Seal Patents (Class 415/230)
  • Patent number: 9568014
    Abstract: A gas system has a first compressor stage for compressing a process gas. The first compressor stage includes an intake side and a pressure side. A seal gas is provided outside the first compressor stage in order to prevent process gas from issuing from leaks in the first compressor stage, having at least one second line for returning a gas mixture issuing from the gas system, this mixture including at least of process gas and seal gas. The at least one second line is configured for returning the issuing gas mixture to the intake side of the first compressor stage and/or to a location in the gas system upstream of the first compressor stage.
    Type: Grant
    Filed: January 26, 2012
    Date of Patent: February 14, 2017
    Assignee: SIEMENS AKTIENGESELLSCHAFT
    Inventors: Ludger Alfes, Klaus Eisele, Thomas Mönk, Markus Reinhold, Axel Spanel
  • Patent number: 9534690
    Abstract: This leakage prevention seal is provided with: a first seal ring which surrounds a rotating shaft and which is in circumferential contact with the surface of a housing which faces the upstream side; a second seal ring, which, on the upstream side of the first seal ring, surrounds the rotating shaft and which is in circumferential contact with the first seal ring; and a heat-driven section which, when high-temperature pressurized water reaches the heat-driven section, reduces the diameter of both the first seal ring and the second seal ring and causes the inner peripheral surfaces of both the first seal ring and the second seal ring to be in contact with the rotating shaft. The circumferential positions of both a first range between the first seal ring and the rotating shaft and a second range formed by the second seal ring are different.
    Type: Grant
    Filed: December 24, 2013
    Date of Patent: January 3, 2017
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Hidetaka Kafuku, Hidekazu Uehara, Yukihiro Sakaguchi
  • Patent number: 9429040
    Abstract: An expansion turbine, comprising: a case having an inlet and an outlet for a working fluid; at least one stator (3) installed inside the case; at least one rotor (2) installed inside the case and rotating around a respective revolution axis (X-X); a short-pipe (4) constrained to the case; a mechanical unit (5) installed inside the short-pipe (4). The mechanical unit (5) comprises a bushing (7) and a shaft (6) rotatably installed inside the bushing (7). The shaft (6) is connected to the rotor (2) in removable manner and the whole mechanical unit (5) inclusive of the shaft (6) is extractable from the short-pipe (4) in a unitary form from the side opposite to said rotor (2).
    Type: Grant
    Filed: December 15, 2011
    Date of Patent: August 30, 2016
    Assignee: EXERGY S.P.A.
    Inventor: Claudio Spadacini
  • Publication number: 20150132116
    Abstract: A hydrodynamic face seal ring for use in a rotary machine includes a support ring having at least two support ring segments and a radially-extending, first face. The support ring is configured to releasably couple to an inner surface of an outer casing of the rotary machine. The face seal ring also includes a sealing ring substantially concentric with the support ring. The sealing ring includes at least two sealing ring segments and a radially-extending, second face. The sealing ring is releasably coupled to the support ring such that the first face is mated against the second face.
    Type: Application
    Filed: November 11, 2013
    Publication date: May 14, 2015
    Applicant: General Electric Company
    Inventors: Xiaoqing Zheng, Roderick Mark Lusted, Azam Mihir Thatte, Christopher David Suttles
  • Publication number: 20150132126
    Abstract: An adjustable seal and method for varying a radial distance between the adjustable seal and a rotor of a turbomachine are provided. The adjustable seal may include a first annular member defining a plurality of radial channels, and a second annular member defining a plurality of slots at least partially extending therethrough. The second annular member may be concentric with the first annular member and configured to rotate relative to the first annular member. The adjustable seal may also include a plurality of seal segments interposed between the first annular member and the second annular member. Each seal segment of the plurality of seal segments may be slidably disposed in a respective radial channel of the plurality of radial channels and may have an axial projection slidably disposed in a respective slot of the plurality of slots.
    Type: Application
    Filed: September 16, 2014
    Publication date: May 14, 2015
    Applicant: DRESSER-RAND COMPANY
    Inventors: James M. Sorokes, Igor M. Belousov, Chris M. Leasure, Austin Kimes, Tyler Johnson
  • Publication number: 20150110621
    Abstract: Embodiments of a gas turbine engine including a finger-foil seal are provided, as are embodiments of a finger-foil seal. In one embodiment, the finger-foil seal includes an aerodynamic foil having a generally annular body through which a first opening is formed. A finger seal retention structure is disposed around the aerodynamic foil. A finger seal backing spring is coupled to the finger seal retention structure and extends radially inward therefrom to contact an outer circumference of the aerodynamic foil. A first anti-rotation pin extends radially from the finger seal retention structure and into the first opening formed in the aerodynamic foil to inhibit rotation of the aerodynamic foil during operation of the finger-foil seal.
    Type: Application
    Filed: October 23, 2013
    Publication date: April 23, 2015
    Inventors: Marshall Saville, Keith Alan Hurley, Joseph Yanof, Tina Hynes, David Waldman
  • Patent number: 9004849
    Abstract: A gas turbine engine includes a bearing structure mounted to the front center body case structure to rotationally support a shaft driven by a geared architecture. A bearing compartment passage structure is in communication with the bearing structure through a front center body case structure.
    Type: Grant
    Filed: January 10, 2012
    Date of Patent: April 14, 2015
    Assignee: United Technologies Corporation
    Inventors: Peter M. Munsell, Philip S. Stripinis
  • Publication number: 20150078893
    Abstract: The present invention relates to a process for producing a seal arrangement (1) for a turbomachine which comprises a seal support (2) and a stripping lining (3) which is arranged on the seal support, wherein the seal support comprises a fiber-reinforced plastic and the stripping lining comprises polysiloxane, and wherein the seal support and the stripping lining are prepared in a non-cured state and are arranged in direct contact with one another in accordance with the configuration of the seal arrangement, and are subsequently subjected to a common curing process such that fiber-reinforced plastic and polysiloxane cross-link with one another. The present invention further relates to a correspondingly produced seal arrangement and to a turbomachine having such a seal arrangement.
    Type: Application
    Filed: September 19, 2014
    Publication date: March 19, 2015
    Inventors: Siegfried SCHMID, Michael SCHOBER, Siegfried SIKORSKI, Axel MATTSCHAS, Robert BADER
  • Patent number: 8974179
    Abstract: A turbine system is disclosed. In one embodiment, the turbine system includes a transition duct. The transition duct includes an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The transition duct further includes an interface member for interfacing with a turbine section. The turbine system further includes a convolution seal contacting the interface member to provide a seal between the interface member and the turbine section.
    Type: Grant
    Filed: November 9, 2011
    Date of Patent: March 10, 2015
    Assignee: General Electric Company
    Inventors: James Scott Flanagan, Jeffrey Scott LeBegue, Kevin Weston McMahan, Daniel Jackson Dillard, Ronnie Ray Pentecost
  • Patent number: 8966895
    Abstract: A turbocharger assembly includes a center housing rotating assembly, which comprises a center housing, bearings housed in the center housing, a shaft rotatably supported in the bearings, and compressor and turbine wheels affixed to opposite ends of the shaft; an engine cylinder head and a housing member formed together as a one-piece integral structure, wherein the housing member defines a compressor volute that receives compressed air from the compressor wheel, a turbine volute for receiving exhaust gas from the engine, a turbine nozzle for directing exhaust gas from the turbine volute into the turbine wheel, and a turbine contour; a compressor contour plug that defines an axial inlet for the compressor and a compressor contour; and a wastegate unit operable for allowing exhaust gas to bypass the turbine wheel when the wastegate unit is open and preventing exhaust gas from bypassing the turbine wheel when the wastegate unit is closed.
    Type: Grant
    Filed: March 21, 2012
    Date of Patent: March 3, 2015
    Assignee: Honeywell International Inc.
    Inventors: Manuel Marques, Jean-Jacques Laissus, Mani Palaniyappan, Alain Lombard, Quentin Roberts, Johann Kurtzmann, Aitor Herrera Celaya, Nicolas Serres
  • Patent number: 8961102
    Abstract: A system and method for sealing a shaft disposed for rotation within a casing, where two axially-spaced seal rings of an oil film seal extend around the shaft and define a clearance therebetween. Oil is pumped into the clearance from an oil reservoir and a portion of the oil is received in an annular port defined in the casing between an outer labyrinth seal and one of the axially-spaced seal rings. The oil mixes with a process gas to for an oil and gas mixture. A blower is in fluid communication with the annular port and circulates the oil and gas mixture to a trap where the oil is separated from the process gas and a separated process gas is returned back to the annular port.
    Type: Grant
    Filed: June 6, 2012
    Date of Patent: February 24, 2015
    Assignee: Dresser-Rand Company
    Inventor: Philippe Auber
  • Publication number: 20150050141
    Abstract: This invention relates to a passive shutdown sealing device (20, 40) for a reactor coolant pump set comprising a set of bimetallic strips (21, 41) having a first position called the cold position when the temperature of said bimetallic strips is less than said temperature threshold, and a second position called the hot position when the temperature of said bimetallic strips is greater than said temperature threshold; a sealing ring (23) with an active position when said bimetallic strips (21, 41) are in their hot position and with an inactive position when said bimetallic strips are in their cold position; locking/unlocking means (25) adapted to lock said sealing ring (23) in its inactive position when said bimetallic strips (21, 41) are in their cold position and to release said sealing ring (23) when said bimetallic strips (21, 41) are in their hot position; elastic means (24) adapted to constrain said sealing ring (23) in the active position when said locking/unlocking means (25) are unlocked.
    Type: Application
    Filed: December 26, 2012
    Publication date: February 19, 2015
    Inventor: Eric Savin
  • Publication number: 20150044444
    Abstract: A thermal barrier coating that includes a YAG-based ceramic is prepared by a solution precursor plasma spray method that includes injecting a precursor solution into a thermal jet, evaporating solvent from the precursor solution droplets, and pyrolyzing the resulting solid to form a YAG-based ceramic that is melted and deposited on a substrate. The thermal barrier coating can include through-coating-thickness cracks that improve the strain tolerance of the coating.
    Type: Application
    Filed: April 22, 2013
    Publication date: February 12, 2015
    Inventors: Maurice Gell, Eric Jordan, Jeffrey Roth
  • Patent number: 8939710
    Abstract: An exemplary turbomachine seal assembly includes a ring seal that has a radially-facing sealing surface, an axially-facing sealing surface, and a first tapered surface. The turbomachine seal assembly also includes a spacer that has a second tapered surface. The second tapered surface interfaces with the first tapered surface to bias the radially facing sealing surface and the axially facing sealing surface toward a sealing position.
    Type: Grant
    Filed: August 24, 2011
    Date of Patent: January 27, 2015
    Assignee: United Technologies Corporation
    Inventor: Scot A. Webb
  • Patent number: 8932011
    Abstract: A shaft assembly for a gas turbine engine that includes a shaft with a threaded shaft segment, an annular rotor disposed on the shaft, and annular stack nut. The stack nut includes a base nut segment and a clamping nut segment. The base nut segment includes a threaded nut bore that is mated with the threaded shaft segment. The clamping nut segment axially extends from the base nut segment to a load bearing surface. The clamping nut segment includes a radial thickness that decreases as the clamping nut segment extends from the load bearing surface towards the base nut segment. The load bearing surface exerts a force against the rotor securing the rotor to the shaft.
    Type: Grant
    Filed: October 6, 2011
    Date of Patent: January 13, 2015
    Assignee: United Technologies Corporation
    Inventors: Eric C. Mundell, Todd M. LaPierre, Marc J. Muldoon, Stephen J. Lyle
  • Patent number: 8927175
    Abstract: A pump has a shaft, an impeller arranged on the shaft, and a labyrinth seal which is arranged between stationary and moving parts of the pump. A plurality of blades are arranged on the rotor and a labyrinth seal extends at least between the shaft and a rear portion of the blades. A gap in the labyrinth seal is designed such that liquid water can be actively carried away, with the labyrinth seal for this purpose being designed at least in places with a channel in the form of a spiral and/or a staircase. The invention also relates to a fuel cell system having such a pump.
    Type: Grant
    Filed: July 23, 2008
    Date of Patent: January 6, 2015
    Assignee: Daimler AG
    Inventors: Oliver Harr, Andreas Knoop, Cosimo S. Mazzotta, Patrick L. Padgett, Hans-Joerg Schabel, Klaus Scherrbacher
  • Patent number: 8919134
    Abstract: An assembly for gas turbine engine includes a cross-over housing, an inter-shaft seal housing, and a linkage. The inter-shaft seal housing is disposed within the cross-over housing. The linkage is connected to the inter-shaft seal housing and extends through a slot in the cross-over housing. The linkage is removable from both the inner radial housing and the outer radial housing.
    Type: Grant
    Filed: January 26, 2011
    Date of Patent: December 30, 2014
    Assignee: United Technologies Corporation
    Inventors: Neil L. Tatman, Christopher J. Larson
  • Patent number: 8915705
    Abstract: A seal assembly disposed between a rotor and a stator especially of a turbo-machinery is provided with a close clearance gap there between. The clearance gap is bordered by a rotor surface at the side of the rotor and by a stator surface at the side of the stator. The rotor surface or the stator surface or both are provided with openings which open into at least one chamber arranged at the side of the openings turned away from the clearance gap.
    Type: Grant
    Filed: January 23, 2009
    Date of Patent: December 23, 2014
    Assignee: Siemens Aktiengesellschaft
    Inventor: Rob Eelman
  • Publication number: 20140369832
    Abstract: A contact seal assembly for a shaft of a gas turbine engine includes a seal runner adapted to be connected to the shaft and rotatable relative to a carbon ring. The seal runner includes concentric inner and outer annular portions radially spaced apart to define at least one internal fluid passage between the inner and outer annular portions of the seal runner.
    Type: Application
    Filed: June 13, 2013
    Publication date: December 18, 2014
    Inventors: Daniel BLAIS, Alain Lewis, Alain C. Martel
  • Patent number: 8911204
    Abstract: A method for servicing a gas turbine engine includes disassembling a bearing compartment, providing access from a forward side of the gas turbine engine to a gearbox contained within said bearing compartment. The gas turbine engine provides a core flow path that extends from the forward side aftward in a core flow direction. The method includes servicing a component located within the bearing compartment. A method for servicing a gas turbine engine includes providing access from a forward side of a front center body assembly, and servicing a component located within a bearing compartment aft of the front center body assembly. The gas turbine engine includes a seal package located aft of a bearing package. A front wall is mounted to the front center body support and is removable from a front center body support to access at least one of the gearbox, the bearing package and the seal package.
    Type: Grant
    Filed: January 2, 2013
    Date of Patent: December 16, 2014
    Assignee: United Technologies Corporation
    Inventors: Todd A. Davis, Brian P. Cigal
  • Publication number: 20140356160
    Abstract: A mechanical seal is disclosed having a rotatable sealing face and a stationary sealing face that are in opposed relation and arranged to be urged, into contact to form a seal. One of the sealing faces is mounted on a support assembly that includes a biasing device operative to move that sealing face into contact with the other sealing face. In one form of the invention, the biasing device comprises one or more resilient members that in use are deformed to provide the biasing force. In a second form of the invention, the support assembly forms part of a fluid barrier of the seal and the biasing device is fluid impervious and forms part of the barrier. In a third form of the invention, the biasing device is exposed to fluid pressure in the chamber and the biasing force increases on increasing the fluid pressure in the chamber.
    Type: Application
    Filed: June 6, 2014
    Publication date: December 4, 2014
    Inventors: Ricardo Abarca Melo, Rodrigo Guzman Castro, Osvaldo Quiroz Venegas
  • Patent number: 8899912
    Abstract: A turbomachine is disclosed that has a main fluid flowpath extending axially along the turbomachine with a rotating shaft partly enclosed in a casing, wherein the rotating shaft and casing are moveable relative to each other and define a clearance opening about the rotating shaft, whereby the main fluid flowpath fluidly communicates with an outside region, and an annular seal body defining a fluid passage having a primary fluid inlet configured to receive a pressurized fluid, a fluid outlet disposed proximate to the clearance opening, and a convergent chamber interposed therebetween, wherein the convergent chamber is configured to accelerate the pressurized fluid out of the fluid outlet so as to create a local reduced pressure at the clearance opening.
    Type: Grant
    Filed: January 15, 2010
    Date of Patent: December 2, 2014
    Assignee: Dresser-Rand Company
    Inventor: Inam Ul Haq
  • Publication number: 20140341731
    Abstract: A gas turbine having a device and a further device is provided. The device includes an outer casing, an inner casing and a seal ring. The outer casing and the inner casing are arranged in such a way that a cooling duct is formed between each other. The seal ring is arranged between the outer casing and the inner casing in such a way that the seal ring seals the cooling duct from an environment surrounding the outer casing. The device and the further device are mounted together such that working fluid is flowable from the further device to the device. Furthermore the device includes a rotatable shaft and the further device includes a further rotatable shaft, wherein the rotatable shaft and the further rotatable shaft are mechanically decoupled from each other, and wherein the seal ring exclusively abuts against the inner casing and against the outer casing of the device.
    Type: Application
    Filed: April 27, 2012
    Publication date: November 20, 2014
    Applicant: SIEMENS AKTIENGESELLSCHAFT
    Inventor: Kevin Scott
  • 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
  • Patent number: 8882459
    Abstract: Wind turbine provided with a bearing supporting a hub carrying rotor blades, the bearing comprising a rotational bearing race connected to the hub and a stationary bearing race, a lubrication area between the bearing races which area is confined at both ends by first seal rings sealing the gap between the rotational bearing race and stationary parts to form a lubrication barrier. At one or both ends of the lubrication area a redundant seal ring is arranged at a distance from the first seal ring in or near the gap to be sealed.
    Type: Grant
    Filed: February 27, 2009
    Date of Patent: November 11, 2014
    Assignee: XEMC Darwind B.V.
    Inventors: Gustave Paul Corten, Cornelis Johannes Antonius Versteegh, Herman Luimes
  • Patent number: 8882446
    Abstract: A bearing system for a rotor in rotating machines, such as compressors, pumps, turbines, expanders, has points of bearing and sealing for the rotor each being in the form of a combined bearing and sealing formed by a stator situated within a rotating machine house and surrounding the rotor. The stator is formed with a bore, whereby an annular clearance is created between stator and rotor, and the bore is having sectional area gradually increasing in the direction of larger pressure within the rotating machine.
    Type: Grant
    Filed: January 29, 2009
    Date of Patent: November 11, 2014
    Assignee: Statoil Petroleum AS
    Inventor: Harald Underbakke
  • Publication number: 20140321969
    Abstract: A turbomachine in the form of a stationary gas turbine or an aircraft engine, respectively a housing structure therefor; the housing structure including an outer housing wall (1) and an inner wall (2) defining the flow channel; and a hollow space (4) being formed between the inner wall and the outer housing wall. The hollow space is separable into at least two regions (5, 6); a movable wire element (slide ring seal) (10, 10?), which is adapted to rest against the contact faces (8, 9), being configured in the hollow space for purposes of the separation.
    Type: Application
    Filed: April 9, 2014
    Publication date: October 30, 2014
    Applicant: MTU Aero Engines AG
    Inventors: Manfred Feldmann, Norbert Schinko, Janine Sangl
  • Patent number: 8870521
    Abstract: A centrifugal pump for delivering hot fluids, having a contacting shaft seal, a seal housing (13) for the shaft seal (14), and a return line (8) for a partial flow of the delivered fluid, in which no delivered fluid is discharged out of the seal housing (13); a separate housing cover (9) is disposed between the seal housing (13) and the pump housing (1); there is a contact surface which minimizes heat transfer between the seal housing (13) and the housing cover (9); and the return line (8) is connected to the housing cover (9) and/or to the pump housing (1).
    Type: Grant
    Filed: December 2, 2011
    Date of Patent: October 28, 2014
    Assignee: KSB Aktiengesellschaft
    Inventors: Bernhard Brecht, Uwe Bruhns, Frank Sehr
  • Patent number: 8870522
    Abstract: In a centrifugal pump, in particular a radial or semi-axial pump including a housing with a pump chamber and a dry chamber, a drive shaft rotatably supported in the housing and connected to an impeller for pumping a liquid flow medium disposed in the pump chamber and a shaft seal arranged in an inner radial area for sealing the dry space with respect to the flow medium, a seal carrier is provided with a guide structure by which fluid flow medium is conducted from an outer radial area to an inner radial area for directing flow medium into the seal for lubrication and cooling of the seal.
    Type: Grant
    Filed: March 30, 2011
    Date of Patent: October 28, 2014
    Assignee: MTU Friedrichshafen GmbH
    Inventors: Wolfgang Reischmann, Alexej Vaulin, Joachim Ruck
  • Patent number: 8864461
    Abstract: The invention concerns a turbine structure for the expansion of gas and vapour, comprising a body or casing with a peripheral work fluid transit volute from an entrance to an exit passage, at least a first stator and possible subsequent stators, a turbine shaft rotating around an axis and carrying at least a first rotor and possible subsequent rotors working together downstream of the first stator and subsequent rotors, respectively, an external tube member jutting out frontally from said body or casing and coaxial to the rotating turbine shaft, and where between the tube member (18) and the turbine shaft (15) is positioned a supporting unit (19) extractable en bloc from said external tube (18) except for the shaft.
    Type: Grant
    Filed: March 16, 2010
    Date of Patent: October 21, 2014
    Assignee: Turboden S.r.l.
    Inventors: Mario Gaia, Roberto Bini
  • Publication number: 20140308112
    Abstract: The present invention refers to a mechanical seal assembly, comprising at least one mechanical seal (2) with a rotating seal ring (21) and a stationary seal ring (22), the rotating seal ring (21) and the stationary seal ring (22) defining a sealing gap (23) between them, and a Tesla pump (6) co-rotating with the rotating seal ring (21).
    Type: Application
    Filed: October 8, 2012
    Publication date: October 16, 2014
    Applicant: EAGLEBURGMANN GERMANY GMBH & CO. KG
    Inventors: Stefan Ledig, Thomas Boehm, Rudolf Kollinger
  • Patent number: 8858166
    Abstract: Systems and devices for substantially fluidly isolating portions of a rotary machine are disclosed. In one embodiment, a seal assembly for a rotary machine includes: a complementary set of seal segments configured relative one another so as to form a substantially continuous body with butt gaps between the seal segments, the segments including: a head flange; and an axial neck connected to the head flange, wherein the axial neck extends radially inboard and includes an axial slot formed substantially there through; and at least one butt gap seal element, wherein the at least one butt gap seal element includes an axial flange and a radial flange, the axial flange disposed within the axial slots of adjacent seal segments; and the radial flange extending radially inboard from the axial slots to a proximity of the rotary machine substantially forming a barrier to axial flow through the butt gap.
    Type: Grant
    Filed: September 7, 2011
    Date of Patent: October 14, 2014
    Assignee: General Electric Company
    Inventors: Xiaoqing Zheng, Bernard Arthur Couture, Jr., Mehmet Demiroglu, Gregory Leonard Diantonio, Daniel Edward Jordy
  • Patent number: 8858162
    Abstract: A labyrinth seal is provided for forming a seal between a first and a second component which rotate relative to each other. The seal has an abradable lining mounted to the first component, and a plurality of fins projecting from the second component. The fins are arranged in abutment with the abradable lining to form a labyrinthal path for a flow of air through the seal. The seal further has a bypass passage which extends through the abradable lining. The bypass passage allows air to flow through the seal and bypass the labyrinthal path.
    Type: Grant
    Filed: July 5, 2011
    Date of Patent: October 14, 2014
    Assignee: Rolls-Royce PLC
    Inventor: Reza Manzoori
  • Publication number: 20140290213
    Abstract: A seal system for a gas turbine engine includes an annular seal carrier and an annular compliant seal mounted around the annular seal carrier, the compliant seal includes a multiple of legs in cross-section.
    Type: Application
    Filed: January 8, 2014
    Publication date: October 2, 2014
    Applicant: United Technologies Corporation
    Inventors: Nicholas Lefevre, John J. Korzendorfer, Peter Balawajder, Paul W. Palmer, Paul J. Colucci, Mahamoud Coulibaly
  • Patent number: 8845282
    Abstract: A seal assembly for a gas turbine engine includes a carbon seal and a seal plate. The seal plate has a contact face configured to slidably engage the carbon seal. The seal plate has a surface disposed on an opposing side of the seal plate from the contact face. The surface forms a portion of a single passage that extends an entire length of the seal plate. The continuous cooling provided by single passage along the seal plate allows for a more uniform temperature profile along the contact face of seal plate.
    Type: Grant
    Filed: September 28, 2011
    Date of Patent: September 30, 2014
    Assignee: United Technologies Corporation
    Inventors: Todd M. LaPierre, Eric Charles Mundell
  • Publication number: 20140271177
    Abstract: A seal for use in a centrifugal pump, the pump having a stationary pump casing, a stationary plate and an axially adjustable side liner, is disclosed. The seal includes a base having an inner surface and an outer surface. A band portion extends from the base and a retainer member extends from the band portion. The retainer member is spaced apart from the base and oriented for positioning against a groove formed in the axially adjustable side plate liner of the centrifugal pump.
    Type: Application
    Filed: March 14, 2014
    Publication date: September 18, 2014
    Applicant: WEIR SLURRY GROUP, INC.
    Inventors: Randy J. Kosmicki, Michael L. Viken
  • Publication number: 20140255181
    Abstract: A gas turbine engine includes a compressor assembly that is rotationally coupled to a shaft. The engine includes a radial diffuser assembly coupled to a shroud of the compressor assembly and positioned to receive compressed air from a centrifugal impeller. The radial diffuser assembly includes a first arcuate wall and a second wall, and a near axial diffuser coupled to the radial diffuser assembly and positioned to receive the compressed air from the radial diffuser assembly. The gas turbine includes a gas seal coupled between the second wall and a wall of the near axial diffuser, the gas seal configured to prevent the compressed air from passing through the seal while allowing relative motion between the radial diffuser assembly and the near axial diffuser.
    Type: Application
    Filed: December 20, 2013
    Publication date: September 11, 2014
    Applicant: Rolls-Royce North American Technologies, Inc.
    Inventors: Robert A. Ress, JR., Andrew Swift
  • Patent number: 8801365
    Abstract: This hydraulic machine comprises a wheel supported by a shaft (5), the wheel and the shaft being able to rotate about a vertical axis (X5) while a radial hydrostatic or hydrodynamic bearing (100) is formed between, on the one hand, a radial peripheral surface (52) of the shaft and, on the other hand, an internal radial surface (102) of a member (101) that is fixed relative to the vertical axis. The bearing (100) extends between two edges (121, 122) which, in normal operation, constitute regions for the removal of a film of water formed in the bearing. At least one cavity (130) is created in the fixed member (101) and opens onto its internal radial surface (102) near a first edge (122) of the bearing. The machine comprises means (131, 132, 133) for placing the cavity (130) in fluidic communication with a volume (V1) situated outside the bearing near the second edge (121) of the bearing (100).
    Type: Grant
    Filed: July 13, 2009
    Date of Patent: August 12, 2014
    Assignee: Alstom Renewable Technologies
    Inventors: Jean-Francois Bertea, Gerard Vuillerod
  • Patent number: 8794918
    Abstract: A system includes a brush seal segment. The brush seal segment includes a movable support including a head, an extension, and a seal surface, wherein the head is configured to mount in a chamber. The brush seal segment also includes a brush coupled to the movable support along the seal surface, wherein the seal surface consists essentially of the brush. The brush seal segment also includes a biasing element coupled to the movable support, wherein the biasing element is configured to bias the movable support from a first position to a second position to increase a brush clearance in a space between the brush and a rotor, and the movable support is configured to move from the second position to the first position to decrease the brush clearance in response to a fluid flow from the space to the chamber.
    Type: Grant
    Filed: January 7, 2011
    Date of Patent: August 5, 2014
    Assignee: General Electric Company
    Inventors: Sulficker Ali, Saravana Bhava Timmareddy, Seshu Kumar Mahankali, Xiaoqing Zheng
  • Patent number: 8770918
    Abstract: A rotating element is associated with at least one bearing compartment that includes a bearing to support the rotating element. A seal resists leakage of lubricant outwardly of the bearing compartment and allows air to flow from a chamber across the seal and into the bearing compartment. The seal has a seal face facing a rotating face rotating with the rotating element. The seal is a non-contact seal. A gas turbine engine is also disclosed.
    Type: Grant
    Filed: October 15, 2013
    Date of Patent: July 8, 2014
    Assignee: United Technologies Corporation
    Inventors: M. Rifat Ullah, Robert E. Peters
  • Publication number: 20140169960
    Abstract: There is provided a fuel pump (10) which includes an impeller (20) in a disk-like shape; a casing (18) comprised of a pump cover (14) and a pump body (16) that rotatably accommodate the impeller; and a motor section (70) that drives to rotate the impeller; wherein, on at least one of seal portions of the casing (18) and in its place facing to a series of recesses (20b,20c) of the impeller, a recessed shape (35,36) in a micron order is formed in expectation of a swelling amount of the series of recesses (20b,20c) of the impeller (20).
    Type: Application
    Filed: October 13, 2011
    Publication date: June 19, 2014
    Applicant: MITSUBISHI ELECTRIC CORPORATION
    Inventor: Yutaro Hamatani
  • Patent number: 8753079
    Abstract: A mechanical seal is disclosed having a rotatable sealing face and a stationary sealing face that are in opposed relation and arranged to be urged, into contact to form a seal. One of the sealing faces is mounted on a support assembly that includes a biasing device operative to move that sealing face into contact with the other sealing face. In one form of the invention, the biasing device includes one or more resilient members that in use are deformed to provide the biasing force. In a second form of the invention, the support assembly forms part of a fluid barrier of the seal and the biasing device is fluid impervious and forms part of the barrier. In a third form of the invention, the biasing device is exposed to fluid pressure in the chamber and the biasing force increases on increasing the fluid pressure in the chamber.
    Type: Grant
    Filed: March 16, 2010
    Date of Patent: June 17, 2014
    Assignee: Vulco S.A.
    Inventors: Ricardo Abarca Melo, Rodrigo Guzman Castro, Osvaldo Quiroz Venegas
  • Patent number: 8740563
    Abstract: A method of assembling a sealing assembly for use in a turbomachine includes providing a rotatable element that includes an end portion with a plurality of grooves partially extending circumferentially about a portion of an outer surface of the end portion of the rotatable element. The method also includes providing a stationary portion that includes an upper section and a lower section. The method further includes inserting at least a portion of the end portion of the rotatable element into the lower section. The method also includes coupling the upper section to the lower section, thereby defining a rotor shaft cavity. The end portion of the rotatable element at least partially extends through the rotor shaft cavity, thereby defining a clearance between the end portion of the rotatable element and the stationary portion.
    Type: Grant
    Filed: November 22, 2010
    Date of Patent: June 3, 2014
    Assignee: General Electric Company
    Inventors: Sudhakar Neeli, Joshy John
  • Publication number: 20140147271
    Abstract: A gas turbine engine has a pair of components having a high-pressure chamber on one side, and a low pressure chamber on an opposed side. A three-sided seal has one side in sealing contact with each of said components. A third side is associated with a third component. At least one non-metallic wear surface is positioned between one of the three sides of the seal and its respective component.
    Type: Application
    Filed: November 29, 2012
    Publication date: May 29, 2014
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventor: United Technologies Corporation
  • Publication number: 20140140820
    Abstract: A bifurcation aerofoil having a leading edge portion and flanks where the leading edge portion is mounted to an inner wall of the bypass duct using a floating seal which permits circumferential movement of the leading edge. A cowl has a wall that provides the flanks of the aerofoil. On closing of the cowl into its flight position any contact between the flanks and the leading edge portion enables realignment of the leading edge portion to the inner wall of the bypass duct.
    Type: Application
    Filed: November 15, 2013
    Publication date: May 22, 2014
    Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Predrag TODOROVIC
  • Publication number: 20140127012
    Abstract: An oil deflector includes a segment array extending radially from a sleeve portion defining a longitudinal axis and configured for mounting on a shaft. The segment array includes a plurality of segments arranged circumferentially relative to the longitudinal axis and defines at least one oil diverting feature configured to create a pressure differential proximate the segment array or across a surface of the segment array during rotation of the oil deflector about the longitudinal axis. The segment array may define an oil diverting feature configured as a radially tapered peripheral surface, an axially inclined annular surface, at least one slot inclined relative to an annular surface of the array, and/or a combination of these configured to divert oil axially and/or radially from the oil deflector during rotation by the shaft in use.
    Type: Application
    Filed: November 6, 2012
    Publication date: May 8, 2014
    Applicant: GM GLOBAL TECHNOLOGY OPERATIONS LLC
    Inventor: Malay Maniar
  • Publication number: 20140105731
    Abstract: A casing structure for a fluid flow machine, in particular for a gas turbine or an aircraft engine, including an outer casing wall and an inner casing wall, which annularly surround a flow channel of the fluid flow machine and are spaced apart in a radial direction with respect to the flow channel. At least one cavity is formed between the inner and outer casing walls. The cavity is axially divided into at least two regions which are separated from each other by an axial seal in such a way that different pressure conditions are created according to the axial position of these regions, which different pressure conditions correspond to the pressure conditions in the flow channel. A corresponding fluid flow machine such as, for example, an aircraft engine.
    Type: Application
    Filed: October 8, 2013
    Publication date: April 17, 2014
    Inventors: Manfred Feldmann, Janine Sangl, Sebastian Kaltenbach, Joachim Lorenz
  • Patent number: 8696312
    Abstract: A damping system for a gas turbine engine comprises a bearing mounted to a rotor shaft and a support connected to an outer race of the bearing. The support has a wall secured to a casing of the gas turbine engine at a connection portion. The wall has a first surface positioned against a surface of the casing with the first surface being in a non-parallel relation with the rotational axis of the rotor shaft. A cavity is defined in the first surface by a narrowing of a thickness of the wall. The cavity contains a damping fluid to dampen elastic deformation of the wall at the cavity resulting from axial oscillations of the rotor shaft. An abutment is provided to limit an amplitude of the elastic deformation of the wall.
    Type: Grant
    Filed: February 1, 2010
    Date of Patent: April 15, 2014
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Jean Thomassin, Charles Faubert, André D. Leblanc
  • Publication number: 20140099200
    Abstract: A fan structure includes a rotation module, a fixing shaft and an impeller, the rotation module comprises a coupling base, a bearing and a sealing member. The bearing comprises an axial hole, an outer ring wall and a through hole, a slot is recessed from the outer ring wall, the through hole communicates with the slot and the axial hole, and the slot is sealed by the sealing member to form an oil storage space. The fixing shaft penetrates the axial hole, and the through hole communicates with the axial hole and the oil storage space. When the rotation module rotates, lubricants in the oil storage space can flow from the through hole to the axial hole for lubricating the fixing shaft and the axial hole. When the rotation module stops, lubricants in the axial hole reflow to the oil storage space via the through hole to avoid loss.
    Type: Application
    Filed: October 4, 2012
    Publication date: April 10, 2014
    Applicant: ADDA CORP.
    Inventors: Kao-Chuan Huang, Yen-Min Su, Jiun-Shian Guo, Chi-Ping Lai, Ting-Cheng Lan
  • Patent number: 8684663
    Abstract: A steam turbine is provided having a relief groove which is arranged in the region of the equalizing piston and extends in the circumferential direction of the rotor. The relief groove, with regard to an inlet passage, is arranged in the axial upstream direction so that it is arranged on the rotor outside a region in which the steam flow enters the bladed flow path via the inlet passage. The relief groove, with regard to the first blade row, is arranged in a region in which the greatest thermal stresses can arise in the rotor. As an option, the relief groove has a cover for reducing vortex flows, and also devices for reducing heating of the groove or devices for active cooling. The steam turbine allows an increased number of risk-free running up and running down operations of the steam turbine with minimum detriment to the turbine performance.
    Type: Grant
    Filed: September 29, 2010
    Date of Patent: April 1, 2014
    Assignee: Alstom Technology Ltd.
    Inventors: Rabiye Bekyigit, Philipp Brunner, Jian Chen, Rolf Dobler, Jozo Drmic, Andreas Ehrsam, Maurus Herzog, Davor Kriz, Thomas Mokulys, Martin Reigl, Luca Ripamonti, Thomas Schreier, Giorgio Zanazzi