Diverse Fluids To Motor Patents (Class 415/117)
  • Patent number: 10677084
    Abstract: A shroud assembly for a gas turbine engine includes a plurality of shroud segments that are attached to a shroud support with an inter-segment joint defined between shroud segments. The shroud assembly also includes a cooling flow path cooperatively defined by the shroud support and the first shroud segment. The cooling flow path includes an internal cooling passage within the shroud segments. The cooling flow path includes an outlet chamber configured to receive flow from the internal cooling passage. The shroud assembly additionally includes a seal arrangement that extends across the inter-segment joint. The seal arrangement, the first shroud segment, and the second shroud segment cooperatively define a seal chamber that is enclosed.
    Type: Grant
    Filed: February 20, 2018
    Date of Patent: June 9, 2020
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Jason Smoke, Kent L. Kime, Blake Petersen, Luke Zurmehly
  • Patent number: 10626731
    Abstract: An airfoil cooling system may be provided. An airfoil may have a pressure side and a suction side that are separated by a leading edge. The leading edge may pass through a stagnation point of the airfoil. A spar may have an outer surface comprising standoffs. The standoffs may define a cooling channel that extends across the leading edge on the outer surface of the spar, from the pressure side to the suction side. The cooling channel may have a first portion and a second portion defined by the standoffs. The first portion may be located closer to a base or a tip of the airfoil than the second portion. The spar may further comprise an inlet on the pressure side or the suction side. The inlet may be configured to convey a cooling fluid from a passageway located inside of the spar to the cooling channel.
    Type: Grant
    Filed: September 24, 2019
    Date of Patent: April 21, 2020
    Assignee: ROLLS-ROYCE CORPORATION
    Inventors: Brett Barker, Bruce Varney, Brian Shoemaker, Charles Bulgrin
  • Patent number: 10619998
    Abstract: A method of measuring the clearance between a rotating component and a static component in a rotating machine. The method comprises installing a rub pin on an interior surface of the static component, operating the rotating machine such that the rotating component impinges on the rub pin, securing the rotating machine, and inserting an optical device to visually ascertain the length of rub pin remaining. The method reduces the time and cost of clearance determinations by avoiding disassembly or the degree of disassembly of the rotating machine required to conduct a clearance determination.
    Type: Grant
    Filed: May 26, 2016
    Date of Patent: April 14, 2020
    Assignee: ROLLS-ROYCE CORPORATION
    Inventors: Mark Whitlock, Jonathan Acker
  • Patent number: 10590803
    Abstract: A turbine ring assembly includes ring sectors made as a single piece of ceramic matrix composite material and being for mounting on a metal ring support structure, the ring support structure having two tabs extending radially towards a gas flow passage, each ring sector having a first portion forming an annular base with a radially inside face defining the inside face of the turbine ring and an outside face from which there extend two tab-forming portions, the ring sectors having a section that is substantially ? shaped. The tabs of each ring sector fit axially over the tabs of the ring support structure with contact between the tabs of the ring support structure and the tabs of each ring sector when cold. The tabs of each ring sector are held to the ring support structure by pegs passing through holes formed in the tabs of each ring sector.
    Type: Grant
    Filed: March 15, 2016
    Date of Patent: March 17, 2020
    Assignees: SAFRAN AIRCRAFT ENGINES, SAFRAN CERAMICS
    Inventors: Lucien Henri Jacques Quennehen, Gaël Frédéric Claude Cyrille Evain, David Mathieu Paul Marsal, Thierry Guy Xavier Tesson
  • Patent number: 10562081
    Abstract: A device to fragment solidified bulk material is disclosed. The device comprises a hydraulic motor, a stationary assembly and rotating assemblies, wherein the rotating assemblies includes, a rotational upper whip mount assembly adapted to rotate in a direction, a rotational middle assembly perimeter adapted to rotate in the same direction as the rotational upper whip mount assembly, and a rotational lower whip mount assembly adapted to rotate in a direction opposite the rotational direction of the upper whip mount and middle perimeter assemblies, and a plurality of flails configured to fracture hardened, solidified bulk material while balancing the torque forces to more accurately keep the dual whip-head head in a desired location when operationally engaged with the bulk material.
    Type: Grant
    Filed: May 31, 2016
    Date of Patent: February 18, 2020
    Inventor: Gregory Wallace Nelson
  • Patent number: 10487848
    Abstract: A fan inlet diffuser housing includes a housing body of composite material and includes a heat exchanger interface portion positioned between an ejector housing portion and a bypass housing portion. A first transition region is formed between the heat exchanger interface portion and the ejector housing portion including an air cycle machine end reinforcement patch proximate to a heat exchanger interface. The air cycle machine end reinforcement patch includes a first patch thickness and a second patch thickness, and a ratio of the first patch thickness to the second patch thickness is between 2.02 and 3.11. An ejector is formed having an ejector gap width between a nozzle portion and a diffuser portion within the ejector housing portion of the housing body. The diffuser portion has a downstream ejector gap width, and a ratio of the downstream ejector gap width to the ejector gap width is between 4.62 and 5.01.
    Type: Grant
    Filed: April 6, 2017
    Date of Patent: November 26, 2019
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Eric Chrabascz, Theodore C. Wright
  • Patent number: 10473061
    Abstract: Methods and systems are provided for injecting water stored in a water reservoir at a plurality of locations in an engine system, including directly into engine cylinders, upstream of a turbocharger turbine, and at an exhaust manifold, and controlling a water level of the water reservoir. In one example, a method may include supplying the water stored in the water reservoir to one or more of a water injection system, a windshield wiper system, an engine coolant system, and a drinking water system based on water supply conditions and responsive to engine operating conditions. When the water level is low (e.g., below a threshold), supply to the water injection system may be prioritized.
    Type: Grant
    Filed: March 21, 2017
    Date of Patent: November 12, 2019
    Assignee: Ford Global Technologies, LLC
    Inventors: Douglas Raymond Martin, John Eric Rollinger, Kenneth James Miller, Aed M. Dudar, Lauren Angelina Martin
  • Patent number: 10465694
    Abstract: A method and system to provide a fan inlet diffuser housing including a housing body formed from a composite material, wherein the composite material includes a base fiberglass material having a first conductivity, a conductive material having a second conductivity, wherein the second conductivity is greater than the first conductivity, and a binder that bonds the base fiberglass material and the conductive material.
    Type: Grant
    Filed: April 5, 2017
    Date of Patent: November 5, 2019
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Eric Chrabascz, Michael E. Folsom, Georgina Tucsa, Murtuza Lokhandwalla
  • Patent number: 10450885
    Abstract: A stator heat shield for a gas turbine having a hot gas flow path, is disclosed. The stator heat shield includes a first surface configured to face the hot gas flow path of the gas turbine; a second surface opposite to the first surface; cooling channels for directing cooling fluid from the second surface towards the first surface; and cavities arranged at the first surface for receiving the cooling fluid from at least a part of the cooling channels; wherein at least a part of the cavities each have at least two corresponding cooling channels open thereto, the at least two corresponding cooling channels being inclined towards each other. In use, a vortex is created in the cavity.
    Type: Grant
    Filed: January 25, 2017
    Date of Patent: October 22, 2019
    Assignee: ANSALDO ENERGIA SWITZERLAND AG
    Inventors: Andrey Sedlov, Maxim Plodistyy, Sergey Vorontsov
  • Patent number: 10273825
    Abstract: A wall arrangement for the main gas path of a gas turbine engine, including: a wall segment which defines the main gas path, the wall segment having a gas path side, an outboard side and a support wall extending from the outboard side towards a supporting structure, and a channel member abutting the support wall and having one or more channels defined by the abutment of the support wall and channel member, the one or more channel having radially separated inlet and outlet.
    Type: Grant
    Filed: May 11, 2016
    Date of Patent: April 30, 2019
    Assignee: ROLLS-ROYCE plc
    Inventors: Simon L. Jones, Mark J. Simms
  • Patent number: 10030520
    Abstract: A blade for a water current turbine rotor, which extends along a radial direction and comprises an outer surface, an inner surface, a leading edge, and a trailing edge. The leading edge is the edge of the blade that extends along the radial direction and is disposed upstream in the direction in which the water flows along the blade, while the trailing edge is the edge of the blade opposite the leading edge and is disposed downstream in the direction of flow. At least one portion of the blade has a profile comprising a thick portion and a thin portion, the cross section being perpendicular to the radial direction. The thick portion and the thin portion each have a maximum thickness along a direction perpendicular to the outer surface, the maximum thickness of the thick portion being at least four times greater than the maximum thickness of the thin portion.
    Type: Grant
    Filed: January 24, 2013
    Date of Patent: July 24, 2018
    Assignee: GE ENERGY POWER CONVERSION TECHNOLOGY LTD
    Inventors: Hugo Duchene, Philippe Cagnin, Antoine Girard-Pecarrere
  • Patent number: 9989070
    Abstract: According to one aspect, an air cycle machine includes a fan rotor, a diffuser cone axially aligned with the fan rotor, and a strut plate assembly. The strut plate assembly includes a first strut plate and a second strut plate with an ejector formed between the first strut plate and the second strut plate. The first strut plate is axially positioned between the fan rotor and the ejector, and the second strut plate is axially positioned between the fan rotor and the diffuser cone. The first strut plate includes a plurality of outer struts and is absent inner struts between the fan rotor and the ejector. The second strut plate includes a plurality of inner struts and outer struts, where the inner struts are axially positioned between the ejector and the diffuser cone.
    Type: Grant
    Filed: October 1, 2014
    Date of Patent: June 5, 2018
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Craig M. Beers, Harold W. Hipsky
  • Patent number: 9963989
    Abstract: A vane seal assembly for a gas turbine engine comprises of a case including a first connector. A notch in the case adjoins the groove. A vane having a second connector mates with the first connector. A seal assembly is provided between the vane and the case to provide a sealed cavity adjoining the notch.
    Type: Grant
    Filed: June 5, 2014
    Date of Patent: May 8, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Anton G. Banks, Robert L. Hazzard
  • Patent number: 9945250
    Abstract: An aircraft gas turbine is constituted by accommodating a compressor (14), a combustor (15), and a turbine (16) in a cylindrical main unit casing (12). A thick wall part (52) is provided on an outer periphery side of rotor blades (34) in the main unit casing. A cooling passage (53), for cooling the thick wall part (52) by circulating compressed air compressed by the compressor, is provided in the thick wall part. Also provided is a discharge passage (55) for discharging compressed air having circulated in the cooling passage to a combustion gas passage A. The structural strength of the thick wall part is ensured by appropriately cooling the thick wall part of the casing, while simplifying the structure and preventing a decrease in efficiency, thereby ensuring effective containment performance and an appropriate clearance between the casing and the rotor blades.
    Type: Grant
    Filed: January 17, 2011
    Date of Patent: April 17, 2018
    Assignee: MITSUBISHI HEAVY INDUSTRIES AERO ENGINES, LTD.
    Inventors: Tsuyoshi Kitamura, Shinichiro Masaki
  • Patent number: 9915153
    Abstract: A shroud segment assembly for use within a turbine shroud of a gas turbine engine may generally include a forward shroud portion having a forward outer arm and a forward inner arm extending from a forward wall and an aft shroud portion having an aft outer arm and an aft inner arm extending from an aft wall. Additionally, the shroud segment assembly may include a first expansion joint positioned between the forward and aft shroud portions such that the first expansion joint extends circumferentially between the forward outer arm of the forward shroud portion and the aft outer arm of the aft shroud portion and a second expansion joint positioned between the forward and aft shroud portions such that the second expansion joint extends circumferentially between the forward inner arm of the forward shroud portion and the aft outer arm of the aft shroud portion.
    Type: Grant
    Filed: May 11, 2015
    Date of Patent: March 13, 2018
    Assignee: General Electric Company
    Inventor: Alexander Martin Sener
  • Patent number: 9909448
    Abstract: A heat transfer apparatus for a gas turbine engine includes: a component having a wall structure defining a flow bounding surface; a chamber formed in the component, the chamber including a wicking structure, a vapor channel, and a working fluid.
    Type: Grant
    Filed: April 15, 2015
    Date of Patent: March 6, 2018
    Assignee: General Electric Company
    Inventors: William Dwight Gerstler, James Michael Kostka, Jeffrey Douglas Rambo, John William Moores
  • Patent number: 9897317
    Abstract: The present invention discloses a novel and improved device and method for securing a combustion liner within a gas turbine combustor. The improved configuration comprises a plurality of equally spaced support tab assemblies secured about the combustion liner and positioned radially outward of the combustion zone. The support tab assemblies comprise parallel liner tabs which provide increased flexibility, greater structural support, and lower operating stresses.
    Type: Grant
    Filed: September 26, 2013
    Date of Patent: February 20, 2018
    Assignee: ANSALDO ENERGIA IP UK LIMITED
    Inventors: Peter John Stuttaford, Stephen Jorgensen, Hany Rizkalla
  • Patent number: 9803494
    Abstract: A sealing element is described for positioning in a turbomachine, for the self-securing of a sealing element in a mounting position, its support structure having a safeguard which has a springy catch section, whose mounting surface is inclined at a smaller angle in the mounting direction than a securing surface in the opposite direction, a sealing unit, and a turbomachine.
    Type: Grant
    Filed: December 2, 2014
    Date of Patent: October 31, 2017
    Assignee: MTU Aero Engines AG
    Inventors: Hans Stricker, Stefan Rauscher
  • Patent number: 9726043
    Abstract: A shroud apparatus for a gas turbine engine includes: an annular metallic hanger; a shroud segment disposed inboard of the hanger, comprising low-ductility material and having a cross-sectional shape defined by opposed forward and aft walls, and opposed inner and outer walls, the walls extending between opposed first and second end faces, wherein the inner wall defines an arcuate inner flowpath surface; and a retainer mechanically coupled to the hanger which engages the shroud segment to retain the shroud segment to the hanger while permitting movement of the shroud segment in a radial direction.
    Type: Grant
    Filed: December 15, 2011
    Date of Patent: August 8, 2017
    Assignee: General Electric Company
    Inventors: Michael John Franks, Jason David Shapiro, Samuel Ross Rulli, Roger Lee Doughty
  • Patent number: 9599411
    Abstract: Provided is a film cooling structure capable of suppressing a cooling medium film from being separated from a wall surface, to increase a film efficiency on the wall surface and thereby-cool the wall surface effectively. One or more pairs of injection holes are formed on a wall surface facing a passage of high-temperature gas to inject a cooling medium to the passage. A single supply passage is formed inside the wall to supply the cooling medium to the injection holes. A separating section is provided between the injection holes in a location forward relative to rear ends of the injection holes to separate the cooling medium into components flowing to the injection holes. An injection direction of the cooling medium is inclined relative to a gas flow direction so that the cooling medium forms swirl flows that push the cooling medium against the wall surface.
    Type: Grant
    Filed: March 2, 2011
    Date of Patent: March 21, 2017
    Assignees: Kawasaki Jukogyo Kabushiki Kaisha, B&B AGEMA GmbH
    Inventors: Ryozo Tanaka, Masahide Kazari, Takao Sugimoto, Karsten Kusterer, Dieter Bohn, Anas Elyas
  • Patent number: 9534785
    Abstract: A seal for sealing a combustor heat shield against an interior surface of a combustor shell, the seal comprising: a first sealing surface on the interior surface of the combustor shell; and a second sealing surface on a rail on an edge of a heat shield, wherein each of the first and second sealing surfaces include first and second projections defining a non-linear leakage path between the projections.
    Type: Grant
    Filed: August 26, 2014
    Date of Patent: January 3, 2017
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Nigel Davenport, Yen-Wen Wang
  • Patent number: 9476317
    Abstract: The present application provides a stage of a gas turbine engine. The stage may include a bucket extending radially about a longitudinal axis of the gas turbine engine, a shroud facing the bucket, the shroud including a fore end portion including a radially inner surface spaced a first distance from the longitudinal axis, and a forward step honeycomb seal positioned on the shroud downstream of the fore end portion and facing the bucket. The forward step honeycomb seal may include a first linear portion including a radially inner surface spaced a second distance from the longitudinal axis, and a forward step portion positioned adjacent to and downstream of the first linear portion, the forward step portion including a radially inner surface spaced a third distance from the longitudinal axis, wherein the second distance is greater than the third distance, and wherein the third distance is greater than the first distance.
    Type: Grant
    Filed: June 24, 2015
    Date of Patent: October 25, 2016
    Assignee: General Electric Company
    Inventor: Rohit Chouhan
  • Patent number: 9447756
    Abstract: An ambient air intake duct of a static gas turbine is provided, having at least one filter, which is arranged in the intake duct, for cleaning the ambient air (A) that can flow through the intake duct. A method for operating a static gas turbine which is equipped with a filter for cleaning the ambient air (A) is also provided. To rapidly provide a higher level of gas turbine power to a generator, it is provided that, by means of a bypass or by means of flaps arranged downstream of the filter, partially to completely unfiltered ambient air (A) can temporarily flow into the compressor inlet.
    Type: Grant
    Filed: July 13, 2012
    Date of Patent: September 20, 2016
    Assignee: SIEMENS AKTIENGESELLSCHAFT
    Inventor: Oliver Schneider
  • Patent number: 9169739
    Abstract: A Blade Outer Air Seal (BOAS) includes a body manufactured of a metal alloy, the body includes a face opposite a forward interface and an aft interface, the face includes a cavity. A non-metallic insert within the cavity such that the insert is flush with the face.
    Type: Grant
    Filed: January 4, 2012
    Date of Patent: October 27, 2015
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Sergey Mironets, Edward F. Pietraszkiewicz, Alexander Staroselsky, Mark F. Zelesky
  • Patent number: 9133722
    Abstract: A system for supplying an injection fluid to a combustor is disclosed. The system includes a transition duct comprising an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The passage defines a combustion chamber. The system further includes a tube providing fluid communication for the injection fluid to flow through the transition duct and into the combustion chamber.
    Type: Grant
    Filed: April 30, 2012
    Date of Patent: September 15, 2015
    Assignee: General Electric Company
    Inventors: Jeffrey Scott LeBegue, Ronnie Ray Pentecost, James Scott Flanagan, Won-Wook Kim, Kevin Weston McMahan
  • Patent number: 9097114
    Abstract: A power plant comprising: a rotor mounted for rotation; a rotor casing; and a rotor casing liner, comprising a plurality of sections, positioned between the rotor and the rotor casing; wherein at least one section of the plurality of sections of the rotor casing liner is sized to enable removal of the at least one section without adapting the rotor.
    Type: Grant
    Filed: August 17, 2012
    Date of Patent: August 4, 2015
    Assignee: ROLLS-ROYCE PLC
    Inventors: James O'Toole, William Playford
  • Patent number: 9074488
    Abstract: The invention refers to an arrangement for sealing an open cavity against hot gas entrainment. The open cavity is arranged between two axially adjacent stationary components limiting radially a hot gas path of a rotary flow machine, of which at least the downstream component carries at least one airfoil extending radially into said hot gas path. A multitude of air jets is directed into the open cavity such that hot gas flowing over the open cavity is prevented from penetrating into the open cavity completely. The invention has an arrangement of supply conduits for air jets which are directed into the open cavity with a jet momentum such that hot gas is induced not to enter the open cavity and forming at least one hot gas vortex close to the hot gas path within the open cavity and preventing hot gas from penetrating into the open cavity beyond the extension of the hot gas vortex.
    Type: Grant
    Filed: January 14, 2014
    Date of Patent: July 7, 2015
    Assignee: ALSTOM Technology Ltd
    Inventors: Paul Marlow, Selma Zahirovic, Robert Marmilic, Marc Widmer, Joerg Krückels
  • Patent number: 9068472
    Abstract: A component of a turbine stage of a gas turbine engine is provided, the component forming an endwall for the working gas annulus of the stage. The component has one or more internal plena behind the endwall which, in use, contain a flow of cooling air. The component further has a plurality of exhaust holes in the endwall. The holes connect the plena to a gas-washed surface of the endwall such that the cooling air effuses through the holes to form a cooling film over the gas-washed surface. Each exhaust hole has a flow cross-sectional area which is greater at an intermediate position between the entrance of the hole from the respective plenum and the exit of the hole to the gas-washed surface than it is at said exit.
    Type: Grant
    Filed: February 8, 2012
    Date of Patent: June 30, 2015
    Assignee: ROLLS-ROYCE PLC
    Inventors: Anthony J. Rawlinson, Peter Ireland, Lynne H. Turner, Ian Tibbott
  • Patent number: 9062561
    Abstract: A component of a turbine stage of a gas turbine engine is provided. The component forms an endwall for the working gas annulus of the stage. The component has one or more internal passages behind the endwall which, in use, carry a flow of cooling air providing convective cooling for the component at the endwall. Each passage is formed by a plurality of straight passage sections. The passage sections connect end-to-end such that the connections between nearest-neighbour passage sections form angled bends. A first portion of the passage sections lie in a first plane. A second portion of the passage sections lie in a second plane which is spaced from and parallel to the first plane. A third portion of the passage sections extend between the first and the second planes.
    Type: Grant
    Filed: August 11, 2011
    Date of Patent: June 23, 2015
    Assignee: ROLLS-ROYCE PLC
    Inventor: Ian Tibbott
  • Publication number: 20150107249
    Abstract: A system includes a gas compressor system and a thermal cycle. The gas compressor system includes a compressor housing defining an interior compressor chamber. A gas compressor is in the interior compressor chamber to compress gas received into interior compressor chamber. A heat exchange fluid passage is provided adjacent to a surface that contacts the gas being compressed by the gas compressor. The thermal cycle includes a working fluid heated using the heat exchange fluid passage of the compressor housing. The working fluid is expanded by the thermal cycle to generate electricity.
    Type: Application
    Filed: October 22, 2013
    Publication date: April 23, 2015
    Applicant: Access Energy LLC
    Inventors: Herman Artinian, Parsa Mirmobin
  • Publication number: 20150086333
    Abstract: An article for mixing ambient fluid with a motive fluid comprises a conduit, and thermally conductive concentric inner and outer nozzles extending from the conduit. The conduit is configured to supply the motive fluid to the outer nozzle and the ambient fluid to the inner nozzle. The inner nozzle extends further downstream from the conduit than the outer nozzle.
    Type: Application
    Filed: September 20, 2013
    Publication date: March 26, 2015
    Applicant: The Boeing Company
    Inventors: Joseph K. Schnoebelen, Kurt E. Acheson
  • Patent number: 8956106
    Abstract: An apparatus is provided having a first zone with a fluid flow at a first pressure, and a second zone with a fluid flow at a second pressure. A sump cavity is provided in fluid communication with the first zone and a sump vent. An eductor system may be provided with a fluid flow path therethrough and in fluid communication with the second zone and the sump vent. The eductor system may be provided with an altitude sensing valve and may also be provided with gage pressure sensing valve. The eductor system may further be provided with a second gage pressure sensing valve and may also be provided with an orifice plate. The gage pressure sensing valves may react to the gage pressure of the second zone.
    Type: Grant
    Filed: December 20, 2011
    Date of Patent: February 17, 2015
    Assignee: General Electric Company
    Inventors: Ning Fang, Benjamin Joseph Simpson, Duane Howard Anstead, Adam Mitchell Record, Donald James Welty
  • Publication number: 20140356128
    Abstract: The present invention relates to a method for providing a fluid flow to a compressor system of a first turbo machine, wherein the compressor system includes at least one compressor housing in which at least one impeller is arranged and through which a compressor flow flows. The method includes feeding a primary fluid flow to a mixing region of the compressor system. The method further includes feeding a secondary fluid flow from an outside region of the compressor housing to the mixing region so that the secondary fluid flow mixes at least in part with the primary fluid flow to form a resulting fluid flow so that between the primary fluid flow and the secondary fluid flow a momentum exchange takes place, and so that the secondary fluid flow is promoted by the primary fluid flow. The method further includes feeding the resulting fluid flow to the compressor flow upstream of the impeller in the direction of the impeller.
    Type: Application
    Filed: December 20, 2012
    Publication date: December 4, 2014
    Applicant: UNIVERSITAT DER BUNDESWEHR MUNCHEN
    Inventors: Stefan Bindl, Marcel Stossel, Reinhard Niehuis, Bastian Muth
  • Patent number: 8790073
    Abstract: A gas turbine engine including a stator vane directing hot combustion gases onto rotor blades is provided. The stator vane includes a platform disposed at the side of the vane radially inward/outward with respect to the axis of rotation of the engine, the platform having a trailing edge portion downstream with respect to the flow of gases past the stator vane. A support and cooling arrangement is included for directing a cooling fluid to an upstream end of a radially inwardly/outwardly facing side of the trailing edge portion of the platform, the arrangement also directing the cooling fluid to flow over the side in a generally axial direction to a downstream end of the side, the cooling fluid cooling the trailing edge portion as it flows over the side, wherein turbulators are included to increase heat transfer from the trailing edge portion as the cooling fluid flows over the side.
    Type: Grant
    Filed: January 21, 2010
    Date of Patent: July 29, 2014
    Assignee: Siemens Aktiengesellschaft
    Inventor: Jonathan Mugglestone
  • Publication number: 20140178176
    Abstract: An axial compressor comprising liquid drop feed means for feeding liquid drops to an operating fluid of the compressor, a casing for forming a flow path through which the operating fluid flows down and a plurality of stages, each of which is composed of one continuous rotor blade row and one continuous stator vane row, the axial compressor being structured so that the liquid drops evaporate inside the compressor, characterized in that: the casing is provided with a cavity therein, and the cavity is formed by an outer casing and an inner casing which is enclosing a periphery of the rotor blade rows at the plurality of stages and forming internally a flow path of the operating fluid, and a flow path is provided for feeding the operating fluid to the cavity on a downstream side of a region forming the cavity of the inner casing.
    Type: Application
    Filed: November 5, 2013
    Publication date: June 26, 2014
    Applicant: Hitachi, Ltd.
    Inventors: Yasuo TAKAHASHI, Tetsuro MORISAKI, Chihiro MYOREN, Kohta KAWAMURA
  • Patent number: 8727705
    Abstract: A steam turbine 10 is provided with a double-structure comprising an inner casing 20 and an outer casing 21. A turbine rotor 22, in which plural stages of moving blades 24 are circumferentially implanted, is operatively disposed in inner casing 20. A diaphragm outer ring 25 and a diaphragm inner ring are disposed along the circumferential direction in inner casing 20. Stationary blades 27 are circumferentially provided between diaphragm outer ring 25 and the diaphragm inner ring, so that diaphragm outer ring 25, the diaphragm inner ring and stationary blades 27 form a stage of stationary blades. The stages of the stationary blades are arranged alternately with the stages of moving blades 24 in the axial direction of turbine rotor 22. A cooling medium passage 40 for passing a cooling medium CM which is supplied through a supply pipe 45 is formed between inner casing 20 and diaphragm outer ring 25.
    Type: Grant
    Filed: July 20, 2010
    Date of Patent: May 20, 2014
    Assignee: Kabushiki Kaisha Toshiba
    Inventors: Asako Inomata, Katsuya Yamashita, Kazuhiro Saito, Takao Inukai, Kunihiko Wada, Kazutaka Ikeda, Takeo Suga
  • Patent number: 8702376
    Abstract: The disclosure relates to a radially fed axial steam turbine with a cold inlet duct, axially displaced from a hot inlet duct such that is it further away from a first blade row than the hot inlet duct. The cold inlet duct receives a cold steam from a cold inlet spiral and directs it into the hot inlet duct in such a way that a boundary layer of cold steam is formed over the rotor circumferential surface between the outlet end of the cold inlet duct and the blade and vane rows. The rotor circumferential surface is also adapted to promote and maintain the boundary layer. In this way, a maximum temperature to which the rotor is exposed can be reduced.
    Type: Grant
    Filed: October 12, 2010
    Date of Patent: April 22, 2014
    Assignee: Alstom Technology Ltd.
    Inventors: Thomas Mokulys, Vishal Borikar, Giorgio Zanazzi, Davor Kriz, Ludwig Boxheimer, Luca Ripamonti
  • Patent number: 8602721
    Abstract: Invention relates to method of operating turbocharged piston engine including the steps of running the engine during a period, shutting down the engine, and restarting the engine. After a first time interval from shutting down the engine, and while a turbine and compressor parts of the turbocharger are rotating, a cleaning agent is introduced into the stream of gas flowing in a flow channel upstream the turbine part during a second time interval prior to restarting the engine.
    Type: Grant
    Filed: December 2, 2009
    Date of Patent: December 10, 2013
    Assignee: Wartsila Finland Oy
    Inventor: Branimir Andonov
  • Patent number: 8591166
    Abstract: A gas turbine engine axial compressor vane is disclosed having an aperture capable of flowing a relatively high pressure working fluid to change a direction of a flow vector downstream of the vane. The relatively high pressure working fluid can originate from a compressor discharge. The vane may have any number of apertures.
    Type: Grant
    Filed: December 17, 2009
    Date of Patent: November 26, 2013
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventor: William Barry Bryan
  • Publication number: 20130266419
    Abstract: Intakes of gas turbine engines are subject to cross winds and high incidence cross flows which can affect the stability of air to the propulsive fan. An active flow control arrangement for an intake comprises a compressed gas supply pipe, a valve arrangement, a controller, and a compressed gas distribution pipe. The supply pipe is fluidly connects between a compressed gas source and the valve arrangement. The distribution pipe fluidly connects between the valve arrangement and intake surface for supply of compressed gas thereto. The active flow control arrangement is operable to supply compressed gas to the intake surface to prevent separation of a main air flow passing through the intake from the inlet surface thereby maintaining stability of the intake air flow to the fan.
    Type: Application
    Filed: December 13, 2012
    Publication date: October 10, 2013
    Applicant: ROLLS-ROYCE PLC
    Inventor: ROLLS-ROYCE PLC
  • Publication number: 20130259638
    Abstract: An example turbomachine assembly includes, among other things, a nose cone of a turbomachine, and a pump at least partially within an interior of the nose cone. The pump is selectively rotated by a motor to communicate air to the interior.
    Type: Application
    Filed: April 2, 2012
    Publication date: October 3, 2013
    Inventors: Gabriel L. Suciu, Simon Pickford, William K. Ackermann, Nathan Snape
  • Publication number: 20130259639
    Abstract: An example turbomachine assembly includes, among other things, a nose cone of a turbomachine, and a pump that is selectively driven by a motor or a shaft to communicate air to an interior of the nose cone. The pump shaft is driven by a dedicated geared architecture.
    Type: Application
    Filed: April 2, 2012
    Publication date: October 3, 2013
    Inventors: Gabriel L. Suciu, Simon Pickford, William K. Ackermann, Nathan Snape
  • Publication number: 20130209239
    Abstract: The invention relates to a device for cooling of electric motor (10), which electric motor comprises a stator (30) with a jacket surface/stator back (35), wherein a housing (40) is arranged to surround the stator (30), the device comprising at least one cooling channel (50) in which a liquid cooling medium is intended to stream for cooling of the electric motor (10), wherein the housing (40) is arranged to run separated from the stator (30) along a main part of the thermoset cased jacket surface (35) of the stator (30) for forming of said cooling channel (50) between the housing (40) and said jacket surface (50), wherein the stator winding (32) of the stator is arranged to run along and axially project from and turn outside of said jacket surface (35), wherein the stator (30) including the projecting stator winding (32) is embedded with said thermoset (E), wherein said cooling channel (50) also is formed between the housing (40) and the thus projecting stator winding (32).
    Type: Application
    Filed: May 18, 2011
    Publication date: August 15, 2013
    Applicant: BAE SYSTEMS HÄGGLUNDS AKTIEBOLAG
    Inventors: Pontus Karlsson, Viktor Lassila
  • Patent number: 8454302
    Abstract: A steam supply for a turbomachine with an inner housing and an outer housing is provided. The steam supply includes an inner pipe and an outer pipe, a cooling medium inlet opening disposed in the outer pipe and a cooling medium entering thereby into space between the inner pipe and the outer pipe, and the inner pipe being cooled thereby.
    Type: Grant
    Filed: July 25, 2008
    Date of Patent: June 4, 2013
    Assignee: Siemens Aktiengesellschaft
    Inventor: Kai Wieghardt
  • Publication number: 20130094939
    Abstract: An in-pipe turbine with the use of an air bubble in a new and unique configuration with electronic controls can improve the efficiency of in-pipe hydroelectric turbines.
    Type: Application
    Filed: June 15, 2011
    Publication date: April 18, 2013
    Applicant: LEVIATHAN ENERGY HYDROELECTRIC LTD.
    Inventors: Daniel Farb, Avner Farkash, Zeev Savion
  • Patent number: 8403629
    Abstract: A stator for installation in a rear section of a jet engine includes a plurality of guide vanes which extend in the radial direction of the stator and between them define ducts for leading a gas. A first side of the stator in its axial direction defines an inlet for the gas and a second side, opposite the first side, defines an outlet for the gas. The guide vanes have such a shape that together they at least substantially cover the gas inlet viewed in the axial direction of the stator from the outlet side thereof.
    Type: Grant
    Filed: October 20, 2005
    Date of Patent: March 26, 2013
    Assignee: Volvo Aero Corporation
    Inventor: Anders Lundbladh
  • Patent number: 8402771
    Abstract: A combustor (14) is placed next to a turbine (16), on the side opposite a compressor (12). A heat insulation device (20) for reducing the transmission of heat from the high-temperature side to the low-temperature side is provided between the combustor/turbine and the compressor. A connection shaft (18) has an axial hole (18a) open on the inlet side of the compressor and axially extending to near a turbine impeller, and also has a radial hole (18b) open near the turbine impeller to the outside of the connection shaft and radially extending to be in communication with the axial hole.
    Type: Grant
    Filed: June 19, 2012
    Date of Patent: March 26, 2013
    Assignee: IHI Corporation
    Inventor: Kosuke Isomura
  • Patent number: 8398375
    Abstract: To provide a can manufacturing pump impeller in which a stress of a base portion of a blade is prevented from increasing while improving the strength of a joint portion of a hub and a boss. In order to reinforce a joint portion of a hub and a boss, a plate is jointed to the inside of an impeller. In order not to overlap a base portion of a blade and the plate with each other on the hub, an opening portion is provided in the plate around the base portion of the blade on the hub. As a shape of the opening portion, a semicircular shape, a semielliptical shape, a rectangular shape, or a trapezoidal shape can be selected. Further, as a plate shape, a flat plate structure, a shell structure, or a curved structure can be selected.
    Type: Grant
    Filed: February 18, 2009
    Date of Patent: March 19, 2013
    Assignee: Hitachi Plant Technologies, Ltd.
    Inventors: Kohei Tanaka, Yoshimasa Chiba, Sadashi Tanaka, Koji Hayashi, Tomohiro Naruse, Takaki Fukuchi, Takeshi Kazama
  • Patent number: 8388301
    Abstract: A turbine system for the utilization of the energy of oceanic waves includes: a chamber that is provided with an opening at its lower end and at its upper end respectively; a duct that is open at both ends for guiding a stream of air, the lower end of the chamber being designated to be submerged in ocean water, and the opening of the upper end being connected with one of the ends of the duct; an energy unit that is mounted coaxial to such and surrounded by the duct; and a device for cleaning the rotor blades of deposits or for preventing the formation of deposits on the rotor blades.
    Type: Grant
    Filed: June 4, 2009
    Date of Patent: March 5, 2013
    Assignee: Voith Patent GmbH
    Inventors: William K. Tease, Janet Lees
  • Patent number: 8360711
    Abstract: An apparatus for cooling air for an intake to a gas turbine, is provided and includes a pressurized water piping and nozzle apparatus for producing a water spray in an airflow to the intake; and evaporative media for receiving the spray and causing a pressurizing of the air in the airflow.
    Type: Grant
    Filed: August 22, 2007
    Date of Patent: January 29, 2013
    Assignee: General Electric Company
    Inventors: Rahul Jaikaran Chillar, Douglas Scott Byrd