Circumferentially Spaced Nozzle Or Stator Segments Patents (Class 415/139)
  • Patent number: 10557366
    Abstract: A blade outer air seal may comprise an arcuate segment. The arcuate segment may comprise an aft wall having a first radially extending protrusion at a circumferential end of the aft wall. A first hook may extend aft from the aft wall. A first gusset may extend from the first radially extending protrusion. A radial height of the first radially extending protrusion may be greater than a radial height of a second radially extending protrusion of the aft wall.
    Type: Grant
    Filed: January 5, 2018
    Date of Patent: February 11, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Christina G Ciamarra, Brian Barainca, Thurman Carlo Dabbs
  • Patent number: 10494944
    Abstract: A guide vane assembly according to the invention comprises an inner ring, on whose radially outer surface an uptake channel runs in the peripheral direction; a plurality of bearing members, which are arranged in the uptake channel of the inner ring; a plurality of guide vanes, each of which is inserted by its radially inner end into one of the bearing members; and at least one sealing element for sealing at least one gap between the inner ring and at least one of the bearing members and/or between two bearing members. A turbomachine according to the invention comprises a guide vane assembly according to the invention. A method according to the invention serves for the installation of a guide vane assembly.
    Type: Grant
    Filed: March 23, 2018
    Date of Patent: December 3, 2019
    Assignee: MTU Aero Engines AG
    Inventor: Werner Humhauser
  • Patent number: 10494946
    Abstract: A method of making a shroud assembly by: forming a shroud frame consisting of a one-piece hook and rail assembly which includes a first rail and a second rail disposed at lateral edges and a first support and a second support connected to the first rail and the second rail, the first and second rails and the first and second supports being integrally joined to one another and defining a central aperture therebetween; joining a metallic backsheet to the shroud frame covering the central aperture; and attaching a honeycomb rubs strip to the metallic backsheet via an upper edge of the honeycomb seal structure.
    Type: Grant
    Filed: July 28, 2016
    Date of Patent: December 3, 2019
    Assignee: General Electric Company
    Inventors: Joseph C. Albers, Monty Lee Shelton, Robert Proctor, Richard Russo
  • Patent number: 10494935
    Abstract: A blade track for a gas turbine engine includes segments and joints that couple the segments together. Each segment extends part-way around a central axis of the engine and the joints couple together adjacent segments to form a full hoop.
    Type: Grant
    Filed: April 8, 2016
    Date of Patent: December 3, 2019
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation, Rolls-Royce plc
    Inventors: Aaron D. Sippel, Daniel K. Vetters, Jun Shi, David J. Thomas, Andrew J. Eifert, Peter Broadhead
  • Patent number: 10487851
    Abstract: A guide vane assembly, with at least one guide vane row and a housing for the at least one guide vane row that extends along a circumferential direction about a central axis. The at least one guide vane row comprises multiple guide vanes that are respectively mounted at the housing in an adjustable manner by means of an adjusting appliance of the guide vane assembly. The adjusting appliance comprises at least one adjusting element for adjusting the guide vanes that is arranged at a radial distance to an outer side of the housing with respect to the central axis. A compensation device is provided, via which a radial distance of the adjusting element to the outer side of the housing is predetermined, and the different thermal expansions of the adjusting element and of the housing are at least partially compensated for the purpose of maintaining these distances.
    Type: Grant
    Filed: November 21, 2017
    Date of Patent: November 26, 2019
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Jeff Bishop
  • Patent number: 10428671
    Abstract: A gas turbine including: a wall component having a gas-facing surface bounding the main gas path; a male-female sealing attachment having a male or female part in which: the male-part includes a component having a main-body, which has first and second arms extending in a common direction and either side of a mid-line plane, wherein the arms are convexly curved in relation to the mid-line plane so as to provide a contact-portion along the length of the arm, the contact-portion being furthest from the mid-line plane; and, the female-part includes a component having a main-body, which includes first and second arms extending therefrom in a common direction and either side of a mid-line plane, wherein the first and second arms are concavely curved in relation to the mid-line plane so as to provide a contact-portion along the length of the arm, the contact portion being closest to the mid-line plane.
    Type: Grant
    Filed: July 28, 2016
    Date of Patent: October 1, 2019
    Inventor: Simon L Jones
  • Patent number: 10393026
    Abstract: This disclosure describes a wall arrangement for a gas turbine engine, comprising: an annular wall comprising a plurality of circumferential wall segments, adjacent wall segments having opposing first and second end wall portions which define a separating gap therebetween, the gap including a saddle portion which faces radially outwards and comprises a first sealing face on the first end wall portion and a second sealing face on the second end wall portion; and, a longitudinal seal member having a curved sealing surface located within the saddle portion, wherein the curved sealing surface contacts the either or both first and second sealing faces along the length of the saddle portion in use, wherein the seal member includes axially compressible segments which allow the seal member to bend longitudinally.
    Type: Grant
    Filed: February 24, 2017
    Date of Patent: August 27, 2019
    Assignee: ROLLS-ROYCE plc
    Inventor: Steven Hillier
  • Patent number: 10329937
    Abstract: A flow path component includes a platform having at least one radially aligned face. A chordal seal extends axially from the radially aligned face. The chordal seal includes a first curved face configured to prevent edge line contact under deflection conditions while the flow path component is installed in an engine.
    Type: Grant
    Filed: September 16, 2016
    Date of Patent: June 25, 2019
    Assignee: United Technologies Corporation
    Inventors: Mark A. Boeke, Jeffrey J. DeGray, Richard M. Salzillo, Jr.
  • Patent number: 10280775
    Abstract: The invention relates to a guide vane ring with at least one guide vane ring segment for a turbomachine, including a plurality of guide vanes arranged radially around an axis of rotation, an outer shroud arranged radially on the outer side of the guide vanes, and an inner shroud arranged radially on the inner side of the guide vanes, wherein the outer shroud or the inner shroud has at least one expansion joint, wherein the guide vane ring segment is formed in one piece with the guide vanes, the outer shroud, and the inner shroud and the at least one expansion joint is sealed in each case by at least one sealing device arranged in the respective expansion joint.
    Type: Grant
    Filed: January 26, 2016
    Date of Patent: May 7, 2019
    Assignee: MTU Aero Engines AG
    Inventors: Christian Liebl, Richard Scharl, Daniel Kirchner, Alexander Buck, Thomas Hess
  • Patent number: 10280778
    Abstract: An assembly for a turbine engine includes a turbine engine first component, a turbine engine second component and a seal assembly. The first component includes a groove and a groove surface. The second component includes a tongue that extends into the groove to a tongue surface. The seal assembly at least partially seals a gap between the groove surface and the tongue surface. The seal assembly includes a rope seal and a clip that attaches the rope seal to the tongue. The rope seal is arranged within the groove between the groove surface and the tongue surface.
    Type: Grant
    Filed: February 24, 2014
    Date of Patent: May 7, 2019
    Assignee: United Technologies Corporation
    Inventors: Mark J. Rogers, Timothy M. Davis, Mark Broomer, Kevin W. White, Craig McGarrah, Carson A. Roy Thill
  • Patent number: 10233776
    Abstract: A gas turbine shroud ring segment assembly (36) with an outer structural block (32A) having cooling channels (72) between inlets (60) on a front face and outlets (74, 76) on a front hanger rail (48). The outlets may be positioned on a radially inner surface (77) of the front rail for impingement and forced convection cooling of backsides of radially inner front lips (44) of adjacent shroud ring segments (30A, 30B) mounted on front and rear rails (48, 50) of the block. The outlets may enter a pocket (86) on the inner surface configured to allow coolant flow in all positions of the ring segments (32A, 32B). The cooling channel may form a main channel (72A) and tributary channels (72B, 72C). These channels may be drilled upward from the rail to the inlet. The tributaries may have offset intersections (72E, 72D) with the main channel.
    Type: Grant
    Filed: May 20, 2014
    Date of Patent: March 19, 2019
    Assignee: SIEMENS ENERGY, INC.
    Inventors: John Pula, Andrew R. Narcus
  • Patent number: 10233968
    Abstract: A rolling bearing for rotatably supporting a rotating shaft; a housing for externally covering the rolling bearing in the radial direction of the rotating shaft; a sleeve disposed inside the housing in the radial direction of the rotating shaft with a gap there between and provided so as to be incapable of being displaced relative to an outer ring in the radial direction and circumferential direction of the rotating shaft; and a damper provided between the housing and the sleeve to support the sleeve so that the sleeve can be displaced relative to the housing in the axial direction of the rotating shaft, the damper absorbing the displacement of the sleeve in the radial direction of the rotating shaft.
    Type: Grant
    Filed: June 4, 2015
    Date of Patent: March 19, 2019
    Assignee: Mitsubishi Heavy Industries Engine & Turbocharger, Ltd.
    Inventors: Byeongil An, Hiroshi Suzuki, Naomichi Shibata
  • Patent number: 10221712
    Abstract: The present disclosure is directed to a shroud assembly for a gas turbine engine that includes a first shroud segment, a second shroud segment spaced from the first shroud segment, and a third shroud segment spaced from the first shroud segment. The first and the second shroud segments define a gap therebetween, and the first and the third shroud segments define a gap therebetween. A first seal portion is positioned at least partially on the first and the third shroud segments and at least partially covers the gap defined by the first and the third shroud segments. A second seal portion is positioned at least partially on the first and the second shroud segments and at least partially covers the gap defined by the first and the second shroud segments. A third seal portion extends between and couples the first and the second seal portions.
    Type: Grant
    Filed: May 16, 2016
    Date of Patent: March 5, 2019
    Assignee: General Electric Company
    Inventors: Michael Anthony Ruthemeyer, David Alan Frey
  • Patent number: 10221723
    Abstract: The present invention relates to an assembly comprising a duct, preferably a turbine duct, and at least one segment formed of at least two rigid shells, each shell comprising at least one fixing orifice for fixing to the duct and at least one fixing element at least one boss per shell which boss is fixed to the duct and against which boss the shell rests, such that at least one orifice and one boss face one another, and that the fixing element passes through the orifice facing the boss and is fixed to the boss.
    Type: Grant
    Filed: June 3, 2013
    Date of Patent: March 5, 2019
    Assignee: GENERAL ELECTRIC TECHNOLOGY GMBH
    Inventors: Kevin Dagorn, Xavier Laurent
  • Patent number: 10196913
    Abstract: A section of a gas turbine engine according to an exemplary aspect of this disclosure includes, among other things, a vane assembly including a featherseal slot. The section further includes a featherseal at least partially received in the featherseal slot. The featherseal includes a radial portion having at least one tapered side.
    Type: Grant
    Filed: December 17, 2015
    Date of Patent: February 5, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Mark A. Boeke, Richard M. Salzillo, Jr., Kevin Rajchel, Jeffrey J. DeGray
  • Patent number: 10138734
    Abstract: A turbine engine turbine ring, in particular for a helicopter, in which vibratory behavior is reduced. The turbine ring includes an essentially cylindrical support, and one or more sectors forming a circle configured to define a segment of an air passage, each sector being fastened to the support by an attachment device, wherein the attachment device includes a hook portion belonging to the support and projecting towards the sector, and a hook portion belonging to the sector and projecting towards the support, the hook portions of the support and of the sector being configured to co-operate in order to fasten the sector to the support, the ring further includes a damper device provided within the attachment device and stressed radially between a portion of the sector and a portion of the support so as to damp relative movements between the sector and the support.
    Type: Grant
    Filed: March 13, 2014
    Date of Patent: November 27, 2018
    Assignee: SAFRAN HELICOPTER ENGINES
    Inventors: Carole Jaureguiberry, Manuel Silva
  • Patent number: 10060278
    Abstract: A guide vane (300) for a turbomachine, having a sealing device (27, 27?) at the radially inner end region of the guide vane (300) for sealing leakage flows (25) between the guide vane (300) and an inner ring (7) joined thereto. The sealing device (27, 27?) is movably configured relative to the guide vane (300). The sealing device (27, 27?) is positionable in at least one open or in a closed configuration for sealing the leakage flows (25). Also, a guide vane (100), as well as a turbomachine.
    Type: Grant
    Filed: November 12, 2014
    Date of Patent: August 28, 2018
    Assignee: MTU Aero Engines AG
    Inventor: Alexander Boeck
  • Patent number: 9863264
    Abstract: According to one aspect of the invention a turbine shroud engagement arrangement includes an outer shroud and an inner shroud operably connectable to the outer shroud. The outer shroud has at least one of a channel formed in and a protruding member extending from an inner radial surface thereof. The inner shroud has at least one of a protruding member extending from an outer radial surface thereof that is complementary to the at least one channel of the outer shroud or a channel formed in the outer radial surface that is complementary to the at least one protruding member of the outer shroud. The turbine shroud engagement arrangement is primarily axially slidably engagable and configured to radially support the inner shroud relative to the outer shroud.
    Type: Grant
    Filed: December 10, 2012
    Date of Patent: January 9, 2018
    Assignee: General Electric Company
    Inventors: Shruti Kulkarni, Venkata Ramana Murthy Hemadribhotla, Ajay Gangadhar Patil
  • Patent number: 9784115
    Abstract: A blade track assembly is disclosed having a variety of features. The assembly can have annular or segmented components, or a combination of the two. In one form the assembly includes blade tracks having a forward and aft edge that can be received in an opening of respective hangers. The hangers can include anti-movement features to discourage movement of a blade track. A rib can extend between hangers and in one form can be used as part of a seal assembly. Clips can be used to secure the blade track in openings of the respective hangers, as well as to discourage movement of the blade track.
    Type: Grant
    Filed: August 13, 2014
    Date of Patent: October 10, 2017
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventors: Clayton C. Smith, George F. Griffiths, Ted Joseph Freeman, William Westphal
  • Patent number: 9638198
    Abstract: A product for use with a turbocharger is disclosed. The product may include a housing with an opening extending through at least part of the housing. An outer bearing race may be positioned in the opening. An inner bearing race may be rotatably positioned in the outer bearing race. A turbine wheel may be fixed to one end of the inner bearing race. A compressor wheel may be fixed to another end of the inner bearing race. The inner bearing race may be comprised of one, two, or more race sections. The turbine wheel may be connected to the compressor wheel only through the inner bearing race or race sections.
    Type: Grant
    Filed: February 24, 2015
    Date of Patent: May 2, 2017
    Assignee: BorgWarner Inc.
    Inventor: John David Norton
  • Patent number: 9617869
    Abstract: A synchronizing assembly for a gas turbine engine has a synchronizing ring. A bumper assembly has a cradle and a bumper held within the cradle. The cradle is secured to the synchronizing ring by at least one fastener without the fastener extending through the bumper. An engine is also disclosed.
    Type: Grant
    Filed: February 12, 2014
    Date of Patent: April 11, 2017
    Assignee: United Technologies Corporation
    Inventors: Ryan Edward LeBlanc, Eugene C. Gasmen
  • Patent number: 9574454
    Abstract: The invention relates to a full arc admission steam turbine, which includes a plurality of nozzle boxes for inducing steam, and a plurality of nozzle plates for bearing nozzles, one nozzle plate corresponding to each nozzle box. The steam turbine 100 further includes a plurality of spacer plates corresponding to the plurality of nozzle boxes, wherein the spacer plate is disposed between the nozzle plate and the nozzle box, by which a flow path is formed between the plurality of nozzle boxes and the plurality of the nozzle plates through the plurality of spacer plates to achieve a full arc admission. With the solution according to embodiments of the present invention, existing partial arc steam turbine may be easily converted to be a full arc admission steam turbine. This will reduce cost of equipment upgrading. Outage due to onsite conversion may be significantly reduced.
    Type: Grant
    Filed: July 25, 2014
    Date of Patent: February 21, 2017
    Assignee: General Electric Technology GmbH
    Inventors: Timothy George Shurrock, Robert Cunningham
  • Patent number: 9127568
    Abstract: A turbine casing includes a plurality of arc-shaped segments having a flange at each side end to connect to a flange of an adjacent arc-shaped segment. The flange extends outward from an outer surface of each arc-shaped segment and extends along the outer surface in a front-to-rear direction. Each arc-shaped segment has a portion of the outer surface that is co-linear with the flange in a front-to-rear direction that does not include the flange.
    Type: Grant
    Filed: January 4, 2012
    Date of Patent: September 8, 2015
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Bradley Edwin Wilson, Matthew Stephen Casavant
  • Patent number: 9022728
    Abstract: A vane segment for a gas turbine engine includes an airfoil disposed between an outer platform and an inner platform. A slot for receiving a seal is defined within the outer platform and includes closed first and second ends and an upper surface spaced apart from a lower surface with a spacing between the upper surface and the lower surfaces that varies along a length of the slot.
    Type: Grant
    Filed: October 28, 2011
    Date of Patent: May 5, 2015
    Assignee: United Technologies Corporation
    Inventors: Alisha M. Zimmermann, Conway Chuong, Shelton O. Duelm
  • 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: 8939712
    Abstract: The invention relates to a housing for covering the ends of a row of rotor blades of an axial turbomachine compressor, the housing being provided with a sealing device between the blade tips and the housing. It comprises a shell segmented along its circumference, each segment being fixed to the housing by a series of elastomeric elements in a recess in the shape of a channel cut into the inner surface of the housing. In this way, in the event of misalignment of the rotor relative to the stator, the rotor blades coming into contact with sections of the shell will be able to move to compensate for this misalignment while reducing the frictional forces generated by contact between the blades and the shell. In the event of alignment being re-established the segments of the shell will be able to resume their initial position because of the elastic behavior of the elements.
    Type: Grant
    Filed: February 29, 2012
    Date of Patent: January 27, 2015
    Assignee: Techspace Aero S.A.
    Inventor: Jean-Francois Cortequisse
  • Patent number: 8905708
    Abstract: According to one aspect of the invention, a turbine assembly includes a first component, a second component circumferentially adjacent to the first component, wherein the first and second components each have a surface proximate a hot gas path and a first side surface of the first component to abut a second side surface of the second component. The assembly also includes a first slot formed longitudinally in the first side surface, a second slot formed longitudinally in the second side surface, wherein the first and second slots are configured to receive a sealing member, and a first groove formed in a hot side surface of the first slot, the first groove extending axially from a leading edge to a trailing edge of the first component.
    Type: Grant
    Filed: January 10, 2012
    Date of Patent: December 9, 2014
    Assignee: General Electric Company
    Inventors: David Wayne Weber, Christopher Lee Golden
  • Patent number: 8888441
    Abstract: Systems and devices for sealing portions of a rotary machine are disclosed. In one embodiment, a seal assembly element includes: a head flange; an axial neck connected to the head flange, wherein the axial neck includes a mating flange extending circumferentially from a distal end of the seal assembly element, the mating flange configured to form a multidirectional seal with a recessed portion of a complementary seal assembly element; and a set of axial seal teeth connected to the axial neck.
    Type: Grant
    Filed: August 3, 2011
    Date of Patent: November 18, 2014
    Assignee: General Electric Company
    Inventors: Daniel Edward Jordy, William Edward Adis, Bernard Arthur Couture, Jr., Dexter Andrew Young
  • Publication number: 20140328672
    Abstract: A stator component of a turbomachine is composed substantially of at least one axially extending outer ring (10) which serves as a frame of an inner ring composed of partial segments (20). The partial segments are arranged on one another such that, on the rotor side, they form a coherent circular circumferential surface in relation to the rotational movement of rotor blades (30). The individual partial segment (20) is composed of a material of uniform construction or, at least in a radial direction, of multiple partial bodies constructed from different materials, such as for example ceramic, wherein a partial segment thus formed exhibits predetermined stress and/or expansion behaviour as a function of the load ranges of the turbomachine.
    Type: Application
    Filed: July 18, 2014
    Publication date: November 6, 2014
    Inventors: Herbert BRANDL, Hans-Peter BOSSMANN
  • Publication number: 20140321984
    Abstract: Systems and devices configured for active thermal control of turbine components are disclosed. In one embodiment, a thermal control system for a turbine includes: a thermal source shaped to connect to a turbine; a set of sensors disposed about the turbine and configured to obtain operational data from the turbine; and a computing device communicatively connected to the thermal source and the set of sensors, the computing device configured to regulate a thermal input of the thermal source to the turbine based on the operational data obtained by the set of sensors.
    Type: Application
    Filed: May 29, 2013
    Publication date: October 30, 2014
    Inventors: David Ernest Welch, Wojciech Grzeszczak
  • Publication number: 20140321985
    Abstract: A method of characterising mechanical and thermal growth of a rotor tip clearance arrangement and a method of controlling such an arrangement. The characterisation method comprising constructing a finite element model and calibration cases; run the model for the calibration cases to obtain displacements; and calculating component growth therefrom. The growth is characterised and scaled for the operating conditions. The clearance is calculated in a time step from the growths and input to a control arrangement for subsequent time steps.
    Type: Application
    Filed: March 24, 2014
    Publication date: October 30, 2014
    Applicant: ROLLS-ROYCE PLC
    Inventor: Leo Vivian LEWIS
  • Publication number: 20140241854
    Abstract: A gas turbine engine includes an annular plenum defined with an outer skin and a perforated inner skin for receiving selective air flow to impinge a support case which supports shrouds of the rotor assemblies of the engine therein for active tip clearance control of the rotor assemblies. In one embodiment a bobbin-type transfer tube for supplying cooling air into the plenum, is provided between an outer case of the engine an the plenum such that the thermally induced relative movement of the outer case and the plenum is permitted.
    Type: Application
    Filed: February 25, 2013
    Publication date: August 28, 2014
    Applicant: PRATT & WHITNEY CANADA CORP.
    Inventor: Pratt & Whitney Canada Corp.
  • Patent number: 8814507
    Abstract: A triple hook ring segment including forward, midsection and aft mounting hooks for engagement with respective hangers formed on a ring segment carrier for supporting a ring segment panel, and defining a forward high pressure chamber and an aft low pressure chamber on opposing sides of the midsection mounting hook. An isolation plate is provided on the aft side of the midsection mounting hook to form an isolation chamber between the aft low pressure chamber and the ring segment panel. High pressure air is supplied to the forward chamber and flows to the isolation chamber through crossover passages in the midsection hook. The isolation chamber provides convection cooling air to an aft portion of the ring segment panel and enables a reduction of air pressure in the aft low pressure chamber to reduce leakage flow of cooling air from the ring segment.
    Type: Grant
    Filed: May 28, 2013
    Date of Patent: August 26, 2014
    Assignee: Siemens Energy, Inc.
    Inventors: Christian X Campbell, Darryl Eng, Ching-Pang Lee, Harry Patat
  • Patent number: 8784041
    Abstract: A feather seal is positioned in a mold and a shroud body is metal injection molded about a proximal end of the feather seal to provide a shroud segment with an integrated feather seal. A seal groove is provided in an opposite lateral side of the shroud body to receive the feather seal of a circumferentially adjacent shroud segment.
    Type: Grant
    Filed: August 31, 2011
    Date of Patent: July 22, 2014
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Eric Durocher, Guy Lefebvre
  • Publication number: 20140193237
    Abstract: The disclosure relates to a turbo-machine comprising a stator and a rotor arranged rotatable inside the stator as well as at least one electric heating device which is arranged on the surface of at least part of the stator for active clearance control. Besides the turbo-machine, a method for operating the active clearance control comprising electric heating devices is disclosed.
    Type: Application
    Filed: January 10, 2014
    Publication date: July 10, 2014
    Applicant: ALSTOM Technology Ltd
    Inventors: Wilhelm REITER, Stefan ROFKA, Giovanni CATALDI, Thomas Peter SOMMER
  • Patent number: 8769817
    Abstract: A seal assembly includes a body having two circumferential sides, a leading end, and a trailing end. At least one of the circumferential sides includes a first channel sidewall, a second channel sidewall, and a channel bottom wall that together define a seal channel for receiving a seal. The seal channel includes a slot that cooperates with a tab on the seal to facilitate securing the seal within the seal channel.
    Type: Grant
    Filed: October 5, 2012
    Date of Patent: July 8, 2014
    Assignee: United Technologies Corporation
    Inventors: Joseph W. Bridges, Jr., Tracy A. Propheter-Hinckley
  • Patent number: 8753073
    Abstract: A turbine shroud sealing apparatus for a gas turbine engine includes: (a) an arcuate shroud segment comprising a low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces of the segment; and (b) a first seal assembly received in at least one slot formed in the first end face, the first seal assembly comprising one or more spline seals which protrude from the first end face and which are arranged to define a continuous sealing surface around the perimeter of the first end face.
    Type: Grant
    Filed: June 23, 2010
    Date of Patent: June 17, 2014
    Assignee: General Electric Company
    Inventors: Joseph Charles Albers, Mark Willard Marusko, Barry Allan Wilson, Aaron Michael Dziech
  • Patent number: 8727709
    Abstract: A casing component (2) of a turbomachine, the casing component (2) comprising: a plurality of casing elements (14) which define a diameter of the casing component; and an actuation means operable to change the diameter of the casing component (2), wherein the actuation means changes the diameter of the casing component (2) as a function of a rotational speed of a rotatable component (4) disposed within the casing component (2).
    Type: Grant
    Filed: August 24, 2010
    Date of Patent: May 20, 2014
    Assignee: Rolls-Royce PLC
    Inventor: Crispin D. Bolgar
  • Patent number: 8727695
    Abstract: An apparatus and method is disclosed herein in which a heat-transfer fluid can be directed through a gap defined between a fillet and a chamfer. The apparatus includes a first member having a body portion and a flange portion projecting from the body portion. The flange portion extends along an endless path encircling an axis to define a receiving aperture. A fillet is defined at a junction of the body portion and an inner surface of the flange portion. The apparatus also includes a second member having a plug portion receivable in the receiving aperture. The plug portion includes a first surface operable to abut the body portion and limit movement of the plug portion into the receiving aperture. The plug portion also includes a second surface slidably engageable with the inner surface of the flange portion to guide movement of the plug portion into the receiving aperture along the axis.
    Type: Grant
    Filed: December 9, 2009
    Date of Patent: May 20, 2014
    Assignee: Rolls-Royce Corporation
    Inventor: Mark Owen Caswell
  • Patent number: 8727710
    Abstract: A feather seal assembly includes a seal having a directional passage to direct an airflow generally non-perpendicular to the seal.
    Type: Grant
    Filed: January 24, 2011
    Date of Patent: May 20, 2014
    Assignee: United Technologies Corporation
    Inventors: Tracy A. Propheter-Hinckley, Stephanie Santoro, Evan Petrakis
  • Patent number: 8684673
    Abstract: A seal structure for a gas turbine engine, the seal structure including first and second components located adjacent to each other and forming a barrier between high and low pressure zones. A seal cavity is defined in the first and second components, the seal cavity extending to either side of an elongated gap extending generally in a first direction between the first and second components. A seal member is positioned within the seal cavity and spans across the elongated gap. The seal member includes first and second side edges extending into each of the components in a second direction transverse to the first direction, and opposing longitudinal edges extending between the side edges generally parallel to the first direction. The side edges include a groove formed therein for effecting a reduction of gas flow around the seal member at the side edges.
    Type: Grant
    Filed: June 2, 2010
    Date of Patent: April 1, 2014
    Assignee: Siemens Energy, Inc.
    Inventors: Santiago Salazar, Andrew Gisch
  • 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: 8678754
    Abstract: According to one aspect of the invention, an assembly for preventing fluid flow between turbine components includes a shim and a first woven wire mesh layer that includes a first surface coupled to a first side of the shim and a second surface of the woven wire mesh layer opposite the first surface. The assembly also includes a first outer layer coupled to the second surface of the woven wire mesh layer, where the first outer layer includes a high temperature non-metallic material.
    Type: Grant
    Filed: January 24, 2011
    Date of Patent: March 25, 2014
    Assignee: General Electric Company
    Inventors: Victor John Morgan, Rebecca Evelyn Hefner, Stephen Gerard Pope
  • Patent number: 8668431
    Abstract: A method for controlling turbine blade tip seal clearance on a non-cowled gas turbine engine includes the step of directing a flow of relatively hot, pressurized air in contact with an exterior surface of the engine core casing circumscribing the turbine. The flow of relatively hot, pressurized air may be selectively directed in contact with the exterior surface of the engine core casing circumscribing the turbine when it is desired to expand the turbine shroud radially outward, such as during transient operation of the gas turbine engine.
    Type: Grant
    Filed: March 29, 2010
    Date of Patent: March 11, 2014
    Assignee: United Technologies Corporation
    Inventors: Daniel T. Rog, Ronald T. Clawson
  • Patent number: 8651799
    Abstract: A turbine vane or blade segment includes at least one airfoil extending radially outwardly from a radially inner band. A plurality of cooling passages are formed in the radially inner band in fluid communication with an internal plenum in the airfoil and exiting the inner band via a plurality of exit holes in the one of the axially-extending side edges of the inner band. The plurality of exit holes are confined to a region along the one of the axially-extending side edges where static pressure PS along the one of the substantially axially-extending side edges lies in a pressure range substantially between the stage inlet total pressure PT and a pressure that is substantially about 1.5 times the dynamic pressure range ?PD, below the stage inlet total pressure.
    Type: Grant
    Filed: June 2, 2011
    Date of Patent: February 18, 2014
    Assignee: General Electric Company
    Inventors: Evan Andrew Sewall, James William Vehr, Frederic Woodrow Roberts, Jr.
  • Patent number: 8647055
    Abstract: Shroud assembly for use in a turbine, having an outer shroud having a side proximate to flow of operative fluid of the turbine, the side having a boss and an outer shroud aperture extending through the boss. An inner shroud is located between the side of the outer shroud proximate to the flow of operative fluid and the operative fluid flow of the turbine, the inner shroud having an inner shroud aperture which is dimensioned to fit over the boss.
    Type: Grant
    Filed: April 18, 2011
    Date of Patent: February 11, 2014
    Assignee: General Electric Company
    Inventors: Gregory Thomas Foster, Robert Coign, Kevin McGovern, David Weber
  • Patent number: 8641371
    Abstract: A turbine shroud (30) of a gas turbine engine comprises a plurality of arcuate shroud segments (31) combined into an annular configuration, each shroud segment including a main body (32) defining an inner circumferential surface opposing the tips of the turbine rotor blades (11a) at a small clearance and an engagement feature including an axial wall (33a, 34a) having a prescribed circumferential length and a prescribed axial length, the turbine casing including an axial slot (51, 52) extending coaxially around the center line of the engine and configured to receive the axially extending wall of each shroud segment. A clearance defined between each circumferential end part (E) of the axial wall and an opposing inner circumferential surface of the turbine casing is greater than that defined between a circumferentially middle part (M) of the axial wall and an opposing inner circumferential surface of the turbine casing under a cool condition of the engine.
    Type: Grant
    Filed: March 26, 2010
    Date of Patent: February 4, 2014
    Assignee: Honda Motor Co., Ltd.
    Inventors: Orio Nakamura, Yoshiyuki Ura
  • Patent number: 8636466
    Abstract: A ferrule of a stator with blades of an axial turbomachine consists of at least two segments having the general form of an arc of a circle and intended to be arranged end to end, so as to form the ferrule, where each segment contains on its outside a plurality of openings arranged at regular distances along the general arc of the circle of the segment, into each of which fits the end of a blade of the stator. Each end of a segment possesses a section of which the profile essentially corresponds with that of the end of the corresponding blade when the segment is placed on the blades of the stator, such that the joint between two adjacent segments corresponds with the profile of the corresponding blade.
    Type: Grant
    Filed: December 10, 2009
    Date of Patent: January 28, 2014
    Assignee: Techspace Aero S.A.
    Inventor: Jean-Fran├žois Cortequisse
  • Patent number: 8622693
    Abstract: A blade outer air seal (BOAS) of a gas turbine engine has a segmented support ring to support a segmented turbine shroud. The support ring has a cooling air distribution system which includes a plurality of inlet cavities extending axially and inwardly to communicate with an inner cooling air passage within the respective support segments. The inlet cavities each are formed with two recesses defined in respective adjacent two support segments.
    Type: Grant
    Filed: July 20, 2010
    Date of Patent: January 7, 2014
    Assignee: Pratt & Whitney Canada Corp
    Inventors: Franco Di Paola, Bruno Chatelois
  • Patent number: 8613590
    Abstract: An article of manufacture has a body formed in part of a first metal alloy and in part of a second metal alloy, the second metal alloy having a thermal coefficient of expansion that is less than the thermal coefficient of expansion of the first metal alloy. A BOAS segment for a gas turbine engine is disclosed wherein the formation of cracks due to thermal mechanical fatigue in the body of the disclosed BOAS segment is minimized, if not eliminated, through a unique construction of the disclosed BOAS segment, whether original equipment manufacture or a repaired blade outer air seal. A method for manufacture of a BOAS segment and a method for modifying a BOAS segment are disclosed.
    Type: Grant
    Filed: July 27, 2010
    Date of Patent: December 24, 2013
    Assignee: United Technologies Corporation
    Inventors: Philip R. Belanger, Susan M. Tholen