an exemplary embodiment of this disclosure, among other possible things, includes a case. A plurality of vane stages circumscribe an interior of the case. Each of the plurality of vane stages include a vane guide and at least one window for inserting a respective at least one vane there through. The at least one window is axially aligned with each of the vane guides The at least one window extends from an outer surface of the case into each of the vane guides.
    Type: Grant
    Filed: September 21, 2012
    Date of Patent: June 14, 2016
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Ken F. Blaney, Neil L. Tatman
  • Patent number: 9267435
    Abstract: A cam-type apparatus is included in a support link between outer and inner cases of gas turbine engines for centering the cases one to another. The cam-type apparatus is lockable to allow locking an adjusted position of the cam-type apparatus.
    Type: Grant
    Filed: September 25, 2013
    Date of Patent: February 23, 2016
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Jeffrey Bernard Heyerman, Bryan W. Olver
  • Patent number: 9162329
    Abstract: The method for removing an inner casing from a machine includes removing a top part of the outer casing, removing a top part of the inner casing, removing the bottom part of the inner casing, before removing the bottom part of the inner casing connecting the bottom part of the inner casing to the rotor, such that the bottom part of the inner casing is supported by the rotor, then rotating the rotor around the longitudinal axis to make the bottom part of the inner casing accessible.
    Type: Grant
    Filed: September 10, 2013
    Date of Patent: October 20, 2015
    Assignee: ALSTOM Technology Ltd.
    Inventors: Tobias Christoph Huber, Gerard Froidevaux, Daniel Seng, Karsten Schwarz, Ivan Rozman
  • Patent number: 9068475
    Abstract: There is disclosed a stator vane assembly comprising a support structure 14 arranged to be mounted to a mounting structure 16, a stator vane 12 radially extending from the support structure 14 and a continuity member 28 coupled to the support structure 14 and arranged in use to extend between the mounting structure 16 and the support structure 14 so as to provide a substantially continuous gas-washed surface across the mounting structure 16 and the support structure 14. There is also disclosed a method of forming a stator vane assembly, the method comprising the steps of forming at least one stator vane radially extending from a support structure having a continuity member coupled thereto.
    Type: Grant
    Filed: March 15, 2012
    Date of Patent: June 30, 2015
    Assignee: ROLLS-ROYCE plc
    Inventors: Graham Littler, Ian A Hood
  • Patent number: 9045984
    Abstract: An assembly for use in a gas turbine engine includes an inner diameter (ID) shroud having a plurality of ID slots and an outer diameter (OD) shroud having a plurality of OD slots. The OD shroud is positioned radially outward from the ID shroud. A first stator airfoil extends from the ID shroud to the OD shroud. The first stator airfoil is positioned at least partially in one of the ID slots and is positioned at least partially in one of the OD slots. A first end of the first stator airfoil has one of a raised tab and an indented notch.
    Type: Grant
    Filed: May 31, 2012
    Date of Patent: June 2, 2015
    Assignee: United Technologies Corporation
    Inventors: Steven J. Feigleson, Dennis R. Tremblay
  • Publication number: 20150143819
    Abstract: Systems, methods, and devices relating to a mechanism which can be used in gas cooling devices, pneumatic motors, turbines and other pressurized gas devices. A rotatable rotor is provided along with a number of hollow conduits that radially radiate from an exit port at the center of the rotor. The pressurized gas is injected into the mechanism at the inlet port(s). The gas enters the conduits and travels from the inlet port(s) to the exit port(s). In doing so, the gas causes the rotor to rotate about its central axis while the gas cools. This results in a colder gas at the exit port(s) than at the inlet port(s).
    Type: Application
    Filed: May 28, 2013
    Publication date: May 28, 2015
    Inventors: Jeliazko Polihronov, Anthony G. Straatman
  • Patent number: 9011085
    Abstract: A Ceramic Matrix Composites (CMC) airfoil for a gas turbine engine includes at least one CMC ply which defines a suction side, an outer platform, a pressure side and an inner platform with a continuous “I”-shaped fiber geometry.
    Type: Grant
    Filed: May 26, 2011
    Date of Patent: April 21, 2015
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Ioannis Alvanos
  • Patent number: 8998573
    Abstract: A turbine flowpath apparatus for a gas turbine engine includes: a flowpath component exposed at least partially to a primary combustion gas flowpath of the engine, the flowpath component comprising low-ductility material; a metallic annular stationary structure surrounding the flowpath component, including a bearing surface which bears against the flowpath component, so as to restrain the flowpath component from axial movement in a first direction; and a spring element disposed between the flowpath component and the stationary structure which resilient urges the flowpath component in the first direction against the bearing surface.
    Type: Grant
    Filed: October 29, 2010
    Date of Patent: April 7, 2015
    Assignee: General Electric Company
    Inventors: Joseph Albers, Mark Marusko, Barry Wilson, Aaron Dziech, Christopher Johnson
  • Patent number: 8961117
    Abstract: A turbine stage of a turbine engine, the stage including a rotor wheel mounted inside a sectorized ring carried by an outer casing, the outer casing including at least a circumferential rim housed in an annular cavity to attach a downstream end of the ring sector. A bottom wall of the annular cavity of the ring sector remains radially spaced apart from the circumferential rim of the outer casing to provide a thermally insulating space between them and includes a radial positioning mechanism acting on the circumferential rim.
    Type: Grant
    Filed: November 24, 2010
    Date of Patent: February 24, 2015
    Assignee: Snecma
    Inventors: Fabrice Marcel Noel Garin, Alain Dominique Gendraud, Gilles Jeannin, Sebastien Jean Laurent Prestel
  • Patent number: 8956111
    Abstract: A rigid mechanical self-centering assembly for a component mounted relative to an opening. Variable radii cylindrical components are accommodated by virtue of variable-length, rigid, structural stays, and flexible mounts with curved faces for flush abuttal to said component, such as a motor or pump. A high efficiency assembly for electrical components is achieved by use of nonferrous materials.
    Type: Grant
    Filed: April 10, 2013
    Date of Patent: February 17, 2015
    Inventor: Lucien Eddisford
  • Patent number: 8951007
    Abstract: In the turbine housing for an exhaust gas turbocharger of a drive assembly at least one spiral channel, which can be coupled to an exhaust gas line of the drive assembly is provided A receiving chamber for a turbine wheel to which exhaust gas can be supplied is disposed upstream of the at least one spiral channel. The turbine wheel is disposed in the turbine housing so as to be rotatable about a rotational axis. A guide baffle is arranged fixed to the turbine housing in a transition region between the at least one spiral channel, the guide baffle being connected to the turbine housing by a metal-to-metal joint whereby the guide baffle is connected to the turbine housing in a particular tight manner.
    Type: Grant
    Filed: August 3, 2011
    Date of Patent: February 10, 2015
    Assignee: Daimler AG
    Inventors: Siegfried Botsch, Stephan Krätschmer, Markus Müller, Siegfried Sumser
  • Patent number: 8939425
    Abstract: A mounting device for mounting a fan includes a base board and two fixing assemblies. The fan includes two opposite boards. The base board forms four rods. Each fixing assembly includes a receiving member and an engaging member. The receiving member includes a first pole capable of extending through a corresponding one of the boards and a first block abutting against an outer surface of the board. The engaging member includes a second pole capable of extending though the other one of the boards to be engaged in the first pole, and a second block abutting against an outer surface of the other board. Each of the first and second blocks defines a fixing hole through which a corresponding one of the rods is capable of extending.
    Type: Grant
    Filed: April 17, 2012
    Date of Patent: January 27, 2015
    Assignee: ScienBiziP Consulting (Shenzhen) Co., Ltd.
    Inventor: Zheng-Heng Sun
  • Patent number: 8939718
    Abstract: A turbocharger has a rotor housing. Said rotor housing has an insertion element. Said insertion element is configured such that the same forms an over-hanging spiral together with said rotor housing.
    Type: Grant
    Filed: July 3, 2009
    Date of Patent: January 27, 2015
    Assignee: Continental Automotive GmbH
    Inventors: Hartmut Claus, Holger Fäth, Andre Kaufmann, Stefan Krauβ
  • Patent number: 8911204
    Abstract: A method for servicing a gas turbine engine includes disassembling a bearing compartment, providing access from a forward side of the gas turbine engine to a gearbox contained within said bearing compartment. The gas turbine engine provides a core flow path that extends from the forward side aftward in a core flow direction. The method includes servicing a component located within the bearing compartment. A method for servicing a gas turbine engine includes providing access from a forward side of a front center body assembly, and servicing a component located within a bearing compartment aft of the front center body assembly. The gas turbine engine includes a seal package located aft of a bearing package. A front wall is mounted to the front center body support and is removable from a front center body support to access at least one of the gearbox, the bearing package and the seal package.
    Type: Grant
    Filed: January 2, 2013
    Date of Patent: December 16, 2014
    Assignee: United Technologies Corporation
    Inventors: Todd A. Davis, Brian P. Cigal
  • Patent number: 8869525
    Abstract: The present invention relates to an exhaust-gas turbocharger (1) having a turbine housing (2) and having a manifold section (3) which is connected to the turbine housing (2), wherein the turbine housing (2) and the manifold section (3) are formed as a single-piece cast part.
    Type: Grant
    Filed: September 10, 2009
    Date of Patent: October 28, 2014
    Assignees: BorgWarner Inc., Bayerische Motoren Werke Aktiengesellschaft
    Inventors: Robert Lingenauber, Patrick Steingass, Jan Velthuis
  • Patent number: 8858165
    Abstract: A variable vane assembly for a gas turbine engine is disclosed herein. The variable vane assembly includes a vane operable to pivot about a pivot axis. The vane includes a flap portion positionable in a fluid stream for controlling a flow of fluid. The vane also includes a stem portion for mounting the flap portion. The vane also includes a button portion positioned between the flap portion and the stem portion along the pivot axis. The button portion is wider than the stem portion in at least one plane containing the pivot axis. The variable vane assembly also includes a bushing encircling the stem portion and abutting the button portion. The variable vane assembly also includes a labyrinth seal positioned between the bushing and the button portion.
    Type: Grant
    Filed: September 30, 2010
    Date of Patent: October 14, 2014
    Assignee: Rolls-Royce Corporation
    Inventors: Brian Peck, Burke Snyder
  • Patent number: 8784051
    Abstract: The strut is for use in a gas turbine engine has body, typically having an airfoil shape, having a leading edge and a trailing edge. The leading edge has at least one gas inlet in direct fluid communication with at least one outlet located in the trailing edge through which gas may be redirected from the leading edge to the trailing edge through the strut for injection back into a wake region downstream of the strut.
    Type: Grant
    Filed: June 30, 2008
    Date of Patent: July 22, 2014
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Remo Marini, Edward Vlasic, Jonathon Peter Findlay
  • Patent number: 8764392
    Abstract: A rectifier stage of an axial turbine engine compressor is placed directly downstream of the input blower of a turbo-reactor or turboshaft engine compressor. The blade roots of the rectifier stage are housed inside the inner shroud by insertion into respective slots. The blade roots include at least one opening protruding from the slot of the shroud, so as to receive a spiral ring having at least two loops so as to prevent the blade roots from escaping from the respective slots of the inner shroud, and so as to form a connection between the blade roots.
    Type: Grant
    Filed: December 22, 2009
    Date of Patent: July 1, 2014
    Assignee: Techspace Aero S.A.
    Inventors: Enrique Penalver Castro, Yves Culot
  • Patent number: 8740556
    Abstract: A structural and aerodynamic module including two blades each extending along a longitudinal axis, in which each blade includes a leading edge, a trailing edge, a radially inner edge, and a radially outer edge, is provided. The module also includes a radially inner platform mechanically connecting the radially inner edges of the two blades, and a radially outer platform mechanically connecting the radially outer edges of the two blades such that the two blades and the radially outer and inner platforms delimit a flow stream. The two blades and the platforms are made from a composite material and the two blades are fixed on the radially outer and inner platforms using screw-nut assemblies.
    Type: Grant
    Filed: February 22, 2011
    Date of Patent: June 3, 2014
    Assignee: SNECMA
    Inventors: Thierry Georges Paul Papin, Alain Raffy, Dominique Raulin
  • Publication number: 20140093363
    Abstract: An assembly includes a plurality of vanes, a forward liner segment, and an aft liner segment. The forward liner segment and the aft liner segment are mounted to the plurality of vanes and each segment comprises an arc of less than 360° in length.
    Type: Application
    Filed: October 22, 2012
    Publication date: April 3, 2014
    Applicant: United Technologies Corporation
    Inventor: United Technologies Corporation
  • Patent number: 8684683
    Abstract: A turbine nozzle attachment assembly includes an outer turbine component (a shroud or a turbine shell) formed with a circumferential groove open in a forward-facing axial direction; a nozzle segment including a vane extending between inner and outer bands, the outer band provided with an upstanding annular hook formed with a hook element extending in an aft-facing axial direction and received in the circumferential groove. The upstanding annular hook and hook element are formed with a circumferentially-oriented slot. An anti-rotation block is located in the circumferentially-oriented slot, and an anti-tipping plate having a circumferential width greater than a corresponding circumferential width of the circumferentially-oriented slot substantially covers a forward face of the anti-rotation block. The anti-rotation block and the anti-tipping plate are fastened directly to the outer turbine component.
    Type: Grant
    Filed: November 30, 2010
    Date of Patent: April 1, 2014
    Assignee: General Electric Company
    Inventors: Thomas James Brunt, Robert Walter Coign, Gregory Thomas Foster
  • Patent number: 8684674
    Abstract: A shroud for turbine engines. The shroud has an integrated anti-rotation device that prevents circumferential movement of the shroud during normal engine operation, and which allows for circumferential installation in split annular case designs. Since the anti-rotation device is an integral part of the shroud and/or annular split turbine case, no additional parts are necessary for assembly or disassembly. Moreover, existing annular split turbine cases can be reworked to accept the anti-rotation device and yet still be backwards compatible with original shroud designs.
    Type: Grant
    Filed: October 29, 2010
    Date of Patent: April 1, 2014
    Assignee: General Electric Company
    Inventors: George Joe-Kueng Chan, Victor Hugo Silva Correia
  • Patent number: 8662819
    Abstract: A method for preventing cracking of a turbine engine case includes the steps of disposing at least two rails upon an exterior surface of a turbine engine case; and securing a first rail to a first means for attaching at least one fan exit guide vane to the turbine engine case and securing a second rail to a second means for attaching the at least one fan exit guide vane to the turbine engine case.
    Type: Grant
    Filed: December 10, 2009
    Date of Patent: March 4, 2014
    Assignee: United Technologies Corporation
    Inventor: Gilford Beaulieu
  • Patent number: 8646744
    Abstract: A structural frame for a turbomachine, such as an intermediate frame or an exhaust frame, the frame including at least two coaxial rings, an inner ring and an outer ring, together with radial arms interconnecting the rings. At least one of these elements includes a plurality of parts that are fastened together by bolting.
    Type: Grant
    Filed: May 14, 2009
    Date of Patent: February 11, 2014
    Assignee: SNECMA
    Inventors: Thierry Francois Maurice Duchatelle, Thierry Georges Paul Papin, Dominique Raulin, Arnaud Sanchez
  • Patent number: 8632046
    Abstract: A mounting apparatus for a fan includes a bracket, two fixing members, two screws, and a shield plate. The bracket includes a fixing plate defining a vent and two first through holes adjacent to opposite ends of a top of the vent. The screws extend through the fixing members and the first through holes of the bracket, in that order, for engaging in an upper portion of the fan arranged behind the fixing plate, with the vent aligning with the fan. A top of the shield plate is rotatably connected between the fixing members. The shield plate hangs vertically by gravity to cover the vent upon a condition that the gravity of the shield plate is not overcome by airflow passing through the vent.
    Type: Grant
    Filed: August 24, 2012
    Date of Patent: January 21, 2014
    Assignee: Hon Hai Precision Industry Co., Ltd.
    Inventor: Zheng-Heng Sun
  • Publication number: 20140003926
    Abstract: A compressor for a gas turbine having a rotor rotating about an axis and a housing coaxially surrounding the rotor, thereby defining a flow channel between the rotor and the housing for a fluid to be compressed. Alternating rows of vanes and blades are arranged within the flow channel, with the vanes being mounted in the inner wall of the housing, and the blades being mounted in the outer wall of the rotor.
    Type: Application
    Filed: June 27, 2013
    Publication date: January 2, 2014
    Inventors: Tobias STEFFEN, Marc RAUCH, Mauro CORRADI, Bjoern VEITH
  • Patent number: 8616839
    Abstract: A turbine is provided and includes a turbine shell including shrouds at multiple stages thereof, and constraining elements, disposed at least at first through fourth substantially regularly spaced perimetrical locations around the turbine shell, which are configured to concentrically constrain the shrouds of the turbine shell.
    Type: Grant
    Filed: June 7, 2012
    Date of Patent: December 31, 2013
    Assignee: General Electric Company
    Inventors: Henry Grady Ballard, Jr., Fred Thomas Willett, Jr.
  • Patent number: 8591182
    Abstract: A device (10) for suspending gas channel elements, in particular for suspending guide blades or guide blade segments or gas channel segments, on a housing of a gas turbines is provided. The device comprises first plate-shaped elements (11, 12, 13, 14) and second plate-shaped elements (15, 16, 17), whereby the first plate-shaped elements (11, 12, 13, 14) and the second plate-shaped elements (15, 16, 17) are connected together by web-like elements (18) which extend in an essentially perpendicular manner in relation to the first and second elements and form a meandering or crenelated profile.
    Type: Grant
    Filed: December 15, 2004
    Date of Patent: November 26, 2013
    Assignee: MTU Aero Engines GmbH
    Inventors: Stefan Morgenstern, Rudolf Stanka
  • Patent number: 8562292
    Abstract: A steam turbine singlet nozzle airfoil with integral outer sidewall is engaged with an inner ring and an outer ring in a nozzle assembly. The interface of the outer sidewall with the outer ring may include a plurality of mechanical hooks on one or both of the upstream face and the outer radial face of the outer sidewall that engage with complimentary structures on the outer ring. The outer interface may further include low energy welds along limited distances of one or both of the upstream or downstream interface of the outer sidewall and the outer ring. An inner radial end of the singlet nozzle airfoil is pinned into position and fastened to the inner ring. Without a need for high heat welds, distortion of the airfoil and the steam flow path and the associated rework is eliminated and stage performance is improved.
    Type: Grant
    Filed: December 2, 2010
    Date of Patent: October 22, 2013
    Assignee: General Electric Company
    Inventors: Steven Sebastian Burdgick, Dominick Joseph Werther