Miscellaneous (e.g., Blade Root Or Root Block, Etc.) Patents (Class 416/248)
  • Patent number: 10738755
    Abstract: Hydrostatic pressure turbine runners according to the present disclosure are designed for maximally exploiting the hydrostatic pressure of a flowing fluid, rather than maximizing extraction of kinetic energy from the flow. The design converts less kinetic energy of the flow into hydropower as compared with current run-of-river turbine runner technologies. However, hydrostatic pressure turbine runners according to the present disclosure convert substantially more potential energy into hydropower. As a result, the total amount of energy converted into hydropower is significantly higher than the hydropower available from conventional run-of-river turbine runner designs, and, without promising any particular utility, may be capable of surpassing the upper limit of converted energy as defined by Betz' law. In a run-of-river context, the total amount of converted energy—mainly converted potential energy—may surpass the amount of kinetic energy of the flow engaged by the turbine runner.
    Type: Grant
    Filed: October 24, 2019
    Date of Patent: August 11, 2020
    Inventor: On Hoter-Ishay
  • Patent number: 10655495
    Abstract: A shroud assembly for a turbine engine comprising a plurality of circumferentially arranged shroud segments having confronting end faces defining first and second radially spaced surfaces. The shroud assembly includes a forward edge spanning to an aft edge to define an axial direction and a set of confronting seal channels formed in each of the confronting end faces with a spline seal located within the confronting seal channels.
    Type: Grant
    Filed: February 24, 2017
    Date of Patent: May 19, 2020
    Assignee: General Electric Company
    Inventors: Robert Charles Groves, II, David Scott Stapleton
  • Patent number: 10570758
    Abstract: An aero gas turbine engine with a last stage turbine disc of a solid bore design. The solid bore turbine disc includes a center tie bolt that attaches to an upstream face of the solid bore disc. The attachment location is under the bore of the upstream stage. The aft side of the solid disc creates a stub shaft upon which a bearing is directly mounted. No fasteners pass through the solid bore disc. Omission of outboard fasteners allow for ease of assembly, reduced cost, reduced weight, and a reduced part count.
    Type: Grant
    Filed: May 18, 2018
    Date of Patent: February 25, 2020
    Assignee: Florida Turbine Technologies, Inc.
    Inventors: Andrew P Wall, Edwin L Kite, Alex Pinera
  • Patent number: 10472975
    Abstract: A damper pin for damping adjacent turbine blades coupled to a rotor disk comprises a first elongated body having a center portion disposed between a first end portion and a second end portion. The first end portion, center portion and second end portion define a generally arcuate top portion of the first elongated body. The first elongated body defines a slot that extends axially therethrough. The damper pin further includes a second elongated body having a generally arcuate top portion. The second elongated body is at least partially disposed within the slot and is slideably engaged in an axial direction with the first elongated body.
    Type: Grant
    Filed: September 3, 2015
    Date of Patent: November 12, 2019
    Assignee: General Electric Company
    Inventors: Spencer A. Kareff, Poorna Krishnakumar, Kevin Lee Worley, Christopher Michael Penny, Stephen Paul Wassynger
  • Patent number: 10329927
    Abstract: A hollow CMC article, a mandrel for forming the article and a method for forming the article are disclosed. The article includes a ply-wrap layer defining a cavity. The ply-wrap layer includes a first face, a second face, a root portion bridging the faces, and a plurality of CMC wrap plies. The root portion defines a terminus of the ply-wrap layer including a cross-sectional conformation consisting of a curve having a single turning point. Each of the plurality of CMC wrap plies are disposed along the first face, wrap over the root portion, and extend along the second face. The hollow article further includes a plurality of CMC lateral plies disposed along the faces.
    Type: Grant
    Filed: August 15, 2016
    Date of Patent: June 25, 2019
    Assignee: General Electric Company
    Inventors: Jacob John Kittleson, James Murray
  • Patent number: 10125615
    Abstract: A turbine wheel for a turbine engine comprising a disc carrying blades. Each blade comprises an upstream radial wall and a downstream radial wall which extend inwards from the platform of the blade. Inter-blade cavities each accommodate one inter-blade sealing and vibration damping member. According to the invention, each inter-blade sealing and vibration damping member comprises at least a first transverse partition wall axially arranged at a distance from a downstream (or upstream, respectively) portion of the member and axially opposite two upstream (or downstream, respectively) so as to obstruct a flow of incoming air into the cavity between two adjacent upstream radial walls or two adjacent downstream radial walls.
    Type: Grant
    Filed: November 3, 2015
    Date of Patent: November 13, 2018
    Assignee: SNECMA
    Inventors: Sébastien Serge Francis Congratel, Franck Boisnault, Patrice Jean-Marc Rosset
  • Patent number: 10036260
    Abstract: A damper seal for a gas turbine engine rotor assembly has an axially elongated body with a leading edge, a trailing edge, a pressure side, and a suction side. The elongated body includes a first enlarged portion formed on the pressure side at the leading edge and a second enlarged portion formed on the suction side adjacent the trailing edge.
    Type: Grant
    Filed: March 7, 2014
    Date of Patent: July 31, 2018
    Assignee: United Technologies Corporation
    Inventors: Brandon M. Rapp, Matthew Andrew Hough
  • Patent number: 9976427
    Abstract: The present disclosure provides systems for preventing improper installation of a damper seal. In various embodiments, an airfoil assembly may comprise a platform, an airfoil extending from the platform, and a platform tab. The airfoil may comprise a gaspath face and a non-gaspath face. The non-gaspath face may at least partially define a cavity. The airfoil may comprise a pressure side and a suction side. The platform tab may be located adjacent to the suction side of the airfoil. The platform tab may extend from the platform in the opposite direction as the airfoil and may be configured to prevent a damper seal tab from being inserted radially inwards of the platform tab.
    Type: Grant
    Filed: May 26, 2015
    Date of Patent: May 22, 2018
    Assignee: United Technologies Corporation
    Inventors: Joshua Daniel Winn, David A. Niezelski
  • Patent number: 9890651
    Abstract: The invention refers to a blade of a rotary flow machine including an airfoil having a suction surface and a pressure surface joining each other along a trailing and a leading edge. A radially outward directed airfoil tip and a radially inward directed end joining an inner platform connect the airfoil to a shank at a radial end of the airfoil and providing, at least one shank pocket radially encircled by an axially extending portion of the platform. At least one radially extending rim extends from the trailing edge side of the shank and has an essentially radially orientated first slot for receiving a seal. A mount extends radially inwardly from said shank pocket. The first slot has a first aperture on a shank surface orientated in an axial direction.
    Type: Grant
    Filed: August 25, 2014
    Date of Patent: February 13, 2018
    Inventors: Sarah Heaven, Shyam Mavani, Jiwen Tao, Stacie Tibos, Vasileios Stefanis, Sascha Justl, Rudolf Kellerer
  • Patent number: 9650902
    Abstract: A fan section for a gas turbine engine includes a fan hub having a slot. A platform is supported by the fan hub. A fan blade has a root that is received in the slot. A wear pad is provided between the fan hub and the root and includes a flap integral with the wear pad to provide a seal relative to the platform. A fan blade for a gas turbine engine includes an airfoil extending from a root. A wear pad is secured to the root and has a free end providing a flap canted toward the root.
    Type: Grant
    Filed: January 11, 2013
    Date of Patent: May 16, 2017
    Inventors: Scott C. Billings, James O. Hansen, Michael A. Weisse
  • Patent number: 9593665
    Abstract: A turbine wheel designed to exploit the head of watercourses that operates partially or totally submerge with means for a wheel mounting enclosure having a cavity equal to 50% of the height of the runner where the runner rest exposing the upper end into the bed of the flowing body of water and said cavity mask the runner from the water incident flow allowing the wheel to perform fully submerged gaining its power and momentum through water current acting upon an array of multifaceted cells attached to spokes radiating from a central circular body member to the outer perimeter of a wheel, distributed wall-to-wall occupying the peripheral annulus of the water stream always presenting a new facet as it rotate around it axis covering 180 degrees of the water incident flow. The outside surface of the runner attaches to a multiplicity of similar runners by means of mechanical devices and to the central circular body member.
    Type: Grant
    Filed: October 2, 2009
    Date of Patent: March 14, 2017
    Inventor: Jose Ramon Santana
  • Patent number: 9103221
    Abstract: A system and method for securing a blade within a disk so as to eliminate the need for permanently deforming materials associated with the blade disk is disclosed. A recess is formed generally within each slot used to secure a blade within the disk. A retaining insert is positioned within the recess and a wedge insert is positioned within a slot of the retaining insert, such that a pressure is applied to the retaining insert thereby deflecting the retaining insert into a pre-set radial position to prevent axial movement of the blade within the slot of the disk.
    Type: Grant
    Filed: February 16, 2012
    Date of Patent: August 11, 2015
    Inventors: Alex Torkaman, Kevin Carpenter, William David Day
  • Patent number: 9051838
    Abstract: A turbine blade of an axial turbine includes internal cooling fluid passages with radially outwardly extending passages connected to holes in the blade root. The holes are generally core printouts providing stability to the core during the casting process, but are not needed and need to be closed to guarantee the functioning of the cooling system. This is achieved by at least one covering plate. The plate is held by at least two slots located at the root of the turbine blade. Thus, the supply holes for cooling fluid located at the root section are closed by a simple mechanical device, e.g., a plate that does not require any subsequent brazing/welding operations. In addition, the plate is removable to facilitate inspection/cleaning, or further processing of the blade at service intervals.
    Type: Grant
    Filed: December 20, 2011
    Date of Patent: June 9, 2015
    Inventors: Brian Kenneth Wardle, Christoph Didion, Herbert Brandl, Shailendra Naik
  • Patent number: 9039382
    Abstract: A blade of a gas turbine engine is provided having an airfoil, a platform, a shank, a dovetail, and a skirt. The airfoil may extend distally from the platform, and the shank may extend proximally from the platform. The dovetail may also be provided to extend proximally from the shank. The skirt may be disposed on an aft side of the shank and may extend from the shank in a direction at least partially axially aft from the shank.
    Type: Grant
    Filed: November 29, 2011
    Date of Patent: May 26, 2015
    Assignee: General Electric Company
    Inventor: David Scott Stapleton
  • Patent number: 9004865
    Abstract: A blade for a turbomachine impeller including an airfoil and at least one platform at one end of the airfoil, the blade configured to be arranged with a plurality of substantially identical blades so as to form a ring, the platform surface having a suction surface profile and a pressure surface profile respectively along the suction surface and the pressure surface. In the blade, the pressure surface profile including a pressure surface recessed part is located axially in an upstream half of the airfoil. Due to this configuration, efficiency of the blade is improved.
    Type: Grant
    Filed: February 27, 2009
    Date of Patent: April 14, 2015
    Assignee: SNECMA
    Inventors: Jean-Michel Guimbard, Olivier Kueny, Ludovic Pintat
  • Patent number: 9004874
    Abstract: A turbomachinery blade includes: an airfoil; and a shank extending from a root of the airfoil, the shank being constructed from a composite material including reinforcing fibers embedded in a matrix The shank includes a pair of spaced-apart side faces that cooperatively define: a dovetail disposed at a radially inboard end of the shank, comprising spaced-apart, diverging faces; a first neck portion having a concave curvature disposed radially outboard of the dovetail, and defining a primary minimum neck at which a thickness of the shank is at a local minimum; and a second neck portion disposed radially outboard of the first minimum neck, the second neck portion having a concave curvature and defining a secondary minimum neck at which the thickness of the shank is at a local minimum.
    Type: Grant
    Filed: February 22, 2012
    Date of Patent: April 14, 2015
    Assignee: General Electric Company
    Inventor: Joshua Brian Jamison
  • Patent number: 8979497
    Abstract: A blade arrangement on a wall of a fluid flow path of a turbomachine includes a locating channel disposed in the wall and having undercut flanks. A plurality of blades each having a blade-side root section corresponding to the undercut flanks. A plurality of intermediate filling pieces correspond to the undercut flanks and separate each of the blade-side root sections. The plurality of blade-side root sections and intermediate filling pieces are seated in a form-fitting manner and fixed in a force-locking manner in the locating channel. The plurality of intermediate filling pieces fill out the locating channel so as to form a gas flow-side surface essentially free of a disturbing contour between the blade-side root sections. Each of the plurality of intermediate filling pieces includes a threaded hole disposed essentially perpendicular to a base of the channel. A screw is disposed in the threaded hole.
    Type: Grant
    Filed: October 26, 2011
    Date of Patent: March 17, 2015
    Assignee: Alstom Technology Ltd.
    Inventors: Ulrich Wellenkamp, Sejko Kolev
  • Patent number: 8973863
    Abstract: 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 connected to the hub. The rotor blade may have a root and a tip and form a conduit extending in the radial 5 direction from the root to the tip. The root may comprise a wall forming a hollow circular cylinder. The hollow circular cylinder may form a portion of the conduit. A plurality of bolts may be distributed circumferential within the wall of the root. The plurality of bolts may extend in the radial direction from the wall of the root to secure the rotor blade to the feathering 10 spindle.
    Type: Grant
    Filed: September 7, 2011
    Date of Patent: March 10, 2015
    Assignee: Groen Brothers Aviation, Inc.
    Inventor: Jacob Johannes van der Westhuizen
  • Patent number: 8967974
    Abstract: A composite blade assembly for mounting on a turbine wheel includes a ceramic airfoil and an airfoil platform. The ceramic airfoil is formed with an airfoil portion, a blade shank portion and a blade dovetail tang. The metal platform includes a platform shank and a radially inner platform dovetail. The ceramic airfoil is captured within the metal platform, such that in use, the ceramic airfoil is held within the turbine wheel independent of the metal platform.
    Type: Grant
    Filed: January 3, 2012
    Date of Patent: March 3, 2015
    Assignee: General Electric Company
    Inventor: Andres Jose Garcia-Crespo
  • Patent number: 8961134
    Abstract: A turbine engine airfoil structure including an airfoil adapted to be supported to extend across a gas passage for a hot working gas in a turbine engine. The airfoil structure further includes a platform structure located at one end of the airfoil and positioned at a location forming a boundary of the gas passage. The platform structure includes a platform member including a gas side surface extending generally perpendicular from the airfoil at a junction with the airfoil, and providing a structural connection to the airfoil. The platform structure further includes a separately formed platform cover attached to the platform member at the gas side surface. The platform cover extends from a location adjacent to one of the sidewalls of the airfoil, and includes an outer surface located for contact with the hot working gas passing through the gas path.
    Type: Grant
    Filed: June 29, 2011
    Date of Patent: February 24, 2015
    Assignee: Siemens Energy, Inc.
    Inventor: Alexander R. Beeck
  • 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
  • Patent number: 8956115
    Abstract: A rotor blade assembly for a wind turbine, and a method for installing a rotor blade assembly on a wind turbine, are disclosed. The rotor blade assembly includes a rotor blade having exterior surfaces defining an aerodynamic profile including a pressure side and a suction side extending between a leading edge and a trailing edge. The rotor blade further extends in a generally span-wise direction between a root and a tip. The rotor blade assembly further includes a blade extension extending in the generally span-wise direction from the root towards the tip, and a plurality of connection devices connecting the blade extension to the rotor blade. Each of the plurality of connection devices includes a mechanical fastener extending through the root in the generally span-wise direction for connecting the rotor blade to a hub of the wind turbine.
    Type: Grant
    Filed: January 20, 2012
    Date of Patent: February 17, 2015
    Assignee: General Electric Company
    Inventors: James Robert Tobin, Aaron John Mashue
  • Patent number: 8951015
    Abstract: A rotor blade arrangement (20), especially for a gas turbine, which can be fastened on a blade carrier (19) and includes in each case a blade aerofoil element (10) and a platform element (14), wherein the platform elements (14) of a blade row form a continuous inner shroud. With such a blade arrangement, a mechanical decoupling, which extends the service life, is achieved by the blade aerofoil element (10) and the platform element (14) being formed as separate elements and by being able to be fastened in each case separately on the blade carrier (19).
    Type: Grant
    Filed: November 13, 2009
    Date of Patent: February 10, 2015
    Assignee: Alstom Technology Ltd.
    Inventors: Herbert Brandl, Hans-Peter Bossmann, Philipp Indlekofer
  • Patent number: 8951016
    Abstract: A rotor blade for an axial flow turbomachine, preferably a turbine, and to a mounting for such a rotor blade is provided. In the rotor blade, the two opposing lateral walls of the blade base are continuously curved along their extension between platform and bottom side of the blade base in order to reduce the mechanical load in the blade base and that of the walls supporting the blade base of a rotor.
    Type: Grant
    Filed: June 17, 2010
    Date of Patent: February 10, 2015
    Assignee: Siemens Aktiengesellschaft
    Inventors: Fathi Ahmad, Günther Walz
  • Patent number: 8926290
    Abstract: An attenuation bracket is provided and includes an annular body having an annular attenuation arm defining first through-holes and an annular base defining second through-holes. A cross-section of the attenuation arm includes a flange, a connector opposite the flange and a curvilinear section extending between the flange and the connector. A cross-section of the base includes a first side corresponding with the flange and a second side opposite the first side and corresponding with the connector. The second side is connectable with the connector such that each of the first through-holes is defined in positional alignment with a corresponding one of the second through-holes.
    Type: Grant
    Filed: January 4, 2012
    Date of Patent: January 6, 2015
    Assignee: General Electric Company
    Inventors: Andrew Clifford Hart, Tushar Sharadchandra Desai, John Herbert Dimmick, III, Matthew Paul Forcier, Chunlian Han, Charles Alexander Smith
  • Patent number: 8926282
    Abstract: By providing a tube of deformable material which can be located within a hollow cavity of a blade it is possible to provide an element which through friction engagement can absorb vibration energy and therefore damp vibration in a hollow blade. The tube incorporates a number of cuts and/or grooves in an appropriate pattern in order to define a deformation profile once the tube is expanded in location. The tube is secured in position internally upon an expandable element which is typically an inflatable device. Once in position the tube is retained in its expanded deformable profile and the engagement between the tube and the hollow cavity wall surface results in energy absorption through vibration episodes. It is possible to provide a tube formed from a shape memory alloy which will expand in location to engage the hollow cavity wall surfaces for energy absorption during vibration episodes.
    Type: Grant
    Filed: July 26, 2013
    Date of Patent: January 6, 2015
    Assignee: Rolls-Royce plc
    Inventor: David Miller
  • Patent number: 8920121
    Abstract: An axial turbomachine rotor is provided. The turbomachine includes a rotor body designed in a rotation symmetrical manner around the rotor axis, a rotor blade ring including rotor blades that are each fixed to the rotor body by the blade foot thereof and a sealing disc designed in a rotation symmetrical manner around the rotor axis that is arranged having the outer edge thereof radially inside, neighboring an axially extending protrusion of the blade foot, so that a hollow space is formed between the blade foot and the sealing disc, wherein a groove exists on the outer edge leading radially to the outside, wherein a sealing ring is mounted that may slide radially to the outside in the groove during operation of the rotor by centrifugal force until the sealing ring radially contacts the inside of the protrusion and thus seals the hollow space on the blade foot.
    Type: Grant
    Filed: March 26, 2010
    Date of Patent: December 30, 2014
    Assignee: Siemens Aktiengesellschaft
    Inventors: Sascha Dungs, Peter Schröder
  • Patent number: 8899933
    Abstract: A wheel dovetail groove with a wheel hook retains blade hooks of mounted blades. Opposed arcuate cut-outs in upper recessed areas of the groove may form an assembly gate. Blade hooks may be inserted into the groove in a first orientation, rotated to a second orientation at the assembly gate, and slid into a predetermined position. Blades may be secured with shims between adjacent bucket dovetails. Blade tip cover blocks may be included to form a cover. All blades may be substantially identical and not need special mounting arrangements at the assembly gate.
    Type: Grant
    Filed: January 3, 2012
    Date of Patent: December 2, 2014
    Assignee: General Electric Company
    Inventors: Thomas Joseph Farineau, Robert Edward Deallenbach, Timothy Scott McMurray
  • Patent number: 8894378
    Abstract: Certain embodiments of the invention may include systems methods, and apparatus for sealing a bucket dovetail in a turbine. According to an example embodiment of the invention, a method is provided for sealing a gap between a bucket dovetail and a rotor wheel slot. The method can include providing a bucket tab associated with a bucket dovetail, wherein the bucket tab is configured to accept a seal tab; configuring the bucket tab and the seal tab to engage at least one dimension upon insertion of the seal tab into the bucket tab; and sealing a gap between the bucket dovetail and a rotor wheel slot with the seal tab; wherein at least a portion of the seal tab changes as a function of temperature for further sealing gap between the bucket dovetail and the rotor wheel slot.
    Type: Grant
    Filed: July 26, 2011
    Date of Patent: November 25, 2014
    Assignee: General Electric Company
    Inventor: Srinivasa Govardhan Jayana
  • Patent number: 8894372
    Abstract: Systems, methods and devices adapted to ease installation of turbine bucket assemblies about a rotor and to reduce related stress concentrations in the rotor are disclosed. In one embodiment, an insert includes: a base portion adapted to complement an entry slot in a rotor of a turbine; and a neck portion extending radially outboard from the base portion, the neck portion adapted to complement a post of the rotor to form a substantially continuous dovetail about the rotor.
    Type: Grant
    Filed: December 21, 2011
    Date of Patent: November 25, 2014
    Assignee: General Electric Company
    Inventors: Fred Thomas Willett, Jr., Laurence Scott Duclos, Michael Dennis Mack, Timothy Scott McMurray, Roy Paul Swintek
  • Patent number: 8888455
    Abstract: One embodiment of the present invention is a unique gas turbine engine blade. Another embodiment is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and blades. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.
    Type: Grant
    Filed: November 10, 2010
    Date of Patent: November 18, 2014
    Assignee: Rolls-Royce Corporation
    Inventor: Richard Lex Seneff
  • Patent number: 8888462
    Abstract: Rotor blade or rotor blade segment for a wind turbine, having at least one cable for fixing the rotor blade or rotor blade segment to a rotor hub or to a further rotor blade segment, wherein the at least one cable is redirected in a U-shaped manner within the rotor blade or rotor blade segment.
    Type: Grant
    Filed: September 1, 2011
    Date of Patent: November 18, 2014
    Assignee: Nordex Energy GmbH
    Inventor: Hendrik Klein
  • Patent number: 8870542
    Abstract: A turbomachine is disclosed. The turbomachine includes a rotor, a plurality of blades arranged side by side on the rotor in a circumferential direction, and a plurality of sealing apparatuses each disposed on a respective blade shaft of the plurality of blades. Each of the plurality of sealing apparatuses includes first and second bottom plates protruding in a respective axial direction on the respective blade shaft and first and second bulkheads which extend in a radial direction along the respective blade shaft and form a double-walled seal in the axial direction. A respective rounded or parabolic transitional cross-section from the bottom plates to the bulkheads is provided and at least one of the bulkheads is offset with respect to a blade root edge of the respective blade shaft in a direction toward a radial longitudinal axis of the respective blade shaft.
    Type: Grant
    Filed: February 2, 2010
    Date of Patent: October 28, 2014
    Assignee: MTU Aero Engines GmbH
    Inventors: Manfred Feldmann, Markus Uecker, Benedikt Heidenreich, Dieter Freno
  • Patent number: 8864473
    Abstract: Provided is a blade for a rotor of a wind turbine having a substantially horizontal rotor shaft, said rotor comprising a hub, from which the blade extends substantially radially when mounted, said blade having a chord plane extending between a leading edge and a trailing edge of said blade, a root area closest to the hub, an airfoil area furthest away from the hub, a transition area between the root area and the airfoil area, a first airfoil extending substantially along the entire airfoil area, and a second airfoil separately mounted to the blade, said second airfoil arranged at a mutual distance transverse to the chord plane and extending along the root area of the blades.
    Type: Grant
    Filed: May 21, 2013
    Date of Patent: October 21, 2014
    Assignee: LM Glasfiber A/S
    Inventor: Peter Grabau
  • Patent number: 8845294
    Abstract: Spacers interposed between blades attached to the disk of a rotor having slots and bottoms of the slots are disclosed. Each spacer is made of an elastically deformable material and at least one longitudinal segment of the spacer presents a transverse profile of arcuate shape to define two lateral contact zones.
    Type: Grant
    Filed: May 24, 2013
    Date of Patent: September 30, 2014
    Assignee: SNECMA
    Inventors: Olivier Belmonte, Jean-Luc Christian Yvon Goga, Jean-Noel Mahieu
  • Patent number: 8834130
    Abstract: A blade for a rotor of a wind turbine having a substantially horizontal rotor shaft, the rotor comprising a hub, from which the blade extends substantially in a radial direction when mounted to the hub. The blade comprises a main blade part having a profiled contour comprising a pressure side and a suction side as well as a leading edge and a trailing edge with a chord extending between the leading edge and the trailing edge. The profiled contour generates a lift when being impacted by an incident airflow. The profiled contour is divided in the radial direction into a root region with a substantially circular or elliptical profile closest to the hub, the substantially circular or elliptical profile having a diameter, an airfoil region with a lift generating profile furthest away from the hub, and a transition region between the root region and the airfoil region.
    Type: Grant
    Filed: April 2, 2009
    Date of Patent: September 16, 2014
    Inventors: Peter Fuglsang, Stefano Bove
  • Patent number: 8827642
    Abstract: A system including: a first turbine segment comprising a first blade coupled to a first shank. The system also includes a second turbine segment including a second blade coupled to a second shank, as well as an elongated flexible seal disposed in a gap between the first and second shanks. The elongated flexible seal includes an opening configured to channel a fluid flow into a hollow region of the elongated flexible seal to induce expansion of the elongated flexible seal in the gap.
    Type: Grant
    Filed: January 31, 2011
    Date of Patent: September 9, 2014
    Assignee: General Electric Company
    Inventors: Jalindar Appa Walunj, Brian Peter Arness, Mark Steven Honkomp, Scott Edmond Ellis, Prashant Shukla, Narayayanaswamy Kuruboor Veerabhadrappa
  • Patent number: 8821127
    Abstract: A blade assembly for a groove of a wheel of rotating machinery is described. The blade assembly includes, a blade root having two longitudinal sides, a base, and a roof, wherein the profile of the longitudinal sides includes a rounded surface, a blade connected to the roof of the blade root, and one or more keys juxtaposed along each longitudinal side of the blade root, each key having an inboard side and an outboard side, wherein the profile of the inboard side of each key is configured to mate with the profile of the blade root. The blade assembly allows replacement of a compressor blade without the need for unstacking the rotor to gain access to the damaged blade.
    Type: Grant
    Filed: April 21, 2011
    Date of Patent: September 2, 2014
    Inventor: Ken Knecht
  • Patent number: 8821122
    Abstract: An integrally bladed rotor disk (20) for a turbine, including rotor blades (40), which are joined in a substance-to-substance bond to a disk element (30), and a sealing device (60) for preventing or reducing the extent to which cooling air is able to flow from a high-pressure side (12) of the rotor disk (20) through openings (24) on the rotor disk (20) to a low-pressure side (14) of the rotor disk (20).
    Type: Grant
    Filed: February 1, 2010
    Date of Patent: September 2, 2014
    Assignee: MTU Aero Engines GmbH
    Inventors: Hans-Peter Borufka, Frank Stiehler, Hernan Victor Arrieta, Patrick Prokopczuk, Joachim Lorenz
  • Patent number: 8813331
    Abstract: A process of preparing a turbine rotor wheel, a repair tool for machining a turbine rotor wheel, and a turbine rotor wheel are disclosed. The process includes providing the turbine rotor wheel, the turbine rotor wheel having a dovetail slot, a cooling slot, and a dovetail acute corner formed by the dovetail slot and the cooling slot and removing a stress region from the dovetail acute corner. The repair tool permits removal of strained material while also reducing the operating stress of the feature. The turbine rotor wheel includes a machined portion resulting in lower stress for the turbine rotor wheel.
    Type: Grant
    Filed: March 29, 2011
    Date of Patent: August 26, 2014
    Assignee: General Electric Company
    Inventor: John H. Dimmick, III
  • Patent number: 8784061
    Abstract: Method and system are provided for controlling a thermal differential within a turbine rotor for use with a turbine system. A thermal barrier coating is applied to a surface of the turbine rotor. The surface is proximate to a wheel rim of the turbine rotor.
    Type: Grant
    Filed: January 31, 2011
    Date of Patent: July 22, 2014
    Assignee: General Electric Company
    Inventors: Narendra Are, Roger Clayton Walker, Matthew Ryan Ferslew, Matthew Paul Forcier
  • Patent number: 8764300
    Abstract: A wind turbine rotor hub bearing where the series of mobile members include more than two annular series of such members whereof at least two have different median diameters which are arranged in more than two rows scaled along the bearing rotational axis, with two end rows each comprising a series of roller bearings having individually a rotational axis transversal to the axis and at least an intermediary row of mobile members comprising balls.
    Type: Grant
    Filed: March 21, 2012
    Date of Patent: July 1, 2014
    Assignee: Defontaine
    Inventors: Germain Errard, Eric Jacquemont, Jean-Michel Delacou
  • Patent number: 8740573
    Abstract: An adaptor assembly for coupling a blade root of a turbine blade to a root slot of a rotor disk is disclosed. The adaptor assembly may generally include an adaptor body having a root configured to be received within the root slot. The adaptor body may also define a slot having an open end configured to receive the blade root. The adaptor body may further define a channel. The adaptor assembly may also include a plate having an outwardly extending foot. The foot may be configured to be received within the channel. Additionally, the plate may be configured to cover at least a portion of the open end of the slot when the foot is received within the channel.
    Type: Grant
    Filed: April 26, 2011
    Date of Patent: June 3, 2014
    Assignee: General Electric Company
    Inventors: John McConnell Delvaux, Andres Jose Garcia-Crespo, Kilmer Joseph Joyce, Allan Randall Tindell
  • Patent number: 8734112
    Abstract: A gas turbine engine includes a disk having an annular hub circumscribed about a centerline with an annular web extending radially outward from the hub to an annular rim. A multiple of slots extend generally axially through the rim and at least one of the multiple of slots having an asymmetric slot root for lower stress and higher service life.
    Type: Grant
    Filed: November 30, 2010
    Date of Patent: May 27, 2014
    Assignee: United Technologies Corporation
    Inventors: Scott D. Virkler, Raymond S. Hummel
  • Patent number: 8727731
    Abstract: The invention relates to a process for manufacturing a blade connection of a rotor blade for a wind energy system which comprises fastening elements for fastening the blade connection to a hub, which fastening elements are provided on a circular arc, preferably equidistant from each other. Furthermore, the invention relates to a blade connection and a fastening element for a blade connection. The invention is based on the problem of improving the fastening of a rotor blade on the hub of a wind energy system as well as improving the manufacture and/or making a suitable blade connection available. The invention solves this problem as regards the process in that fastening elements formed in pieces are arranged on the circular arc and spaced from each other with spacer elements.
    Type: Grant
    Filed: April 8, 2009
    Date of Patent: May 20, 2014
    Assignee: REpower Systems AG
    Inventors: Urs Bendel, Markus Werner, Martin Knops
  • Patent number: 8727735
    Abstract: A blade retainer for a gas turbine engine includes a plate-like member with an arcuate outer face, an opposed inner face, and two spaced-apart end faces. The member has an outer portion disposed adjacent the outer face, and an inner portion disposed adjacent the inner face, and a wedge-shaped recess with a concave radiused valley is formed in the inner portion adjacent each end face. The retainer is left-right symmetrical.
    Type: Grant
    Filed: June 30, 2011
    Date of Patent: May 20, 2014
    Assignee: General Electric Company
    Inventors: Michael Lee, David Coburn, Joseph Fagan
  • Patent number: 8721292
    Abstract: A gas-turbine blade root 1 has at least two essentially rectangularly adjoining surfaces 4, 5 for locating the gas-turbine blade root 1 and a transition area of the surfaces 4, 5 includes a bevelled, plane edge 6.
    Type: Grant
    Filed: October 30, 2008
    Date of Patent: May 13, 2014
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: James McLaughlan, Roger Ashmead
  • Patent number: 8708656
    Abstract: The blade dovetails and associated dovetail slots of a gas turbine engine rotor assembly are shaped so that during windmilling the high stress regions of the blade dovetails are shielded from rubbing against the disk and vice versa. Bumper surfaces are provided in low stress regions of the dovetail assembly such that the windmilling contact points between the blade dovetails and the disk are in non-critical areas of the dovetail assembly.
    Type: Grant
    Filed: May 25, 2010
    Date of Patent: April 29, 2014
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Barry Barnett, Philippe Bonniere
  • Patent number: 8696320
    Abstract: A gas turbine and a seal assembly for a machine having a rotating shaft, a wheel coupled to the rotating shaft, the wheel including a bucket coupled to the wheel comprising a coverplate that is fastened to the wheel and the bucket and a seal positioned between the coverplate and the wheel and the bucket.
    Type: Grant
    Filed: March 12, 2009
    Date of Patent: April 15, 2014
    Assignee: General Electric Company
    Inventors: John Wesley Harris, Jr., Matthew Robert Piersall, Brian Denver Potter
  • Publication number: 20140079559
    Abstract: A blade root shim comprises a base, a suction side shim wall, a pressure side shim wall, and a contact relief region. The base extends longitudinally between a leading shim end and a trailing shim end. The suction side shim wall extends along the base and corresponds to a suction side blade root bearing surface. The pressure side shim wall, spaced circumferentially apart from the suction shim wall, corresponds to a pressure side blade bearing surface. The contact relief region is formed into an upper wall portion of either the suction side shim wall or the pressure side shim wall.
    Type: Application
    Filed: September 14, 2012
    Publication date: March 20, 2014
    Inventor: Blake J. Luczak