Having Specific Vane Mounting Means Patents (Class 415/209.3)
  • Patent number: 10465541
    Abstract: A method of assembling gas turbine engine front architecture includes positioning a first shroud and a first shroud portion radially relative to one another. Multiple vanes are arranged circumferentially between the first shroud and the first shroud portion. A second shroud portion is secured to the first shroud portion about the vanes. The first and second shroud portions provide a second shroud. The vanes are mechanically isolated from the first and second shrouds.
    Type: Grant
    Filed: March 12, 2014
    Date of Patent: November 5, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Steven J. Feigleson
  • Patent number: 10337342
    Abstract: A stator assembly comprises an annular platform (1) defining a boundary of an annulus and a plurality of guide vanes (2) for arranging in a circumferential array on the annular platform (1). The platform (1) includes a circumferential array of slots each slot having, at a first end, walls converging (3) from an annulus facing side towards an opposite side of the platform and then extending parallel (4) towards a second end. One or more cooling holes (5) is arranged in a wall (3,4) of the slot. Each vane (2) includes a root portion (7) which converges in a first region (8) distal to the root end and then extends parallel towards the root end in a second region (9). The root portion (7) is configured to engage in a slot of the platform (1) with the first region (8) abutting a convergent wall portion (3) of the slot and the second region (9) spaced from a parallel wall (4) of the slot.
    Type: Grant
    Filed: September 15, 2017
    Date of Patent: July 2, 2019
    Assignee: ROLLS-ROYCE plc
    Inventor: Anthony J. Rawlinson
  • Patent number: 10253641
    Abstract: Flow path assemblies for gas turbine engines are provided. For example, a flow path assembly comprises an inner wall; a unitary outer wall; and a plurality of nozzle airfoils having an inner end radially opposite an outer end. The unitary outer wall defines a plurality of outer pockets each configured for receipt of the outer end of one of the nozzle airfoils, and the inner wall includes defines a plurality of inner pockets each configured for receipt of the inner end of one of the plurality of nozzle airfoils. A portion of each inner pocket is defined by a forward inner wall segment and an aft inner wall segment. In another embodiment, a flow path assembly comprises an inner wall defining a plurality of bayonet slots that each receive a bayonet included with each of a plurality of nozzle airfoils that are integral with a unitary outer wall.
    Type: Grant
    Filed: February 23, 2017
    Date of Patent: April 9, 2019
    Assignee: General Electric Company
    Inventors: Jason David Shapiro, Donald Brett Desander, Edward Charles Vickers
  • Patent number: 10060263
    Abstract: A gas turbine engine component is described. The gas turbine engine component includes an inner diameter edge, an outer diameter edge, a trailing edge and a leading edge. The leading edge has a positive (aft) aerodynamic sweep across substantially an entire span of the leading edge. The gas turbine engine component has a camber angle greater than 50 degrees across substantially an entire span of the component. The gas turbine engine component may have asymmetrical tangential stacking of the component in the radial direction.
    Type: Grant
    Filed: August 14, 2015
    Date of Patent: August 28, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Daniel K. Van Ness, Mark A. Stephens, Edward J. Gallagher, Joseph C. Straccia, Vikram A. Kumar
  • Patent number: 9951654
    Abstract: The present application relates to a stator blade sector configured to be fixed to a housing of an axial turbomachine, the sector having a plurality of blades with platforms juxtaposed, so as to describe an arc of a circle. At least one of the platforms comprises on its outer face a fixing screw and at least one other platform has no fixing screws, the platforms being fixed together at their adjacent edges. The application also relates to a stator or portion of stator having a housing forming a generally circular wall and blade sectors arranged along the wall. The housing includes several parts connected to each other by longitudinal flanges. Platforms with no fixing screws are located opposite the flanges.
    Type: Grant
    Filed: July 2, 2014
    Date of Patent: April 24, 2018
    Assignee: SAFRAN AERO BOOSTERS SA
    Inventor: Jean-François Cortequisse
  • Patent number: 9926943
    Abstract: Disclosed is an axial blower that comprises a substantially circular cylindrical blower pipe wherein, in the blower pipe, a blower stator is provided that includes a central construction arranged in the blower pipe and a number of guide blades being disposed downstream of the blower rotor to the effect that they are, at their proximal ends, secured to the central construction and, at their distal ends, securely mounted to the inner side of the blower pipe, whereby the guide blades and the central construction are secured relative to the blower pipe. The central construction includes a number of separate stator segments that are mutually secured to each other; and wherein each of the guide blades is configured as an integral unit along with one of the stator segments.
    Type: Grant
    Filed: July 31, 2012
    Date of Patent: March 27, 2018
    Assignee: NOVENCO A/S
    Inventors: Martin Rasmussen, Andreas Berglund
  • Patent number: 9909431
    Abstract: An adjustable blade root spring device for turbine blade fixation in turbomachinery. The device is designed to be placed in a space in a rotor disk cavity adjacent to a tip of a blade root, where the device applies a radial outward force on the turbine blade to fix the blade position in the rotor disk. The device includes a wave spring with integral end blocks which is compressed by a bolt and a coil spring. When the wave spring is compressed in length, it increases in height and makes contact with the rotor disk and the turbine blade. The force of the wave spring on the turbine blade can be adjusted via the bolt, and the coil spring provides an increased compliance range. The body of the device has an oblong cross-sectional shape, thereby preventing rotation of the device in the space between the blade and the disk.
    Type: Grant
    Filed: April 29, 2015
    Date of Patent: March 6, 2018
    Assignee: Siemens Energy, Inc.
    Inventors: Charalambos Polyzopoulos, Mohit Gupta, Robert Hudson, Erica Holden, David Myers
  • Patent number: 9896972
    Abstract: The invention relates to an external composite housing for a compressor of an axial turbomachine, the housing having a generally circular wall with a matrix and fiber reinforcement. The housing includes a circular wall with an internal surface having a continuous curve around the circumference of the wall. The wall includes flat facets that are flush with the internal curved surface of the wall. The facets are arranged in annular rows to receive annular rows of stator vanes. The facets are flat disks against which the vanes bear to optimize the orientation of the vanes, while reducing the concentrations of mechanical stresses at the platform/wall interfaces.
    Type: Grant
    Filed: April 10, 2015
    Date of Patent: February 20, 2018
    Assignee: Safran Aero Boosters SA
    Inventors: Kris Hoes, Angela Durie, Alain Derclaye
  • Patent number: 9869192
    Abstract: The present application relates to a method for assembling a stator stage of a turbomachine, the stage having an inner ring, an outer ring, and vanes extending radially between the inner ring and the outer ring. The method includes at least the following essential step: applying at least one inflatable bladder against at least one opening between a vane and one of the inner ring and the outer ring on that face of the ring which is opposite the face for application of a sealing material, so as to form one or more retention surfaces for the sealing material. The present application also relates to an assembly device designed for implementing the method.
    Type: Grant
    Filed: July 30, 2015
    Date of Patent: January 16, 2018
    Assignee: SAFRAN AERO BOOSTERS SA
    Inventor: Georges Duchaine
  • Patent number: 9869328
    Abstract: A stator vane assembly is provided. The stator vane assembly may comprise a stator vane, an outer shroud, and a spring. A first end of the stator vane may be fixed to an inner diameter (ID) surface of a vane platform. A slot may be disposed in a surface of the outer shroud, wherein a portion of the stator vane is configured to be located within the slot. In various embodiments, the stator vane may be configured to translate in a radial direction in response to a force between the stator vane and a rotor. In various embodiments, the spring may be configured to be coupled to an outer diameter (OD) surface of the vane platform, wherein the spring is configured to bias the ID surface of the vane platform toward the outer shroud.
    Type: Grant
    Filed: June 29, 2015
    Date of Patent: January 16, 2018
    Assignee: United Technologies Corporation
    Inventor: William R. Edwards
  • Patent number: 9828866
    Abstract: A nozzle assembly includes at least one stationary nozzle and an outer ring having a predefined shape. The outer ring includes at least one groove defined therein configured to receive at least a portion of the at least one stationary nozzle. The nozzle assembly also includes an attachment member coupled between the stationary nozzle and the outer ring. The attachment member has a first configuration at a first nozzle assembly operating temperature a second configuration at a second nozzle assembly operating temperature.
    Type: Grant
    Filed: October 31, 2013
    Date of Patent: November 28, 2017
    Assignee: General Electric Company
    Inventors: David Orus Fitts, David Robert Schumacher, Laurence Scott Duclos, Anand Aravindrao Kulkarni, David Bruce Knorr
  • Patent number: 9777584
    Abstract: A method of assembling a gas turbine engine comprising the steps of providing a casing having an insertion aperture in its outer surface. A guide vane is inserted through the insertion aperture. The guide vane is secured to the outer surface of the casing such that the guide vane can be serviced from an outer part of the casing.
    Type: Grant
    Filed: December 30, 2013
    Date of Patent: October 3, 2017
    Assignee: ROLLS-ROYCE PLC
    Inventor: Michel Cadieux
  • Patent number: 9709072
    Abstract: An angular diffuser sector for a turbine engine compressor is provided. The sector includes an inner shroud; an outer shroud; a vane; a casing element mounted at least in part around one of the shrouds and having an open groove facing an axial end of the corresponding shroud; a wedge-forming fitting interposed between the casing element and the corresponding shroud, the wedge presenting a first surface that contacts with a bearing surface of the axial end of the corresponding shroud, and a second surface that is inclined relative to the first surface and that contacts with a corresponding sloping surface of the groove in the casing element; and a device that exerts an axial force on the wedge so as to keep its first surface in contact with the bearing surface and its second surface in contact with the sloping surface of the groove in the casing element.
    Type: Grant
    Filed: January 11, 2013
    Date of Patent: July 18, 2017
    Assignee: SNECMA
    Inventors: Yvon Cloarec, Laurent Gilles Dezouche
  • Patent number: 9546559
    Abstract: A lock link for locking variable stage stator vanes in a compressor includes a substantially planar body portion having a slot formed on one edge and a narrow neck portion extending away from an opposite edge, the narrow neck portion adapted to seat in a corresponding slot in an adjacent lock link attached to an adjacent vane; and a profiled opening in the substantially planar body portion adapted to receive a key provided on a vane stem to prevent relative rotation between the vane and the lock link.
    Type: Grant
    Filed: October 8, 2013
    Date of Patent: January 17, 2017
    Assignee: General Electric Company
    Inventors: Harry McFarland Jarrett, Jr., Jayakrishna Velampati, Andrew John Lammas, Laurie Ann Cribley, Saurabh Deshmukh
  • Patent number: 9506361
    Abstract: A gas turbine having an annular casing with a series of circumferentially spaced openings defined therethrough; a plurality of vanes extending radially inwardly though respective casing openings, an outer end of the vanes projecting radially outwardly from the casing through the respective openings and located within the respective openings by grommets, and an inner end of the vanes being mounted to an inner portion of the casing; a flexible, segmented strap extending around the annular casing, surrounding the projecting outer ends of the vanes; and a spring radially loading the flexible strap configured to apply a tension force to the flexible strap.
    Type: Grant
    Filed: March 8, 2013
    Date of Patent: November 29, 2016
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Bruce Fielding, Nathan Tomes, Thomas Veitch
  • Patent number: 9494053
    Abstract: A gas turbine engine includes inner and outer shrouds forming an annular gas path, and a plurality of struts connecting the inner shroud to the outer shroud. Airfoil shaped shields surround the struts, and each of the shields include a main body having an upstream leading edge defining a chordal axis extending in a downstream axial direction from the leading edge toward a downstream end of the shield. A trailing edge flap is located at the downstream end of each shield, the trailing edge flap including first and second span-wise portions. The first span-wise portion is oriented to direct flow at an angle relative to the chordal axis of the main body and the second span-wise portion is oriented to direct flow in a direction that is at a different angle than the angle of first span-wise portion.
    Type: Grant
    Filed: September 23, 2013
    Date of Patent: November 15, 2016
    Assignee: siemens Aktiengesellschaft
    Inventor: John A. Orosa
  • Patent number: 9388703
    Abstract: A gas turbine engine is provided, which comprises an outlet guide vane provided downstream of a compressor; an outer casing supporting a radially outward part of the outlet guide vane; and an inner diffuser supporting a radially inward part. The outlet guide vane includes a radially inward inner flange; a projecting part projecting radially inward from the inner flange; and an engagement part protruding to one side in an axial direction of the projecting part. The inner diffuser includes a smaller-diameter part having a smaller outer diameter than the other part located upstream. The inner diffuser is provided with an engagement groove extending to one side in the axial direction from an outer peripheral surface of the smaller-diameter part or a region in the vicinity thereof. The engagement part is inserted into the engagement groove with a gap between the engagement part and groove.
    Type: Grant
    Filed: March 18, 2011
    Date of Patent: July 12, 2016
    Assignee: Kawasaki Jukogyo Kabushiki Kaisha
    Inventors: Takuya Ikeguchi, Yusuke Sakai, Koji Terauchi
  • Patent number: 9266602
    Abstract: An empennage (1.1) of a helicopter comprising a ducted counter-torque device with a multi-blade rotor (4) of rotor blades (3) and optional vertical tail fins (1.2). Flow-straightening stators (5) of stationary vanes are disposed substantially in a star configuration parallel to the rotor plane downstream from the rotor (4). A shroud (2.1) of the ducted counter-torque device is sheathed with a composite structure of an outer erosion protecting surface layer (7.1, 8.1) made of a hard plastic or a plastic composite material, and at least one succeeding layer (7.2, 8.2) of an elastomeric damping material.
    Type: Grant
    Filed: September 9, 2013
    Date of Patent: February 23, 2016
    Assignee: Airbus Helicopters Deutschland
    Inventors: Wolfgang Kreitmair-Steck, Michael Hebensperger
  • Patent number: 9222363
    Abstract: A stator angular sector for a turbine engine compressor and including: an outer shroud and an inner shroud; and at least one vane extending radially between the shrouds and connected thereto at its radial ends. At one of its axial ends the outer shroud includes a cavity opening out to the axial end and extending between a radially-inner tongue of the outer shroud to which the radially-outer end of the vane is connected and a radially-outer tongue of the outer shroud carrying a mounting mechanism for mounting the stator angular sector to a casing of the engine. An abutment-forming insert is housed at least in part in the cavity, the abutment-forming insert configured to limit radial movements of the radially-inner tongue by contact and thus to modify vibratory behavior of the radially-inner tongue.
    Type: Grant
    Filed: June 16, 2011
    Date of Patent: December 29, 2015
    Assignee: SNECMA
    Inventor: Yvon Cloarec
  • Patent number: 9145777
    Abstract: An article of manufacture has a first component configured for use with a turbomachine. The first component is configured for attachment to a second component, and reduces the possibility of attachment with an undesired third component by modification of a characteristic of the first component. This modification is matched by a complementary characteristic of the second component. The first component has a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a scalable table selected from the group consisting of TABLES 1-11. Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying by a number. 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: July 24, 2012
    Date of Patent: September 29, 2015
    Assignee: General Electric Company
    Inventors: Michael James Dutka, John Duong, Ya-Tien Chiu, Alexander David Shrum, Kelvin Rono Aaron, Christopher Edward LaMaster, San-Dar Gau, Franco Monteleone, Paul Griffin Delvernois, Matthew John McKeever, Govindarajan Rengarajan, Jeremy Peter Latimer, Marc Edward Blohm, Eric Richard Bonini, Venkata Siva Prasad Chaluvadi, Jamie Dean Lumpkin, Thomas Robbins Tipton
  • Patent number: 9097124
    Abstract: A stator vane assembly includes a vane having an inner end. In one example, the vane is aluminum. An inner shroud has an aperture receiving the inner end. A flexible material secures the inner end to the inner shroud. The material has an inner surface opposite the vane providing a seal land in one example. The inner shroud provides an arcuate inner shroud segment, which is constructed either cast aluminum or stamped sheet steel. An inner shroud segment has an arcuate wall providing multiple apertures, for example. First and second flanges are integral with and extending radially inwardly from a concave side of the wall.
    Type: Grant
    Filed: January 24, 2012
    Date of Patent: August 4, 2015
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: David P. Dube, Michael E. McMahon, Steven J. Feigleson
  • Patent number: 9068471
    Abstract: The invention relates to a clearance control system and a method for adjusting a running clearance between a rotor having rotor blades of a turbomachine, and a casing that surrounds at least sections thereof. At least one adjusting gear unit, which can be coupled to at least one casing segment allows for movement of at least one segment radially in relation to the rotational axis of the rotor. An adjusting element can be arranged around the rotor and coupled to at least one adjusting gear unit and can be moved in relation to it for actuating the adjusting gear unit, whereby axial movement and/or pivoting of the adjusting element in relation to the rotor actuates adjustment of the running clearance, with each adjusting gear unit converting an at least predominantly axial movement of the adjusting element into at least predominantly radial movement of the assigned segment of the casing.
    Type: Grant
    Filed: May 18, 2010
    Date of Patent: June 30, 2015
    Assignee: MTU AERO ENGINES GMBH
    Inventor: Hermann Klingels
  • Patent number: 9062560
    Abstract: A variable stator vane assembly for a gas turbine engine includes a variable stator vane and a non-structural fairing on the variable stator vane.
    Type: Grant
    Filed: March 13, 2012
    Date of Patent: June 23, 2015
    Assignee: United Technologies Corporation
    Inventors: Richard K. Hayford, David P. Dube
  • Patent number: 9051849
    Abstract: A stator assembly for a turbofan gas turbine engine is disclosed. The stator assembly is coupled to a shroud of the engine. The stator assembly includes an endless case fixedly coupled to the engine shroud. The case includes a forward portion, an aft portion and a central portion disposed therebetween. The case extends about an axis of the engine. The forward and aft portions of the case include rails that extend towards each other and form forward and aft pockets with the central portion respectfully. The stator assembly also includes a locking stator segment. The locking stator segment includes a shroud that includes a forward hook and a pair of aft hooks with a platform disposed therebetween. The forward and aft hooks are retained in the forward and aft pockets of the case respectfully.
    Type: Grant
    Filed: February 13, 2012
    Date of Patent: June 9, 2015
    Assignee: United Technologies Corporation
    Inventors: Mark David Ring, Jonathan J. Earl
  • Patent number: 9039364
    Abstract: A gas turbine engine includes a compressor, a combustor section, and a turbine. The turbine includes an integrated case/stator segment that is comprised of a ceramic matrix composite material.
    Type: Grant
    Filed: June 29, 2011
    Date of Patent: May 26, 2015
    Assignee: United Technologies Corporation
    Inventors: Ioannis Alvanos, Gabriel L. Suciu
  • Publication number: 20150132124
    Abstract: An inner ring of a fluid flow machine includes fixing rings and seal carriers split into at least two fixing ring segments and into at least two seal carrier segments, respectively. The fixing ring segments and the seal carrier segments are arranged with the respective end faces facing each other. A first fixing ring segment has a first ring segment shoulder and a second fixing ring segment has an offset second ring segment shoulder. A first seal carrier segment has a first carrier segment shoulder, and a second seal carrier segment has a second carrier segment shoulder, which is offset with respect to the first carrier segment shoulder. In a separation plane of the inner ring, the first carrier segment shoulder abuts the second ring segment shoulder at the end face. Also in the separation plane, the second carrier segment shoulder abuts the first ring segment shoulder at the end face.
    Type: Application
    Filed: November 10, 2014
    Publication date: May 14, 2015
    Inventors: Lothar ALBERS, Georg Zotz, Rudolf Pilzweger, Hermann Becker
  • Publication number: 20150125290
    Abstract: A core ring for a torque converter comprising: an annular body portion including an inner concave surface, an outer convex surface, an inner circumferential edge, and an outer circumferential edge; a plurality of blade tab slots for receiving a plurality of blades; and at least one positioning element including material protruding axially inward from the inner concave surface to form a tip of the positioning element for aligning a stator. A method for installing a torque converter onto a transmission is also provided.
    Type: Application
    Filed: October 23, 2014
    Publication date: May 7, 2015
    Applicants: Schaeffler Group USA, Inc., Schaeffler Technologies GmbH & Co. KG
    Inventor: Aditya Dattawadkar
  • Publication number: 20150118041
    Abstract: A nozzle assembly includes at least one stationary nozzle and an outer ring having a predefined shape. The outer ring includes at least one groove defined therein configured to receive at least a portion of the at least one stationary nozzle. The nozzle assembly also includes an attachment member coupled between the stationary nozzle and the outer ring. The attachment member has a first configuration at a first nozzle assembly operating temperature a second configuration at a second nozzle assembly operating temperature.
    Type: Application
    Filed: October 31, 2013
    Publication date: April 30, 2015
    Applicant: General Electric Company
    Inventors: David Orus Fitts, David Robert Schumacher, Laurence Scott Duclos, Anand Aravindrao Kulkarni, David Bruce Knorr
  • Publication number: 20150118040
    Abstract: A support ring for a row of vanes in an engine section of a gas turbine engine includes an annular main body portion for providing structural support for a row of vanes in the engine section, an aft hook, a forward wall, and a strong back plate. The aft hook extends from an aft side of the main body portion and is coupled to an outer engine casing for structurally supporting the support ring in the engine section. The forward wall extends generally radially outwardly from a forward side of the main body portion. The strong back plate spans between the forward wall and the aft hook and effects a reduction in dynamic displacement between the forward wall and the aft hook during operation of the engine.
    Type: Application
    Filed: October 25, 2013
    Publication date: April 30, 2015
    Inventors: Ching-Pang Lee, Mrinal Munshi, Adam C. Pela, Paul Bradley Davis, Matthew H. Lang
  • Publication number: 20150104303
    Abstract: A turbocharger for an internal combustion engine having a housing, an impeller arranged in the housing interior having an impeller shaft and being mounted in a bearing block, and an intermediate element between the impeller and the bearing block. The housing includes at least one flow channel for feeding or discharging a fluid to or from the impeller, and the intermediate element includes a wall section that delimits a least a section of at least one of the flow channels.
    Type: Application
    Filed: December 17, 2014
    Publication date: April 16, 2015
    Inventor: Jan VELTHUIS
  • Patent number: 9003812
    Abstract: A supporting structure for a gas turbine engine includes at least one annular member, and a plurality of circumferentially spaced elements that extend in a radial direction of the annular member and that are connected to the annular member. At least one of the circumferentially spaced elements has an airfoil shape in cross section. The annular member includes at least two substantially flat panel segments that are arranged side by side in a circumferential direction of the annular member. The panel segments are connected to each other in a connection region that extends along facing end parts of the two panel segments. The airfoil shaped element is connected to the annular member at the connection region. A mean camber line of the airfoil shaped element at least along a portion of its length is inclined in relation to an axial direction of the annular member, and the connection region at least along a portion of its length is inclined in relation to the axial direction of the annular member.
    Type: Grant
    Filed: May 8, 2009
    Date of Patent: April 14, 2015
    Assignee: GKN Aerospace Sweden AB
    Inventor: Roger Sjöqvist
  • Publication number: 20150098813
    Abstract: A lock link for locking variable stage stator vanes in a compressor includes a substantially planar body portion having a slot formed on one edge and a narrow neck portion extending away from an opposite edge, the narrow neck portion adapted to seat in a corresponding slot in an adjacent lock link attached to an adjacent vane; and a profiled opening in the substantially planar body portion adapted to receive a key provided on a vane stem to prevent relative rotation between the vane and the lock link.
    Type: Application
    Filed: October 8, 2013
    Publication date: April 9, 2015
    Applicant: General Electric Company
    Inventors: Harry McFarland JARRETT, JR., Jayakrishna Velampati, Andrew John Lammas, Laurie Ann Cribley, Saurabh Deshmukh
  • Publication number: 20150098812
    Abstract: An integrated strut and turbine vane nozzle (ISV) arrangement according to an embodiment, includes a single-piece interturbine duct (ITD) and a plurality of vane nozzle segments removably attached to the ITD. Vane airfoils of the vane nozzle segments in combination with trailing edge portions of the struts, form a vane nozzle integrated with the ITD.
    Type: Application
    Filed: October 8, 2013
    Publication date: April 9, 2015
    Applicant: Pratt & Whitney Canada Corp.
    Inventors: VINCENT PARADIS, CHRIS PATER
  • Patent number: 8998574
    Abstract: A vane assembly of a gas turbine engine includes a plurality of circumferentially spaced vanes extending radially between an outer case and an inner case. A spring-tensioned stator restraining strap is provided around the outer case and surrounding outer ends of the respective vanes. The outer ends of the vanes are received in corresponding openings defined in the outer case and project radially outwardly from the outer case. The spring-tensioned strap compresses the respective vanes radially and inwardly in position.
    Type: Grant
    Filed: September 1, 2011
    Date of Patent: April 7, 2015
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: David Harold Menheere, Richard Ivakitch, Andreas Eleftheriou
  • Patent number: 8998575
    Abstract: An airfoil comprises a leading edge, a trailing edge, and pressure and suction surfaces defined therebetween. An inner platform is coupled to a root section of the airfoil, with a curvilinear gusset extending along a lower surface of the inner platform, opposite the root section. An outer platform is coupled to a tip section of the airfoil, with a multi-lobed gusset extending along an upper surface of the inner platform, opposite the tip section.
    Type: Grant
    Filed: November 14, 2011
    Date of Patent: April 7, 2015
    Assignee: United Technologies Corporation
    Inventors: John P. Lucashu, Gregory E. Reinhardt, John C. Ditomasso
  • Patent number: 8992175
    Abstract: The present invention relates to a compact fan, comprising a fan wheel, in particular a radial fan wheel (1), which is fastened on a rotor of an external rotor motor (82). The fan wheel (1) is supported between a front plate (8) having an air inlet opening (9), which is central, and a motor mount (11). The front plate (8) and the motor mount (11) are connected to one another via multiple spacers (12), which are disposed around the circumference. The front plate (8) and the motor mount (11) are formed as plastic or metal spray parts. The spacers (12) are formed as plastic or metal parts entirely or partially in one piece to the front plate (8) and/or the motor mount (11).
    Type: Grant
    Filed: January 30, 2009
    Date of Patent: March 31, 2015
    Assignee: ebm-papst Mulfingen GmbH & Co. KG
    Inventors: Thomas Heli, Jürgen Schöne, Christian Haag, Alfred Korwin
  • Patent number: 8979489
    Abstract: The invention relates to a low pressure turbine (1) of a turbomachine comprising a nozzle (62) belonging to an upstream stage (20B) and a nozzle (162) belonging to a downstream stage (20C), the nozzle (62) forming segments (62a) having an external structure (66) comprising: a tab (76) bearing radially on a hook (79) fixed to the case, a tab (85) bearing radially on a reaming (87) in the case, the tabs (76, 85) delimiting an annular upstream cooling air circulation cavity (91), a contact surface (84) extending in the downstream direction from the tab (85) and lined with an abradable element (86) on the inside, the contact surface comprising a downstream end (92) bearing axially on the nozzle (162) and bearing radially on a stop (93) of the case, the contact surfaces (84) delimiting an annular downstream cooling air circulation cavity (94) communicating with cavity (91).
    Type: Grant
    Filed: November 21, 2011
    Date of Patent: March 17, 2015
    Assignee: SNECMA
    Inventors: Jean-Claude Christian Taillant, Alain Dominique Gendraud
  • Publication number: 20150064000
    Abstract: A coupling support member including a pair of divided pieces is placed in a coupling part between a vane proximal end portion of a guide vane and an attachment flange, and the pair of divided pieces are joined to the vane proximal end portion from both the sides in the vane thickness direction. A linear protrusion is formed on one of joint surfaces of the vane proximal end portion to the pair of divided pieces. A groove engaged with the linear protrusion formed in the vane proximal end portion is formed on one of respective joint surfaces of the pair of divided pieces of the coupling support member. The vane proximal end portion is held between the pair of divided pieces of the coupling support member, by the fastening force that is applied to the pair of divided pieces of the coupling support member from both the sides in the vane thickness direction. It is possible to obtain a high structural strength while contributing to a reduction in weight of a jet engine.
    Type: Application
    Filed: February 1, 2013
    Publication date: March 5, 2015
    Applicant: IHI CORPORATION
    Inventors: Hiroyuki Yagi, Tadahiro Ishigure, Takaomi Inada, Takeshi Murooka, Hideo Morita, Tatsuhito Honda
  • Patent number: 8944753
    Abstract: A turbine exhaust case comprises inner and outer annular shrouds defining therebetween an annular hot gaspath. A circumferential array of exhaust struts extends across the gaspath. The exhaust struts are mounted at one radial end thereof on a flexible strut mounting structure. The flexible strut mounting structure is radially deflectable relative to the outer and inner shrouds to accommodate thermal expansion of the exhaust struts during engine operation.
    Type: Grant
    Filed: November 9, 2011
    Date of Patent: February 3, 2015
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Richard Bouchard, Daniel Trottier, Gaetan Girard
  • Publication number: 20150030442
    Abstract: In a seal member, a turbine, and a gas turbine, a plurality of vanes includes a vane main body extending in a radial direction of an axis, an outer shroud, an inner shroud and forming a main flow path of a combustion gas between the outer shrouds and the inner shroud, and a retainer protruding from an inner surface in the radial direction of the inner shroud to the inside in the radial direction. The retainers in the vanes, which are adjacent to each other in the circumferential direction, are adjacent to each other in the circumferential direction via a third gap, and relative to one end of the seal member, the other end is positioned downstream in a direction along the axis in the combustion gas to close the third gap.
    Type: Application
    Filed: March 25, 2013
    Publication date: January 29, 2015
    Applicant: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Kunihiko Waki, Masato Araki, Kenichi Arase
  • Publication number: 20150027131
    Abstract: An axial compressor includes: a rotor as a rotational shaft; a plurality of rotor blades mounted on the rotor; a compressor casing that covers the rotor and the rotor blades; a plurality of stator vanes mounted on the compressor casing. The rotor blades and the stator vanes are each disposed in a circumferential direction of the rotational shaft to form a rotor-blade cascade and a stator-vane cascade, respectively. The rotor-blade cascade and the stator-vane cascade are arranged in plural rows, respectively, in an axial direction of the rotational shaft. The stator vane has a dovetail as a base for supporting a vane section. The compressor casing has a dovetail groove formed therein. The dovetail groove extends in the circumferential direction of the rotational shaft to receive the dovetail inserted therein to fix the stator vanes. Two or more stator vanes, the stator vanes belonging to stator-vane cascades different from each other, are fixed in the dovetail groove.
    Type: Application
    Filed: July 28, 2014
    Publication date: January 29, 2015
    Inventors: Hiroki TAKEDA, Yasuo TAKAHASHI, Chihiro MYOREN
  • Publication number: 20150003979
    Abstract: A steam turbine nozzle vane arrangement includes a first nozzle vane comprising a first radially outer end and a first radially inner end, the first nozzle vane located in a steam turbine housing and operatively coupled to the steam turbine housing proximate the first radially outer end. Also included is a second nozzle vane operatively coupled to the steam turbine housing proximate a second radially outer end, the second nozzle vane located adjacent the first nozzle vane in a circumferentially aligned turbine stage. Further included is a first cover located proximate the first radially inner end and having a first hole. Yet further included is a second cover located proximate a second radially inner end of the second nozzle vane and having a second hole. Also included is a pin disposed within the first and second hole, the pin configured to fixedly couple the first and second nozzle vanes.
    Type: Application
    Filed: July 1, 2013
    Publication date: January 1, 2015
    Inventor: Fred Thomas Willett, JR.
  • Patent number: 8920112
    Abstract: A stator subassembly includes an array of circumferentially arranged stator vanes. A damper spring is provided between the array and an outer case, which supports the array. The damper spring is configured to bias the array radially inwardly from the outer case.
    Type: Grant
    Filed: January 5, 2012
    Date of Patent: December 30, 2014
    Assignee: United Technologies Corporation
    Inventor: Mark David Ring
  • 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: 8920116
    Abstract: A wear prevention system for securing compressor airfoils within a turbine engine while reducing wear of related components may include a compressor diaphragm spring positioned in an airfoil receiving channel between a radially outer surface of a diaphragm base and a radially inner surface of the airfoil receiving channel. The spring may bias the diaphragm base and airfoil attached thereto radially inward against upstream and downstream arms formed from upstream and downstream recesses extending axially from the airfoil receiving channel in the compressor case. The compressor diaphragm spring may dampen vibration and increase service life of the diaphragm base.
    Type: Grant
    Filed: October 7, 2011
    Date of Patent: December 30, 2014
    Assignee: Siemens Energy, Inc.
    Inventors: David J. Wiebe, Adam C. Pela
  • Patent number: 8905711
    Abstract: A vane structure for a gas turbine engine according includes a multiple of CMC airfoil sections integrated between a CMC outer ring and a CMC inner ring.
    Type: Grant
    Filed: May 26, 2011
    Date of Patent: December 9, 2014
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Ioannis Alvanos, Brian D. Merry, Christopher M. Dye
  • Publication number: 20140356158
    Abstract: The gas turbine engine vane assembly has a vane having an elongated airfoil body extending to a tip and a grommet disposed around the tip. An insert having a closed loop shape with an inner surface matingly shaped to receive the outer surface of the grommet, and an outer surface matingly shaped to be snugly received in the slot. A method of mounting such a vane assembly is also disclosed.
    Type: Application
    Filed: May 28, 2013
    Publication date: December 4, 2014
    Applicant: Pratt & Whitney Canada Corp.
    Inventor: Barry BARNETT
  • Patent number: 8899914
    Abstract: A stator subassembly includes an array of circumferentially arranged stator vanes. An attachment liner secures the stator vanes to one another to provide the subassembly. A damper spring is integral with the attachment liner and is provided between the array and an outer case, which supports the array. The damper spring is configured to bias the array radially inwardly from the outer case.
    Type: Grant
    Filed: January 5, 2012
    Date of Patent: December 2, 2014
    Assignee: United Technologies Corporation
    Inventor: Mark David Ring
  • Patent number: 8888451
    Abstract: A method for producing a vane for application in a component in a gas turbine engine includes casting at least one of a vane leading edge part and a vane trailing edge part and connecting the leading edge part and the trailing edge part.
    Type: Grant
    Filed: October 11, 2007
    Date of Patent: November 18, 2014
    Assignee: Volvo Aero Corporation
    Inventors: Lisa Falk, Elin Skoglund
  • Publication number: 20140301840
    Abstract: A guide vane arrangement for a turbomachine, particularly a gas turbine, is disclosed. The guide vane arrangement includes an external shroud band, on which at least two guide vanes protrude radially inward. A pair of axial ribs spaced apart from each other in the peripheral direction and disposed between two adjoining guide vanes in the peripheral direction protrude radially outward from a circumferential surface of the external shroud band and/or axially from a radial flange of the external shroud band.
    Type: Application
    Filed: April 3, 2014
    Publication date: October 9, 2014
    Applicant: MTU Aero Engines AG
    Inventors: Manuel Hein, Markus Uecker, Rudolf Stanka