Bearing, Seal, Or Liner Between Runner Portion And Static Part Patents (Class 415/170.1)
  • Patent number: 11287045
    Abstract: A seal ring system is provided. The seal ring system comprises a segment defining a slot, a pedal along the slot, and an opening offset from the slot. A retention fastener may be disposed in the opening. A seal ring system is also provided comprising a first segment defining a first opening, a second segment defining a second opening, and a retention fastener extending through the first and second openings. The retention fastener configured to allow relative radial movement of the first segment and the second segment. A seal is further provided comprising a seal ring having a central axis, a petal extending radially inward with respect to the central axis of the seal ring, and a sealing disk axially proximate the seal ring. The sealing disk may have a seal shoe configured as a primary seal. The petal may extend toward the seal shoe.
    Type: Grant
    Filed: January 9, 2019
    Date of Patent: March 29, 2022
    Assignee: Raytheon Technologies Corporation
    Inventors: Michael G. McCaffrey, John R. Farris, Theodore W. Hall, John J. Korzendorfer, Elizabeth F. Vinson, Jeffrey Michael Jacques, John E. Paul, Ross Wilson, Edwin Otero, Alan W. Stoner
  • Patent number: 11248476
    Abstract: A turbine part, such as a turbine blade or a distributor fin, for example, including a substrate made of superalloy based on monocrystalline nickel, including rhenium and/or ruthenium, and having a ??-NisAI phase that is predominant by volume and a ?-Ni phase, the part also including a sublayer made of metal superalloy based on nickel covering the substrate, wherein the sublayer has a ??-NisAI phase that is predominant by volume and wherein the sublayer has an average atomic fraction of aluminium of between 0.15 and 0.25, of chromium of between 0.03 and 0.08, of platinum of between 0.01 and 0.05, of hafnium of less than 0.01 and of silicon of less than 0.01. A process for manufacturing a turbine part including a step of vacuum deposition of a sublayer made of a superalloy based on nickel having predominantly by volume a ??-NisAI phase, on a substrate made of superalloy based on nickel including rhenium and/or ruthenium.
    Type: Grant
    Filed: September 21, 2018
    Date of Patent: February 15, 2022
    Assignee: SAFRAN
    Inventors: Amar Saboundji, Virginie Jaquet
  • Patent number: 11215222
    Abstract: A turbocharger includes a rotor shaft that is rotationally driven, a compressor impeller attached to the rotor shaft, and a cylindrical bearing portion that includes an inner cylinder and an outer cylinder, and that supports the rotor shaft in a rotatable manner. A first damping portion is provided between an axial first end portion of the inner cylinder and an axial first end portion of the outer cylinder, and an axial second end portion of the inner cylinder is connected with an axial second end portion of the outer cylinder. A second damping portion is provided between a housing and the axial second end portion. The housing and the bearing portion are fixed by a flange portion provided at the first end portion of the outer cylinder in such a manner as to restrict movement of the flange portion in a radial direction and in an axial direction.
    Type: Grant
    Filed: February 4, 2019
    Date of Patent: January 4, 2022
    Assignee: MITSUBISHI HEAVY INDUSTRIES MARINE MACHINERY & EQUIPMENT CO., LTD.
    Inventors: Takaya Futae, Naoyuki Nagai, Shinji Ogawa, Taiyo Shirakawa
  • Patent number: 11187267
    Abstract: Provided is a bearing structure, including: a damper groove formed in at least one of an outer peripheral surface of an outer ring of a rolling bearing or an inner peripheral surface of a bearing hole so as to extend in a circumferential direction of a shaft; and a second oil drain hole having one end communicating with the damper groove, and another end opened to an outside of a cylindrical portion.
    Type: Grant
    Filed: November 5, 2020
    Date of Patent: November 30, 2021
    Assignee: IHI Corporation
    Inventors: Yutaka Uneura, Takahiro Tanaka, Hiroki Mochizuki, Shunsuke Nishii, Hideyuki Kojima
  • Patent number: 11168704
    Abstract: A stator vane body which is disposed in a flow path through which a working fluid flows and by which a clearance is formed between the stator vane body and an inner casing; a rotary shaft which is configured to rotate such that an angle of the stator vane body with respect to a flow direction of a main flow of the working fluid is varied; and a connection part which is configured to connect the stator vane body to the rotary shaft are provided. The connection part includes a first guide surface which is configured to guide the working fluid in a direction in which a flow direction of a leakage flow of the working fluid in the clearance which has flowed into toward a leading edge side of the stator vane body is directed in a flow direction of the main flow.
    Type: Grant
    Filed: March 30, 2018
    Date of Patent: November 9, 2021
    Assignee: MITSUBISHI POWER, LTD.
    Inventors: Ryosuke Mito, Hidetaka Okui
  • Patent number: 11125384
    Abstract: The present invention improves the drainability of lubricating oil at a thrust bearing. The present invention comprises: a rotating shaft; a thrust bearing that is provided to the rotating shaft and restricts the axial-direction movement of the rotating shaft; and an oil reservoir part (20) that has formed therein an oil reservoir space (20a) that is provided to be adjacent to the thrust bearing in the axial direction and to open downward, the oil reservoir space (20a) having formed therein an inclined surface (20aa) that, in a region that is in and below a horizontal plane H that passes through the center of the rotating shaft, protrudes to the thrust bearing side and is inclined along the rotational direction of the rotating shaft.
    Type: Grant
    Filed: March 1, 2016
    Date of Patent: September 21, 2021
    Assignee: MITSUBISHI HEAVY INDUSTRIES ENGINE & TURBOCHARGER, LTD
    Inventors: Yuya Kojima, Takashi Nambu, Yosuke Dammoto, Takaya Futae, Shuichi Isayama, Yoji Akiyama
  • Patent number: 11125096
    Abstract: A blade outer air seal assembly includes a blade outer air seal that has a plurality of seal segments that extend circumferentially about an axis and mounted in a support structure via a carrier. Each of the seal segments has a base portion that extends between a first circumferential side and a second circumferential side and from a first axial side to a second axial side. A first and second hook extend along the base portion in an axial direction. The first and second hooks are engaged with the carrier. The carrier has a wall forward or aft of the first and second hooks and extends radially inward of the first and second hooks.
    Type: Grant
    Filed: May 3, 2019
    Date of Patent: September 21, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Thomas E. Clark, William M. Barker
  • Patent number: 11118594
    Abstract: A seal apparatus for a casing of a turbomachine. The seal apparatus may include an annular body having first and second annular body portions and an appendage. The second annular body portion may extend axially from the first annular body portion and may have an outer annular surface radially offset from an outer annular surface of the first annular body portion. The appendage may extend axially from the first annular body portion and may have an outer annular surface and an inner annular surface. The inner annular surface of the appendage and the outer annular surface of the second annular body portion may define an annular cavity therebetween, and at least a portion of the appendage may be configured to be displaced radially outward in order to maintain contact with first and second inner cylindrical surfaces of the casing during radial expansion of the casing.
    Type: Grant
    Filed: May 2, 2018
    Date of Patent: September 14, 2021
    Assignee: DRESSER-RAND COMPANY
    Inventor: Daniel J. Griffin
  • Patent number: 11105334
    Abstract: Methods and systems are provided for a coolant pump. In one example, the coolant pump may be a dual-volute coolant pump with an impeller driving circulation of coolant through the pump and a seal disposed around a shaft of the impeller. A set of anti-vortex structures may be arranged within an inner chamber of the pump, the structures generating a pressure differential in the inner chamber that drives a cross-flow of coolant, thereby convectively cooling the seal.
    Type: Grant
    Filed: May 17, 2019
    Date of Patent: August 31, 2021
    Assignee: Ford Global Technologies, LLC
    Inventors: Justin Craft, William Michael Sanderson, Timothy Comer
  • Patent number: 11041503
    Abstract: A turbomachine impeller is disclosed, which includes: a hub having a rotation axis; a shroud; a plurality of blades between the hub and the shroud; and a plurality of flow vanes, each flow vane being defined between the hub, the shroud and neighboring blades, each flow vane having a flow vane inlet and a flow vane outlet. Each flow vane extends radially inwardly from the flow vane inlet towards a radially innermost flow vane section, and from the radially innermost flow vane section to a flow vane outlet.
    Type: Grant
    Filed: September 14, 2016
    Date of Patent: June 22, 2021
    Assignee: NUOVO PIGNONE SRL
    Inventors: Giuseppe Iurisci, Simone Corbo
  • Patent number: 10934941
    Abstract: An interface for a gas turbine engine. The interface includes a full-hoop vane ring around the engine axis, the full-hoop vane ring comprises a forward vane rail with a vane ring forward contact surface and a vane ring anti-rotation tab, the vane ring anti-rotation tab engaged with the anti-rotation case slot; and a multiple of BOAS segments around the engine axis, each of the multiple of BOAS segments comprise a BOAS aft engagement feature and a BOAS aft contact surface, the BOAS aft engagement feature engaged with the engine case and the anti-rotation case slot, the BOAS aft contact surface abuts the vane ring forward contact surface.
    Type: Grant
    Filed: November 19, 2018
    Date of Patent: March 2, 2021
    Assignee: Raytheon Technologies Corporation
    Inventor: Michael G. McCaffrey
  • Patent number: 10934877
    Abstract: An air seal assembly, comprising a control ring comprising a leading edge side and a trailing edge side opposite the leading edge side, a hook protruding axially from the trailing edge side, a clip receiver communicating through the control ring from the leading edge side to the trailing edge side, a clip mounting flange extending from the trailing edge side proximate the receiver; a blade outer air seal coupled to the control ring, the blade outer air seal comprises a body having a leading edge and a trailing edge opposite thereof, a pocket formed into the body having an upper region and a lower region, the pocket receives and engages with the hook; a notch is formed into the upper region, a shelf formed from the lower region extending axially outward from the pocket on the trailing edge side of the body; and a clip insertable into the clip receiver.
    Type: Grant
    Filed: October 31, 2018
    Date of Patent: March 2, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Dean W. Johnson, Thomas E. Clark
  • Patent number: 10907499
    Abstract: A rotor-blade-side sealing apparatus is configured to seal leakage of working fluid between rotor blade rings connected to distal end portions of rotor blade main bodies attached so as to extend in a radial direction from a rotor main body configured to rotate about an axis in a casing, and an inner circumferential surface of the casing. The rotor-blade-side sealing apparatus includes a sealing fin protruding in the radial direction from a side of the inner circumferential surface of the casing toward one of the rotor blade rings and extending in a circumferential direction. The sealing fin includes: a first sealing-fin main body portion and a second sealing-fin main body portion separated from each other in the circumferential direction across a gap portion that is a discontinuity along the circumferential direction; and an extending portion extending toward an upstream side in an axial direction of the rotor main body.
    Type: Grant
    Filed: February 22, 2019
    Date of Patent: February 2, 2021
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Makoto Iwasaki, Rimpei Kawashita, Yasunori Tokimasa
  • Patent number: 10907686
    Abstract: A flexible bearing cage includes a base ring comprising a plurality of mount sections arranged along a circular path and a plurality of compressible fold sections. One of the compressible fold sections is located between each adjacent pair of the mount sections, and a finger projects axially from each of the plurality of mount sections. Each of the fingers has a partially spherical concave surface configured such that the finger projecting from a first mount section on one side of a first one of the compressible fold sections and the finger projecting from a second mount section on a second side of the first one of the compressible fold sections define a partially spherical cavity configured to receive and retain a respective rolling body.
    Type: Grant
    Filed: May 1, 2020
    Date of Patent: February 2, 2021
    Assignee: AKTIEBOLAGET SKF
    Inventor: Maurizio Bertola
  • Patent number: 10794294
    Abstract: A gas turbine engine includes: an engine core, compressor system, and core shaft. A compressor exit pressure is defined as an average airflow pressure at the exit of the highest pressure compressor at cruise conditions. The core has an annular splitter and bypass flow. Stagnation streamlines around the engine circumference form a streamsurface. A fan is upstream the core with blades having leading and trailing edges, and a radially inner portion within the streamtube. A fan root entry pressure is an average airflow pressure across the radially inner portion leading edge of each fan blade at cruise conditions. An overall pressure ratio, OPR, is defined as the compressor exit pressure divided by the fan root entry pressure. A bypass jet velocity is defined as the jet velocity of air flow exiting the bypass exhaust nozzle at cruise conditions. A jet velocity to OPR ratio is in a range between 4.7 m/s and 7.7 m/s.
    Type: Grant
    Filed: November 26, 2019
    Date of Patent: October 6, 2020
    Assignee: ROLLS-ROYCE plc
    Inventors: Pascal Dunning, Craig W Bemment
  • Patent number: 10746038
    Abstract: An airfoil includes an airfoil piece that defines at least a portion of an airfoil profile. The airfoil piece has a radial end and a first radial slot in the radial end. An end section has a second radial slot adjacent the first radial slot. The first radial slot and the second radial slot together form a radial seal slot. A seal is disposed in the radial seal slot.
    Type: Grant
    Filed: November 17, 2016
    Date of Patent: August 18, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Tracey A. Propheter-Hinckley, Michael G. McCaffrey
  • Patent number: 10662794
    Abstract: Systems and methods for reducing heat exposure of a turbine casing in a gas turbine engine may be provided. The system may include blade track segments. The blade track segments may include a cavity formed at a circumferential end of the blade track segment. The blade track segments may further include an assembly groove configured to provide a clearance for axial insertion of an inter-segment strip seal. An inter-segment strip seal may be axially inserted past the assembly grooves and into the cavity. The inter-segment strip seal may cover a gap between adjacent blade track segments, thus blocking hot, high pressure fluid from contacting the turbine casing.
    Type: Grant
    Filed: January 17, 2018
    Date of Patent: May 26, 2020
    Assignee: ROLLS-ROYCE CORPORATION
    Inventor: Sayon Das
  • Patent number: 10634042
    Abstract: A rotating machine includes a rotating body configured to rotate around a central axis, and a casing configured to accommodate at least a part of the rotating body, and the casing, includes a main section made of a metallic material, and a high-porosity section made of the same material as the main section and having a porosity higher than the main section.
    Type: Grant
    Filed: March 18, 2016
    Date of Patent: April 28, 2020
    Assignee: MITSUBISHI HEAVY INDUSTRIES ENGINE & TURBOCHARGER, LTD.
    Inventors: Takao Yokoyama, Hiroshi Suzuki, Yosuke Dammoto, Tadashi Kanzaka, Atsushi Takita
  • Patent number: 10544680
    Abstract: A gas turbine having a compressor section provided with a plurality of compressor blades and vanes for compressing air; a combustion section; a turbine section a rotor having an axis and extending from a compressor section to the turbine section for supporting the compressor and turbine blades, the rotor having a last rotor disk having a downstream portion for supporting a bearing cover and an upstream portion for supporting a last turbine blade; and a cooling duct system configured for supplying cooling air from a downstream end of the turbine section to the last turbine blade passing inside the last rotor disk, and having an axial bore in the downstream portion of the last rotor disk along the rotor axis; and a first plurality of inclined radial bores in the upstream portion of the last rotor disk off the axis.
    Type: Grant
    Filed: December 28, 2017
    Date of Patent: January 28, 2020
    Assignee: ANSALDO ENERGIA SWITZERLAND AG
    Inventors: Klaus Döbbeling, Gerard Dusomos, Jose Anguisola McFeat
  • Patent number: 10519811
    Abstract: A flange heat shield is provided. The flange heat shield may comprise an annular body having a forward end opposite an aft end. The forward end of the flange heat shield may comprise a radial snap configured to interface with an inner surface of an engine case. The inner surface of the engine case may comprise an airflow ramp forward of the radial snap. The aft end of the flange heat shield may comprise a plurality of notches defining voids on the aft end. The aft end of the flange heat shield may also comprise mounting tabs configured to couple the flange heat shield to the engine case.
    Type: Grant
    Filed: October 4, 2016
    Date of Patent: December 31, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Timothy Dale, Jonathan Jeffery Eastwood
  • Patent number: 10495102
    Abstract: An impeller includes a back cover plate, and vanes and a hub disposed on the back cover plate. The impeller further includes a sealing ring disposed on one end of the impeller away from the back cover plate. A pump using the impeller includes a volute housing and a driving device. The volute housing includes a diffusor chamber, an inlet pipe and an outlet pipe. The impeller is rotatably received in the diffusor chamber and connected to the driving device. A baffle portion is disposed on an end wall in the diffusor chamber adjacent the inlet pipe. The baffle portion engages with the sealing ring to prevent back flow of the fluid. The pump has enhanced fluid delivery efficiency. The back cover plate may further define arc strip-shaped balance holes for reducing an axial force applied to the impeller, such that rotation of the impeller is more stable.
    Type: Grant
    Filed: December 23, 2016
    Date of Patent: December 3, 2019
    Assignee: JOHNSON ELECTRIC INTERNATIONAL AG
    Inventors: Chuan Jiang Guo, Chuan Hui Fang, Xiao Liang Zhang
  • Patent number: 10494955
    Abstract: Turbine housing assemblies and related turbocharger systems are provided. One exemplary turbine housing assembly includes an inner shell defining an inner inlet portion and a volute portion providing an outer contour of a volute, an outer shell surrounding the volute portion and defining an outer inlet portion circumscribing the inner inlet portion, and one or more energy absorbing members coupled to an inner surface of the outer shell between the outer shell and the inner shell. The inner shell includes a first plurality of sheet metal structures coupled together in a first plane and the outer shell includes a second plurality of sheet metal structures coupled together in a second plane transverse to the first plane.
    Type: Grant
    Filed: January 30, 2017
    Date of Patent: December 3, 2019
    Assignee: GARRETT TRANSPORTATION I INC.
    Inventors: Katsumi Azuma, Kouichirou Ishihara, Shinya Goto
  • Patent number: 10458254
    Abstract: Coating systems for components of a gas turbine engine, such as a compressor blade tip, are provided. The coating system can include an abradable material disposed along the compressor blade tip and may be used with a bare compressor casing. The abradable coating is softer than the compressor casing and can reduce the overall rub ratio thereby increasing the lifetime of the compressor blade and casing. Methods are also provided for applying the coating system onto a compressor blade.
    Type: Grant
    Filed: November 16, 2016
    Date of Patent: October 29, 2019
    Assignee: General Electric Company
    Inventors: Sathyanarayanan Raghavan, Neelesh Nandkumar Sarawate, Kenneth Martin Lewis, Larry Steven Rosenzweig, Changjie Sun, Ananda Barua
  • Patent number: 10443443
    Abstract: A gas turbine engine includes a fan, a compressor section, a combustor, and a turbine section. The engine also includes a rotating element and at least one bearing compartment including a bearing for supporting the rotating element, a seal for resisting leakage of lubricant outwardly of the bearing compartment and for allowing pressurized air to flow from a chamber adjacent the seal into the bearing compartment. A method and section for a gas turbine engine are also disclosed.
    Type: Grant
    Filed: March 10, 2017
    Date of Patent: October 15, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: M. Rifat Ullah, Robert E. Peters
  • Patent number: 10428689
    Abstract: A subassembly of a gas turbine engine includes a heat shield and carrier subassembly for a turbine section are disclosed. The carrier includes support features to couple to an engine casing. The upstream end of the carrier includes a radially inward arm extending toward to an engine axis. The outer end of the radially floating heat shield is coupled to the radially inward arm via a pin-and-slot joint configured to allow movement of the heat shield relative to the radially inward arm of the carrier. In response to thermal expansion and contraction of the vane, the heat shield is configured to move radially outward and inward, respectively, relative to the radially inward arm to maintain contact with the outer platform of the vane.
    Type: Grant
    Filed: July 13, 2017
    Date of Patent: October 1, 2019
    Assignee: ROLLS-ROYCE DEUTSCHLAND LTD & CO KG
    Inventor: Marcel Schmidt
  • Patent number: 10422247
    Abstract: The present invention relates to a turbomachine with a housing structure as well as a corresponding housing structure an outer housing wall and an inner housing wall, which, passing around the flow duct of the turbomachine at a distance from each other, surround the outer side of the flow duct, wherein the inner housing wall of the housing structure is formed by an OAS (outer air seal, outer fluid seal) in the region of the rotating blades of the turbomachine, which rotate around an axial axis of the turbomachine, wherein a heat protection shield is constructed between the outer housing wall and the OAS. The heat protection shield has a plurality of spacers in the peripheral direction that are distanced from one another in the peripheral direction and are situated additionally to and in the radial direction outside of the heat protection element.
    Type: Grant
    Filed: December 1, 2016
    Date of Patent: September 24, 2019
    Assignee: MTU Aero Engines AG
    Inventors: Petra Kufner, Walter Gieg
  • Patent number: 10369630
    Abstract: A polyhedral-sealed article is disclosed including an article having a surface and a polyhedral seal layer disposed on the surface. The polyhedral seal layer includes a polyhedral structure having a plurality of polyhedral units. The polyhedral seal layer further includes at least one of a composition including an HTW composition, a heterogeneous pattern of the polyhedral structure, an orientation of the polyhedral structure extending from the surface at non-orthogonal angle, and at least one polyhedral unit conformation other than a hexagonal prism. A method for forming the polyhedral-sealed article is disclosed including forming a polyhedral seal layer by binder jet additive manufacturing and disposing the polyhedral seal layer on a surface of an article.
    Type: Grant
    Filed: February 24, 2017
    Date of Patent: August 6, 2019
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Srikanth Chandrudu Kottilingam, Brian Lee Tollison, Yan Cui, Surinder Singh Pabla
  • Patent number: 10352195
    Abstract: A gas turbine engine includes a fan, a compressor section, a combustor, and a turbine section. The engine also includes a rotating element and at least one bearing compartment including a bearing for supporting the rotating element, a seal for resisting leakage of lubricant outwardly of the bearing compartment and for allowing pressurized air to flow from a chamber adjacent the seal into the bearing compartment. A method and section for a gas turbine engine are also disclosed.
    Type: Grant
    Filed: January 10, 2017
    Date of Patent: July 16, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: M. Rifat Ullah, Robert E. Peters
  • Patent number: 10294963
    Abstract: An axially split inner ring for a fluid flow machine is disclosed. The inner ring is constructed for connecting to guide vanes and includes at least a first ring segment arranged upstream and a second ring segment arranged downstream. The second ring segment has a first sealing segment, where at least one section of the second ring segment is arranged in a radially inward manner relative to the first ring segment. A guide vane ring of a fluid flow machine and an aircraft engine are also disclosed.
    Type: Grant
    Filed: February 12, 2016
    Date of Patent: May 21, 2019
    Assignee: MTU Aero Engines AG
    Inventors: Werner Humhauser, Hermann Klingels
  • Patent number: 10267171
    Abstract: The present disclosure relates to a turbomachine that includes a first component and a second component coupled to another and a seal assembly disposed between the two components. The seal assembly may include an upstream corner shim, a downstream corner shim, and/or one or more intersegment seals that are configured to block a flow of fluid between the two components.
    Type: Grant
    Filed: December 8, 2015
    Date of Patent: April 23, 2019
    Assignee: General Electric Company
    Inventors: Bodhayan Dev, Neelesh Nandkumar Sarawate, Jason Edward Albert
  • Patent number: 10253645
    Abstract: A blade outer air seal (BOAS) for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a seal body having a radially inner face and a radially outer face that axially extend between a leading edge portion and a trailing edge portion. A retention flange extends from the leading edge portion and a leaf seal contacts the retention flange.
    Type: Grant
    Filed: December 12, 2014
    Date of Patent: April 9, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Brian Ellis Clouse, David F. Cloud, Donna Clough
  • Patent number: 10190454
    Abstract: An impeller for pressurizing an intake air of an engine is provided on a left side end portion in a supercharger rotary shaft of the supercharger. The power from the engine is transmitted to a second sprocket, which is provided on a right side end portion of an input shaft of a speed increaser, through a chain to thereby allow the supercharger to drive. The second sprocket is removably fitted to the input shaft by means of a bolt. The supercharger rotary shaft, the input shaft, the second sprocket and the bolt are all accommodated in a supercharger casing. The supercharger casing has a right side end face formed with an access opening through which access can be made to the second sprocket and the bolt from an axial direction.
    Type: Grant
    Filed: January 7, 2015
    Date of Patent: January 29, 2019
    Assignee: KAWASAKI JUKOGYO KABUSHIKI KAISHA
    Inventors: Shohei Naruoka, Hisatoyo Arima, Yoshiharu Matsuda
  • Patent number: 10189045
    Abstract: A blackbody material application system for a turbine. The system includes a blackbody material supply and a moveable hose connected to the blackbody material supply wherein the hose sprays blackbody material onto a selected area within the turbine. The system also includes a rotatable bracket that holds the hose, wherein rotation of the bracket moves the hose toward the selected area within the turbine to enable application of the blackbody material onto the selected area. In addition, the system includes a motor for rotating the bracket and a moveable arm that holds the bracket wherein the bracket is inserted through an opening in the turbine and movement of the arm enables positioning of the bracket and hose in relative close proximity to the selected area suitable for spraying blackbody material onto the selected area.
    Type: Grant
    Filed: August 31, 2016
    Date of Patent: January 29, 2019
    Assignee: SIEMENS ENERGY, INC.
    Inventors: Dustin C. Boudin, Clifford Hatcher, Jr., Anand A. Kulkarni, Kevin Licata, David Letter, Alejandro Bancalari
  • Patent number: 10132182
    Abstract: A platform includes a platform body. The platform body has an airfoil support surface, an axially extending base surface opposite the airfoil support surface, and a leading edge. The leading edge includes an upstream extending flange with a raised portion and a trough portion downstream of and radially inward from the raised portion. The raised portion and the trough portion are for holding a vortex of fluid flow. The upstream extending flange includes a converging surface connecting the upstream extending flange to the base surface. The converging surface converges in a direction toward the axially extending base surface and is at an angle relative to the base surface.
    Type: Grant
    Filed: November 10, 2015
    Date of Patent: November 20, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Andrew J. Aggarwala, Russell J. Bergman
  • Patent number: 10107294
    Abstract: The present invention relates to a coreless donut-type fan, and more particularly, to a coreless donut-type motor fan for ventilation and cooling, in which a rotating force is generated by wings themselves, without a separate rotational power such as a motor provided in a central portion thereof, and a through hole is formed in the central portion thereof to prevent a “wind barrier” phenomenon during rotation at a high speed, thereby maintaining smooth air flow, minimizing power consumption, in particular, preventing rotational noise due to induction of smooth rotation, and improving rotational efficiency.
    Type: Grant
    Filed: May 14, 2015
    Date of Patent: October 23, 2018
    Inventor: Suk Ho Jang
  • Patent number: 10094232
    Abstract: Aspects of the disclosure are directed to a seal comprising: a shoe, and at least one beam coupled to the shoe, wherein the seal includes a single crystal material with a predetermined crystalline orientation. Aspects of the disclosure are directed to a method for designing a seal, comprising: obtaining a requirement associated with at least one of: a geometrical profile of the seal, a temperature range over which the seal is to operate, a natural frequency associated with the seal, or a range of deflection associated with the seal, selecting a crystalline orientation for a single crystal material of the seal based on the requirement, and fabricating the seal based on the selected crystalline orientation.
    Type: Grant
    Filed: August 13, 2015
    Date of Patent: October 9, 2018
    Assignee: United Technologies Corporation
    Inventors: Michael G. McCaffrey, Eric A. Hudson
  • Patent number: 10053998
    Abstract: A gas turbine engine assembly includes a first module, a second module rotatable about a center line of the gas turbine engine and fluidly coupled with the first module, and a multi-purpose seal support. The multi-purpose seal support includes an aft end secured to the first module, and a forward end disposed proximate the second module. The forward end has a discourager portion, a seal portion, and a meshing portion.
    Type: Grant
    Filed: December 23, 2013
    Date of Patent: August 21, 2018
    Assignee: United Technologies Corporation
    Inventors: Tuan David Vo, Conway Chuong, Matthew Budnick, Jonathan Ariel Scott
  • Patent number: 10012097
    Abstract: A nozzle sector of an aircraft turbo-machine, including a hooking member (64) having a projection (70, 70a, 70b) radially extending towards the outside of the sector, a recess (72) being provided through at least one part of a distal end of the projection (70, 70a, 70b), the recess (72) being configured to accommodate a shoulder member (74) forming a stop for a surface of an adjacent sector (26).
    Type: Grant
    Filed: February 19, 2014
    Date of Patent: July 3, 2018
    Assignee: SNECMA
    Inventors: Sébastien Jean Laurent Prestel, Denis Aydin, Rémi Blanc, Hélène Condat, Patrice Jean-Marc Rosset
  • Patent number: 10012111
    Abstract: A gas turbine, including: axially adjacent first and second components each having a gas path facing surface within an engine casing, inter-component cavity located between first and second components on the gas path outboard side, an axial-restrictor within the inter component cavity for restricting movement of the first or second component relative to at least one other first and second component or engine casing, wherein the axial-restrictor is radially located in the engine casing or other first and second component and includes a radially facing surface; a retaining element, including a body having circumferential length extending around the gas turbine engine and axial length extending between axially adjacent first and second components when in use; an obstructing portion between the radially facing surface of the axial-restrictor and opposing second radial surface of the other first or second component or engine casing to restrict radial movement of in use axial-restrictor.
    Type: Grant
    Filed: September 3, 2015
    Date of Patent: July 3, 2018
    Assignee: ROLLS-ROYCE plc
    Inventors: Andrew James Hurst, Mark John Simms
  • Patent number: 9982685
    Abstract: A turbocharger compressor cover (114) including an inner shroud contour (122) configured to receive a compressor wheel (118) having a plurality of blades (140). Each blade (140) includes a leading edge (142), a contour edge (144), and a trailing edge (146). An inlet passage (124) leads to the inner shroud contour (122) and a circumferential groove (130) is formed around the inlet passage (124). The groove (130) includes a trailing edge (136) that is aligned with the outboard end (148) of the leading edge (142) of the blades. The compressor cover (114) includes an edge relief (138) formed along the groove trailing edge (136), such as a 45 degree chamfer. The circumferential groove (130) has a width and a depth, wherein the width and depth are approximately equal. The chamfer intersects the groove (130) approximately half the depth from the bottom of the groove (130).
    Type: Grant
    Filed: July 11, 2013
    Date of Patent: May 29, 2018
    Assignee: BorgWarner Inc.
    Inventor: Prasanth Vengala
  • Patent number: 9982539
    Abstract: Turbomachines having guide ducts are disclosed. One disclosed example turbomachine includes a rotor rotatable about an axis of rotation and having rotor blade ducts, a housing having housing ducts to allow the inflow or outflow of working medium and guide blade ducts fixed in the housing, where the rotor blade ducts are in fluid communication with the housing ducts via the guide blade ducts.
    Type: Grant
    Filed: April 30, 2014
    Date of Patent: May 29, 2018
    Assignee: DUERR CYPLAN LTD.
    Inventor: Frank Eckert
  • Patent number: 9951640
    Abstract: A structure providing compliance and sealing between ceramic or ceramic composite (CMC) part and a metallic part has an interface component for centering the CMC part in the metallic part, thus reducing thermal stress motion of the CMC component. In gas turbine engine applications, the structure comprises a CMC blade track inserted in a clip placed within a metallic hanger. The clip provides for radial compliance and secures controlled leakage of cooling air required to ensure that acceptable temperatures are maintained for the metallic structures. A washer is positioned adjacent to the clip provide for axial orientation of the blade track.
    Type: Grant
    Filed: December 27, 2013
    Date of Patent: April 24, 2018
    Assignee: Rolls-Royce Corporation
    Inventors: William I. Westphal, Clayton C. Smith
  • Patent number: 9915161
    Abstract: A process gas compressor/gas turbine section including a process gas compressor and a gas turbine which is coupled to the shaft of the process gas compressor in order to drive said compressor is provided. The process gas compressor is designed to compress combustible process gas and is equipped to seal the process gas compressor inner chamber from the atmosphere using a shaft seal which can be sealed with a seal gas and which has at least one leakage line. The leakage line can conduct leakage gas away from the shaft seal and is connected to the air inlet of the gas turbine such that the leakage gas together with the inlet air at the air inlet can be conducted into the gas turbine during the operation of the process gas compressor/gas turbine section.
    Type: Grant
    Filed: September 25, 2013
    Date of Patent: March 13, 2018
    Assignee: SIEMENS AKTIENGESELLSCHAFT
    Inventor: Henk Blekkenhorst
  • Patent number: 9850775
    Abstract: An integrated shroud structure surrounds a circumferential array of stator vanes and a circumferential array of rotor blades of a gas turbine engine. The shroud structure includes a plurality of vane shroud segments and a plurality of blade shroud segments. The blade shroud segments integrally extend downstream from the vane shroud segments and each pair of circumferentially adjacent blade shroud segments defines an inter-segment gap. At least one slot extends axially from a location downstream of the vane shroud segments to an aft end of the blade shroud segment. The inter-segment gaps and slots are sealed by a sealing band mounted around the full circumference of the integrated shroud structure.
    Type: Grant
    Filed: October 31, 2016
    Date of Patent: December 26, 2017
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: John Pietrobon, Remy Synnott
  • Patent number: 9835049
    Abstract: A distributor of a turbomachine configured to be mounted in a housing, including: a plurality of segments; a plurality of anti-rotation pins, mounted both on a segment of the distributor and on the housing; and a thermal protection sheet, including at least one axial tab configured to radially abut against an inner face of a first anti-rotation pin, and at least one radial tab configured to axially abut against an upstream face of a second anti-rotation pin.
    Type: Grant
    Filed: September 9, 2013
    Date of Patent: December 5, 2017
    Assignee: SNECMA
    Inventor: Julien Arnould
  • Patent number: 9835040
    Abstract: A turbomachine is described, which includes an annular space seal for at least reducing a fluid exchange between an annular space, through which a main stream flows, and at least one cavity situated radially on the inside and/or radially on the outside of the annular space, the annular space seal having a plurality of sheet-like elastic elements, which are oriented in the radial direction of the turbomachine and in the flow direction of a main stream flowing through the particular guide blade row, and thereby acting as a protective device for the rotor and/or stator during a relative axial displacement with respect to the stator in addition to providing an improved cavity coverage.
    Type: Grant
    Filed: October 7, 2014
    Date of Patent: December 5, 2017
    Assignee: MTU Aero Engines AG
    Inventor: Guenter Ramm
  • Patent number: 9822657
    Abstract: The aircraft-engine gas turbine includes an outer sealing ring for sealing an array of rotor blades that can be attached to a housing by a clamping mechanism (80) in a friction fit, and a plurality of ring segments (20i, 20i+1), wherein a free axial path length (af) of a sealing ring segment counter to the direction of through-flow is at least as large as an axial engagement (a1) of a rotation locking member (10) of the outer sealing ring (af?a1), which is free of form fit counter to the direction of through-flow, and/or an axial overhang (a2) of a radial mounting rail (23) of the outer sealing ring (af?a2), and/or an axial offset (a3, a4) of a sealing fin (31, 41); and/or a quotient of a specific clearance sum of the outer sealing ring attached to the housing in a friction fit.
    Type: Grant
    Filed: December 29, 2014
    Date of Patent: November 21, 2017
    Assignee: MTU AERO ENGINES AG
    Inventors: Walter Gieg, Petra Kufner, Rudolf Stanka
  • Patent number: 9631557
    Abstract: A sealing device for a nozzle of a turbomachine turbine including a turbine rotor. The turbine nozzle includes at least one inner annular platform. The turbine rotor includes a downstream spoiler disposed substantially axially. The sealing device includes at least one sealing sheet disposed, radially, between the inner face of the inner platform and the downstream spoiler of the rotor of the turbine so as to form an overlap clearance.
    Type: Grant
    Filed: May 4, 2012
    Date of Patent: April 25, 2017
    Assignee: SNECMA
    Inventors: Florent Pierre Antoine Luneau, Patrick Joseph Marie Girard, Sebastien Jean Laurent Prestel, Jean-Luc Soupizon
  • Patent number: 9605684
    Abstract: The invention relates to a pump for pumping contaminated liquid comprising solid matter, the pump comprising a hydraulic unit (2), a drive unit (3), and a sealing unit (4), the hydraulic unit having a pump chamber (5) and an impeller (8) that is suspended in a drive shaft (9), said impeller and said drive shaft forming a rotatable unit, the sealing unit comprising a seal housing cover (15) that delimits said pump chamber (5) and that forms a seat for a drive shaft sealing assembly (16), the seal housing cover (15) comprising a first gap-delimiting part (20) and the rotatable unit comprising a second gap-delimiting part (21), which jointly define an axially extending gap (22) situated in the pump chamber. The pump is characterized in that, in each arbitrary radially extending plane taken through said gap (22), the first gap-delimiting part (20) has a broken circular outer gap-delimiting surface (23) at the same time as the second gap-delimiting part (21) has a broken circular inner gap-delimiting surface (24).
    Type: Grant
    Filed: October 4, 2012
    Date of Patent: March 28, 2017
    Assignee: XYLEM IP HOLDINGS LLC
    Inventor: Patrik Andersson
  • Patent number: 9581041
    Abstract: The disclosure relates to a high temperature mechanical system, such as a gas turbine engine, including a first coating deposited on a first substrate and a second coating deposited on a second substrate. The first coating includes a first bond layer, a second bond layer, and a first ceramic outer layer, wherein the second bond layer is between the first bond layer and first ceramic outer layer. The second coating includes a third bond layer deposited on the substrate and a second ceramic outer layer deposited on the third bond layer. The second coating is configured to abrade the first coating, e.g., during operation of the high temperature mechanical system.
    Type: Grant
    Filed: February 9, 2011
    Date of Patent: February 28, 2017
    Assignee: Rolls-Royce Corporation
    Inventors: Raymond J. Sinatra, Jesse S. Daugherty, Marvin Alexander