With Heating, Cooling Or Thermal Insulation Means Patents (Class 416/95)
  • Patent number: 10487674
    Abstract: A securing device for a turbine blade wherein the securing device prevents the turbine blade from moving radially and axially and includes a retaining piece that includes a projection which extends into a recess in the root of the turbine blade and which prevents the blade from moving axially.
    Type: Grant
    Filed: January 5, 2016
    Date of Patent: November 26, 2019
    Assignee: Siemens Aktiengesellschaft
    Inventor: Andreas Rehnsch
  • Patent number: 10472969
    Abstract: A cooling structure for a turbine includes a plurality of disks configured to rotate integrally with blades, the disks being arranged along a rotational axis; and the disks have disk holes defined therein and arranged in a circumferential direction for supplying cooling air for cooling the blades to downstream disks. At least one of the disk holes is set such that, when a rotational direction of the disk is defined as a positive direction and a direction opposite the rotational direction is defined as a negative direction, an outlet absolute circumferential velocity vector which is a component in the rotational direction of a velocity vector of the cooling air at an outlet of the disk hole is smaller than an inlet absolute circumferential velocity vector which is a component in the rotational direction of a velocity vector of the cooling air at an inlet of the disk hole.
    Type: Grant
    Filed: September 7, 2015
    Date of Patent: November 12, 2019
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventor: Daigo Fujimura
  • Patent number: 10393428
    Abstract: The invention relates to a device for cooling and/or liquefying, at a low-temperature, a working fluid containing helium or consisting of pure helium. The device includes a working circuit provided with a compressor station and a cold box. The compressor station includes one or more compression stages, each using one or more compressors that include a compressor wheel rigidly connected to an axle that is rotatably mounted on bearings. The axle of each compressor is rotated by an output shaft of a motor via a gear mechanism placed in a mechanical housing including lubricating oil. Said device is characterized in that the inner space of the mechanical housing contains a gaseous atmosphere consisting of a gaseous mixture having a mean molar mass that smaller than the molar mass of the air.
    Type: Grant
    Filed: November 6, 2014
    Date of Patent: August 27, 2019
    Assignee: L'Air Liquide Societe Anonyme Pour L'Etude Et L'Exploitation Des Procedes Georges Claude
    Inventors: Jean-Marc Bernhardt, Fabien Durand
  • Patent number: 10316751
    Abstract: a gas turbine engine structure includes a body radially spanning an inner portion and an outer portion. The structure body includes a first passage interior to the structure body. The first passage includes a first opening on one of a radially outward edge and a radially inward edge of the structure, and a second opening on the other of the radially outward edge and the radially inward edge of the structure. A second passage is also included interior to the structure. The second passage is approximately aligned with the first passage, and is disposed between the first passage and one of the first surface and the second surface of the structure. The second passage insulates the first passage from heat transfer through one of the first surface and the second surface.
    Type: Grant
    Filed: August 27, 2015
    Date of Patent: June 11, 2019
    Assignee: United Technologies Corporation
    Inventors: Benjamin F. Hagan, Ryan Alan Waite
  • Patent number: 10247015
    Abstract: A gas turbine engine and a blisk are disclosed, including methods of making the same. The blisk may include a disk, spars of airfoils, platforms, and shanks of airfoils integrally formed as a unit. Such blisk features may be integrally formed by a casting process or additive manufacturing. The blisk includes cooled airfoils, such that the spar is hollow, and a cover panel is bonded to an outer surface of standoffs to define passages between the cover panel and the spar. Cooling air is fed to the hollow spar through a cooling feed channel defined in the disk or shank portion.
    Type: Grant
    Filed: January 13, 2017
    Date of Patent: April 2, 2019
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Matthew T. Kush, Douglas D. Dierksmeier
  • Patent number: 10233761
    Abstract: A turbine airfoil for a rotating blade or stationary nozzle vane includes an airfoil body including a leading edge and a trailing edge. A coolant supply passage extends within the airfoil body, and a coolant return passage extends within the airfoil body. A first trench is in an external surface of the airfoil body, the first trench extending to the trailing edge and being in fluid communication with the coolant supply passage. A second trench is in the external surface of the airfoil body, the second trench extending to the trailing edge and being in fluid communication with the coolant return passage and the first trench. A cover seats in the airfoil body and encloses the trenches to form coolant passages with the airfoil body. In embodiments, two coolant passages to and back from the trailing edge may be used to allow for a recycling flow.
    Type: Grant
    Filed: October 26, 2016
    Date of Patent: March 19, 2019
    Assignee: General Electric Company
    Inventors: Zachary John Snider, Gregory Thomas Foster, Joseph Anthony Weber, James Fredric Wiedenhoefer
  • Patent number: 10190422
    Abstract: A turbine blade for a gas turbine engine may include an outer, peripheral wall extending along a suction side and a pressure side of the blade from a leading edge to a trailing edge of the blade and from a root end to a tip end of the blade, a substantially vertical bifurcating internal wall extending between the leading edge and the trailing edge of the blade in between the suction side and the pressure side of the blade, a plurality of pressure side cooling fluid passages defined between the peripheral wall on the pressure side of the blade and the bifurcating internal wall and extending at least part way from the root end to the tip end of the blade, and a plurality of suction side cooling fluid passages defined between the peripheral wall on the suction side of the blade and the bifurcating internal wall and extending at least part way from the tip end to the root end of the blade.
    Type: Grant
    Filed: April 12, 2016
    Date of Patent: January 29, 2019
    Assignee: Solar Turbines Incorporated
    Inventors: Luzeng Zhang, Juan Yin, Hee Koo Moon
  • Patent number: 10156244
    Abstract: A fan assembly for use in a gas turbine engine includes a fan wheel and a plurality of blades extending radially from the fan wheel away from a central axis of the fan assembly. Each of the blades includes a root coupled with the fan wheel and an airfoil extending radially outwardly from the root. The blades are adapted to rotate about the central axis to push air.
    Type: Grant
    Filed: February 12, 2016
    Date of Patent: December 18, 2018
    Assignee: Rolls-Royce Corporation
    Inventors: Roy D. Fulayter, Jonathan M. Rivers
  • Patent number: 10072585
    Abstract: A cooling system for a gas turbine engine turbine section includes a rotor supporting a blade having a cooling passage. A disc is secured relative to the rotor and it forms a cavity between the rotor and the disc. A bleed air source is in fluid communication with the cavity. An impeller is arranged in the cavity. The impeller is configured to increase a fluid pressure within the cavity to drive bleed air from the bleed air source and thereby provide a pressurized cooling fluid to the cooling passage.
    Type: Grant
    Filed: March 10, 2014
    Date of Patent: September 11, 2018
    Assignee: United Technologies Corporation
    Inventors: John H. Mosley, James P. Chrisikos, John J. O'Connor, Charles C. Wu, David Glasspoole, Roger Gates
  • Patent number: 10036255
    Abstract: A platform cooling device directs a cooling fluid onto a root side of a platform of a turbomachine part. The platform cooling device includes a first segment to be positioned at a root of the turbomachine part and a second segment, at an angle to the first segment, to be positioned at the root side of the platform of the turbomachine part. The second segment may include at least one impingement channel having an inlet for receiving at least a part of the cooling fluid and an outlet for releasing the received cooling fluid onto the root side of the platform. The first segment and the second segment may define a path for the cooling fluid via the impingement channel. A turbomachine component includes the platform cooling device.
    Type: Grant
    Filed: March 18, 2014
    Date of Patent: July 31, 2018
    Assignee: Siemens Aktiengesellschaft
    Inventors: Janos Szijarto, Lieke Wang
  • Patent number: 9869185
    Abstract: A turbine airfoil includes: a concave pressure sidewall and a convex suction sidewall joined together at a leading edge and a trailing edge, and extending between a root and a tip; an internal rib extending between the pressure sidewall and the suction sidewall; and a crossover hole formed in the rib, the crossover hole having a noncircular cross-sectional shape with a major axis defining a maximum dimension of the cross-sectional shape; wherein the major axis of the crossover hole lies in plane with the rib and is non-parallel to an imaginary curvilinear lateral centerline which defines a locus of points lying halfway between the pressure and suction sidewalls. The orientation of the crossover holes minimizes stress concentration caused by the presence of the crossover holes.
    Type: Grant
    Filed: July 30, 2013
    Date of Patent: January 16, 2018
    Assignee: General Electric Company
    Inventors: Shawn Michael Pearson, Steven Robert Brassfield, Stephen Mark Molter, Mark Edward Stegemiller, Nicholas Ertel, Vanessa Camarillo
  • Patent number: 9835139
    Abstract: In order to maximize cooling while minimizing drag in aerial vehicles of airborne wind turbines, it may be preferable to dissipate the cooling energy of the motors via a radiator in a region with advantageous airflow parameters. Aerial vehicle rotors operating in thrust mode may produce relatively more airflow velocity in certain regions further away from the center of the rotor blades, both radially and longitudinally. Placing a radiator in a rotor-supporting pylon and offset from the center of the rotor blades and aft of the rotor blades may allow for greater cooling while the aerial vehicle while in thrust mode.
    Type: Grant
    Filed: March 10, 2014
    Date of Patent: December 5, 2017
    Assignee: X Development LLC
    Inventor: Damon Vander Lind
  • Patent number: 9810072
    Abstract: A rotor blade includes a mounting portion comprising a mounting body that is formed to receive a coolant therein. An airfoil portion extends substantially radially outwardly from the mounting body and includes an airfoil body. The mounting body and the airfoil body define a plurality of primary cooling passages that extend substantially radially therein for routing the coolant through the airfoil body. Each of the primary cooling passages includes a cooling flow outlet that is formed along a tip portion of the airfoil body. The airfoil body further defines a plurality of trailing edge cooling passages, each having a coolant outlet that is formed along a trailing edge portion of the airfoil body. At least a portion of the trailing edge cooling passages are formed along a radially outer portion of the trailing edge proximate to the tip portion of the airfoil body.
    Type: Grant
    Filed: May 28, 2014
    Date of Patent: November 7, 2017
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Zhirui Dong, Xiuzhang James Zhang, Jason Adam Neville
  • Patent number: 9810234
    Abstract: A fan impeller for the conveyance of a gaseous fluid includes several blades arranged with constant angular spacing around a rotation axis. At least one blade has a boundary zone and an inner zone, together with a bead extending between them along a curved path and/or the boundary zone is determined by a first blade surface and the inner zone is determined by a second blade surface, which are arranged with varying geometry.
    Type: Grant
    Filed: September 10, 2014
    Date of Patent: November 7, 2017
    Assignee: Punker GmbH
    Inventors: Henning Bähren, Christian Hornhardt, Matthias Wolf, Yingan Xia
  • Patent number: 9770785
    Abstract: A system for forming a cooling hole in an airfoil includes a liquid-jet guided laser. The liquid-jet guided laser generates a laser beam confined within a fluid column. The fluid column/laser beam is directed at an outer surface of the airfoil. The system also includes a purge medium supply that is fluidly coupled to an aperture of the airfoil. The purge medium supply provides a purge medium into an inner cavity of the airfoil. The purge medium flow is oriented to flow in a flow direction that is substantially parallel to an inner surface of the cavity. A cooling hole is formed in the airfoil and extends through the outer surface and penetrates the inner surface of the cavity. A centerline of the cooling hole forms an acute angle with respect to the purge medium flow direction. The system described herein provides a method for manufacturing an airfoil.
    Type: Grant
    Filed: November 18, 2014
    Date of Patent: September 26, 2017
    Assignee: General Electric Company
    Inventors: Zhaoli Hu, Abe Denis Darling, Shamgar Elijah McDowell, Douglas Anthony Serieno
  • Patent number: 9670784
    Abstract: Various embodiments of the invention include turbine buckets and systems employing such buckets. Various particular embodiments include a turbine bucket having: a base including: a casing having at least one exhaust aperture on an outer surface of the casing; and a core within the casing, the core having: a serpentine cooling passage; and at least one outlet passage fluidly connected with the serpentine cooling passage and the exhaust aperture, wherein the at least one outlet passage permits flow of a coolant from the serpentine cooling passage to the at least one exhaust aperture on the outer surface of the casing; and an airfoil connected with the base at a first end of the airfoil, the airfoil including: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side.
    Type: Grant
    Filed: October 23, 2013
    Date of Patent: June 6, 2017
    Assignee: General Electric Company
    Inventors: Jason Douglas Herzlinger, Harish Bommanakatte, Anthony Louis Giglio, Jacob Charles Perry, II
  • Patent number: 9382802
    Abstract: A compressor rotor is provided having a rotor blade groove thereon and also includes a device for cooling the rotor in the region of a compressor rotor exit. Efficient cooling is achieved by the compressor rotor, in a compressor rotor exit region, having a ring which is pushed concentrically, and at a distance, forming a gap, over a rotor disk of the rotor, and is fastened on the disk, by the rotor blades, in the compressor rotor exit region, being inserted into corresponding grooves on the ring and being retained there, by first means for directing an axial flow of cooling medium from the compressor rotor exit through the ring, and by second means for deflecting the cooling medium which issues from the ring such that the cooling medium flows back in the axial direction through the gap between the ring and the rotor disk, encompassed by the ring.
    Type: Grant
    Filed: July 24, 2012
    Date of Patent: July 5, 2016
    Assignee: GENERAL ELECTRIC TECHNOLOGY GMBH
    Inventors: Christian Dombek, Mauro Corradi
  • Patent number: 9243504
    Abstract: A damper pin for coupling platforms of adjacent turbine blades includes a first flat longitudinal end region, a second flat longitudinal end region and a reduced cross sectional area. The reduced cross sectional area is separated from the first flat longitudinal end region by a first main body region and the reduced cross sectional area is separated from the second flat longitudinal end region by a second main body region. The cross sectional area of the reduced cross sectional area is less than the cross sectional area of each of the first and second main body regions.
    Type: Grant
    Filed: December 30, 2013
    Date of Patent: January 26, 2016
    Assignee: United Technologies Corporation
    Inventors: Seth J. Thomen, Christopher Corcoran
  • Patent number: 9217334
    Abstract: The present application provides a cover plate assembly for use with a rotor disk. The cover plate assembly may include a radial flange extending from the rotor disk, a flange aperture extending through the radial flange, a cover plate segment with a fastening aperture and a hook for receiving the radial flange, and a fastener extending through the flange aperture and the fastening aperture.
    Type: Grant
    Filed: October 26, 2011
    Date of Patent: December 22, 2015
    Assignee: General Electric Company
    Inventors: John Wesley Harris, Jr., Gary Charles Liotta
  • Patent number: 9188008
    Abstract: In a turbine for aeronautic engines, a first and at least a second turbine disk rotating around a common axis respectively carrying a first and a second moving-blade crown, with which first and, respectively, second axial passages are defined through which a cooling air mass for the turbine disks can pass, a device for conveying cooling air being interposed between the first and the second axial passages to receive the mass of air passing through the first axial passages and send it through the second axial passages.
    Type: Grant
    Filed: December 21, 2011
    Date of Patent: November 17, 2015
    Assignee: Avio S.p.A.
    Inventors: Daniele Coutandin, Massimiliano Albani
  • Patent number: 9181805
    Abstract: A bladed rotor of a gas turbine for aeronautic engines is cooled by making an air mass flow through a plurality of passages, each one defined by a turbine disk on one side and by a root of a corresponding blade coupled to this turbine disk on the other, the incoming air of each passage being subdivided into two or more airflows and each flow being directed towards the turbine disk in a predefined direction.
    Type: Grant
    Filed: December 20, 2011
    Date of Patent: November 10, 2015
    Assignee: AVIO S.p.A.
    Inventors: Daniele Coutandin, Stefano Zecchi
  • Patent number: 9181810
    Abstract: A system includes a cover segment set configured to mount in first and second grooves circumferentially along a blade mounting region of a turbine rotor. The cover segment set includes a seal segment and a cover segment. The seal segment has a seal body with a lock feature, wherein the seal segment is configured to mount circumferentially along the second groove. The cover segment includes first and second lips extending along first and second circumferential portions of a cover body. The first and second lips are at an offset from one another. The first lip is configured to mount circumferentially along the first groove, the second lip is configured to mount circumferentially along the second groove adjacent the seal segment, and the second lip includes a mating lock feature configured to couple with the lock feature of the seal body.
    Type: Grant
    Filed: April 16, 2012
    Date of Patent: November 10, 2015
    Assignee: General Electric Company
    Inventors: John Herbert Dimmick, III, Raymond Joseph Lecuyer, Norman K. Austin
  • Patent number: 9175566
    Abstract: A gas turbine engine preswirler (470) includes an outer ring (471) and an inner ring (472). The inner ring (472) includes a plurality of angled holes (490). Each angled hole (490) follows a vector which is angled in at least one plane. A component of the vector is located on a plane perpendicular a radial from an axis of the preswirler (470). The component of the angle is angled relative to an axial direction of the preswirler (470).
    Type: Grant
    Filed: September 26, 2012
    Date of Patent: November 3, 2015
    Assignee: Solar Turbines Incorporated
    Inventors: Hongzhou Xu, Michael D. Fox, Scott L. Stafford, Edward T. Ramirez
  • Patent number: 9151274
    Abstract: A wind turbine has a nacelle wherein a component is equipped with a first temperature sensor for detecting a temperature of the component, a second temperature sensor for detecting an outside temperature inside or outside the nacelle, a heater associated with a component to heat the latter, and a heater controller. The detected temperature of the component and the detected outside temperature are provided as input signals to the heater controller which activates the heater for heating when the detected temperature of the component is below a predetermined switch-on value for the heater. The switch-on value for the heater is, in at least one predetermined temperature interval, dependent on the detected outside temperature. The switch-on value for a first outside temperature is greater than the switch-on value for a second outside temperature in the temperature interval when the second outside temperature is greater than the first outside temperature.
    Type: Grant
    Filed: March 9, 2012
    Date of Patent: October 6, 2015
    Assignee: Nordex Energy GmbH
    Inventors: Moritz Dreher, Lars Scheibig, Frederic Radou
  • Patent number: 9145772
    Abstract: A rotor disk for a gas turbine engine includes a hub; a rim with a forward portion and an aft portion; and a plurality of circumferentially spaced radial scallops in the rim to form cooling slots between two disks when the rotor disk is connected to another rotor disk.
    Type: Grant
    Filed: March 21, 2012
    Date of Patent: September 29, 2015
    Assignee: United Technologies Corporation
    Inventors: Richard C. Baxley, Christopher St. Mary, Cagdas Yilmaz, Gary S. Odell
  • Patent number: 9139287
    Abstract: According to one embodiment, a propeller blade includes a carbon foam core and a structural layer that surrounds at least a portion of the carbon foam core.
    Type: Grant
    Filed: June 26, 2012
    Date of Patent: September 22, 2015
    Assignee: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Michael E. Folsom, Blair A. Smith, David P. Nagle
  • Patent number: 9121291
    Abstract: Provided is a turbine blade including: a platform; a blade body including a cooling flow channel including a meandering serpentine cooling flow channel; a fillet portion provided in a joint surface between the blade body and the platform; and a base portion including a cooling flow channel communicated with the serpentine cooling flow channel. The cooling flow channel includes a bypass flow channel that is branched off from a high-pressure part of the cooling flow channel, passes through along the inside of the fillet portion, and is connected to a low-pressure part of the cooling flow channel.
    Type: Grant
    Filed: November 30, 2011
    Date of Patent: September 1, 2015
    Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.
    Inventor: Satoshi Hada
  • Patent number: 9109457
    Abstract: A turbine blade rotor assembly provides sealing for the rotor components and bi-direction axially locking of the blades on the rotor using a seal plate on the aft exhaust side without axial locking on the forward intake side of the rotor and blade array. As a result, the blades can be removed from the aft direction without moving a turbine casing.
    Type: Grant
    Filed: August 30, 2011
    Date of Patent: August 18, 2015
    Assignee: SIEMENS ENERGY, INC.
    Inventors: Guido Ahaus, Axel Buschmann, Harald Hoell, Peter Schroeder
  • Patent number: 9091173
    Abstract: A gas turbine engine configured to rotate in a circumferential direction about an axis extending through a center of the gas turbine engine comprises a turbine stage. The turbine stage comprises a disk, a plurality of blades and a mini-disk. The disk comprises an outer diameter edge having slots, an inner diameter bore surrounding the axis, a forward face, and an aft face. The plurality of blades is coupled to the slots. The mini-disk is coupled to the aft face of the rotor to define a cooling plenum therebetween in order to direct cooling air to the slots. In one embodiment of the invention, the cooling plenum is connected to a radially inner compressor bleed air inlet through all rotating components so that cooling air passes against the inner diameter bore.
    Type: Grant
    Filed: May 31, 2012
    Date of Patent: July 28, 2015
    Assignee: United Technologies Corporation
    Inventors: John H. Mosley, Ioannis Alvanos, Phililp S. Stripinis, Douglas Paul Freiberg, Hector M. Pinero, John J. O'Connor, Jon Pietrobon
  • Patent number: 9080455
    Abstract: The present invention proposes a rotor device for a jet engine with a disk wheel and several rotor blades connected to said disk wheel, with the rotor blades being arranged in each case via a blade root substantially in the axial direction inside recesses of the disk wheel. Several locking segments are provided in the recesses of the disk wheel for axially locking the rotor blades, said locking segments interacting on the one hand with grooves of the rotor blades and on the other hand with at least one groove of the disk wheel. In the area of the groove of at least one of the rotor blades between the groove of the rotor blade and a locking segment there is a positive fit preventing a relative movement between the rotor blades and the locking segments.
    Type: Grant
    Filed: June 11, 2012
    Date of Patent: July 14, 2015
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventor: Ulf Gerstberger
  • Patent number: 9080456
    Abstract: The present application provides a near flow path seal for a gas turbine. The near flow path seal includes a base, a pair of arms extending from the base, and a curved indentation positioned between the pair of arms.
    Type: Grant
    Filed: January 20, 2012
    Date of Patent: July 14, 2015
    Assignee: General Electric Company
    Inventors: John Wesley Harris, Jr., Bruce J. Badding, Brian D. Potter
  • Patent number: 9073631
    Abstract: A rotorcraft is disclosed. The rotorcraft may include an airframe, at least one engine connected to the airframe, and a rotor connected to the airframe. The rotor may include a hub, a rotor blade, and a feathering spindle connecting the rotor blade to the hub. The rotorcraft may further include a flow of oil passing proximate the feathering spindle. The flow of oil may cool the feathering spindle during take off and landing of the rotorcraft. Additionally, the flow of oil may heat the feathering spindle during travel of the rotorcraft at altitude.
    Type: Grant
    Filed: September 7, 2011
    Date of Patent: July 7, 2015
    Assignee: GROEN BROTHERS AVIATION, INC.
    Inventor: Jacob Johannes van der Westhuizen
  • Patent number: 9074582
    Abstract: The present invention relates to a wind turbine nacelle having a top face with a longitudinal extension in a wind direction. The nacelle comprises a cooling device having a cooling area and extending from the first face of the nacelle, and a cover having at least one inner face and at least a front edge facing the wind direction. The cooling device is enclosed by the first face of the nacelle and the inner face of the cover and is arranged in a front distance of at least 440 mm from the front edge of the cover.
    Type: Grant
    Filed: January 29, 2010
    Date of Patent: July 7, 2015
    Assignee: Vestas Wind Systems A/S
    Inventors: Krishnamoorthi Sivalingam, Anand Bahuguni, Ravi Kandasamy, Srikanth Narasimalu, John K. Grevsen, Jesper Nyvad, Paul T. Tietze
  • Patent number: 9068461
    Abstract: A turbine rotor body having at least one inlet orifice in fluid communication with a pre-swirl system such that the inlet orifice receives cooling fluids from the pre-swirl system is disclosed. The inlet orifice may be configured to reduce the relative velocity loss associated with cooling fluids entering the inlet orifice in the rotor, thereby availing the cooling system to the efficiencies inherent in pre-swirling the cooling fluids to a velocity that is greater than a rotational velocity of the turbine rotor body. As such, the system is capable of taking advantage of the additional temperature and work benefits associated with using the pre-swirled cooling fluids having a rotational speed greater than the turbine rotor body.
    Type: Grant
    Filed: August 18, 2011
    Date of Patent: June 30, 2015
    Assignee: SIEMENS AKTIENGESELLSCHAFT
    Inventors: Vincent P. Laurello, Ching-Pang Lee
  • Patent number: 9039368
    Abstract: The present invention relates to a wind turbine nacelle having a first face with a longitudinal extension in a wind direction, comprising a cooling device having a cooling area and extending from the first face of the nacelle, and a cover having at least one inner face, the cooling device being enclosed by the first face of the nacelle and the inner face of the cover. A first distance between at least one of the faces and the cooling area is at least 30 mm.
    Type: Grant
    Filed: January 29, 2010
    Date of Patent: May 26, 2015
    Assignee: Vestas Wind Systems A/S
    Inventors: Krishnamoorthi Sivalingam, Anand Bahuguni, Ravi Kandasamy, Srikanth Narasimalu, John K. Grevsen, Jesper Nyvad, Paul T. Tietze
  • Patent number: 9039369
    Abstract: The present invention relates to a wind turbine nacelle having a top face with a longitudinal extension in a wind direction, comprising a cooling device extending from the top face of the nacelle and a cover having at least one inner face. The cooling device is enclosed by the top face of the nacelle and the inner face of the cover.
    Type: Grant
    Filed: January 29, 2010
    Date of Patent: May 26, 2015
    Assignee: Vestas Wind Systems A/S
    Inventors: Krishnamoorthi Sivalingam, Anand Bahuguni, Ravi Kandasamy, Srikanth Narasimalu, John K. Grevsen, Jesper Nyvad, Paul T. Tietze
  • Publication number: 20150110612
    Abstract: The invention relates to a cooled wall segment in the hot gas path of a gas turbine, particularly to a cooled stator heat shield. Such components have to be properly cooled in order to avoid thermal damages of these components and to ensure a sufficient lifetime. The wall segment according to the invention includes a first surface, exposed to a medium of relatively high temperature, a second surface, exposed to a medium of relatively low temperature, and side surfaces connecting said first and said second surface and defining a height of the wall segment. At least one cooling channel for a flow-through of a fluid cooling medium extends through the wall segment. Each cooling channel is provided with an inlet for the cooling medium and an outlet for the cooling medium.
    Type: Application
    Filed: October 3, 2014
    Publication date: April 23, 2015
    Inventors: Herbert BRANDL, Andrey Anatolievich SEDLOV, Artem IVANOV
  • Publication number: 20150104313
    Abstract: A brush configured to engage a rotating component to transfer an electrical signal and/or power is provided including a body formed from a core material. A coating material is disposed over a portion of the body configured to contact the rotating component. A contact area between the brush and the rotating component increases as the coating material wears.
    Type: Application
    Filed: October 15, 2013
    Publication date: April 16, 2015
    Applicant: Hamilton Sundstrand Corporation
    Inventor: Chang Cheng Gao
  • Publication number: 20150086361
    Abstract: A turbine rotor blade is provided with a blade root, platform adjoining it, and turbine blade on that side of the platform which faces away from the blade root, with at least one opening for feeding coolant into the turbine rotor blade interior on an underside of the blade root, which opening merges into a coolant duct. An axial rotor section for a rotor is provided, having an outer circumferential surface adjoining two end-side first side surfaces with rotor blade holding grooves distributed over the circumference and extending along an axial direction, wherein a turbine rotor blade is arranged in every holding groove, wherein a multiplicity of sealing elements are at the side of a side surface of the rotor section, and lie opposite the end sides of blade roots to form a gap. Multiple outlet holes for impingement cooling of the sealing elements are provided in the end surface.
    Type: Application
    Filed: April 15, 2013
    Publication date: March 26, 2015
    Applicant: SIEMENS AKTIENGESELLSCHAFT
    Inventors: Fathi Ahmad, Nihal Kurt
  • Patent number: 8984855
    Abstract: A rotating inlet cowl for a turbine engine, having a rotation axis and for which the forward end is arranged to be eccentric relative to this rotation axis. Furthermore, a forward cone of the cowl is truncated by a truncation surface defining the forward end of the inlet cowl.
    Type: Grant
    Filed: March 31, 2010
    Date of Patent: March 24, 2015
    Assignee: SNECMA
    Inventors: Mickael Delapierre, Herve Gignoux, Gael Loro, Sylvie Wintenberger
  • Publication number: 20150075180
    Abstract: A turbine bucket is disclosed herein. The turbine bucket may include a platform and a shank portion extending radially inward from the platform. The shank portion may include a slash face, a radial seal pin groove formed in the slash face, and at least one cooling hole disposed in the slash face about the radial seal pin groove.
    Type: Application
    Filed: September 18, 2013
    Publication date: March 19, 2015
    Applicant: General Electric Company
    Inventors: Xiuzhang James Zhang, James W. Vehr
  • Publication number: 20150078898
    Abstract: Multi-scale turbulation features, including first turbulators (46, 48) on a cooling surface (44), and smaller turbulators (52, 54, 58, 62) on the first turbulators. The first turbulators may be formed between larger turbulators (50). The first turbulators may be alternating ridges (46) and valleys (48). The smaller turbulators may be concave surface features such as dimples (62) and grooves (54), and/or convex surface features such as bumps (58) and smaller ridges (52). An embodiment with convex turbulators (52, 58) in the valleys (48) and concave turbulators (54, 62) on the ridges (46) increases the cooling surface area, reduces boundary layer separation, avoids coolant shadowing and stagnation, and reduces component mass.
    Type: Application
    Filed: November 18, 2014
    Publication date: March 19, 2015
    Inventors: Ching-Pang Lee, Nan Jiang, John J. Marra, Ronald J. Rudolf
  • Publication number: 20150071772
    Abstract: Through the use of different ceramic heat insulation coatings (7, 13) on turbine blades, it is possible to produce or restore different configurations of gas turbines, which are then optimized for a respective baseload operation application or peak load operation application. Differences in the sprayed-on heat insulation coatings (7, 13) can be generated by means of a different material composition of the powder, for example zirconium oxide, by means of a different number of layers (10), by means of different coating thicknesses and/or by means of different porosities.
    Type: Application
    Filed: December 18, 2012
    Publication date: March 12, 2015
    Applicant: SIEMENS AKTIENGESELLSCHAFT
    Inventors: Patrick Bullinger, Martin Grosshäuser, Andreas Pahl, Dietmar Reiermann, Michael Rindler, Werner Stamm
  • Patent number: 8973375
    Abstract: One embodiment of the present application includes a hot section component of a gas turbine engine having a covering. The covering includes a protrusion and is attached to the hot section component though a flexible retainer. In one form the covering is made from ceramic matrix composite. The flexible retainer has a closed position and an open position. The retainer secures the protrusion to the hot section component when it engages part of the protrusion when in the closed position.
    Type: Grant
    Filed: December 9, 2009
    Date of Patent: March 10, 2015
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventor: Mark O'Leary
  • Patent number: 8961130
    Abstract: A system and method to cool the air inside the nacelle and the heat generating components, particularly of an offshore wind turbine is presented. The ambient air first enters an air handling unit near the tower bottom where the airborne water droplets and salt particles are removed. The clean air is then compressed adiabatically, thus increasing the dew point temperature of the water vapor in the air. The high pressure, high temperature air from the compressor is then cooled and dehumidified in a sea water-to-air heater exchanger or an air-to-air heat exchanger. The high pressure air from the heat exchanger then enters the turbine at the tower bottom and flows up to the nacelle where it is allowed to expand adiabatically in a duct. The duct helps direct the resulting cold air over the heat generating components. The cold air can also used to cool these components internally. The warm air ultimately exits the nacelle at the rear top.
    Type: Grant
    Filed: June 3, 2011
    Date of Patent: February 24, 2015
    Assignee: Gamesa Innovation & Technology, S.L.
    Inventor: Peri Sabhapathy
  • Patent number: 8961136
    Abstract: A film cooling hole for an air cooled turbine airfoil, where the film cooling hole includes a first expansion section with expansion only on the downstream wall and a second expansion section with expansion on the downstream wall and the two side walls. No expansion is formed on the upstream walls on the first and second expansion sections.
    Type: Grant
    Filed: February 15, 2012
    Date of Patent: February 24, 2015
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: George Liang
  • Patent number: 8961137
    Abstract: A turbine wheel for a turbine engine, comprising a disk carrying blades, each having a platform carrying an airfoil and connected by a tang to a root, and sealing and damping sheets housed in the inter-tang spaces, the platforms including projections on their radially internal faces against which the sheets bear radially in operation, in order to define radial clearance and create at least one space between the sheets and the platforms, and the sheets including holes for feeding air to the or each space.
    Type: Grant
    Filed: April 17, 2012
    Date of Patent: February 24, 2015
    Assignee: Snecma
    Inventors: Emmanuel Berche, Jean-Luc Bacha, Tangi Brusq
  • Publication number: 20150050159
    Abstract: A turbine blade includes a core element having a base portion, a tip portion, and an intermediate portion extending between the base portion and the tip portion. The intermediate portion includes a non-uniform cross-section and is a high-strength fiber material. The turbine blade further includes a shell disposed around the core element, and the volume between the core element and the shell forms a void.
    Type: Application
    Filed: August 14, 2013
    Publication date: February 19, 2015
    Inventors: Kenneth G. Caldeira, William David Duncan, Bran Ferren, William Gates, W. Daniel Hillis, Roderick A. Hyde, Muriel Y. Ishikawa, Edward K.Y. Jung, Jordin T. Kare, John Latham, Nathan P. Myhrvold, Stephen H. Salter, Clarence T. Tegreene, David B. Tuckerman, Thomas Allan Weaver, Charles Whitmer, Lowell L. Wood,, JR., Victoria Y.H. Wood
  • Publication number: 20150044047
    Abstract: A connector for connecting an impeller to a shaft is provided. The impeller has a shaft-side hub extension with a central recess. The impeller is formed of a material having a greater coefficient of thermal expansion than the material of the shaft. The connector is inserted into the recess to frictionally connect an outwardly facing surface of the connector with a radially inner surface of the hub extension. The connector has a threaded portion carrying a thread which screws onto a corresponding threaded portion of the shaft, such that the connector provides a rotationally fixed connection between the impeller and the shaft. The connector is formed of a material having a coefficient of thermal expansion which is greater than the coefficient of thermal expansion of the material of the shaft.
    Type: Application
    Filed: December 10, 2012
    Publication date: February 12, 2015
    Applicant: NAPIER TURBOCHARGERS LIMITED
    Inventors: Ian Pinkney, Osarobo Famous Okhuahesogie, Paul Eifion Roach, Neil Ryan Thomas, Ian Patrick Clare Brown, Peter Kay, Stephen Wilson, David Leslie Smith, Robert Neil George, Paul Leslie Jacklin, Geoff Kinpoy Ngao, Kevin John Musson, Matthew Elijah Moore, Jamie Clare, Thomas Jarlath Murray, Stuart Michael Potter, Christopher John Monaghan, Alan Martin Taylor, Francis Joseph Geoffrey Heyes, Trevor Knighton
  • Publication number: 20150044046
    Abstract: A method for casting a collar (44, 46) for a heat shield (36) of a strut (32) in a gas turbine exhaust section (20). A casting geometry (60, 70) is defined with extra wall thickness (56, 68) in an area of wall curvature (53, 54), which provides a flow path beyond a final geometry of the collar to facilitate a flow of molten metal in the mold (63, 64). The extra thickness is removed after casting, leaving the collar in its final geometry, which may have uniform wall thickness (T, T2). The extra thickness in the casting geometry may be provided by increased radius (R3) in the wall curvature and/or by casting feed portals (66, 68) that span the wall curvature between a tubular portion (50) and a flange (52) of the collar.
    Type: Application
    Filed: August 7, 2013
    Publication date: February 12, 2015
    Inventors: Yevgeniy Shteyman, Matthew R. Porter, Mrinal Munshi, Douglas R. Roth, Timothy J. Stewart, JR.