Between Axial Flow Runner And Vane Or Vane Diaphragm Structure Patents (Class 415/173.7)
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Patent number: 9726033Abstract: 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: GrantFiled: November 12, 2012Date of Patent: August 8, 2017Assignee: SNECMAInventors: Alain Dominique Gendraud, Fabrice Marcel Noel Garin, Romain Nicolas Lunel
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Patent number: 9719363Abstract: 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: GrantFiled: June 4, 2015Date of Patent: August 1, 2017Assignee: United Technologies CorporationInventors: David R Pack, Julian Partyka, James D. Hill, Gabriel L Suciu, Gregory M Dolansky, Brian D Merry
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Patent number: 9650895Abstract: 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: GrantFiled: May 28, 2014Date of Patent: May 16, 2017Assignee: SNECMAInventors: Josselin Sicard, Helene Barret, Stephane Pierre Guillaume Blanchard, Youki Olivier Ito-Lardeau, Bertrand Pellaton
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Patent number: 9624784Abstract: 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: GrantFiled: July 8, 2013Date of Patent: April 18, 2017Assignee: General Electric CompanyInventor: Matthew Troy Hafner
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Patent number: 9617855Abstract: 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: GrantFiled: October 12, 2012Date of Patent: April 11, 2017Assignee: HK TURBINE CO., LTD.Inventors: Young Il Chang, Ki Tae Kim, Yong Sik Hah, Jung Hoon Kim
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Patent number: 9540941Abstract: 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: GrantFiled: April 16, 2014Date of Patent: January 10, 2017Assignee: Siemens Energy, Inc.Inventors: Mahesh Janarthanan, Jeffrey A. Kain, Mushtaq Kazi
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Patent number: 9458726Abstract: 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: GrantFiled: December 2, 2013Date of Patent: October 4, 2016Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies, Inc.Inventors: Joseph P. Lamusga, Ted J. Freeman
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Patent number: 9416673Abstract: 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: GrantFiled: January 17, 2012Date of Patent: August 16, 2016Assignee: United Technologies CorporationInventors: Joseph T. Caprario, Russell J. Bergman, Pamela A. Humphrey, Jonathan Perry Sandoval
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Patent number: 9394999Abstract: 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: GrantFiled: September 24, 2015Date of Patent: July 19, 2016Assignee: ALSTOM TECHNOLOGY LTD.Inventor: Jonathan David Seaton
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Patent number: 9371742Abstract: 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: GrantFiled: October 25, 2011Date of Patent: June 21, 2016Assignee: SNECMAInventors: Olivier Belmonte, Ludovic Gallego, Lionel Rene Henri Weller
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Patent number: 9181815Abstract: 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: GrantFiled: May 2, 2012Date of Patent: November 10, 2015Assignee: United Technologies CorporationInventor: Eric A. Grover
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Patent number: 9145771Abstract: 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: GrantFiled: July 28, 2010Date of Patent: September 29, 2015Assignee: United Technologies CorporationInventor: Eric W. Malmborg
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Patent number: 9133712Abstract: A blade includes an airfoil having a base and a free, tip end. The tip end includes at least one porous, abradable element.Type: GrantFiled: April 24, 2012Date of Patent: September 15, 2015Assignee: United Technologies CorporationInventors: Benjamin T. Fisk, Tracy A. Propheter-Hinckley
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Patent number: 9133732Abstract: 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: GrantFiled: May 20, 2011Date of Patent: September 15, 2015Assignee: SIEMENS ENERGY, INC.Inventor: Gennadiy Afanasiev
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Patent number: 9109450Abstract: 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: GrantFiled: June 14, 2012Date of Patent: August 18, 2015Assignee: United Technologies CorporationInventors: Raymond S. Hummel, Matthew P. Ricker, Scott D. Virkler, Virginia L. Ross
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Patent number: 9039375Abstract: 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: GrantFiled: September 1, 2009Date of Patent: May 26, 2015Assignee: GENERAL ELECTRIC COMPANYInventors: Andrew Ray Kneeland, Andres Jose Garcia-Crespo, Bradley T. Boyer, Thomas William Vandeputte, Sylvain Pierre
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Publication number: 20150114001Abstract: 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: ApplicationFiled: October 28, 2013Publication date: April 30, 2015Applicant: General Electric CompanyInventors: Brian Denver Potter, Gary Charles Liotta
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Patent number: 9017012Abstract: 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: GrantFiled: October 26, 2011Date of Patent: April 28, 2015Assignee: 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
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Patent number: 9017013Abstract: 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: GrantFiled: February 7, 2012Date of Patent: April 28, 2015Assignee: Siemens AktiengesellschaftInventors: Vincent P. Laurello, Kok-Mun Tham
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Patent number: 9011078Abstract: The present application provides a seal carrier for use about a number of flow orifices of a platform of a turbine nozzle. The seal carrier may include an inner surface facing the platform with the inner surface having a number of slots therein aligning with the flow orifices of the platform and an opposed outer surface with a seal positioned about the outer surface.Type: GrantFiled: January 9, 2012Date of Patent: April 21, 2015Assignee: General Electric CompanyInventors: Aaron Gregory Winn, Robert Walter Coign
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Patent number: 8992168Abstract: An inner diameter vane seal for a gas turbine engine comprises an annular, ring-like body having inner and outer diameter rims, forward and aft faces and an air passage. The outer diameter rim extends circumferentially for engaging inner diameter ends of stator vanes. The inner diameter rim extends circumferentially and is spaced radially from the inner outer diameter rim. The forward and aft faces extend radially between the outer diameter rim and the inner diameter rim. The air passage extends from the forward face to the aft face between the inner and outer diameter rims.Type: GrantFiled: October 28, 2011Date of Patent: March 31, 2015Assignee: United Technologies CorporationInventors: James W. Norris, Joseph W. Bridges, Jr.
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Patent number: 8979479Abstract: A gas turbine (1) includes a combustion chamber (2) followed by a stator airfoil row (4) defining a plurality of guide vanes and separated by the combustion chamber (2) by a first gap (5), and a rotor airfoil row (6) separated by the stator airfoil row (4) by a second gap (7). The stator airfoils (15) of the stator airfoil row (4) are connected to guide vane boxes (17) collecting a cooling fluid (A) and injecting it through nozzles (20) in the second gap (7) to make it to enter rotor airfoil inlets (23). The guide vane boxes (23) are provided with passages (30) connecting a zone (31) upstream of the guide vane boxes (17) to a zone (32) of the second gap (7) downstream of the guide vane boxes (32). Moreover, the mouths (3) of the passages (30) facing the rotor airfoil row (6) are closer to a hot gases path than the nozzles (20).Type: GrantFiled: September 15, 2010Date of Patent: March 17, 2015Assignee: Alstom Technology LtdInventors: Ulrich Steiger, Carlos Simon-Delgado, Axel Heidecke, Thomas Zierer, Robert Marmilic
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Patent number: 8979481Abstract: A turbine bucket includes a radially inner mounting portion, a shank radially outward of the mounting portion, a radially outer airfoil and a substantially planar platform radially between the shank, and the airfoil. At least one axially-extending angel wing seal flange is formed on a leading end of the shank forming a circumferentially extending trench cavity along the leading edge of the shank, radially between an underside of the platform leading edge and the angel wing seal flange. A plurality of substantially radially-extending purge air holes are formed in the angel wing seal flange, adapted to fluidly connect a turbine rotor wheel space cavity with the trench cavity and thereby supply purge air to the outer surface of the angel wing seal flange.Type: GrantFiled: October 26, 2011Date of Patent: March 17, 2015Assignee: General Electric CompanyInventor: Clint Luigie Ingram
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Patent number: 8979489Abstract: 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: GrantFiled: November 21, 2011Date of Patent: March 17, 2015Assignee: SNECMAInventors: Jean-Claude Christian Taillant, Alain Dominique Gendraud
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Publication number: 20150071771Abstract: An inter-stage seal for a turbomachine includes a sealing member extending from a first end to a second end through an intermediate portion having a sealing surface, a first mounting member extending from a first end portion coupled to the sealing member adjacent the first end to a second, cantilevered end portion having a first rotor mounting element, and a second mounting member extending from a first end portion coupled to the sealing member adjacent the second end to a second, cantilevered end portion having a second rotor mounting element.Type: ApplicationFiled: September 12, 2013Publication date: March 12, 2015Applicant: General Electric CompanyInventors: Xiaoqing Zheng, Thomas Joseph Farineau, Revanth Krishna Nallam
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Publication number: 20150044032Abstract: In an integrated strut and turbine vane nozzle (ISV) configuration, lug/slot or tag/groove arrangements may be provided between an interturbine duct (ITD) of the ISV and a vane ring of the ISV such that struts of the ITD and associated vanes are angularly positioned to form integrated strut-vane airfoils, reducing mismatch at the integration.Type: ApplicationFiled: August 7, 2013Publication date: February 12, 2015Applicant: Pratt & Whitney Canada Corp.Inventors: VINCENT PARADIS, JOHN WALTER PIETROBON, RICHARD L. BOUCHARD
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Patent number: 8950069Abstract: A low leakage, integral fixed vane system for a gas turbine engine compression system which can accommodate the latest 3-D aerodynamic airfoil geometries and provide endwall ovalization control. A unitized construction wherein the vanes are integral with the case wall in the compression system.Type: GrantFiled: December 21, 2007Date of Patent: February 10, 2015Assignee: Rolls-Royce North American Technologies, Inc.Inventor: Robert A. Ress, Jr.
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Publication number: 20150010393Abstract: 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: ApplicationFiled: July 8, 2013Publication date: January 8, 2015Inventor: Matthew Troy Hafner
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Patent number: 8926283Abstract: A gas turbine engine, including: a plurality of blades (60) assembled into an annular row of blades and partly defining a hot gas path (26) and a cooling fluid path (24), wherein the cooling fluid path extends from a rotor cavity (22) to the hot gas path; an angel wing assembly (99) disposed on a side (74) of a base (76) of the row of blades; and pumping features (130) distributed about the angel wing assembly configured to impart, at a narrowest gap (42) of the cooling fluid path, motion to a flow of cooling fluid flowing there through. The plurality of pumping features, the angel wing assembly, and the base of the row of blades are effective to produce a helical motion to the flow of cooling fluid as it enters the hot gas path.Type: GrantFiled: November 29, 2012Date of Patent: January 6, 2015Assignee: Siemens AktiengesellschaftInventors: Ching-Pang Lee, Kok-Mun Tham, Paul H. Vitt, Eric Schroeder
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Patent number: 8911205Abstract: A knife edge seal assembly includes at least one knife edge and at least one honeycomb ring seal. The at least one knife edge has material removed to a first knife edge radial height and the least one honeycomb ring seal has material removed to a finished radial thickness for sealable engagement with the at least one knife edge. The finished radial thickness of the replacement honeycomb ring seal establishes a first radial gap between an inner annular surface of the replacement honeycomb ring seal and the knife edge before the knife edge seal assembly begins rotating in the gas turbine.Type: GrantFiled: October 12, 2011Date of Patent: December 16, 2014Assignee: United Technologies CorporationInventors: William M. Rose, Robert A. Charbonneau
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Patent number: 8888441Abstract: 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: GrantFiled: August 3, 2011Date of Patent: November 18, 2014Assignee: General Electric CompanyInventors: Daniel Edward Jordy, William Edward Adis, Bernard Arthur Couture, Jr., Dexter Andrew Young
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Patent number: 8882453Abstract: A rotor element including an annular surface portion about the rotor rotational axis, a fluid passage being formed through the surface portion, a passage-blocking mechanism including a blocking element that is deformable depending on the rotor rotating speed and arranged so as to adjust the fluid flow depending on the rotor rotating speed, and an annular collar with a free edge engaging with the blocking element so as to form the blocking mechanism. The free edge of the annular collar defines, together with the blocking portion of the blocking element, a diaphragm that blocks the fluid passage.Type: GrantFiled: March 10, 2010Date of Patent: November 11, 2014Assignee: SNECMAInventor: Stephane Rousselin
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Patent number: 8864451Abstract: An interstage seal is provided for installation between forward and aft stage discs of a turbine section of a gas turbine engine. The seal has a forward annular portion, which extends forward to contribute to an air seal at the outer periphery of the forward stage disc, and an aft annular portion, which extends rearward to contribute to an air seal at the outer periphery of the aft stage disc. The seal has a peripheral slot into which static vane inner rails are loadable. The seal includes a first component, which provides the forward annular portion, and a second component, which provides the aft annular portion. The second component is separably connectable to the first component such that the first and second components, when connected, cooperate to form the peripheral slot. Loading the static vane inner rails into the slot prevents the second component separating from the first component.Type: GrantFiled: March 11, 2011Date of Patent: October 21, 2014Assignee: Rolls-Royce PLCInventors: Katherine Sophia Piggott, Paul Antony Davis, Mark John Simms
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Patent number: 8864452Abstract: In a gas turbine engine, a flow directing member includes a platform supported on a rotor, a radially facing endwall, at least one axial surface extending radially inwardly from a junction with the endwall, an airfoil extending radially outwardly from the endwall, and a fluid flow directing feature. The fluid flow directing feature includes a groove extending axially into the axial surface and has radially inner and outer groove ends. The outer groove end defines an axially extending notch in the junction between the axial surface and the endwall and forms an opening in the endwall for directing a cooling fluid to the endwall. The groove further includes a first groove wall extending from the inner groove end to the outer groove end, and a second groove wall opposed from the first groove wall and extending from the inner groove end to the outer groove end.Type: GrantFiled: August 18, 2011Date of Patent: October 21, 2014Assignee: Siemens Energy, Inc.Inventors: Kok-Mun Tham, Ching-Pang Lee
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Patent number: 8864453Abstract: A near flow path seal member for a turbomachine includes a seal body having a seal support member including a first end portion that extends to a second end portion through an intermediate portion. An arm member extends from the first end portion of the seal body. The arm member has a first end that extends to a second end to define an axial dimension of the arm member, a first edge that extends to a second, opposing edge to define a circumferential dimension of the arm member, and a surface having a profile that establishes a thickness variation of the arm member in each of the axial dimension and the circumferential dimension.Type: GrantFiled: January 20, 2012Date of Patent: October 21, 2014Assignee: General Electric CompanyInventors: David Randolph Spracher, John Wesley Harris, Jr., Brian Denver Potter, Zachary James Taylor, Ryan Zane Ziegler
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Patent number: 8858167Abstract: A gas turbine engine component has an airfoil and a squealer tip. The airfoil has a pressure side and a suction side. The squealer tip is located at one end of the airfoil to engage with an adjacent surface and thereby form a seal. The squealer tip terminates in a squealer tip apex with an arched cross-sectional profile in a plane extending from the pressure side to the suction side of the airfoil. A method for producing an airfoil seal for the gas turbine engine component is also provided.Type: GrantFiled: August 18, 2011Date of Patent: October 14, 2014Assignee: United Technologies CorporationInventor: Paul W. Baumann
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Patent number: 8844131Abstract: A process is provided for forming a leaf-spacer pair for use in a leaf seal which effects a seal between two components. The process includes the steps of: (a) providing a leaf section which maintains, in the leaf seal, wiping contact with one of the components, and a root section from which the leaf section extends and which, in the leaf seal, is fixed relative to the other component, the leaf section and the root section being formed from a first sheet of material of substantially uniform thickness; (b) providing a spacer formed from a second sheet of material, the spacer being physically separate from the leaf section and the root section; and (c) fastening the spacer to the root section to form a leaf-spacer pair in which the spacer overlays the root section and remains fixed relative thereto on handling of the leaf-spacer pair.Type: GrantFiled: August 1, 2012Date of Patent: September 30, 2014Assignee: Rolls-Royce PLCInventor: Gervas Franceschini
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Patent number: 8845284Abstract: An apparatus for restricting fluid flow in a turbo-machine is disclosed. The apparatus includes: a first inter-stage sealing member configured to be located between a first rotating airfoil stage and a second rotating airfoil stage attached to a rotor shaft, the first inter-stage sealing member including a segmented structure that includes a plurality of segments forming a circumferential surface, the first inter-stage sealing member including: a first base portion including a securing mechanism configured to at least substantially radially and tangentially secure the inter-stage sealing member to an inter-stage support structure; a first axial retention mechanism; and a first axially extending sealing portion configured to be outwardly radially loaded against at least one of the first rotating airfoil stage and the second rotating airfoil stage.Type: GrantFiled: July 2, 2010Date of Patent: September 30, 2014Assignee: General Electric CompanyInventors: Thomas Raymond Farrell, Gary Charles Liotta, Ian David Wilson
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Publication number: 20140255169Abstract: A turbine including a plurality of stages, each stage including a rotatable disk and blades carried thereby. An annular gap defined between a pair of adjacent rotatable disks. A sealing band is located in opposing sealing band receiving slots formed in the adjacent disks to seal the annular gap, the sealing band including band engagement structure. A disk engagement structure is defined in the pair of adjacent rotatable disks. The disk engagement structure extends axially into the pair of adjacent rotatable disks and circumferentially aligns with the band engagement structure. A clip member is positioned in engagement with the sealing band through the band engagement structure and in engagement with the pair of adjacent rotatable disks through the disk engagement structure. The clip member restricts movement of the sealing band in only a circumferential direction of the slots.Type: ApplicationFiled: March 8, 2013Publication date: September 11, 2014Inventors: Christopher J. Muller, David J Mitchell, Michael J Olejarski
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Publication number: 20140255168Abstract: An assembly for a gas turbine engine includes a first module, a second module, and a flow discourager. The second module is connected to the first module along a joint. The flow discourager is connected to the first module and extends to be received in a notch in the second module. The flow discourager acts to direct an ingestion gas flow away from the joint between the first module and the second module.Type: ApplicationFiled: December 29, 2012Publication date: September 11, 2014Applicant: UNITED TECHNOLOGIES CORPORATIONInventor: UNITED TECHNOLOGIES CORPORATION
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Patent number: 8820748Abstract: A sealing system for a turbomachine for sealing an annular gap between a rotor and a stator of the turbomachine has a sealing body which can be inserted into the annular gap and can bridge the latter, said sealing body being embodied elastically and thereby able to compensate for a height variation of the annular gap, and at least one sealing ring which is embedded in the sealing body such that the sealing ring is held by the sealing body in the annular gap between the rotor and the stator.Type: GrantFiled: October 7, 2008Date of Patent: September 2, 2014Assignee: Siemens AktiengesellschaftInventor: Oliver Berendt
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Patent number: 8821115Abstract: A seal assembly arranged adjacent to a primary flow region, the seal assembly including: first and second components; a seal arranged between the first and second components to seal a secondary flow region from the primary flow region; and a first recess portion provided in the first component and arranged adjacent to the seal and the primary flow region, the first recess portion further being arranged to receive flow from at least one of the primary flow region and the secondary flow region and shed flow to the primary flow region, wherein the first recess portion is configured to promote a first flow feature within the first recess portion, the first flow feature flowing with a portion of the first flow feature adjacent to the primary flow region and the portion of the first flow feature being shed to the primary flow region in substantially the same direction as the flow in the primary flow region.Type: GrantFiled: July 6, 2011Date of Patent: September 2, 2014Assignee: Rolls-Royce PLCInventors: Adam M. Bagnall, Ross D. Maxwell
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Patent number: 8813359Abstract: A process is provided for manufacturing leaf seals for effecting seals between coaxial, relatively rotating components. Each leaf seal has an annular pack of leaves which are stacked face-to-face, and are mountable to one of the components at respective root portions of the leaves. The annular pack has a pack radius at the wiping contact edges which is matched within tolerance limits to the radius of the sealing surface. The process includes: determining production parameters for the production of a plurality of leaf seals, the parameters being determined such that at least a portion of the produced leaf seals will have pack radii which violate the tolerance limit; producing the leaf seals using the determined production parameters; and modifying the pack radii of the portion of the produced leaf seals which violate the tolerance limit such that the modified pack radii match the sealing surface within the tolerance limits.Type: GrantFiled: October 4, 2012Date of Patent: August 26, 2014Assignee: Rolls-Royce, PLCInventor: Ingo Henry Johannes Jahn
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Patent number: 8790073Abstract: A gas turbine engine including a stator vane directing hot combustion gases onto rotor blades is provided. The stator vane includes a platform disposed at the side of the vane radially inward/outward with respect to the axis of rotation of the engine, the platform having a trailing edge portion downstream with respect to the flow of gases past the stator vane. A support and cooling arrangement is included for directing a cooling fluid to an upstream end of a radially inwardly/outwardly facing side of the trailing edge portion of the platform, the arrangement also directing the cooling fluid to flow over the side in a generally axial direction to a downstream end of the side, the cooling fluid cooling the trailing edge portion as it flows over the side, wherein turbulators are included to increase heat transfer from the trailing edge portion as the cooling fluid flows over the side.Type: GrantFiled: January 21, 2010Date of Patent: July 29, 2014Assignee: Siemens AktiengesellschaftInventor: Jonathan Mugglestone
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Patent number: 8752288Abstract: A first process is provided for forming a stack of leaves for use in a leaf seal which effects a seal between two components. Corresponding processes are provided for forming a leaf-spacer pair and then for forming a stack of leaves from such pairs. Each leaf of the stack has a leaf section which maintains wiping contact with one of the components and a root section which is fixed relative to the other component and from which the leaf section extends. The stack includes a plurality of spacers which interpose between the root sections.Type: GrantFiled: August 1, 2012Date of Patent: June 17, 2014Assignee: Rolls-Royce PLCInventors: David S. Williams, Ingo H. J. Jahn, Gervas Franceschini
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Patent number: 8740554Abstract: An air seal assembly for a gas turbine engine includes a first cover plate with a radially extending knife edge seal defined about and axis of rotation. The first cover plate is mountable to a first rotor disk for rotation therewith, the first radially extending knife edge seal interfaces with a vane structure. A second cover plate with a second radially extending knife edge seal defined about the axis of rotation, the second cover plate mountable to the second rotor disk for rotation therewith. The second radially extending knife edge seal interfaces with the vane structure.Type: GrantFiled: January 11, 2011Date of Patent: June 3, 2014Assignee: United Technologies CorporationInventors: Scott D. Virkler, Roger Gates
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Publication number: 20140147257Abstract: A fan shroud and seal ring are assembled together to allow a condenser, radiator, and fan module (CRFM) to be vertically loaded into an engine compartment of a vehicle to be mounted to the vehicle chassis and engine with a fan stator. The fan shroud has a plurality of first attachment components, and the seal ring has a plurality of second attachment components, each of which corresponds to a first attachment component. Each first attachment component engages with a corresponding second attachment component to secure the seal ring to the fan shroud, such that the seal ring is positioned around at least a portion of the fan stator after the CRFM has been mounted and the assembly is in its final configuration.Type: ApplicationFiled: November 29, 2012Publication date: May 29, 2014Applicant: GM GLOBAL TECHNOLOGY OPERATIONS LLCInventors: Raymond H. Sasinowski, Adrian O. Balmaceda
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Publication number: 20140127007Abstract: A rotary seal for sealing a bladed rotor of a gas turbine engine to a stator thereof comprises a sealing element and a sealing element support comprising a radially outer edge portion on which the sealing element is fixed, a radially inner mounting portion adapted to be attached to a supported rotor hub, and a flexible, medial web portion extending between the radially outer edge portion and the radially inner mounting portion.Type: ApplicationFiled: November 7, 2012Publication date: May 8, 2014Applicant: UNITED TECHNOLOGIES CORPORATIONInventor: United Technologies Corporation
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Publication number: 20140119879Abstract: Various embodiments include a turbomachine with a plasma seal system. The turbomachine can include: a diaphragm section having: an axially facing diaphragm wall; and a discourager seal protruding axially from the axially facing diaphragm wall; a rotor section having: a bucket having an axially facing bucket wall opposing the axially facing diaphragm wall; and a seal member extending from the axially facing bucket wall, wherein the seal member axially overlaps a portion of the discourager seal of the diaphragm section leaving a radial gap between the seal member and the discourager seal; and a plasma generator coupled to the diaphragm section for generating a plasma which reduces the radial gap between the seal member and the discourager seal.Type: ApplicationFiled: October 29, 2012Publication date: May 1, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Sanjeev Kumar Jha, Sheo Narain Giri
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Publication number: 20140112766Abstract: A sealing band is located in opposing sealing band receiving slots of adjacent turbine disks to seal an annular gap therebetween. A through hole is defined in one of the disks, wherein the through hole defines a longitudinal hole axis and extends to the sealing band receiving slot in the disk. At least one engagement feature is defined on the disk and extends laterally of the through hole, perpendicular to the longitudinal hole axis. A pin member extends through the hole and is positioned within the sealing band receiving slot passing through an opening in the sealing band for resisting movement of the sealing band relative to the disk. The pin member includes a laterally extending cooperating feature positioned in engagement with the engagement feature for retaining the pin within the opening in the sealing band.Type: ApplicationFiled: October 23, 2012Publication date: April 24, 2014Inventors: BRIAN D. NEREIM, REBECCA L. KENDALL, PIYUSH SANE