Dynamically Created Seal Patents (Class 415/171.1)
  • Patent number: 9828881
    Abstract: A seal support structure for a turbomachine includes a mounting portion shaped to mount to a stationary structure of a turbomachine and a cylindrical leg portion disposed on the mounting portion extending axially from the mounting portion. The cylindrical leg portion can include a radially extending flange. The flange can extend at an angle of 90 degrees from the end of the cylindrical leg portion. The flange can extend at least partially in an axial direction. The cylindrical leg portion can be formed integrally with the mounting portion. In embodiments, the cylindrical leg portion is not integral with the mounting portion, i.e., the cylindrical leg portion is a separate piece joined to the mounting portion.
    Type: Grant
    Filed: March 19, 2015
    Date of Patent: November 28, 2017
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Seth A. Max, Anthony P. Cherolis, Steven D. Porter, Joshua D. Winn, Gregory E. Reinhardt, Jeffrey J. Lienau
  • Patent number: 9464536
    Abstract: A sealing arrangement for a turbine system includes a bucket having an outer tip and at least one bucket ridge extending radially outwardly from the outer tip, the at least one bucket ridge comprising an abradable material. Also included is a stationary shroud disposed radially outwardly from the outer tip of the bucket. Further included is at least one shroud ridge extending radially inwardly from the stationary shroud toward the outer tip of the bucket, the at least one shroud ridge comprising the abradable material.
    Type: Grant
    Filed: October 18, 2012
    Date of Patent: October 11, 2016
    Assignee: General Electric Company
    Inventors: Xiuzhang James Zhang, Gary Michael Itzel, Ibrahim Sezer
  • Patent number: 9391482
    Abstract: A grease leakage preventing structure is provided for a gear reducer of a dynamoelectric machine with a gear reducer, which is capable of preventing, if soft grease with high consistency is employed in a gear reducer driven at a high speed for high output power, leakage of grease from the reducer toward the dynamoelectric machine, by covering an output shaft of the dynamoelectric machine with a grease blocking member.
    Type: Grant
    Filed: January 15, 2014
    Date of Patent: July 12, 2016
    Assignee: Oriental Motor Co., Ltd.
    Inventor: Shinya Kuwata
  • Patent number: 9115594
    Abstract: An axial flow compressor for a gas turbine engine is disclosed having a casing treatment that includes a shrouded rotor and an airflow member disposed in a passage between a casing and the shrouded rotor. In one form the airflow member is stationary with the casing and in another the airflow member is coupled to rotate with the shrouded rotor. The airflow member can have an airfoil shape in some embodiments. A passage inlet that extracts working fluid and provides it to the passage can be formed between a leading edge of the rotor and a trailing edge. A passage outlet can be formed upstream of the leading edge of the rotor.
    Type: Grant
    Filed: December 22, 2011
    Date of Patent: August 25, 2015
    Assignee: Rolls-Royce Corporation
    Inventor: Michael S. Krautheim
  • Patent number: 9039357
    Abstract: A seal assembly between a disc cavity and a turbine section hot gas path includes a stationary vane assembly and a rotating blade assembly downstream from the vane assembly and including a plurality of blades that are supported on a platform and rotate with a turbine rotor and the platform during operation of the engine. The platform includes a radially outwardly facing first surface, a radially inwardly facing second surface, a third surface, and a plurality of grooves extending into the third surface. The grooves are arranged such that a space is defined between adjacent grooves. During operation of the engine, the grooves guide purge air out of the disc cavity toward the hot gas path such that the purge air flows in a desired direction with reference to a direction of hot gas flow through the hot gas path.
    Type: Grant
    Filed: October 2, 2013
    Date of Patent: May 26, 2015
    Assignee: Siemens Aktiengesellschaft
    Inventor: Ching-Pang Lee
  • 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: 20150110609
    Abstract: An internal combustion engine includes in one aspect a source of a pressurized working medium and an expander. The expander has a housing and a piston, movably mounted within and with respect to the housing, to perform one of rotation and reciprocation, each complete rotation or reciprocation defining at least a part of a cycle of the engine. The expander also includes a septum, mounted within the housing and movable with respect to the housing and the piston so as to define in conjunction therewith, over first and second angular ranges of the cycle, a working chamber that is isolated from an intake port and an exhaust port. Combustion occurs at least over the first angular range of the cycle to provide heat to the working medium and so as to increase its pressure.
    Type: Application
    Filed: October 20, 2014
    Publication date: April 23, 2015
    Inventors: Nikolay Shkolnik, Alexander C. Shkolnik
  • Publication number: 20150098806
    Abstract: A turbine engine assembly is provided. The turbine engine assembly includes a stator assembly and a rotor assembly having a rotor disk coupled to a plurality of rotor blades, the plurality of rotor blades extending radially outward from the rotor disk. The assembly also includes a casing that at least partially circumscribes the plurality of rotor blades. The assembly also includes a dynamic sealing device coupled to the stator assembly. The at least one dynamic sealing device is configured to insert a seal between the casing and the plurality of rotor blades to facilitate reducing a clearance gap defined between the plurality of rotor blades and the casing while the rotor assembly is operating.
    Type: Application
    Filed: October 9, 2013
    Publication date: April 9, 2015
    Applicant: General Electric Company
    Inventor: Michael John Bowman
  • Patent number: 8951008
    Abstract: The invention relates to a compressor blade of a compressor which, along a main axis, comprises a blade base, a platform area and an adjacent blade profile having a profile tip. The blade profile is configured by a convex wall at the suction end and a concave wall at the pressure end opposite the wall at the suction end. These surfaces extend, with respect to a flow medium, from a leading edge to a trailing edge, a profile center line extending in the center between the two. A front face is arranged on the profile tip at an angle to the main axis, a sealing lip at least partially extending from the leading edge to the trailing edge and the blade profile including the sealing lip having a blade profile height extending in the direction of the main axis. In order to allow for an inexpensive compressor blade having improved aerodynamic properties and a modified sealing lip while having the same sealing properties, the height of the sealing lip is less than 2 percent of the height of the blade profile.
    Type: Grant
    Filed: June 20, 2005
    Date of Patent: February 10, 2015
    Assignee: Siemens Aktiengesellschaft
    Inventors: Christian Cornelius, Bernhard Küsters, Stephan Mais, Andreas Peters, Achim Schirrmacher, Lutz Stephan, Bernd van den Toorn
  • Patent number: 8939733
    Abstract: A fan for an engine ventilation system includes a housing defining an inlet and an outlet. A hydraulic motor is coupled to the fan housing and includes a motor housing, motor shaft, and shaft seal disposed between the motor housing and the motor shaft. An impeller assembly is disposed in the housing, as well as a stationary baffle that includes a baffle inner edge disposed axially between the impeller assembly and a second wall of the fan housing. A deflector disc is coupled to the impeller assembly and includes a deflector disc outer edge positioned axially rearward of the baffle inner edge. The deflector disc and baffle direct any hydraulic fluid leaking past the shaft seal away from the impeller assembly to a collection chamber.
    Type: Grant
    Filed: June 22, 2011
    Date of Patent: January 27, 2015
    Assignee: Caterpillar Inc.
    Inventors: Ryan Chiaki Mann, Kalpeshbhai G. Patel, William N. O'Neill
  • Patent number: 8926269
    Abstract: A seal carrier for a seal used between rotating and non-rotating components includes an arcuate sheet metal seal carrier body formed to include a stepped, conical configuration wherein an inner diameter at a forward end is larger than the diameter at an aft end, with plural stepped sections defined by alternating radial and axial portions between the forward end and the aft end. Each axial portion is adapted to carry a seal element, preferably a honeycomb seal. Mounting flanges are provided at the forward end and the aft end of the arcuate sheet metal seal carrier body to enable attachment to the non-rotating component.
    Type: Grant
    Filed: September 6, 2011
    Date of Patent: January 6, 2015
    Assignee: General Electric Company
    Inventors: Daniel Jackson Dillard, Gregory Thomas Foster, Niranjan Gokuldas Pai
  • 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
  • Patent number: 8834095
    Abstract: A bearing support assembly for supporting a bearing assembly within a bearing compartment of a gas turbine engine includes a centering spring and a bearing support member integrally joined together to form a one piece structure. The centering spring connects to the bearing assembly and has a portion that extends conically relative to a centerline axis of the gas turbine engine. The bearing support member extends from the centering spring to connect to an engine case of the gas turbine engine.
    Type: Grant
    Filed: June 24, 2011
    Date of Patent: September 16, 2014
    Assignee: United Technologies Corporation
    Inventor: Todd A. Davis
  • Patent number: 8821115
    Abstract: 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: Grant
    Filed: July 6, 2011
    Date of Patent: September 2, 2014
    Assignee: Rolls-Royce PLC
    Inventors: Adam M. Bagnall, Ross D. Maxwell
  • Patent number: 8801364
    Abstract: An impeller or axial stage compressor disk backface shroud for use with a gas turbine engine is disclosed. The backface shroud includes, but is not limited to, a substantially funnel shaped body having a surface. The substantially funnel shaped body is configured to be statically mounted to the gas turbine engine substantially coaxially with the impeller or axial stage compressor disk. The surface and a backface of the impeller or axial stage compressor disk form a cavity that guides an airflow portion to a turbine when the substantially funnel shaped body is mounted coaxially with the impeller or axial stage compressor disk and axially spaced apart therefrom. The airflow portion has a tangential velocity and a recessed groove in the surface of the backface shroud is oriented generally transversely to the tangential velocity to at least partially interfere with the airflow portion, thus affecting static pressure in the cavity.
    Type: Grant
    Filed: June 4, 2010
    Date of Patent: August 12, 2014
    Assignee: Honeywell International Inc.
    Inventors: Mark C. Morris, Alexander MirzaMoghadam, Khosro Molla Hosseini, Kin Poon, Jeff Howe, Alan G. Tiltman
  • Patent number: 8764380
    Abstract: A rotor blade for a gas turbine engine, comprising an aerofoil having pressure and suction surfaces, leading and trailing edges, and an array of passages at a tip region of the aerofoil. The passages extend from the pressure surface to the suction surface of the aerofoil and are disposed so that the array creates, in operation, a planar jet of gas issuing from the suction surface. The jet is inclined outwardly from the suction surface and towards the tip, and in the direction from the leading edge to the trailing edge. The jet inhibits migration away from the suction surface of a clearance vortex formed by leakage of air over the tip of the rotor blade.
    Type: Grant
    Filed: June 30, 2011
    Date of Patent: July 1, 2014
    Assignee: Rolls-Royce PLC
    Inventors: Neil W. Harvey, Stephane M. M. Baralon
  • 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: 20140112765
    Abstract: A fluidic actuator comprising: a fluid nozzle for delivering fluid and a tube having an open end and a closed end, the open end spaced from the fluid nozzle. Also a pair of electrodes mounted in the tube and spaced apart to create a spark gap therebetween. A voltage source is arranged to supply a voltage across the pair of electrodes wherein the voltage causes plasma formation in the spark gap thereby shortening the effective length of the tube.
    Type: Application
    Filed: September 19, 2013
    Publication date: April 24, 2014
    Applicant: ROLLS-ROYCE PLC
    Inventors: Marko BACIC, Ronald William DANIEL
  • Patent number: 8678756
    Abstract: In accordance with one embodiment of the present disclosure, a method may include installing a first seal around a motor shaft. The method may also include installing a second seal around the motor shaft, wherein the second seal and the first seal may form a hydrodynamic seal when the motor shaft rotates. The method may further include installing a spacer in-between the second seal and the first seal.
    Type: Grant
    Filed: February 8, 2010
    Date of Patent: March 25, 2014
    Assignee: Raytheon Company
    Inventor: Jaime Robledo
  • Patent number: 8657573
    Abstract: A circumferential sealing arrangement is disclosed herein. The circumferential sealing arrangement includes a seal runner operable to be fixed to a structure for concurrent rotation with the structure about an axis. The circumferential sealing arrangement also includes a housing that encircles the seal runner or is encircled by the seal runner. The circumferential sealing arrangement also includes a primary seal element at least partially disposed in the housing. The primary seal element includes a first surface cooperating with a second surface of the seal runner to form a circumferential seal between the primary seal element and the seal runner. The circumferential sealing arrangement also includes a secondary seal element positioned between the housing and the primary seal element on a first side of the primary seal element along the axis of rotation. A second side of the primary seal element along the axis of rotation opposite the first side seals against the housing.
    Type: Grant
    Filed: April 13, 2010
    Date of Patent: February 25, 2014
    Assignee: Rolls-Royce Corporation
    Inventor: John Munson
  • Publication number: 20140003917
    Abstract: The invention relates to a hydrodynamic sliding bearing of a shaft (2), in particular of a magnetic coupling pump (1), wherein the hydrodynamic sliding bearing (4) comprises a clamping sleeve (7) disposed between bearing sleeves (6), wherein the bearing sleeves (6) are each mounted with their bearing front side (8) on an axial bearing element (9). The hydrodynamic sliding bearing (4) is characterized in that the bearing sleeve (6) and the clamping sleeve (7) have on their respective front sides (11, 12) a respectively correspondingly designed spherical region (18, 19) which intermesh, wherein the clamping sleeve (7) has at least one concentric groove (28, 29, 31) and wherein the axial bearing element (9) has a recess (42) adapted to the bearing front side (8) of the bearing sleeve (6).
    Type: Application
    Filed: March 1, 2012
    Publication date: January 2, 2014
    Inventors: Günther Schneider, Michael Westib, Dirk Koep
  • Patent number: 8545174
    Abstract: A nose dome for a turbomachine rotor is provided. The turbomachine rotor has an impeller which is arranged in an overhung fashion with respect to a bearing point of the turbomachine rotor. The nose dome can be connected axially to the impeller in order to guide an axial inflow and/or outflow of the impeller, and includes a coupling device. The impeller and the nose dome can be mechanically coupled radially with the coupling device, such that the vibration behavior of the turbomachine rotor may be influenced. The turbomachine with the turbomachine rotor including the nose dome is also provided. The impeller and nose dome are coupled radially using the coupling device, such that the vibration of the turbomachine rotor is damped.
    Type: Grant
    Filed: June 5, 2008
    Date of Patent: October 1, 2013
    Assignee: Siemens Aktiengesellschaft
    Inventors: Thomas Mönk, Axel Spanel, Wolfgang Zacharias
  • Publication number: 20130227931
    Abstract: A turbopump for feeding a low-thrust rocket engine comprises a pump, a turbine, and a common rotary shaft connected to the pump and to the turbine. First and second bearings closer respectively to the pump and to the turbine serve to support the common shaft. The second bearing is a hydrodynamic bearing connected to a gas supply source, and the turbopump also includes at least one dynamic sealing gasket around the shaft and interposed between the first and second bearings.
    Type: Application
    Filed: August 31, 2011
    Publication date: September 5, 2013
    Applicant: Snecma
    Inventors: Francois Danguy, Laurent Fabbri, Sebastien Guingo
  • Publication number: 20130183176
    Abstract: The present invention provides a rotary blood pump with both an attractive magnetic axial bearing and a hydrodynamic bearing. In one embodiment according to the present invention, a rotary pump includes an impeller assembly supported within a pump housing assembly by a magnetic axial bearing and a hydrodynamic bearing. The magnetic axial bearing includes at least two magnets oriented to attract each other. One magnet is positioned in the spindle of the pump housing while the other is disposed within the rotor assembly, proximate to the spindle. In this respect, the two magnets create an attractive axial force that at least partially maintains the relative axial position of the rotor assembly. The hydrodynamic bearing is formed between sloping surfaces that form tight clearances below the rotor assembly.
    Type: Application
    Filed: January 11, 2013
    Publication date: July 18, 2013
    Applicant: THORATEC CORPORATION
    Inventor: THORATEC CORPORATION
  • Publication number: 20130170944
    Abstract: According to one aspect of the invention, a turbine assembly includes a first bucket with a first slashface and a second bucket including a recess formed in a second slashface of the second bucket, wherein the second slashface is adjacent to the first slashface when the first bucket is positioned adjacent to the second bucket. The turbine assembly also includes a pin configured to be placed in the recess, wherein the pin is magnetically urged toward the first slashface to reduce fluid flow between the first and second buckets.
    Type: Application
    Filed: January 4, 2012
    Publication date: July 4, 2013
    Applicant: General Electric Company
    Inventors: Mahesh Pasupuleti, Shadab Ali, Mohankumar Banakar, Viswanathan Venkatachalapathy
  • Patent number: 8434998
    Abstract: A seal assembly for a compressor includes a static member fixedly disposed within a compressor casing and having an end surface and a rotatable separator coupled with a compressor shaft and spaced from the static member. The separator has an axial end with a radial end surface located adjacent to the static member end surface such that a clearance space is defined therebetween. The separator has a plurality of openings extending inwardly from the end surface and spaced about the shaft axis such that land surface sections are defined on the end surface. The land surface sections or/and the openings are configured to prevent fluid flow radially inwardly through the clearance space. The static member has two annular walls receiving an end portion of the separator, with annular ridges providing labyrinth seals disposed against inner and outer surfaces of the separator, and an annular deflector with an angled deflector surface.
    Type: Grant
    Filed: September 17, 2007
    Date of Patent: May 7, 2013
    Assignee: Dresser-Rand Company
    Inventor: William C. Maier
  • Patent number: 8430628
    Abstract: A pressure balance seal includes a sealing surface facing an inward radial direction, and a stator interface comprising at least one surface interfacing with a stator. The pressure balance seal further includes a friction reducing feature. The friction reducing feature includes a cavity on the sealing surface. The cavity is configured to receive a fluid such that a normal force acting on the pressure balance seal is counterbalanced by a force generated by a pressure of the fluid.
    Type: Grant
    Filed: December 4, 2009
    Date of Patent: April 30, 2013
    Assignee: General Electric Company
    Inventors: Norman Arnold Turnquist, Keith Michael Parker, Xiaoqing Zheng, Rodrigo Rodriguez Erdmenger, Robbert Christiaan Pannekeet, Alexander Kimberley Simpson, Biao Fang
  • Patent number: 8430630
    Abstract: A rotary coupling having a first element and a coaxial second element, the first and second elements being rotatable relative to each other and defining an annular passage between radially facing walls thereof. The coupling has a sealing ring at an end of the annular passage, the sealing ring being mounted to the wall of the first element and rotating relative to the second element, and having an active configuration in which the sealing ring is urged against the wall of the second element to seal the end of the annular passage, and a return configuration in which the sealing ring does not seal the end of the annular passage. A control system is used to apply a variable load to the sealing ring, wherein the sealing ring moves between the active and return configurations in response to variation in the applied load.
    Type: Grant
    Filed: July 2, 2010
    Date of Patent: April 30, 2013
    Assignee: Rolls-Royce PLC
    Inventor: Antony Morgan
  • Patent number: 8388309
    Abstract: A sealing apparatus in a gas turbine. The sealing apparatus includes a seal housing apparatus coupled to a disc/rotor assembly so as to be rotatable therewith during operation of the gas turbine. The seal housing apparatus comprises a base member, a first leg portion, a second leg portion, and spanning structure. The base member extends generally axially between forward and aft rows of rotatable blades and is positioned adjacent to a row of stationary vanes. The first leg portion extends radially inwardly from the base member and is coupled to the disc/rotor assembly. The second leg portion is axially spaced from the first leg portion, extends radially inwardly from the base member, and is coupled to the disc/rotor assembly. The spanning structure extends between and is rigidly coupled to each of the base member, the first leg portion, and the second leg portion.
    Type: Grant
    Filed: November 3, 2009
    Date of Patent: March 5, 2013
    Assignee: Siemens Energy, Inc.
    Inventors: John Joseph Marra, Brian J. Wessell, George Liang
  • Publication number: 20130017069
    Abstract: Disclosed is a turbine, a turbine seal structure, and a process of servicing a turbine. The turbine includes the seal structure. The seal structure is mechanically secured within the hot gas path of the turbine. The process of servicing includes positioning the seal structure within the hot gas path of the turbine and mechanically securing the seal structure within the turbine.
    Type: Application
    Filed: July 13, 2011
    Publication date: January 17, 2013
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: George Albert GOLLER, Dennis William CAVANAUGH, Matthew LAYLOCK
  • Patent number: 8353671
    Abstract: A fan with pressurizing structure includes a rotor having a main body, blades spaced on the main body, a magnetic body annularly mounted in the main body, and a shaft axially connected to an inner side of the main body; a frame having a sleeve and at least one bearing rotatably received in the sleeve, and an opposing end of the shaft being inserted into the bearing; a stator assembly fitted around the sleeve and including silicon steel plates and a base plate; and a plurality of first pressurizing sections selectively provided on one of the base plate and an end face of the magnetic body. With the first pressurizing sections, deposition of moisture and salt fog in the sleeve and the rotor can be prevented to avoid corroded and damaged bearing and rotor shaft, and the service life of the whole fan is increased.
    Type: Grant
    Filed: October 15, 2009
    Date of Patent: January 15, 2013
    Assignee: Asia Vital Components Co., Ltd.
    Inventors: Bor-Haw Chang, Shu-Fan Liu, Chang-Hsien Liu
  • Patent number: 8333557
    Abstract: An apparatus is provided and includes a first member with a flow diverting member extending from a surface thereof and a second member disposed proximate to the first member with a clearance gap area defined between a surface of the second member and a distal end of the flow diverting member such that a fluid path, along which fluid flows from an upstream section and through the clearance gap area, is formed between the surfaces of the first and second members. The second member is formed to define dual vortex chambers at the upstream section in which the fluid is directed to flow in vortex patterns prior to being permitted to flow through the clearance gap area.
    Type: Grant
    Filed: October 14, 2009
    Date of Patent: December 18, 2012
    Assignee: General Electric Company
    Inventors: Joshy John, Sanjeev Kumar Jain, Sachin Kumar Rai
  • Publication number: 20120294707
    Abstract: A steam seal system is disclosed. In one embodiment, the steam seal system includes: a low pressure steam turbine positioned on a shaft; a pair of end packings surrounding the shaft, each of the pair of end packings located proximate an axial end of the low pressure steam turbine along the shaft; and an pair of extraction conduits fluidly connected to the low pressure steam turbine and the shaft, the pair of extraction conduits connected to the shaft at a location axially outward of the pair of end packings and the low pressure steam turbine.
    Type: Application
    Filed: May 16, 2011
    Publication date: November 22, 2012
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Nestor Hernandez Sanchez, Kamlesh Mundra
  • Publication number: 20120251290
    Abstract: An aspirating face seal includes a primary seal, a secondary seal, and a biasing device. The primary seal includes a first seal component and a second seal component. The first seal component is configured to be coupled to a rotor and rotatable with the rotor. The secondary seal includes a plurality of flexible elements and configured to be disposed between the second seal component and a stator housing. A biasing device is coupled to the second seal component such that the second seal component is biased along an axial direction away from the first seal component during a non-operating condition.
    Type: Application
    Filed: March 31, 2011
    Publication date: October 4, 2012
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Norman Arnold Turnquist, Rodrigo Rodriguez Erdmenger, Xiaoqing Zheng, Robbert Christiaan Pannekeet, Keith Michael Parker
  • Publication number: 20120171022
    Abstract: Certain embodiments of the invention may include systems, methods, and apparatus for providing a turbine interstage rim seal. According to an example embodiment of the invention, a method is provided for sealing a turbine rotor-bucket interface. The method can include linking a first portion of one or more rim seal segments with one or more flow path seal segments. The method includes rotating the one or more rim seal segments, upon application of centrifugal force, to displace a second portion of the one or more rim seal segments; and sealing at least a portion of a gap between a rotor and a bucket associated with a turbine with at least one or more rotated rim seal segments.
    Type: Application
    Filed: January 4, 2011
    Publication date: July 5, 2012
    Applicant: GENERAL ELECTRIC COMPANY
    Inventor: Matthew Troy Hafner
  • Patent number: 8167545
    Abstract: Self-balancing face seals and gas turbine engine systems involving such seals are provided. In this regard, a representative self-balancing face seal assembly includes: a rotatable seal runner having a first seal runner face and an opposing second seal runner face; a first face seal operative to form a first seal with the first seal runner face, the first face seal being one of a hydrostatic seal and a hydrodynamic seal; and a second face seal operative to form a second seal with the second seal runner face, the first face seal being one of a hydrostatic seal and a hydrodynamic seal.
    Type: Grant
    Filed: February 27, 2008
    Date of Patent: May 1, 2012
    Assignee: United Technologies Corp.
    Inventors: Jorn A. Glahn, Peter M. Munsell
  • Patent number: 8113768
    Abstract: A mid-turbine frame assembly includes a mid-turbine frame, a ring structure and a plurality of actuated struts. The ring structure surrounds the mid-turbine frame, and has an interior surface and an exterior surface. The actuated struts connect the ring structure to the mid-turbine frame. The actuated struts are strain actuated so that the actuated struts reposition the ring structure in response to a strain.
    Type: Grant
    Filed: July 23, 2008
    Date of Patent: February 14, 2012
    Assignee: United Technologies Corporation
    Inventors: Nagendra Somanath, Keshava B. Kumar, Christopher M. Dye
  • Patent number: 8109716
    Abstract: Gas turbine engine systems involving hydrostatic face seals with anti-fouling provisioning are provided. In this regard, a representative turbine assembly for a gas turbine engine comprises: a turbine having a hydrostatic seal; the hydrostatic seal having a seal face, a seal runner, a carrier, and a biasing member; the seal face and the seal runner defining a high-pressure side and a lower-pressure side of the seal; the carrier being operative to position the seal face relative to the seal runner; and the biasing member being located on the lower-pressure side of the seal and being operative to bias the carrier such that interaction of the biasing member and gas pressure across the seal causes the carrier to position the seal face relative to the seal runner.
    Type: Grant
    Filed: August 17, 2007
    Date of Patent: February 7, 2012
    Assignee: United Technologies Corp.
    Inventors: Jorn A. Glahn, Peter M. Munsell
  • Patent number: 8109721
    Abstract: A bearing arrangement for a turbine rotor of a turbine is adapted to be mounted in a drill string and to be driven by the flow of drilling fluid. The bearing arrangement includes a turbine chamber surrounding the turbine rotor and having an inflow and an outflow, a stator on which the turbine rotor is rotatably mounted, and a cavity formed between the turbine rotor and the stator and accommodating at least one radial plain bearing and being separated from the turbine chamber by an axial plain bearing constructed as a bearing ring seal and by a conveyor screw which is disposed on the turbine rotor and operates to convey from the cavity to the turbine chamber.
    Type: Grant
    Filed: February 11, 2008
    Date of Patent: February 7, 2012
    Assignee: Weatherford Energy Services GmbH
    Inventors: Helmut Winnacker, Uwe Draeger
  • Patent number: 8105024
    Abstract: A seal assembly for a gas turbine is arranged in grooves of a rotor heat shield having several bends. The assembly comprises four seal portions overlapping one another and extending in the axial, radial, and circumferential direction with respect to the turbine rotor. A holding means retains the radial sections of one seal portion allowing a limited movement of said seal portion independent of another seal portion. The independent movement assures contact of the individual seal portions with all mating surfaces of the rotor heat shield and improved sealing function regardless of displacements of the rotor heat shield and tolerances of turbine parts.
    Type: Grant
    Filed: September 24, 2008
    Date of Patent: January 31, 2012
    Assignee: Alstom Technology Ltd
    Inventors: Alexander Khanin, Arkadi Fokine, Maxim Konter, Sergey Vorontsov
  • Patent number: 8105021
    Abstract: Gas turbine engine systems involving hydrostatic face seals with integrated back-up seals are provided. In this regard, a representative seal assembly for a gas turbine engine includes: a stator assembly and a rotor assembly configured to operatively engage each other to form a first seal and a second seal; the first seal being provided by a hydrostatic seal having a seal face and a seal runner; and the second seal being provided by a back-up seal such that responsive to a failure of the first seal, the back-up seal maintains at least a portion of a pressure differential established by the first seal prior to the failure.
    Type: Grant
    Filed: August 20, 2007
    Date of Patent: January 31, 2012
    Assignee: United Technologies Corp.
    Inventors: Jorn A. Glahn, Peter M. Munsell
  • Patent number: 8079806
    Abstract: A turbine seal member for use in a gas turbine engine includes a turbine seal substrate having a gas-path side and a ceramic layer disposed on the gas-path side that includes a plurality of mechanical indentations.
    Type: Grant
    Filed: November 28, 2007
    Date of Patent: December 20, 2011
    Assignee: United Technologies Corporation
    Inventors: Susan M. Tholen, Christopher W. Strock
  • Publication number: 20110135453
    Abstract: A leaf seal 10 in a rotary machine is located between a higher pressure region 14 and a lower pressure region 16 of the machine. Blow-down forces are greater on the lower pressure side 16 of the leaf seal 10 than on its higher pressure side 14, resulting in greater inward deflection of the leaves 20 on the lower pressure side of the seal than on its higher pressure side, leading in turn to greater wear of the leaves and the contacting rotor surface 44 on the lower pressure side 16 of the seal. To counteract this, the free ends 36 of the leaves 20 can be given a tapered profile 42 to gradually reduce the length of each leaf 20 over its width ‘w’ from its higher pressure side 14 to its lower pressure side 16, so that the leaves 20 are free to deflect under the blow-down forces by the amount of their reduction in length (a maximum of ‘x’), before they contact the rotor surface.
    Type: Application
    Filed: January 21, 2011
    Publication date: June 9, 2011
    Inventor: Neil Howes
  • Patent number: 7938616
    Abstract: A dynamic sealing system between two coaxial rotary shafts respectively comprising an inner shaft and an outer shaft. Connected to the inner shaft, the system comprises a sectorized annular assembly of wipers that are movable under the effect of centrifugal force, and an annular receptacle for liquid arranged in the inside surface of the outer shaft.
    Type: Grant
    Filed: October 5, 2007
    Date of Patent: May 10, 2011
    Assignee: SNECMA
    Inventors: Laurent Gille, Serge Rene Morreale
  • Publication number: 20110085892
    Abstract: An apparatus is provided and includes a first member with a flow diverting member extending from a surface thereof and a second member disposed proximate to the first member with a clearance gap area defined between a surface of the second member and a distal end of the flow diverting member such that a fluid path, along which fluid flows from an upstream section and through the clearance gap area, is formed between the surfaces of the first and second members. The second member is formed to define dual vortex chambers at the upstream section in which the fluid is directed to flow in vortex patterns prior to being permitted to flow through the clearance gap area.
    Type: Application
    Filed: October 14, 2009
    Publication date: April 14, 2011
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Joshy John, Sanjeev Kumar Jain, Sachin Kumar Rai
  • Publication number: 20110081236
    Abstract: The static seal (30) includes a rotary seal body (32) comprising an annular base portion (34) which is drivingly mountable on a rotary component such as a shaft and an annular cantilever portion (40) connected at one end to the base portion (34). The seal (30) 5 further includes a rotary seal face (48) and circumferential weights (44) connected to the cantilever portion (40). The seal is configured to dilate under centrifugal force to provide a running clearance between the rotary seal face and a complementary static seal face with which the rotary seal face is in contact when the rotary seal body (28) is stationary. The rotary seal body is further configured so as to facilitate the breaking up of slurry which may set around the seal when the pump (10) of which the seal forms part is inoperative.
    Type: Application
    Filed: July 24, 2008
    Publication date: April 7, 2011
    Inventor: Siegfried Geldenhuys
  • Patent number: 7918643
    Abstract: A compressor of a gas turbine engine comprises blades 2, 4 provided on blade platforms 8, 12 of a rotor. Stator vanes 20 lie between the blades 2, 4 and are connected to a vane support structure 22. Sealing rings 38 are secured to the vane support structure 22 to restrict air flow into stator wells 36 on each side of the vane support structure 22. The sealing rings 38 are made from a flexible material so that they deflect on installation of the vane support structure 22 in a direction radially inwards between the adjacent blade platforms 8, 12.
    Type: Grant
    Filed: June 4, 2007
    Date of Patent: April 5, 2011
    Assignee: Rolls-Royce plc
    Inventor: Kevin J Weaver
  • Patent number: 7878756
    Abstract: In one embodiment, a method for controlling seal clearance in a turbine engine includes positioning a seal ring within a turbine engine, the seal ring having an inner annular surface and an outer annular surface, the inner annular surface and the outer annular surface both being circular but non-concentric, rotating the seal ring within the engine until the seal ring is placed in an aligned orientation at which a center of a circle that defines the inner annular surface coincides with a centerline of the engine, and securing the seal ring while in the aligned orientation.
    Type: Grant
    Filed: October 31, 2007
    Date of Patent: February 1, 2011
    Assignee: United Technologies Corporation
    Inventors: Todd Davis, Jennifer Reid
  • Publication number: 20100254805
    Abstract: A gas turbine inner flow path cover piece for a gas turbine a first turbine wheel and a second turbine wheel is provided is provided. The gas turbine inner flow path cover piece can include a main body having an first surface and a second surface, side pieces disposed on the first surface of the main body and mating pairs disposed on the second surface of the main body.
    Type: Application
    Filed: April 2, 2009
    Publication date: October 7, 2010
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Andres Jose Garcia-Crespo, Bradley Taylor Boyer, John Wesley Harris, JR., Brian Denver Potter, Ian David Wilson
  • Publication number: 20100098530
    Abstract: A compressor for a gas turbine, in particular an aircraft gas turbine, has a rotor hub carrying rotor blades, a stator equipped with stator vanes, a shroud associated to the stator vanes, and an arrangement providing sealing between the shroud and rotor hub to prevent leakage. To achieve almost complete suppression of leakage air and, concurrently, simplification of design and manufacture, the sealing arrangement (20) between the shroud (8) and rotor hub (3) is formed by a discharge arrangement (23) for leakage air.
    Type: Application
    Filed: October 9, 2009
    Publication date: April 22, 2010
    Applicant: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventors: Carsten CLEMEN, Jens ORTMANNS