Labyrinth Seal Patents (Class 415/174.5)
  • Patent number: 9920626
    Abstract: A rotor disc (1) for a turbomachine, including a radial flange (2) that includes a plurality of fastening holes (3), and a plurality of scallops (4) forming notches in the flange (2), and being separated by inter-scallop flange portions (7). The flange alternatively has, in its circumferential direction: a fastening hole (3) and an inter-scallop flange portion (7) arranged in the radial extension of the fastening hole (3), and a scallop (4), in such a way that one or more of the scallops (47, 48, 49; 42, 45-47, 48-411, 414) has a volume greater than the volume of each of the other scallops (41-46, 410-414; 41, 43, 44, 412, 413), and one or more of the inter-scallop flange portions (73) has a volume less than the volume of each of the other inter-scallop flange portions (71, 72, 74), in order to balance said disc (1). A turbomachine including that rotor disc and a method for balancing a turbomachine rotor disc are also disclosed.
    Type: Grant
    Filed: May 18, 2015
    Date of Patent: March 20, 2018
    Assignee: SNECMA
    Inventors: Pascal Casaliggi, Remi Bourion, Thierry Capolungo
  • Patent number: 9540955
    Abstract: A stator assembly or a stator stage is disclosed. The stator assembly includes an endless case that is coupled to or includes at least one lug for engaging an anti-rotation stator segment. The anti-rotator segment includes one curved side edge and one straight or linear side edge. The case also accommodates a plurality of middle stator segments, each having curved side edges on both sides. Finally, a third type of stator segment is a “neighbor” stator segment with one curved side edge and one linear side edge that abuttingly engages the linear side edge of the anti-rotation stator segment. The straight or linear side edges of the anti-rotation stator segments and the neighbor stator segments enable an endless case to be loaded with stator segments from an axial direction. None of the stator segments need to be installed from a radial direction.
    Type: Grant
    Filed: May 9, 2012
    Date of Patent: January 10, 2017
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: Mark David Ring
  • Patent number: 9103224
    Abstract: A sealing assembly for use with a rotating machine is described herein. The rotating machine includes a stator casing that includes a radially inner surface that defines a cavity therein, and a rotor positioned within the cavity and spaced inwardly from the stator inner surface. The sealing assembly includes a support ring coupled to the stator casing, and a plurality of plate members coupled to the support ring and oriented circumferentially about the rotor. A resistance member extends inwardly from the support ring towards the rotor outer surface. The resistance member is coupled to the support ring and extends through each plate member of the plurality of plate members. At least one rotor land is defined circumferentially about the rotor outer surface. Each plate member is oriented adjacent the at least one rotor land.
    Type: Grant
    Filed: December 29, 2011
    Date of Patent: August 11, 2015
    Assignee: General Electric Company
    Inventors: Ajay Keshava Rao, Hrishikesh Vishvas Deo, Hemant Vinayak Gedam, Vishwas Kumar Pandey
  • Patent number: 9016692
    Abstract: In sealing rings for a labyrinth seal that are arranged on a rotationally symmetrical component and in frictional contact with a stationary run-in layer, a part of the sealing ring (8) that contacts the run-in layer is in the form of a wear protection ring segment (15) that is built up on a truncated sealing ring (14) and which includes a metal matrix (16) with wear protection particles (13) embedded therein. The manufacture of the wear protection ring segment is carried out by laser build-up welding, wherein the proportion of wear protection particles contained in the metal powder flow supplied to the laser beam can be controlled and increased in an edge or tip region of the sealing ring.
    Type: Grant
    Filed: November 24, 2010
    Date of Patent: April 28, 2015
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Thomas Haubold, Andreas Kohns
  • Publication number: 20150104291
    Abstract: A seal assembly for sealing a fluid passageway from contaminants is disclosed. The fluid passageway is formed by a rotating shaft entering an opening in a housing. The fluid passageway connects an interior of the housing, and any exterior of the housing. The seal assembly includes a first sealing member and a second sealing member, which divides the fluid passage into an interior section, an open section, and a sealed section. The interior section is exposed to the interior of the housing. The sealed section is fluidly sealed between the interior section and the open section. A sensor is disposed within the sealed section. The sensor is configured to sense the contaminants within the sealed section and is electronically coupled to a controller configured to send an alarm signal. The sensor is a moisture sensor and extends into an annular recess formed in the stationary member.
    Type: Application
    Filed: October 9, 2014
    Publication date: April 16, 2015
    Inventors: Randy J. Kosmicki, Michael L. Viken
  • Patent number: 8984895
    Abstract: A method and apparatus are disclosed for a gas turbine spool design combining metallic and ceramic components in a way that controls clearances between critical components over a range of engine operating temperatures and pressures. In a first embodiment, a ceramic turbine rotor rotates just inside a ceramic shroud and separated by a small clearance gap. The ceramic rotor is connected to a metallic volute. In order to accommodate the differential rates of thermal expansion between the ceramic rotor and metallic volute, an active clearance control system is used to maintain the desired axial clearance between ceramic rotor and the ceramic shroud over the range of engine operating temperatures. In a second embodiment, a ceramic turbine rotor rotates just inside a ceramic shroud which is part of a single piece ceramic volute/shroud assembly.
    Type: Grant
    Filed: July 11, 2011
    Date of Patent: March 24, 2015
    Assignee: ICR Turbine Engine Corporation
    Inventors: James B. Kesseli, Matthew Stephen Baldwin
  • Patent number: 8979480
    Abstract: A plurality of blades are studded in a rotor disc integrated with the rotor along the circumferential direction of the rotor, a plurality of vanes are attached to a casing covering the rotor along the circumferential direction of the rotor, and an internal diaphragm disposed on rotor-side surfaces of the vanes in such a way that the internal diaphragm faces the rotor disc. The vanes and the blades adjacent to each other in the axial direction of the rotor form a turbine stage. A rotor-side cooling path is formed through the rotor disc in the axial direction of the rotor, and a diaphragm-side cooling path is formed through the internal diaphragm in the axial direction of the rotor, and a cooling medium flowing through the rotor-side cooling path diverts into the diaphragm-side cooling path and a labyrinth flow path provided between the internal diaphragm and the rotor.
    Type: Grant
    Filed: January 15, 2010
    Date of Patent: March 17, 2015
    Assignee: Kabushiki Kaisha Toshiba
    Inventors: Asako Inomata, Katsuya Yamashita, Kazuhiro Saito, Takao Inukai, Kazutaka Ikeda
  • Patent number: 8967957
    Abstract: A rotating airfoil component equipped with one or more angel wings that inhibit the ingress of a hot working fluid into interior regions of a turbomachine in which the component is installed. The component includes an airfoil and a feature for mounting the component to enable rotation of the component within the turbomachine. An angel wing projects from the component to have a first surface facing the airfoil, an oppositely-disposed second surface facing the mounting feature, and at least one lateral surface therebetween. A thermal-insulating coating system is present on the first surface to inhibit heat transfer from the working fluid to the angel wing but not on the second or lateral surfaces so as not to inhibit heat transfer from the second and lateral surfaces of the angel wing.
    Type: Grant
    Filed: November 3, 2011
    Date of Patent: March 3, 2015
    Assignee: General Electric Company
    Inventors: Gary Michael Itzel, Christopher Michael Penny, Aaron Ezekiel Smith, Kevin Leon Bruce
  • Publication number: 20150040566
    Abstract: A helical seal system includes a first component, and a second component rotatable relative to the first component. The second component extends from a high pressure portion to a low pressure portion through an intermediate portion. A helical seal is provided on the intermediate portion of the second component. The helical seal includes at least one thread component having a pitch that is configured and disposed to draw fluids from the low pressure portion toward the high pressure portion when the second component is rotated.
    Type: Application
    Filed: August 6, 2013
    Publication date: February 12, 2015
    Applicant: General Electric Company
    Inventors: Radu Ioan Danescu, David Martin Johnson
  • Publication number: 20150040567
    Abstract: A turbine assembly is disclosed herein. The turbine assembly may include a rotor with at least one bucket extending radially therefrom. The turbine assembly also may include a stator assembly positioned adjacent to the at least one bucket. Moreover, the turbine assembly may include a seal assembly. The seal assembly may include a first flange extending in a substantially axial direction from the at least one bucket. The seal assembly also may include a second flange extending from the stator assembly in the substantially axial direction opposite the first flange. The second flange may include at least one protuberance projecting towards the first flange.
    Type: Application
    Filed: August 8, 2013
    Publication date: February 12, 2015
    Applicant: General Electric Company
    Inventors: Guoqiang Lu, Xiaoqing Zheng, Jong Youn Pak
  • Patent number: 8950069
    Abstract: 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: Grant
    Filed: December 21, 2007
    Date of Patent: February 10, 2015
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventor: Robert A. Ress, Jr.
  • Publication number: 20150037146
    Abstract: To reduce the amount of exhaust gas leaking through the inlet side of the turbine wheel and the back face to the brazed portion and to suppress decrease in strength of the brazed portion due to increase in the temperature of the brazed portion in operation, a turbocharger having a turbine rotor including a turbine wheel and a shaft which are joined to each other with a brazing material comprises: a turbine housing 3; a bearing housing 10; and a back plate 11 disposed on a back face side of the turbine wheel 5 and along the back face with a space; the back plate 11 comprising: a fixing portion 11a formed in an outer peripheral portion of the back plate 11, the back plate 11a fixed in a joint portion of the turbine housing 3 and the bearing housing 10; and an opening portion 35 formed in an inner peripheral portion of the back plate 11, into which an cylindrical flange portion 10b is inserted with a space; wherein a narrowed portion 36 is formed between the back face of the turbine wheel 5 and a lateral face of
    Type: Application
    Filed: February 20, 2013
    Publication date: February 5, 2015
    Inventors: Hideki Yamaguchi, Takashi Arai, Takao Yokoyama
  • 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: 8932001
    Abstract: Certain embodiments of the invention may include systems, methods and apparatus for providing a labyrinth seal. In an example embodiment, a method is provided for sealing a flow path between a stationary element and a rotating element of a turbomachine. The method can include disposing at least one fixture on an inner surface of a stationary element associated with the turbomachine; disposing a packing ring linked via a spring element to the fixture wherein the packing ring comprises at least one bore; and disposing, according to a predetermined profile, a plurality of interdigitated packing ring teeth and rotor teeth intermediate to the packing ring and the rotating element; wherein the bore, packing ring teeth, and rotor teeth, cooperate to counter a moment associated with one or more axial forces.
    Type: Grant
    Filed: September 6, 2011
    Date of Patent: January 13, 2015
    Assignee: General Electric Company
    Inventors: Xiaoqing Zheng, Hrishikesh Deo, Binayak Roy
  • Publication number: 20140369821
    Abstract: The present invention relates to a shaft earth and/or sealing assembly for use with housed rotating equipment such as electric motors to earth the shaft and also provide an IP69K-rated seal that is flame and spark resistant.
    Type: Application
    Filed: December 19, 2012
    Publication date: December 18, 2014
    Inventor: Peter Finck
  • Patent number: 8911205
    Abstract: 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: Grant
    Filed: October 12, 2011
    Date of Patent: December 16, 2014
    Assignee: United Technologies Corporation
    Inventors: William M. Rose, Robert A. Charbonneau
  • Publication number: 20140356145
    Abstract: Embodiments of the present disclosure are directed towards a seal assembly including a first seal and a second seal, wherein the first seal and the second seal axially abut one another within a retaining bore of a compressor, and cooperatively form an outer radial contour of the seal assembly that is retained by the retaining bore.
    Type: Application
    Filed: May 30, 2013
    Publication date: December 4, 2014
    Inventors: Thomas Edward Gerber, Jonathan David Clemons
  • Patent number: 8864443
    Abstract: A sealing structure in which free-cutting spacers on a sealing base plate and sealing fins on a rotor are opposed to each other is provided. The sealing base plate is disposed so as to be movable in an axial direction of the rotor. When a steam turbine increases in load, a pressure head moves in an axial steam-pressure loading direction of the rotor and the sealing base plate connected to the pressure head moves in the axial steam-pressure loading direction. Since the free-cutting spacers at positions opposed to those of the sealing fins existing after the movement of the sealing base plate are maintained in a non-contact state, clearances between the sealing fins and the free-cutting spacers are dimensionally minimized.
    Type: Grant
    Filed: July 13, 2011
    Date of Patent: October 21, 2014
    Assignee: Hitachi, Ltd.
    Inventors: Kenjiro Narita, Haruyuki Yamazaki, Takeshi Kudo, Kenichi Murata
  • Patent number: 8845284
    Abstract: 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: Grant
    Filed: July 2, 2010
    Date of Patent: September 30, 2014
    Assignee: General Electric Company
    Inventors: Thomas Raymond Farrell, Gary Charles Liotta, Ian David Wilson
  • Patent number: 8844936
    Abstract: According to one embodiment of the disclosure, an annular seal generally includes a hollow member having two ends and an inner surface. The hollow member has a number of depressions formed in and extending around its inner surface. Each of the depressions having a depth that is a function of its distance from one of the two ends.
    Type: Grant
    Filed: December 9, 2011
    Date of Patent: September 30, 2014
    Assignee: The Texas A&M University System
    Inventor: Dara W. Childs
  • Publication number: 20140271150
    Abstract: The present invention relates to a labyrinth disk for a turbomachine comprising a hub, a web and a frustoconical peripheral portion, having on one face labyrinth seal teeth and on the other face radial ribs (78?) the flanks (78?f) of which delimit, between one another, channels (80) which open out at the periphery of the disk, the width of said channels decreasing from the base of the frustoconical portion to the opening at the periphery, wherein the ribs are split close to the periphery, a recess (79?) being created between the two flanks (78?f) of one and the same rib.
    Type: Application
    Filed: July 17, 2013
    Publication date: September 18, 2014
    Inventors: Emilie POUZET, Didier Pasquiet, Frederic Lespinasse
  • Patent number: 8834096
    Abstract: In an axial flow gas turbine efficient cooling and a long life-time can be achieved by providing the outer blade platforms (45) with a plurality of outer teeth (46a-c) running parallel to each other in the circumferential direction and being arranged one after the other in the direction of the hot gas flow. The teeth (46a-c) are divided into first and second teeth (46a; 46b-c), the second teeth (46b-c) being located downstream of the first teeth (46a), the first teeth (46a) are opposite to a downstream projection (33) of the adjacent vanes (21) of the turbine stage (TS), and the second teeth (46b-c) are opposite to the respective stator heat shields (27).
    Type: Grant
    Filed: November 29, 2011
    Date of Patent: September 16, 2014
    Assignee: Alstom Technology Ltd.
    Inventor: Alexander Anatolievich Khanin
  • Patent number: 8784046
    Abstract: The turbine is provided with a blade (50) and a structure body (11) which rotates relatively with respect to the blade (50). A stepped part (52A) having a step surface (53A) is installed at one of the leading end of the blade (50) and the structure body (11) corresponding to the leading end thereof, while a seal fin (15A) which extends toward the stepped part (52A) to form a small space (H) is installed at the other of them. A cavity (C1) is formed between the blade (50) and the structure body (11) and also between the seal fin (15A) and the partition wall which faces thereto in the rotating shaft direction of the structure body (11) on the upstream side. When a distance of the cavity (C1) between the partition wall and the seal fin (15A) is given as a cavity width (W), and a distance between the seal fin (15A) and the end edge (55) of the stepped part (52A) in the rotating shaft direction on the upstream side is given as (L), at least one of the distances (L) satisfies the following formula (1). 0.7H?L?0.
    Type: Grant
    Filed: October 4, 2010
    Date of Patent: July 22, 2014
    Assignee: Mitsubishi Heavy Industries, Ltd.
    Inventors: Yoshihiro Kuwamura, Kazuyuki Matsumoto, Hiroharu Ooyama, Yoshinori Tanaka, Asaharu Matsuo
  • Patent number: 8770928
    Abstract: An air cycle machine includes turbine and compressor housings respectively having a turbine and a compressor. An insulator seal plate is fastened between the turbine and compressor housings. The insulator seal plate includes a bore. A seal has an outer diameter that engages the bore. The seal also includes an inner diameter provided between lateral sides defining a first width. The inner diameter provides a seal and configured to engage a rotating surface. The outer diameter to the inner diameter provides a first ratio of 1.30-1.31. The inner diameter to the first width provides a second ratio of 1.59-1.61. A rotor shaft is disposed in the seal and includes knife edges extending from the rotor shaft to the seal land. The rotor shaft supports the turbine and the compressor.
    Type: Grant
    Filed: December 21, 2010
    Date of Patent: July 8, 2014
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Eric Chrabascz, Darryl A. Colson, Seth E. Rosen
  • Patent number: 8740554
    Abstract: 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: Grant
    Filed: January 11, 2011
    Date of Patent: June 3, 2014
    Assignee: United Technologies Corporation
    Inventors: Scott D. Virkler, Roger Gates
  • Publication number: 20140140827
    Abstract: A vane assembly has a vane including an inner platform with a mount rail extending radially inwardly toward an engine center axis. An air seal is attached to the inner platform. The air seal has a single-piece ring extending circumferentially about the engine center axis. A ring nut secures the air seal to the inner platform. A biasing member cooperates with the ring nut and air seal to seal fore and aft locations on the vane.
    Type: Application
    Filed: September 27, 2012
    Publication date: May 22, 2014
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventor: UNITED TECHNOLOGIES CORPORATION
  • 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
  • Patent number: 8678785
    Abstract: A ventilation fan includes a rotor holder rotating around a rotation axis, an impeller cup including a plurality of blades provided on an outer circumference thereof, and a base portion arranged to rotatably support the rotor holder through a bearing portion. The base portion includes an outer circumferential wall extending upwards in an axial direction from an outer circumferential edge portion thereof. A gap defining a labyrinth structure is provided between an upper end portion of the outer circumferential wall of the base portion and a lower end portion of an outer circumferential portion of the impeller cup. A lower end portion of a cylindrical portion is located axially lower than the upper end portion of the outer circumferential wall of the base portion.
    Type: Grant
    Filed: July 30, 2010
    Date of Patent: March 25, 2014
    Assignee: Nidec Corporation
    Inventors: Sakae Nogami, Hirotsugu Yokotani, Kenji Iwamoto
  • Publication number: 20140072415
    Abstract: A seal assembly for sealing between a rotating component and a stationary component in a turbomachine. The seal assembly includes a plurality of radially inwardly projecting, axially spaced teeth extending from the stationary component, wherein at least one of the plurality of teeth has at least one axially extending hole therethrough. Axial flow of an operating fluid through the holes acts as an air-curtain to interrupt swirl flow in a seal cavity, therefore reducing steam force that could act to destabilize rotordynamics.
    Type: Application
    Filed: September 11, 2012
    Publication date: March 13, 2014
    Applicant: GENERAL ELECTRIC COMPANY
    Inventors: Xiaoqing Zheng, Daniel Mark Brown, Jason Winfred Jewett, Fred Thomas Willett, JR.
  • Patent number: 8662835
    Abstract: A turbine nozzle for a turbomachine, including inner and outer annular platforms connected together by vanes, the inner platform carrying annular elements of abradable material co-operating with annular wipers of a rotor of the turbomachine to form a labyrinth seal, these elements of abradable material being carried by annular sheet-metal sectors of substantially L-, S-, or C-shaped section that are fastened by brazing or welding at their outer peripheries to the inner platform and at their inner peripheries to the elements of abradable material.
    Type: Grant
    Filed: March 13, 2009
    Date of Patent: March 4, 2014
    Assignee: SNECMA
    Inventors: Thierry Fachat, Patrick Joseph Marie Girard, Jean-Luc Soupizon
  • Patent number: 8651801
    Abstract: A seal monitoring and control system for a gas lubricated non-contacting seal includes various sensors providing signals to a programmable logic control system. The control system is disposed to determine a presence of an anomalous operating condition of the seal, for example, based on phase, relative position of rotor to stator or other signals in combination provided by the various sensors to provide an output signal, which in one embodiment performs at least one mitigating process to correct the anomalous operating condition by adjusting at least one operating parameter of the seal.
    Type: Grant
    Filed: May 20, 2009
    Date of Patent: February 18, 2014
    Assignee: John Crane Inc.
    Inventors: Elhanafi A. Shamseldin, Joe Delrahim, Paul A. Hosking, Joseph L. Savio, Vladimir Bakalchuk
  • Patent number: 8650753
    Abstract: A seal (48) between a compressor rotor blade (26) and compressor casing (28) comprises an abradable structure (59) on the compressor casing (28). The abradable structure (59) comprises a metallic foam (60) having pores (66, 68). The metallic foam (60) has a first a region (62) and a second region (64). The first region (62) of the metallic foam (60) is arranged adjacent to the compressor casing (28) and the second region (64) of the metallic foam (60) is spaced from the compressor casing (28) by the first region (62) of the metallic foam (60). The pores (68) of the second region (64) of the metallic foam (60) contain an abradable material (70) and the pores (66) of the first region (62) of the metallic foam (60) do not contain an abradable material.
    Type: Grant
    Filed: October 8, 2009
    Date of Patent: February 18, 2014
    Assignee: Rolls-Royce, PLC
    Inventors: Christopher Sellars, Glen Pattinson, John T Gent
  • Patent number: 8636466
    Abstract: A ferrule of a stator with blades of an axial turbomachine consists of at least two segments having the general form of an arc of a circle and intended to be arranged end to end, so as to form the ferrule, where each segment contains on its outside a plurality of openings arranged at regular distances along the general arc of the circle of the segment, into each of which fits the end of a blade of the stator. Each end of a segment possesses a section of which the profile essentially corresponds with that of the end of the corresponding blade when the segment is placed on the blades of the stator, such that the joint between two adjacent segments corresponds with the profile of the corresponding blade.
    Type: Grant
    Filed: December 10, 2009
    Date of Patent: January 28, 2014
    Assignee: Techspace Aero S.A.
    Inventor: Jean-François Cortequisse
  • Patent number: 8591181
    Abstract: A turbomachine seal assembly includes a plurality of sealing strips configured and disposed to inhibit a flow of fluid from passing through a channel defined by a first member and a second member. At least one of the plurality of sealing strips includes a paddle element that is configured and disposed to create a fluid recirculation zone at the channel. The fluid recirculation zone further inhibits the flow of fluid through the channel.
    Type: Grant
    Filed: October 18, 2010
    Date of Patent: November 26, 2013
    Assignee: General Electric Company
    Inventors: Ravi Shankar Venkata Kasibhotla, William Edward Adis, Venkata Siva Jagadeeswararao Anjuri, Anantha Padmanabhan Bhagavatheeswaran
  • Patent number: 8573940
    Abstract: A compressor for a turbine engine includes multiple compressor disks having rotor blades mounted about the circumference of each of the disks. A plurality of stator blades extend between the rotor blades of axially adjacent disks. A knife edge seal is supported and retained by retaining flanges extending from a rim on each disk, and contacts the stator blades to limit the recirculation of air within the compressor. A plurality of lock assemblies are spaced about the circumference of disk backbones formed in each disk, with a plurality of knife edge seals located between each lock assembly. When in the lock position the lock assemblies reduce the slack used for assembly of the final knife edge seal to prevent shifting and rotating during operation.
    Type: Grant
    Filed: July 7, 2006
    Date of Patent: November 5, 2013
    Assignee: United Technologies Corporation
    Inventors: John T. Pickens, Tuy Tran, Allan R. Penda
  • Publication number: 20130223998
    Abstract: Turbo machinery includes a rotating body, a stator, and a labyrinth seal disposed in a gap between the rotating body and the stator. The labyrinth seal includes a first seal fin and a second seal fin both of which protrude from a portion of one of the rotating body and the stator toward an opposing portion of the other one of the rotating body and the stator. The first seal fin is disposed on the high-pressure side of the center of the labyrinth seal in the axial direction of the rotating body. The second seal fin is disposed on the low-pressure side of the first seal fin to form a cavity together with the first seal fin. A gap to the portion opposing the first seal fin is smaller than a gap to the portion opposing the second seal fin.
    Type: Application
    Filed: February 27, 2013
    Publication date: August 29, 2013
    Applicant: HITACHI, LTD.
    Inventor: Hitachi, Ltd.
  • Patent number: 8517666
    Abstract: A turbine engine section has a stationary vane stage and a rotating blade stage. The blade stage is spaced from the vane stage to form an annular chamber therebetween. A manifold delivers a pressurized fluid to the chamber. An outer diameter (OD) sealing system restricts leakage of the pressurized fluid from the chamber. An inner diameter (ID) sealing system restricts leakage of the pressurized fluid from the chamber. A flow guide extends radially between the inner diameter sealing system and the manifold. The flow guide bisects the chamber to form a stationary chamber portion and a rotating chamber portion, the rotating chamber portion at least partially along a disk of the first blade stage.
    Type: Grant
    Filed: September 12, 2005
    Date of Patent: August 27, 2013
    Assignee: United Technologies Corporation
    Inventors: Ioannis Alvanos, Rajendra K. Agrawal, Hector M. Pinero
  • Publication number: 20130170965
    Abstract: A sealing assembly for use with a rotating machine is described herein. The rotating machine includes a stator casing that includes a radially inner surface that defines a cavity therein, and a rotor positioned within the cavity and spaced inwardly from the stator inner surface. The sealing assembly includes a support ring coupled to the stator casing, and a plurality of plate members coupled to the support ring and oriented circumferentially about the rotor. A resistance member extends inwardly from the support ring towards the rotor outer surface. The resistance member is coupled to the support ring and extends through each plate member of the plurality of plate members. At least one rotor land is defined circumferentially about the rotor outer surface. Each plate member is oriented adjacent the at least one rotor land.
    Type: Application
    Filed: December 29, 2011
    Publication date: July 4, 2013
    Inventors: Ajay Keshava Rao, Hrishikesh Vishvas Deo, Hemant Vinayak Gedam, Vishwas Kumar Pandey
  • Publication number: 20130149118
    Abstract: A labyrinth seal impedes leakage flow though a gap between confronting static and moving parts in a turbomachine. The seal includes axially spaced and circumferentially extending sealing fins arranged in leakage flow series and projecting across the gap from at least one of the confronting parts into sealing proximity with the opposing confronting part. The fins have at least a distal portion that is curved or inclined in the upstream direction of the leakage flow to deflect the leakage flow in the upstream direction. Successive fins define chambers that accommodate recirculating vortices produced by the deflected leakage flow.
    Type: Application
    Filed: June 29, 2012
    Publication date: June 13, 2013
    Applicant: ALSTOM TECHNOLOGY LTD.
    Inventors: Osama Lotfi, Christophe Simonet, Niall Macdonald
  • Patent number: 8459939
    Abstract: A compressor stator blade 10 includes a seal mechanism 12 configured to hermetically seal a part between a radial inner end on the upstream side and an outer surface of a rotary body, and a remainder part on the downstream side of the seal mechanism includes a hub clearance 14 between the outer surface of the rotary body and itself. Additionally, a compressor rotor blade 20 includes a seal mechanism 22 configured to hermetically seal a part between a radial outer end on the upstream side and an inner surface of a stationary body, and a remainder part on the downstream side of the seal mechanism includes a tip clearance 24 between the inner surface of the stationary body and itself.
    Type: Grant
    Filed: March 28, 2007
    Date of Patent: June 11, 2013
    Assignee: IHI Corporation
    Inventors: Shinya Goto, Takeshi Murooka
  • 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: 8393859
    Abstract: A card seal with an annular arrangement of cards that form the card seal, where the cards are interweaved and staggered to increase a sealing capability of the cards. The card seal is formed from leading edge cards staggered with trailing edge cards, and the cards have a thicker outer end and a thinner inner end where the interweaving occurs. Because of the varying thickness of the staggered cards, each card has a taper on the lower outer end that decreases from a high to a low on the inner side in order that a foot print for the card is constant across the bottom surface that floats on the rotating part.
    Type: Grant
    Filed: September 18, 2009
    Date of Patent: March 12, 2013
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: Daniel R Dillon
  • Patent number: 8388311
    Abstract: A turbomachinery includes a labyrinth seal (2) to prevent unstable vibration of a rotor formed by dividing the seal into segments (7) in a circumferential direction and combining the segments (7) whose comb teeth (5) differ in height. The labyrinth seal (2) preferably includes two kinds of segments (7) whose comb teeth (5) differ in height for each kind of segment, and the segments (7a) of the greater comb tooth height are arranged in a certain reference direction on a cross section right-angled to a rotational axis, and in a direction opposite to the reference direction, and the segments (7b) of the smaller comb tooth height are arranged in a direction right-angled to the reference direction, and in a direction opposite to that right-angled to the reference direction.
    Type: Grant
    Filed: June 25, 2009
    Date of Patent: March 5, 2013
    Assignee: Hitachi, Ltd.
    Inventors: Kazuyuki Yamaguchi, Yohei Magara, Toyomi Yoshida, Michiyuki Takagi, Kenichi Murata, Takeshi Kudo
  • 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
  • Patent number: 8388310
    Abstract: A disc seal assembly for use in a turbine engine. The disc seal assembly includes a plurality of outwardly extending sealing flange members that define a plurality of fluid pockets. The sealing flange members define a labyrinth flow path therebetween to limit leakage between a hot gas path and a disc cavity in the turbine engine.
    Type: Grant
    Filed: January 30, 2008
    Date of Patent: March 5, 2013
    Assignee: Siemens Energy, Inc.
    Inventor: Ihor S. Diakunchak
  • Publication number: 20130045086
    Abstract: The invention relates to a pump turbine system comprising a turbine with a turbine impeller as well as a turbine spiral housing; and a pump with a pump impeller as well as a pump spiral housing; an electrical machine which is in drive communication with the shaft or can be brought into such communication; a hydraulic short circuit can be produced between turbine and pump.
    Type: Application
    Filed: April 26, 2012
    Publication date: February 21, 2013
    Inventor: Manfred Stummer
  • Patent number: 8376692
    Abstract: A turbo compressor in an axial type of construction is disclosed. The turbo compressor has a bladed stator and a bladed rotor, and has a longitudinally split compressor casing and a guide blade ring with adjustable guide blades. The guide blades are pivotably mounted about radial axes radially within their aerofoil on an inner ring belonging to the stator. The inner ring is split, i.e., segmented, at at least two points of its circumference. Furthermore, the inner ring has for each guide blade at least one bearing bush which can be inserted radially into an opening from inside.
    Type: Grant
    Filed: May 18, 2007
    Date of Patent: February 19, 2013
    Assignee: MTU Aero Engines GmbH
    Inventor: Frank Stiehler
  • Patent number: 8360712
    Abstract: A seal assembly for a turbomachine may include at least one arcuate plate coupled to an interior surface of a stationary housing; a circumferentially-segmented packing ring disposed intermediate to a rotor and the plate; a plurality of arcuate teeth disposed intermediate to the ring and the rotor, wherein a clearance of each tooth decreases progressively going from an upstream side of the turbomachinery to a downstream side; wherein the progressive decrease in the clearances of the teeth creates a passive feedback, such that as a tip clearance decreases, outward radial forces cause the packing ring to move away from the rotor and as the tip clearance increases, inward radial forces cause the packing ring to move toward the rotor; and a biasing member disposed intermediate to the arcuate plate and the ring and coupled to both.
    Type: Grant
    Filed: January 22, 2010
    Date of Patent: January 29, 2013
    Assignee: General Electric Company
    Inventors: Hrishikesh Vishvas Deo, Binayak Roy
  • Patent number: 8356974
    Abstract: A steam turbine 20 is provided with a casing 109, a turbine rotor 25 disposed through the casing 109, and labyrinth portions 50, 55 which are disposed at the boundary between the casing 109 and the turbine rotor 25. The steam turbine 20 is further provided with a sealing steam pipe 65 for supplying sealing steam to the labyrinth portions 50, 55 and a gas supply pipe 60 for supplying the labyrinth portions 50, 55 with a cooling gas for cooling the turbine rotor 25 or a heating gas for heating the turbine rotor 25.
    Type: Grant
    Filed: July 8, 2009
    Date of Patent: January 22, 2013
    Assignee: Kabushiki Kaisha Toshiba
    Inventors: Asako Inomata, Katsuya Yamashita, Koji Yamaguchi
  • 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