Between Axial Flow Runner And Vane Or Vane Diaphragm Structure Patents (Class 415/173.7)
  • Patent number: 10669877
    Abstract: A gas turbine engine includes a coupling and an air seal attachment. The annular coupling extends along a centerline and has coupling teeth that extend axially rearward. The annular air seal attachment includes an air seal at an axially rearward end and air seal attachment teeth at an axially forward end that extend axially forward to interlock with the coupling teeth such that the air seal attachment teeth and the coupling teeth alternate in a circumferential direction.
    Type: Grant
    Filed: December 21, 2017
    Date of Patent: June 2, 2020
    Assignee: United Technologies Corporation
    Inventor: Brian P. Cigal
  • Patent number: 10633992
    Abstract: A rim seal located between a stator and a rotor in a gas turbine engine includes an axial overlap between platform rims of the stator and the rotor. The axial length of the platform rim of one of the stator and the rotor is accommodated within a radially aligned trench defined in the other of the stator and the rotor.
    Type: Grant
    Filed: March 8, 2017
    Date of Patent: April 28, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Remy Synnott, John Pietrobon, Franco Di Paola, Lorenzo Sanzari
  • Patent number: 10633984
    Abstract: A turbine for a turbine engine, the turbine comprising a rotor including blades the radially external periphery of which includes at least one first wiper radially extending outwards, sealing means radially extending about the blades and including a ring made of abradable material, with the radially external ends of the wipers cooperating with said ring made of abradable material so as to form a labyrinth-type seal, wherein said ring includes at least one first portion axially extending upstream of the first wiper and a second portion, different from the first portion, axially extending downstream of the first wiper, with the first portion and/or the second portion including a groove, wherein the first wiper has been inserted, with said groove being defined by the first portion and by the second portion.
    Type: Grant
    Filed: November 14, 2017
    Date of Patent: April 28, 2020
    Assignee: Safran Aircraft Engines
    Inventors: Jean-Baptiste Vincent Desforges, Gaël Frédéric Claude Cyrille Evain, Olivier Arnaud Fabien Lambert
  • Patent number: 10590798
    Abstract: A rotor includes a rotor hub, a plurality of blades mounted in a circumferentially-spaced arrangement on the rotor hub and a plurality of platform segments circumferentially arranged, respectively, between neighboring ones of the blades. The platform segments include core gas-path defining surfaces and are mounted with a freedom to circumferentially move relative to the neighboring ones of the blades.
    Type: Grant
    Filed: March 19, 2014
    Date of Patent: March 17, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Blake Luczak
  • Patent number: 10577933
    Abstract: A rotor is provided for a gas turbine engine. The rotor includes a rim that extends transverse to the web. The rim has a rotor spacer arm which defines a coating pocket and a stress relief protrusion opposite the coating pocket.
    Type: Grant
    Filed: August 14, 2014
    Date of Patent: March 3, 2020
    Assignee: United Technologies Corporation
    Inventors: Evan K Fink, Michael R DeRosa
  • Patent number: 10577936
    Abstract: Turbomachinery hardware, used in a rotor assembly and a stator assembly, including an airfoil portion including a leading edge, a trailing edge, a pressure side, and a suction side, and a platform on which the airfoil portion is disposed. The platform including a platform axis, a pressure side mateface located adjacent to the pressure side of the airfoil portion and a suction side mateface located adjacent to the suction side airfoil portion, wherein a portion of a pressure side mateface includes a first geometry, and a portion of a suction side mateface includes a second geometry. The first geometry is selected from a group consisting of: oblique to a platform axis, and a first curved portion. The second geometry is selected from a group consisting of: oblique to the platform axis and a second curved portion.
    Type: Grant
    Filed: August 21, 2014
    Date of Patent: March 3, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Scott D. Lewis, John W. Magowan
  • Patent number: 10526893
    Abstract: A turbine rotor for a gas turbine engine, includes an upstream turbine disk; a downstream turbine disk; an annular flange; a first ferrule connecting the upstream turbine disk to the annular flange; a second ferrule connecting the downstream turbine disk to the annular flange; an air flow separator device including: a first part, forming a first ring, arranged between the upstream turbine disk and the downstream turbine disk; a second part, forming a second ring, having a first portion facing the downstream turbine disk, and a second portion arranged between the first ferrule and the second ferrule; and a thermal insulation area arranged between the first part and the second part.
    Type: Grant
    Filed: May 7, 2015
    Date of Patent: January 7, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Josselin Luc Florent Sicard, Bertrand Pellaton, Hélène Marie Barret, Benoit Guillaume Silet, Anne-Flore Karine Houlet
  • Patent number: 10428661
    Abstract: A gas turbine engine includes a turbine section having static turbine vane rings and turbine wheel assemblies. The vane rings are arranged to direct combustion products toward blades included in the turbine wheel assemblies to cause the turbine wheel assemblies to rotate.
    Type: Grant
    Filed: October 26, 2016
    Date of Patent: October 1, 2019
    Assignees: Roll-Royce North American Technologies Inc., Rolls-Royce Corporation
    Inventors: David J. Thomas, Ted J. Freeman, Aaron D. Sippel, Daniel K. Vetters
  • Patent number: 10415410
    Abstract: An air seal may comprise an annular ring defined by at least a proximal surface, a distal surface, an aft side and a forward side. A channel may be disposed in the forward side of the air seal and/or the aft side of the air seal and may extend between the proximal surface and the distal surface. An additional channel extending from at least one of the forward side or the aft side may be disposed in the distal surface. The channel and the additional channel may be circumferentially in line. The channels may define a flow path for direction cooling air from a proximal side of the air seal to a distal side of the air seal.
    Type: Grant
    Filed: October 6, 2016
    Date of Patent: September 17, 2019
    Assignee: United Technologies Corporation
    Inventors: James W Taubler, Peter E Gunderson, Sunny Anant Patel, Andrew P Boursy
  • Patent number: 10400615
    Abstract: A disc of a gas turbine engine system with particular retaining ring placement and engagement implementation are provided. For example, the disc includes a disc bore including, a groove formed on an axially extending surface of the disc bore, wherein the groove includes a forward surface that extends radially into the disc bore to a groove floor that is cut into the disc bore, and wherein the groove extends axially to an aft surface that extends radially outward to at least the axially extending surface of the disc bore, and a disc web that extends radially outward from the disc bore, relative to an axis of rotation of the gas turbine engine.
    Type: Grant
    Filed: March 15, 2016
    Date of Patent: September 3, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Nicholas Waters Oren, Steven D. Porter
  • Patent number: 10385707
    Abstract: A disc of a gas turbine engine system is provided. The disc includes a disc bore including, an interstage coupling disposed on an axially extending surface at a peripheral edge of the disc bore that includes a protrusion that extends axially beyond an outer surface of the disc bore, and a groove formed on the axially extending surface of the disc bore wherein an aft surface of the groove is also a forward surface of the interstage coupling, wherein the groove includes a forward surface that extends radially into the disc bore to a groove floor that is cut into the disc bore and extends axially to the aft surface that extends radially outward to at least the axially extending surface of the disc bore, and a disc web that extends radially outward from the disc bore, relative to an axis of rotation of the gas turbine engine.
    Type: Grant
    Filed: March 15, 2016
    Date of Patent: August 20, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Steven D. Porter, Nicholas Waters Oren
  • Patent number: 10371162
    Abstract: An integrally bladed fan (IBF) rotor of a gas turbine engine. The IBF rotor includes a hub and a plurality of fan blades extending radially outwardly from the hub and integral therewith. The hub has a fan attachment flange disposed at an end of the hub on a trailing edge side thereof for mounting a booster rotor to a trailing edge side of the fan. The fan attachment flange is disposed at a radial distance from a longitudinal center axis of the integrally bladed fan rotor. The hub has an outer hub surface disposed radially inward from the radial distance of the fan attachment flange.
    Type: Grant
    Filed: October 5, 2016
    Date of Patent: August 6, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Andreas Eleftheriou, Richard Ivakitch, David Menheere
  • Patent number: 10337345
    Abstract: A sealing system for a multi-stage turbine includes multiple interstage seal segments disposed circumferentially about a turbine rotor wheel assembly and extending axially between a forward turbine stage and an aft turbine stage. Each of the interstage seal segments includes a forward end portion including an outer seal surface and an inner support face, an aft end portion, including an outer seal surface and an inner support face and a main body portion extending axially from the forward end portion to the aft end. The main body portion includes at least two support webs coupling the outer seal surfaces and the inner support faces. The outer seal surfaces are configured to be retained in a radial direction by a land support on each of a forward and aft stage turbine buckets, such that substantially all the centrifugal load from the multiple interstage seal segments is transferred to the forward and aft stage turbine buckets. A method of assembling the sealing system is disclosed.
    Type: Grant
    Filed: February 20, 2015
    Date of Patent: July 2, 2019
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Omprakash Samudrala, Fernando Jorge Casanova, Edip Sevincer, Jonathan Michael Webster
  • Patent number: 10294805
    Abstract: An integrally bladed rotor includes a rotor that has a rim that provides an inner flow surface. Circumferentially spaced apart radially extending airfoils integrally with and from the rotor and joined by an airfoil fillet. An asymmetrical trench is provided in the rim between adjacent airfoils.
    Type: Grant
    Filed: December 10, 2014
    Date of Patent: May 21, 2019
    Assignee: United Technologies Corporation
    Inventors: Christopher L. Potter, David A. Knaul, Michael Espinoza
  • Patent number: 10287905
    Abstract: One exemplary embodiment of this disclosure relates to a gas turbine engine. The engine includes a first rotor disk, a second rotor disk, and a circumferentially segmented seal. The segmented seal engages the first rotor disk and the second rotor disk. The segmented seal further includes a fore surface contacting the first disk, an aft surface contacting the second disk, and a radially outer surface. Further, (1) the aft surface and (2) one of the fore surface and the radially outer surface include perforations to allow fluid to flow through the interior of the segmented seal.
    Type: Grant
    Filed: November 11, 2014
    Date of Patent: May 14, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: James D. Hill, Gabriel L Suciu, Brian D. Merry, Ioannis Alvanos
  • Patent number: 10190416
    Abstract: A blade cascade for a turbomachine, in particular a gas turbine, including multiple identical blade groups which are situated next to each other and which each include a first individual blade (10) having a vane (12) having a blade profile and a first side wall (11), and a second individual blade (20), which differs from the first, having a vane (22) having a blade profile and a second side wall (21), the first and second side walls (11, 21) having different contourings.
    Type: Grant
    Filed: April 8, 2014
    Date of Patent: January 29, 2019
    Assignee: MTU Aero Engines AG
    Inventor: Carsten Zscherp
  • Patent number: 10156141
    Abstract: The present disclosure generally relates to a rotor assembly, and in particular relates to an improved rotor heat shield which provides an innovative configuration for securing the same to the rotor assembly. The rotor heat shield element is secured to the rotor assembly in correspondence of the groove in which it is inserted. Embodiments of the present disclosure can allow the removal of current fixation features on heat shields and blades. Furthermore, since the heat shield is no longer connected to a blade but directly to the rotor assembly, there is more freedom in selecting the number of heat shield elements to be provided to form the circumferential heat shield.
    Type: Grant
    Filed: December 4, 2015
    Date of Patent: December 18, 2018
    Assignee: ANSALDO ENERGIA SWITZERLAND AG
    Inventors: Edgar Font-Calafell, Carlos Simon-Delgado, Fabian Neubrand
  • Patent number: 10138745
    Abstract: A sealing system in a cavity under the stator of a turbomachine flow path, the cavity being located between a root of a vane of the stator and a complementary rotor device, the root including two surfaces each provided with an abradable coating, the rotor device being provided with a first and a second sealing element, arranged facing the first and the second surface respectively, the first surface and the first sealing element forming a first sealing pair and delimiting a first leakage section between them, the second surface and the second sealing element forming a second sealing pair and delimiting a second leakage section between them, one of the two pairs tending towards a minimum leakage section when the other tends towards a maximum leakage section, and vice versa.
    Type: Grant
    Filed: November 12, 2014
    Date of Patent: November 27, 2018
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventor: Christophe Scholtes
  • Patent number: 10107127
    Abstract: A gas turbine engine including an axial high pressure compressor having expansion slots in the outer rim of the rotor section. The expansion slots may be positioned between blades of a rotor segment. The fore end of the slots may have an axial seal which is coupled to the inner surface of the outer rim in the first rotor segment, and may comprise a fin configuration. The axial seal may be integral to the inner surface of the outer rim. The compressor may comprise a plurality of expansion slots and axial seals, including in a plurality of rotor segments.
    Type: Grant
    Filed: July 7, 2015
    Date of Patent: October 23, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: James Hill, Brian Merry, Gabriel Suciu
  • Patent number: 10100918
    Abstract: A device with a torque-proof first structural component and a second structural component that is connected at least in certain areas in a rotatable manner to the first structural component, wherein hydraulic fluid can be guided to lubrication points via the first structural component and the second structural component. The second structural component is embodied with blade areas which are extending substantially at a defined angle in the radial direction inside the second structural component and between which transmission areas for hydraulic fluid of the second structural component are provided, with their flow cross sections decreasing in the transmission areas in the flow direction of the hydraulic fluid.
    Type: Grant
    Filed: December 3, 2015
    Date of Patent: October 16, 2018
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Gideon Venter
  • Patent number: 10060279
    Abstract: An assembly for a gas turbine engine includes a first module, a second module interconnected with the first module, a first gas turbine component, and a seal assembly. The first gas turbine component includes a body extending generally radially between an inner mounting portion and an outer seal carrier portion. The inner mounting portion is fastened to the first module such that the first gas turbine component forms a boundary between a first annular cavity in the first module, and a second annular cavity in the second module. The seal assembly is mounted to the seal carrier portion of the first gas turbine component, and includes a flow diverter assembly having a flow diverter and a finger seal commonly fastened to a first axial side of the seal carrier portion.
    Type: Grant
    Filed: December 23, 2013
    Date of Patent: August 28, 2018
    Assignee: United Technologies Corporation
    Inventors: Tuan David Vo, Jonathan Ariel Scott
  • Patent number: 10024179
    Abstract: The invention relates to a fixed diffuser vanes assembly (10) for guiding flow through a turbomachine, comprising an internal annular platform (12) and a plurality of fixed vanes (11) which are mounted on this platform, the internal platform comprising a support plate (121) forming the base of said vanes, a radial annular partition (120) extending from the support plate toward an axis of the vanes assembly, and an internal ring (122) attached to the radial annular partition and having an internal surface on which an abradable material (123) is arranged, the vanes assembly being characterized in that the internal ring comprises at least one cut-out (1223) delimiting a tongue (1226), the tongue being bent to press against the radial annular partition (120). The invention also relates to a method of manufacturing such a vanes assembly and to a turbomachine incorporating such vanes.
    Type: Grant
    Filed: January 22, 2014
    Date of Patent: July 17, 2018
    Assignee: SNECMA
    Inventors: Sebastien Congratel, Marion Chambre, Bruno Richard, Romain Roullet
  • Patent number: 10018063
    Abstract: Anti-rotation knife edge seals and gas turbine engines including the same are provided. The anti-rotation knife-edge seal includes a first end portion having at least one knife edge, an opposing second end portion including an outside peripheral edge having a nut anti-rotation feature and an inside peripheral edge having a shaft anti-rotation feature, and an intermediate portion extending between the first end portion and the opposing second end portion. The first end portion, the opposing second end portion, and the intermediate portion form a one-piece annular seal member. A method is also provided for substantially preventing rotation of a stack nut against an adjacent rotatable component.
    Type: Grant
    Filed: June 10, 2015
    Date of Patent: July 10, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Christopher T. Anglin, Yuk-Kwan Brian Yuen
  • Patent number: 9988920
    Abstract: A fan section for a gas turbine engine is provided. The fan section having a fan hub with a slot and a fan blade with an airfoil extending from a root to a tip, the airfoil having a leading edge and the root is received in the slot, wherein a first platform is secured to the fan hub and arranged between adjacent fan blades of the fan section, the first platform having a first platform seal including a platform seal leading edge and a base is secured to a side of the first platform and a first winglet extends from the platform seal leading edge and contacts the airfoil leading edge.
    Type: Grant
    Filed: April 8, 2015
    Date of Patent: June 5, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Royce Tatton
  • Patent number: 9951638
    Abstract: A shaped rim cavity wing includes an upper surface and a lower surface. The lower surface has a geometric shape to control the separation of airflow as it passes around the lower surface to the top surface. A point of maximum extent defines the boundary between the upper surface and the lower surface, wherein the point of maximum extent defines a corner that that separates airflow from the shaped rim cavity rim and creates a flow re-circulation adjacent to the top surface of the shaped rim cavity wing.
    Type: Grant
    Filed: September 21, 2015
    Date of Patent: April 24, 2018
    Assignee: United Technologies Corporation
    Inventor: Eric A. Grover
  • Patent number: 9926790
    Abstract: A turbine shroud for a turbine of a gas turbine engine is disclosed. The turbine shroud is configured to direct products of a combustion reaction in a combustor of the gas turbine engine toward a plurality of rotatable turbine blades of the turbine to cause the plurality of turbine blades to rotate.
    Type: Grant
    Filed: July 13, 2015
    Date of Patent: March 27, 2018
    Assignee: Rolls-Royce Corporation
    Inventors: Sean E. Landwehr, Joseph P. Lamusga
  • Patent number: 9909595
    Abstract: A compressor has a plurality of stages, and each of the stages includes a wheel. Each wheel is configured to receive one or more rotor blades. The compressor includes a patch ring mounted on a first rotor wheel. The first rotor wheel has a first rabbet machined therein, and the patch ring is located on the first rabbet. A second rotor wheel is located upstream from the first rotor wheel. The second rotor wheel has a second rabbet machined therein, and the second rabbet is configured to be located opposite to the first rabbet. The second rabbet has a second fillet located between axial and radial surfaces of the second rabbet. The patch ring has a radial height greater than or equal to a radial height of the second fillet.
    Type: Grant
    Filed: July 21, 2015
    Date of Patent: March 6, 2018
    Assignee: General Electric Company
    Inventors: Andrew Joseph Colletti, Bryan Edward Williams
  • Patent number: 9879558
    Abstract: An interface within a gas turbine engine includes a multiple of segmented components, each with a segment flange with a multiple of apertures, at least one of the multiple of apertures a first slot aperture. A full ring component with a ring flange that defines a multiple ring of apertures, at least one of the multiple of ring apertures a second slot aperture, the second slot aperture transverse to the first slot aperture.
    Type: Grant
    Filed: February 5, 2014
    Date of Patent: January 30, 2018
    Assignee: United Technologies Corporation
    Inventors: Mark J Rogers, Mark Broomer, Craig R. McGarrah, Timothy M Davis, Anthony B Swift, Russell E Keene, Carson A. Roy Thill, Timothy A. Dunbar
  • Patent number: 9777593
    Abstract: A hybrid metal and composite spool includes metal rings on an outer diameter of a composite spool shell. Metal rings may include features such as annular or axial dovetail slots. Adhesive layers may be between the metal rings and composite shell which may be connected by a shrink bonded joint. The metal rings may include a single seal tooth ring with an annular radially extending seal tooth. A method for fabricating the spool may include fabricating one or more metal rings with the features therein, positioning the metal rings in place on an outer surface of an uncured composite spool shell of the spool before curing the shell, and curing the shell with the one or more metal rings positioned in place. Alternatively, rings may be heated to a temperature at least sufficient to slide rings over a cured composite shell, and allowed to cool and shrink onto shell.
    Type: Grant
    Filed: February 23, 2015
    Date of Patent: October 3, 2017
    Assignee: General Electric Company
    Inventors: Bowden Kirkpatrick, Nicholas Joseph Kray, Todd Alan Anderson, Stefaan Guido Van Nieuwenhove, Po-Ching Yeh
  • Patent number: 9771802
    Abstract: A turbomachine including a rotor having an axis and a plurality of disks positioned adjacent to each other in the axial direction, each disk including opposing axially facing surfaces and a circumferentially extending radially facing surface located between the axially facing surfaces. At least one row of blades is positioned on each of the disks, and the blades include an airfoil extending radially outward from the disk A non-segmented circumferentially continuous ring structure includes an outer rim defining a thermal barrier extending axially in overlapping relation over a portion of the radially facing surface of at least one disk, and extending to a location adjacent to a blade on the disk A compliant element is located between a radially inner circumferential portion of the ring structure and a flange structure that extends axially from an axially facing surface of the disk.
    Type: Grant
    Filed: February 25, 2014
    Date of Patent: September 26, 2017
    Assignee: SIEMENS ENERGY, INC.
    Inventors: Christopher W. Ross, Bulent Acar
  • Patent number: 9771820
    Abstract: A turbine in a gas turbine engine that includes a stator blade and a rotor blade having a seal formed in a trench cavity. The trench cavity may include an axial gap defined between opposing inboard faces of the stator blade and rotor blade. The seal may include: a stator overhang extending from the stator blade toward the rotor blade so to include an outboard edge and an inboard edge and, defined therebetween, an overhang face; a rotor outboard face extending radially inboard from a platform edge, the rotor outboard face opposing at least a portion of the overhang face across the axial gap of the trench cavity; and a first axial projection extending from the rotor outboard face toward the stator blade. The stator overhang and the first axial projection of the rotor blade may be configured so to axially overlap.
    Type: Grant
    Filed: December 30, 2014
    Date of Patent: September 26, 2017
    Assignee: General Electric Company
    Inventors: Richard William Johnson, Kevin Richard Kirtley, David Richard Johns, James William Vehr, Andrew Paul Giametta
  • Patent number: 9726033
    Abstract: A rotor wheel for a turbine engine, such as an airplane turboprop or turbojet, the rotor wheel including a rotor disk including teeth at its outer periphery defining slots for axially mounting and radially retaining blade roots. An annular lip includes an annular rim extending axially downstream from and radially towards an inside of a radial retaining mechanism formed to project axially from an upstream face of the disk, and a sealing mechanism is arranged radially inside the annular lip and upstream ends of platforms of the blades.
    Type: Grant
    Filed: November 12, 2012
    Date of Patent: August 8, 2017
    Assignee: SNECMA
    Inventors: Alain Dominique Gendraud, Fabrice Marcel Noel Garin, Romain Nicolas Lunel
  • Patent number: 9719363
    Abstract: A seal segment for a gas turbine engine includes a first axial span that extends between the first radial span and the second radial span. A second axial span extends between the first radial span and the second radial span, the first radial span, the second radial span, the first axial span and the second axial span forming a torque box.
    Type: Grant
    Filed: June 4, 2015
    Date of Patent: August 1, 2017
    Assignee: United Technologies Corporation
    Inventors: David R Pack, Julian Partyka, James D. Hill, Gabriel L Suciu, Gregory M Dolansky, Brian D Merry
  • Patent number: 9650895
    Abstract: A turbine wheel including a plurality of blades having roots engaged axially and held radially in slots in a disk alternating between teeth of the disk, in which the blades have platforms arranged circumferentially end to end and each connected to a blade root by a tang, is provided. Separator walls extend from the tangs in a circumferential direction and from upstream to downstream so as to define radially between the platforms and the teeth of the disk at least a radially inner cavity and a radially outer cavity between two adjacent tangs.
    Type: Grant
    Filed: May 28, 2014
    Date of Patent: May 16, 2017
    Assignee: SNECMA
    Inventors: Josselin Sicard, Helene Barret, Stephane Pierre Guillaume Blanchard, Youki Olivier Ito-Lardeau, Bertrand Pellaton
  • Patent number: 9624784
    Abstract: A system includes a multi-stage turbine that includes a first turbine stage having a first wheel having a plurality of first blade segments spaced circumferentially about the first wheel. The turbine also includes a second turbine stage having a second wheel having a plurality of second blade segments spaced circumferentially about the second wheel. The turbine also includes a seal assembly extending axially between the first and second turbine stages. The seal assembly includes a first coverplate coupled to the first turbine stage. The first coverplate includes a first air director. The seal assembly also includes a second coverplate coupled to the second turbine stage. The second coverplate comprises a second air director. The seal assembly also includes an interstage seal. The first coverplate, the second coverplate, or both are configured to support the interstage seal.
    Type: Grant
    Filed: July 8, 2013
    Date of Patent: April 18, 2017
    Assignee: General Electric Company
    Inventor: Matthew Troy Hafner
  • Patent number: 9617855
    Abstract: A reaction-type turbine according to the present invention is configured in that a portion of a rotary shaft module which penetrates through a side with an inlet portion of a housing has a diameter larger than the diameters of other portions. Thus, the pressurized area in which a working fluid applies pressure to a rotary shaft in the direction opposite to the working fluid flow direction increases, thus increasing force in the direction opposite to the working fluid flow direction. As a result, axial direction force applied to the rotary shaft in the working fluid flow direction may be reduced. Therefore, the reaction-type turbine of the present invention has the advantages of eliminating the necessity of installing a separate thrust bearing for supporting axial force in the working fluid flow direction.
    Type: Grant
    Filed: October 12, 2012
    Date of Patent: April 11, 2017
    Assignee: HK TURBINE CO., LTD.
    Inventors: Young Il Chang, Ki Tae Kim, Yong Sik Hah, Jung Hoon Kim
  • Patent number: 9540941
    Abstract: A seal assembly is provided for a turbine engine and includes an annular labyrinth seal holder supported on a radially inner end of vanes A plurality of radially extending labyrinth seal elements are supported on the labyrinth seal holder, and a brush seal assembly is supported to the labyrinth seal holder downstream from the labyrinth seal elements. The brush seal assembly includes a brush seal holder and a brush seal located adjacent to an axially rearward one of the rotor arms. The brush seal holder is attached to an axially facing surface of the labyrinth seal holder. A seal plate defining a detachable labyrinth seal element extends radially inward from the axially facing surface of the labyrinth seal holder to the rearward rotor arm at a location upstream of the brush seal.
    Type: Grant
    Filed: April 16, 2014
    Date of Patent: January 10, 2017
    Assignee: Siemens Energy, Inc.
    Inventors: Mahesh Janarthanan, Jeffrey A. Kain, Mushtaq Kazi
  • Patent number: 9458726
    Abstract: A turbine shroud for a gas turbine engine includes a metallic support ring and a ceramic blade track. The blade track is formed from a plurality of blade track segments including dovetail posts. The dovetail posts are inserted through apertures in the support ring and are coupled to the support ring by segment retainers coupled to the dovetail posts providing a retention system for the ceramic blade track.
    Type: Grant
    Filed: December 2, 2013
    Date of Patent: October 4, 2016
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies, Inc.
    Inventors: Joseph P. Lamusga, Ted J. Freeman
  • Patent number: 9416673
    Abstract: A turbine section has a turbine rotor carrying turbine blades. The turbine blades include seal members at a radially inner location. A vane section is formed of a plurality of circumferentially spaced vane components, each of which has an airfoil extending radially outwardly of a platform. A first seal member is fixed to the platform, and is positioned to be adjacent a seal from a blade which is positioned in one axial direction relative to the first seal member. A second seal member extends circumferentially beyond at least a plurality of the vane components and is positioned to be adjacent a seal member of a blade on an opposed axial side from the first blade. A vane component is also disclosed and claimed.
    Type: Grant
    Filed: January 17, 2012
    Date of Patent: August 16, 2016
    Assignee: United Technologies Corporation
    Inventors: Joseph T. Caprario, Russell J. Bergman, Pamela A. Humphrey, Jonathan Perry Sandoval
  • Patent number: 9394999
    Abstract: The invention relates to a sealing system for sealing between a first component and a second component wherein at least one or either the first component or the second component is a rotating component. The first component has a circumferential groove in which a sealing segment has first and fifth end portions adjacent the groove and second, third and fourth portions that form a U shape that mirrors the shape of and extends into the circumferential groove.
    Type: Grant
    Filed: September 24, 2015
    Date of Patent: July 19, 2016
    Assignee: ALSTOM TECHNOLOGY LTD.
    Inventor: Jonathan David Seaton
  • Patent number: 9371742
    Abstract: A set of rotor disks for a turbine engine, or an airplane turboprop or turbojet, the set including disks rigidly connected together by bolts and shaped at their outer peripheries with slots for mounting blade roots. Each disk includes a rim extending radially and not having any axial flanges, two consecutive disks being connected together with help of an axially-extending ferrule that is fastened to the rims of the disks and that is fitted with a holder plate for holding the blade roots of the downstream disk.
    Type: Grant
    Filed: October 25, 2011
    Date of Patent: June 21, 2016
    Assignee: SNECMA
    Inventors: Olivier Belmonte, Ludovic Gallego, Lionel Rene Henri Weller
  • Patent number: 9181815
    Abstract: A shaped rim cavity wing includes an upper surface and a lower surface. The lower surface has a geometric shape to control the separation of airflow as it passes around the lower surface to the top surface. A point of maximum extent defines the boundary between the upper surface and the lower surface, wherein the point of maximum extent defines a corner that that separates airflow from the shaped rim cavity rim and creates a flow re-circulation adjacent to the top surface of the shaped rim cavity wing.
    Type: Grant
    Filed: May 2, 2012
    Date of Patent: November 10, 2015
    Assignee: United Technologies Corporation
    Inventor: Eric A. Grover
  • Patent number: 9145771
    Abstract: A disk spacer for a gas turbine engine includes a rim, a bore, a web and a load path spacer. The web extends between the rim and the bore. The load path spacer is positioned between the rim and the bore.
    Type: Grant
    Filed: July 28, 2010
    Date of Patent: September 29, 2015
    Assignee: United Technologies Corporation
    Inventor: Eric W. Malmborg
  • Patent number: 9133712
    Abstract: A blade includes an airfoil having a base and a free, tip end. The tip end includes at least one porous, abradable element.
    Type: Grant
    Filed: April 24, 2012
    Date of Patent: September 15, 2015
    Assignee: United Technologies Corporation
    Inventors: Benjamin T. Fisk, Tracy A. Propheter-Hinckley
  • Patent number: 9133732
    Abstract: A turbine engine vane assembly assembled using an anti-rotation pin method can include a vane assembly having a vane supported on a shroud ring and a cavity seal coupled to the vane assembly by a securement mechanism. The cavity seal defines a securement receiving portion through which the securement mechanism is inserted. The securement receiving portion also includes a deformation receiver. The securement mechanism has a deformable rim at a first end and a key at a second end. The securement mechanism is rotatable between a first configuration and a second configuration where the key matingly engages the shroud ring and the cavity seal to reduce axial movement of the vane assembly. The deformable rim can be deformed into the deformation receiver to prevent rotation of the securement mechanism and disengagement of the securement mechanism from the vane assembly and cavity seal.
    Type: Grant
    Filed: May 20, 2011
    Date of Patent: September 15, 2015
    Assignee: SIEMENS ENERGY, INC.
    Inventor: Gennadiy Afanasiev
  • Patent number: 9109450
    Abstract: A rotor assembly includes a first rotor having first tabs and a second rotor that is arranged coaxial with the first rotor and that includes second tabs that are interlocked with the first tabs. A retainer locks the first tabs and the second tabs together.
    Type: Grant
    Filed: June 14, 2012
    Date of Patent: August 18, 2015
    Assignee: United Technologies Corporation
    Inventors: Raymond S. Hummel, Matthew P. Ricker, Scott D. Virkler, Virginia L. Ross
  • Patent number: 9039375
    Abstract: Turbine blade assemblies of a turbine include airfoils that are mounted on bases. The leading and/or trailing edges of the bases are provided with curved portions. Likewise, curved portions may be provided on leading and/or trailing edges of the angle wings of a turbine blade assembly. Also, curved portions may be provided on the leading and/or trailing edges of nozzle assemblies of a turbine.
    Type: Grant
    Filed: September 1, 2009
    Date of Patent: May 26, 2015
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Andrew Ray Kneeland, Andres Jose Garcia-Crespo, Bradley T. Boyer, Thomas William Vandeputte, Sylvain Pierre
  • Publication number: 20150114001
    Abstract: A sealing component for reducing secondary airflow in a turbine system includes a first end segment configured to be disposed between, and retained in a radial direction by, a first land on a first rotor disk and a first turbine bucket platform operatively coupled to the first rotor disk. Also included is a second end segment configured to be disposed between, and retained in a radial direction by, a second land on a second rotor disk and a second turbine bucket platform operatively coupled to the second rotor disk. Further included is a main body portion extending axially from the first end segment to the second end segment.
    Type: Application
    Filed: October 28, 2013
    Publication date: April 30, 2015
    Applicant: General Electric Company
    Inventors: Brian Denver Potter, Gary Charles Liotta
  • Patent number: 9017013
    Abstract: A gas turbine engine is provided comprising a forward rotor disk and blade assembly capable of rotating; an aft rotor disk and blade assembly capable of rotating; and a row of vanes positioned between the forward rotor disk and blade assembly and the aft rotor disk and blade assembly. The vane row and the forward rotor disk and blade assembly may define a forward cavity. The vane row may comprise at least one stator vane comprising: a main body and an inner shroud structure comprising a cover. The cover may include a first inner cavity receiving cooling air. The cover may further include at least one cooling flow passage. Cooling air flowing from the cooling flow passage has a tangential velocity component.
    Type: Grant
    Filed: February 7, 2012
    Date of Patent: April 28, 2015
    Assignee: Siemens Aktiengesellschaft
    Inventors: Vincent P. Laurello, Kok-Mun Tham
  • Patent number: 9017012
    Abstract: A ring segment for a gas turbine engine includes a panel and a cooling system. The cooling system is provided within the panel and includes a cooling fluid supply trench having an open top portion and extending radially inwardly from a central recessed portion of the panel. The cooling system further includes a plurality of cooling fluid passages extending from the cooling fluid supply trench to a leading edge and/or a trailing edge of the panel. The cooling fluid passages receive cooling fluid from the cooling fluid supply trench, wherein the cooling fluid provides convective cooling to the panel as it passes through the cooling fluid passages.
    Type: Grant
    Filed: October 26, 2011
    Date of Patent: April 28, 2015
    Assignee: Siemens Energy, Inc.
    Inventors: Marco Claudio Pio Brunelli, Sameer A. Khan, Kenneth K. Landis, Walter H. Marussich, Nicholas F. Martin, Beatriz Suarez-Crosse, William W. Pankey