Resilient Or Deformable Patents (Class 416/221)
  • Patent number: 10815799
    Abstract: A turbine blade has a first end, and an opposing second end. A base includes a dovetail for complementing a corresponding dovetail slot in a rotor. The dovetail has a body and a plurality of projections extend from the body in opposing directions. A tapered groove extends through the body from the first end to the second end, and has a tapered profile such that a first depth of the tapered groove near the first end is greater than a second depth of the tapered groove near the second end. The tapered profile gradually transitions from the first depth to the second depth. The tapered groove is open at a bottom surface of the body and is sized to engage a shim. The tapered groove includes a flat section near the first end or the second end, and the flat section has a constant depth.
    Type: Grant
    Filed: November 15, 2018
    Date of Patent: October 27, 2020
    Assignee: General Electric Company
    Inventors: Steven Sebastian Burdgick, John James Ligos
  • Patent number: 10760529
    Abstract: A composite wear pad for being coupled to a slider block of a convergent nozzle of a gas turbine engine includes a high heat capacity composite having a resin and a plurality of carbon fibers bonded together by the resin. The composite wear pad also includes a first rod coupled to the high heat capacity composite at a first axial end of the composite wear pad such that a first end thickness. The composite wear pad also includes a second rod coupled to the high heat capacity composite at a second axial end of the composite wear pad such that the first axial end and the second axial end of the composite wear pad each have an end thickness that is greater than a middle thickness of the composite wear pad.
    Type: Grant
    Filed: March 2, 2018
    Date of Patent: September 1, 2020
    Assignee: RAYTHEON TECHNOLOGY CORPORATION
    Inventors: Donald W. Peters, Emma J. Place
  • Patent number: 10669868
    Abstract: Fixing set for securely assembling and locking a blade shaped element, for instance a turbine blade, on a support, for instance a turbine rotor. The blade shaped element is adapted to be inserted into a groove of the external surface of the support and the fixing set includes first, second and third locking elements adapted to be inserted into the groove, between the lower end surface of the root portion of the blade shaped element and the groove base surface. The first, second and third locking elements are adapted to securely lock the blade shaped element on the support and are further adapted to allow easy and simple installation by an operator with no need of additional working and extra machining.
    Type: Grant
    Filed: December 21, 2017
    Date of Patent: June 2, 2020
    Assignee: NUOVO PIGNONE TECNOLOGIE SRL
    Inventor: Marco Pieri
  • Patent number: 10364687
    Abstract: A fan for gas turbine engine that includes hub and annular array of fan blades mounted to hub and extending radially outwardly from hub, each fan blade includes blade root. The hub includes a plurality of hub grooves having shape complimentary to shape of blade root and each hub groove receives and radially retains one blade root. A slot is provided on the suction side and on the pressure side of each blade root. Plurality of keys is provided, each key engages with slots in one blade root and with corresponding hub groove so as to axially retain fan blade. The key includes two arms and joining member, two arms are received in slots provided on blade root and joining member extends between the arms. Interface is defined between key arms and slots in blade root, and greater or equal percentage of interface is curved than is planar.
    Type: Grant
    Filed: September 8, 2015
    Date of Patent: July 30, 2019
    Assignee: ROLLS-ROYCE plc
    Inventors: Keith Christopher Goldfinch, Antonios Kalochairetis
  • Patent number: 10316673
    Abstract: Damping systems are provided for a rotor blade platform. The damping system may include a blade platform defining a damper pocket and a CMC wedge damper positioned within the damper pocket. The CMC wedge damper has at least one damper angled surface parallel to a longitudinal axis. The damper pocket comprises a pocket angled surface positioned about the at least one damper angled surface.
    Type: Grant
    Filed: March 24, 2016
    Date of Patent: June 11, 2019
    Assignee: General Electric Company
    Inventor: Matthew Mark Weaver
  • Patent number: 10215035
    Abstract: A wheel assembly for a gas turbine engine is disclosed. The wheel assembly includes a disk arranged for rotation about a central axis and formed to include a plurality of slots. The wheel assembly also includes a plurality of blades sized to be received in the plurality of slots so that the blades are coupled to the disk for common rotation about the central axis. The wheel assembly further includes a plurality of blade biasers positioned in the slots between the disk and the blades so that the blade biasers are engaged with the disk and the blades to preload the blades away from the central axis.
    Type: Grant
    Filed: December 18, 2015
    Date of Patent: February 26, 2019
    Assignee: Rolls-Royce North American Technologies Inc.
    Inventors: Douglas D. Dierksmeier, Tab M. Heffernan
  • Patent number: 10041363
    Abstract: A blade-disk assembly of a turbomachine is provided, the blade-disk assembly having a plurality of adjacent rotor blades and a closure blade which are tilted into an anchoring groove, and at least one circumferential retention element which interlockingly cooperates with at least one blade, as well as a plurality of tilt-out prevention elements which are disposed between the groove base and the root portions and which, in the rest state, space the blades from the groove base when in the upper position. The blade-disk assembly further has a locking element, a portion of which is located between the groove base and the root portions and which, in the rest state, spaces the closure blade from the groove base when in the upper position. A method for assembling such a blade-disk assembly, as well as a turbomachine, is also provided.
    Type: Grant
    Filed: November 18, 2014
    Date of Patent: August 7, 2018
    Assignee: MTU Aero Engines AG
    Inventors: Werner Humhauser, Herman Klingels, Alexander Kloetzer
  • Patent number: 9944880
    Abstract: In order to prevent deterioration in performance of an oil-free screw compressor and scuffing caused by rust, surfaces of both male and female rotors are coated with heat-resistance coatings containing a solid lubricant. A coating contains Polyimide resin to which Molybdenum disulfide, as a solid lubricant, and Aluminum oxide and Titanium oxide, as additives, are added. Accordingly, it is possible to realize a coating that is higher in heat resistance and longer in lifetime than a conventional one.
    Type: Grant
    Filed: July 7, 2014
    Date of Patent: April 17, 2018
    Assignees: HITACHI INDUSTRIAL EQUIPMENT SYSTEMS CO., LTD., KAWAMURA RESEARCH LABORATORIES, INC.
    Inventors: Yukiko Ikeda, Kazuaki Shiinoki, Masakatsu Okaya, Natsuki Kawabata, Masahiro Kawamura, Iwao Aoki
  • Patent number: 9909439
    Abstract: A gas turbine rotor and blade include a root portion, a platform and airfoil portion arranged along a span direction of the rotor blade, the platform located between the root and airfoil portion. The platform has an upstream and downstream side, side faces which extend from upstream to downstream side, an axial groove in each side face extends perpendicular to the span direction with a minor component of extension in span direction. A radial groove in each side face extends towards the axial groove with a component of extension in span direction and a component of extension perpendicular to the span direction. The radial groove has a first end that shows away from the axial groove and a second end that shows towards the axial groove. The second end is located a distance from the axial groove forming a groove free section between the second end and axial groove.
    Type: Grant
    Filed: January 14, 2014
    Date of Patent: March 6, 2018
    Assignee: SIEMENS AKTIENGESELLSCHAFT
    Inventors: Richard Bluck, David Butler, Jonathan Mugglestone, David Overton
  • Patent number: 9840931
    Abstract: A gas turbine engine component has an axial seal pin assembly for sealing between adjacent platform regions where the seal pin assembly design provides a seal pin damper slot extending to a forward axial stop in a forward buttress region. The forward axial stop includes a relief slot to interrupt the loadpath from the airfoil into the blade neck and attachment regions to reduce the stress concentrations in these regions.
    Type: Grant
    Filed: September 30, 2013
    Date of Patent: December 12, 2017
    Assignee: ANSALDO ENERGIA IP UK LIMITED
    Inventors: Gaurav K. Joshi, John Cuyler Hunt, Orestes J. Maurell, Adam L. Hart
  • Patent number: 9677403
    Abstract: A securement system for securing an attachment portion of at least one rotor blade or rotor blade segment in a mounting site of a rotor base. The securement system has at least one holder element and a second holder element, each of which has a holding portion and a connecting portion. The connecting portions can be introduced into the mounting site so as to establish a clip connection and can be locked together in the mounting site. The holding portions are configured so as to fasten the attachment portion of the at least one rotor blade or of the rotor blade segment in the mounting site in the locked state of the connecting portions. Further disclosed is a method for securing an attachment portion of at least one rotor blade or rotor blade segment in a mounting site of a rotor base and a rotor having a securement system.
    Type: Grant
    Filed: April 4, 2014
    Date of Patent: June 13, 2017
    Assignee: MTU Aero Engines AG
    Inventors: Frank Stiehler, Felix Kern
  • Patent number: 9540093
    Abstract: A bladed rotor wheel for a turbine engine, the rotor wheel including a disk including, formed in its outer periphery, at least one slot for mounting the roots of blades, and a spacer mounted between each blade root and a bottom of the slot. The spacer includes at least one member of type that is bistable in position and that can occupy a first stable position for assembly or disassembly in which the member does not exert force on the blade root, and a second stable position in which the bistable member exerts a radial force on the blade root. The spacer also includes at least one resilient damper member mounted between the bottom of the slot and the blade root.
    Type: Grant
    Filed: August 2, 2012
    Date of Patent: January 10, 2017
    Assignee: SNECMA
    Inventors: Luc Henri Chatenet, John Le Quellec
  • Patent number: 9505092
    Abstract: Fan assemblies, and in particular fan wheels and stator assemblies for fan assemblies, are disclosed. In one embodiment, the fan wheel includes a wheel back having an outer surface forming one of a curved dome-shape and a truncated cone-shape. The fan wheel may also include a plurality of fan blades radially spaced about and mounted to the outer surface of the wheel back. In one embodiment, each of the fan blades is formed from a segment of an airfoil-shaped aluminum extrusion defining at least one internal cavity. The fan blade first ends can be provided with a compound cut profile with at least one curved cut such that the first end of the blade is mounted flush to the wheel back outer surface. The stator assembly can also be provided with a plurality of stator blades formed from airfoil-shaped aluminum extrusion segments and provided with compound cut profiles.
    Type: Grant
    Filed: February 25, 2013
    Date of Patent: November 29, 2016
    Assignee: Greenheck Fan Corporation
    Inventors: Kyle Andrew Brownell, Shamus William Doran, Jared Clyde Wesenick, Neil Jacob Printz
  • Patent number: 9410440
    Abstract: A rotor assembly includes a rotor disc and a plurality of circumferentially-spaced, radially outwardly extending rotor blades. The rotor disc has a rim and a plurality of circumferentially spaced slots provided in the rim of the rotor disc, each rotor blade having a root, the root of each rotor blade being arranged in a corresponding one of the slots in the rim of the rotor disc, and at least one of the slots having a chocking device accommodated within a space between a radially outer surface of the slot and a radially inner surface of the root of the rotor blade. The chocking device includes at least a first spring and a second spring, the first and second springs each abutting a radially inner surface of the root of the corresponding rotor blade and arranged transversely relative to a longitudinal axis of the slot.
    Type: Grant
    Filed: July 9, 2013
    Date of Patent: August 9, 2016
    Assignee: ROLLS-ROYCE PLC
    Inventor: Stephen Jonathan Dimelow
  • Patent number: 9366142
    Abstract: A turbine rotor disk includes a row of buckets secured about a radially outer periphery of the rotor disk, each bucket having an airfoil, a platform, a shank and a mounting portion, the mounting portion received in a radial slot formed in the rotor disk such that adjacent buckets in adjacent radial slots are separated by a rotor disk post located between adjacent mounting portions and a shank cavity between adjacent shanks, radially outward of the rotor disk post and radially inward of adjacent platforms. The shank cavity is substantially filled with at least one discrete thermal plug.
    Type: Grant
    Filed: October 28, 2011
    Date of Patent: June 14, 2016
    Assignee: General Electric Company
    Inventor: Jeffrey John Butkiewicz
  • Patent number: 9321537
    Abstract: A beam for suspending a turboshaft engine from an aircraft structure, including a first attachment mechanism configured to be secured to the aircraft structure and at least one second attachment mechanism configured to be secured to the engine. The beam is at least partially made from a metal-matrix composite material including reinforcing fibers. In one embodiment, the beam takes a form of a circle arc.
    Type: Grant
    Filed: July 27, 2010
    Date of Patent: April 26, 2016
    Assignee: SNECMA
    Inventors: Patrick Dunleavy, Guillaume Lefort, Richard Masson, Thibaut Francois Roux, Guilhem Seize
  • Patent number: 9246372
    Abstract: A support rib for securing a rotor pole to a flange in a gearless drive is described. The support rib is undivided and passes through an opening of the flange. The support rib can be joined with the flange and/or the rotor pole using an adhesive. The rib preferably has at least one notch that engages an edge of the flange opening to establish mechanical connection between the rib and flange. An insert with two ends that slideably engages a rib edge and rotor pole channel can be used to couple the rib to the rotor pole.
    Type: Grant
    Filed: January 20, 2012
    Date of Patent: January 26, 2016
    Assignee: Fluor Technologies Corporation
    Inventor: Alexander Kheifets
  • Patent number: 9243501
    Abstract: A blade for a gas turbine engine includes a shank interconnecting a root and a platform, and an airfoil extending radially from the shank. The shank includes a pocket with the platform overhanging the pocket. A rail extends axially along a lateral edge of the platform and extends radially inward from the platform in a direction opposite the airfoil. A gusset extends from an underside of the platform facing the pocket and in a circumferential direction between the rail and the shank.
    Type: Grant
    Filed: September 11, 2012
    Date of Patent: January 26, 2016
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Seth J. Thomen, Edward F. Pietraszkiewicz
  • Publication number: 20150110635
    Abstract: An adjustable blade root spring device for turbine blade fixation in turbomachinery. The device is designed to be placed in a space in a rotor disk cavity adjacent to a tip of a blade root fir tree, where the device applies a radial outward force on the turbine blade to fix the blade position in the rotor disk. The device includes an accordion-shaped spring which is compressed by a bolt and a coil spring. When the accordion spring is compressed in length, it increases in height and makes contact with the rotor disk and the turbine blade. The force of the accordion spring on the turbine blade can be adjusted via the bolt, and the coil spring provides an increased compliance range. The device can be inserted into the space without scraping against the blade root or the rotor disk, and expanded once it is in position.
    Type: Application
    Filed: August 12, 2014
    Publication date: April 23, 2015
    Inventors: Jeffrey A. Kain, Mohit Gupta, Leonard J. Meyer, Ryan S. Yamane, James A. Chonody, Charalambos Polyzopoulos
  • Patent number: 8992180
    Abstract: A rotor assembly. The rotor assembly may include a rotor, at least one axial slot positioned about the rim of the rotor having a first staking recess positioned therein, a blade positioned within each of the axial slots having a second staking recess positioned therein, a staking insert having a base portion and a projection extending therefrom with the base portion being disposed within the first staking recess and the projection being disposed within the second staking recess, and a shim positioned within the first staking recess adjacent to the base portion, opposite the projection, of the staking insert. The first staking recess retains the staking insert while the projection of the staking insert retains the blade in both the aft and forward directions.
    Type: Grant
    Filed: August 24, 2011
    Date of Patent: March 31, 2015
    Assignee: General Electric Company
    Inventors: Sukumar Agaram, Narasimha K V Rao
  • Patent number: 8956122
    Abstract: A safety device for a turbine blade is provided. The safety device includes a shear pin, a clamping piece and a securing element, wherein the shear pin is arranged in a corresponding bore in the turbine blade foot and the clamping piece is designed having an upper limb and a lower limb, wherein the clamping piece exerts a radial force on the turbine blade foot for radial safeguarding.
    Type: Grant
    Filed: September 17, 2010
    Date of Patent: February 17, 2015
    Assignee: Siemens Aktiengesellschaft
    Inventors: Thomas Helmis, Heinrich Stüer
  • 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: 8894370
    Abstract: A retention system retains a turbine blade dovetail in a retention ring dovetail slot. The retention system includes a retention opening formed in the blade dovetail. A through hole is formed in the retention ring, wherein the through hole is positioned such that it is aligned with the retention opening when the dovetail is assembled in the dovetail slot. A connector is disposed in the through hole and engages the retention opening. In this manner, undesirable relative movement of parts can be reduced or eliminated, thereby preventing excessive wear.
    Type: Grant
    Filed: April 4, 2008
    Date of Patent: November 25, 2014
    Assignee: General Electric Company
    Inventors: Stephen P. Wassynger, Nick Martin, Steven E. Tomberg
  • Patent number: 8858181
    Abstract: The invention relates to a device (30) for blockage of vanes in a circumferential groove (10) of a turbine engine disc, the device being intended to deploy in a radial direction to be locked in the circumferential groove open radially. According to the invention, the blocking device comprises a first and a second piece (32, 34) designed to deploy in the radial direction by relative displacement of these pieces in the circumferential direction (23).
    Type: Grant
    Filed: September 2, 2011
    Date of Patent: October 14, 2014
    Assignee: SNECMA
    Inventor: Yvon Cloarec
  • Patent number: 8851854
    Abstract: A gas turbine engine fan assembly includes a rotor disk, a fan blade and a spacer. The rotor disk includes a longitudinally extending slot with a first spacer contact surface. The fan blade includes a root with a second spacer contact surface arranged within the slot. The spacer includes a leaf spring backbone and a compliant member. The leaf spring backbone includes one or more root contact segments connected longitudinally to one or more slot contact segments. A first of the root contact segments contacts the second spacer contact surface, and a first of the slot contact segments contacts the first spacer contact surface. The compliant member is radially between the first spacer contact surface and the first root contact segment, and radially between the second spacer contact surface and the first slot contact segment.
    Type: Grant
    Filed: December 16, 2011
    Date of Patent: October 7, 2014
    Assignee: United Technologies Corporation
    Inventor: Phillip Alexander
  • 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: 8840375
    Abstract: A lock assembly includes a lock body with an undercut slot which receives a retaining wire of a polygon shape.
    Type: Grant
    Filed: March 21, 2011
    Date of Patent: September 23, 2014
    Assignee: United Technologies Corporation
    Inventor: Scott D. Virkler
  • Patent number: 8801385
    Abstract: A vibration-damping device for a turbomachine blade including a blade root configured to be inserted into a pocket of a carrier disk of a bladed wheel, the device configured to be positioned between the blade root and a retaining wall of the pocket. The device includes at least one shim including an assembly of layers of rigid materials and of viscoelastic materials, and including two portions, each forming a lateral branch which can be inserted along one of the two retaining walls, the two lateral branches being connected to one another, so as to constitute a single part, by a third portion forming a shim bottom of rigid material. At least one layer of viscoelastic material is positioned between two layers of rigid materials.
    Type: Grant
    Filed: August 5, 2009
    Date of Patent: August 12, 2014
    Assignee: SNECMA
    Inventor: Adrien Jacques Philippe Fabre
  • Publication number: 20140190181
    Abstract: A cover plate for a rotor disk in a gas turbine machine includes a cylindrical body having multiple outward facing snaps and multiple inward facing snaps.
    Type: Application
    Filed: January 9, 2013
    Publication date: July 10, 2014
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Mark Borja, Ehren B. Holt
  • Patent number: 8770938
    Abstract: A rotor is provided for an axial-throughflow turbo machine, which carries a plurality of moving blades which are each pushed with a blade root into a rotor groove extending about the axis and are held. The blade root includes a hammer root with a hammerhead and is supported on radial stop faces of the rotor groove which lie further outward in the radial direction, against centrifugal forces acting on the moving blades, and are supported on axial stop faces lying further inward in the radial direction, against axial forces which act on the moving blade. The rotor groove has at its bottom, to reduce thermal stresses, an axially and radially widened bottom region with a continuously curved cross-sectional contour. In such a rotor, an advantageous adaptation of the blading is achieved by the blade root of the moving blades being adapted to the widened bottom region in the radial direction.
    Type: Grant
    Filed: November 9, 2010
    Date of Patent: July 8, 2014
    Assignee: Alstom Technology Ltd
    Inventors: Erich Kreiselmaier, Kurt Rubischon, Christoph Nagler, Herbert Brandl
  • Publication number: 20140178202
    Abstract: A turbine engine rotor wheel including a disk including at least one slot formed in its outer periphery for mounting roots of blades, a presser being mounted between each blade root and a bottom of the slot. The presser is bistable in position and is capable of occupying a first stable position for assembly and disassembly in which it does not exert a force on the blade root, and a second stable position in which it exerts a radial force on the blade root to hold the blade stationary and to stabilize the blade in a final position.
    Type: Application
    Filed: May 14, 2012
    Publication date: June 26, 2014
    Applicant: SNECMA
    Inventors: Luc Henri Chatenet, John Le Quellec
  • Patent number: 8753090
    Abstract: A bladed disk assembly includes a disk, a blade, and a retaining clip. The disk is centered on an axis. The disk has at least one groove extending along the axis. The blade is received in the groove. The retaining clip contacts the blade and limits movement of the blade along the axis. The retaining clip is engaged with the disk through a snap-fit.
    Type: Grant
    Filed: November 24, 2010
    Date of Patent: June 17, 2014
    Assignee: Rolls-Royce Corporation
    Inventors: Matthew Peter Basiletti, Richard Christopher Uskert, Michelle Lynn Tucker
  • Publication number: 20140161617
    Abstract: A bladed rotor wheel for a turbine engine, the rotor wheel including a disk including, formed in its outer periphery, at least one slot for mounting the roots of blades, and a spacer mounted between each blade root and a bottom of the slot. The spacer includes at least one member of type that is bistable in position and that can occupy a first stable position for assembly or disassembly in which the member does not exert force on the blade root, and a second stable position in which the bistable member exerts a radial force on the blade root. The spacer also includes at least one resilient damper member mounted between the bottom of the slot and the blade root.
    Type: Application
    Filed: August 2, 2012
    Publication date: June 12, 2014
    Applicant: SNECMA
    Inventors: Luc Henri Chatenet, John Le Quellec
  • Patent number: 8662845
    Abstract: A rotor disk assembly for a gas turbine engine includes a rotor disk with a circumferentially intermittent slot structure that extends radially outward relative to an axis of rotation. A heat shield has a multiple of radial tabs engageable with the circumferentially intermittent slot structure to provide axial retention of the cover plate to the rotor disk.
    Type: Grant
    Filed: January 11, 2011
    Date of Patent: March 4, 2014
    Assignee: United Technologies Corporation
    Inventors: Scott D. Virkler, Jason Arnold
  • Patent number: 8651817
    Abstract: An aerofoil blade assembly having a rotor disc having a radially outer surface provided with an axial slot and a radially inner surface provided with a circumferential slot, wherein the lower region of the axial slot intersects the upper region of the circumferential slot; an aerofoil blade having a blade root which is received by the axial slot and which is provided with a locating slot which corresponds to the circumferential slot; a retention key which engages with the circumferential slot and the locating slot to restrict axial displacement of the aerofoil blade with respect to the rotor disc, the retention key being provided with a socket which, when the retention key is engaged in the circumferential slot and the locating slot, is substantially aligned with the axial slot.
    Type: Grant
    Filed: August 5, 2010
    Date of Patent: February 18, 2014
    Assignee: Rolls-Royce PLC
    Inventor: Steven A. Radomski
  • Patent number: 8651821
    Abstract: This blade attachment device comprises a shell (28) installed around an outer collar (23) of the pivot (15) of the blade (27) and capable of rotating by an angle sufficient for cleats (30, 31) to close the ends of the pivot groove and retain the root of the blade (27) in it, and mobile shims that cooperate to retain the root in the groove. Application to aircraft engines.
    Type: Grant
    Filed: July 16, 2009
    Date of Patent: February 18, 2014
    Assignee: SNECMA
    Inventors: Daniel Bernard Dao, Adrien Jacques Philippe Fabre, Alain Paul Madec
  • Publication number: 20140023508
    Abstract: A rotor assembly includes a rotor disc and a plurality of circumferentially-spaced, radially outwardly extending rotor blades. The rotor disc has a rim and a plurality of circumferentially spaced slots provided in the rim of the rotor disc, each rotor blade having a root, the root of each rotor blade being arranged in a corresponding one of the slots in the rim of the rotor disc, and at least one of the slots having a chocking device accommodated within a space between a radially outer surface of the slot and a radially inner surface of the root of the rotor blade. The chocking device includes at least a first spring and a second spring, the first and second springs each abutting a radially inner surface of the root of the corresponding rotor blade and arranged transversely relative to a longitudinal axis of the slot.
    Type: Application
    Filed: July 9, 2013
    Publication date: January 23, 2014
    Inventor: Stephen Jonathan DIMELOW
  • Patent number: 8622699
    Abstract: A device adapted to be fitted with propeller blades includes a first retention ring including over a periphery thereof a plurality of radial bores; and a second retention ring including over a periphery thereof a plurality of radial bores, the first and second retention rings being mounted one on top of the other in the radial direction, each bore in the first retention ring being positioned opposite a bore in the second retention ring, a bore in the first retention ring arranged opposite a bore in the second retention ring forming a bore pair adapted to receive a foot of a blade.
    Type: Grant
    Filed: October 14, 2010
    Date of Patent: January 7, 2014
    Assignee: SNECMA
    Inventors: François Gallet, Patrick Morel, Wouter Balk
  • Patent number: 8616850
    Abstract: A mounting arrangement for a gas turbine engine blade having a root employs a lightweight, simple and economical leaf spring spacer which biases the blade root in a radially outward direction to minimize unwanted movement of the root within a conforming slot in a blade hub under conditions such as windmilling when centrifugal force alone is inadequate to tightly seal the root within the slot.
    Type: Grant
    Filed: June 11, 2010
    Date of Patent: December 31, 2013
    Assignee: United Technologies Corporation
    Inventors: Eric J. Ward, Brian K. Richardson
  • Patent number: 8616849
    Abstract: A fan blade platform assembly comprises a plate insert shaped and dimensioned to span a gap formed between the opposed facing platforms of adjacent fan blades of a turbo fan engine. The plate insert can be retained in engagement under arresting shoulders provided on the adjacent fan blades by a spring force exerted by a spring insert held captive and in contact between the plate insert and an outer surface of the fan hub.
    Type: Grant
    Filed: February 18, 2009
    Date of Patent: December 31, 2013
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: David H. Menheere, Andreas Elfetheriou, Philip Ridyard
  • Patent number: 8613599
    Abstract: A turbine blade assembly, in particular for a gas turbine, is provided. The turbine blade assembly includes a disc with a rotation axis, turbine blades, each turbine blade including an airfoil, a blade root and a platform between the airfoil and the blade root by which it may be fixed to the disc, locking plates and bent seal strips. The turbine blades are arranged adjacent to each other on the disc, such that gaps are present between the platforms of adjacent turbine blades and root cavities are present between the portions of the roots of adjacent turbine blades. The turbine blades are secured axially to the disc by the locking plates. The seal strips are arranged in the gaps between the platforms of neighboring turbine blades to seal the gap and protrude axially over the blade root and over the locking plate.
    Type: Grant
    Filed: September 16, 2008
    Date of Patent: December 24, 2013
    Assignee: Siemens Aktiengesellschaft
    Inventors: Peter Lake, Rene James Webb
  • Patent number: 8608436
    Abstract: A connection between an annular sleeve on a gas turbine engine first rotor component includes an annular tapered conical slot extending axially inwardly into the sleeve from an annular opening and tapers axially into the sleeve from the opening. An annular rim of a second rotor component is received within the conical slot and includes a rim inner conical surface mating with and contacting a sleeve inner conical surface in part bounding the conical slot. A sleeve cylindrical outer surface in part bounds the conical slot in the sleeve and a rim outer cylindrical surface on the annular rim contacts the sleeve cylindrical outer surface. An annular lip may extend radially inwardly from the sleeve and sleeve inner conical surface at the annular opening to the conical slot. The connection may be used between a first stage disk and an interstage seal.
    Type: Grant
    Filed: August 31, 2010
    Date of Patent: December 17, 2013
    Assignee: General Electric Company
    Inventors: Daniel Edward Wines, James Hamilton Grooms, Craig William Higgins
  • Patent number: 8585369
    Abstract: A device for axial retention of mobile vanes mounted on a rotor disc includes two open rings, superimposed. At least one of the rings includes a rotating stop mechanism configured to cooperate with at least one hook of the disc. The two open rings are mounted in a discontinuous groove formed in the hooks, at the end of teeth situated on the periphery of the rotor disc, such that the rotating stop mechanism of the first ring is placed in the opening of the second ring. The significance of contact surfaces between the two rings allows a damping of vibrations during operation.
    Type: Grant
    Filed: April 24, 2009
    Date of Patent: November 19, 2013
    Assignee: SNECMA
    Inventors: Stephan Yves Aubin, Erick Jacques Boston, Yvon Cloarec
  • Patent number: 8573942
    Abstract: A gas turbine engine component having an axial pin stop assembly that reduces stress around a seal pin damper slot between a platform and a buttress is disclosed. The seal pin damper slot is extended to the leading edge of the buttress and an axial pin stop seal extends into the pin damper slot to limit movement of the seal pin damper while relieving stress concentration at the interface between the buttress and platform.
    Type: Grant
    Filed: November 25, 2008
    Date of Patent: November 5, 2013
    Assignee: Alstom Technology Ltd.
    Inventors: James Page Strohl, RuthAnn Rawlings
  • Patent number: 8573944
    Abstract: An anti-wear device of a turbomachine rotor including a disk with a rim and axial recesses machined on the rim for the individual housing of blades; and a ring being fitted to one face of the rim, the ring being pierced with holes in the axial extension of the recesses, is disclosed. At least one of the holes in the extension of the recesses is closed by a plug including a metal head forming a bearing surface for the blades. The plug includes a stud in the extension of the metal head, an insert made of deformable material surrounding at least partly the stud, and a clamping device. The insert is made of deformable material being deformed by the clamping device so as to immobilize the plug in the hole.
    Type: Grant
    Filed: July 28, 2010
    Date of Patent: November 5, 2013
    Assignee: SNECMA
    Inventors: Michael Delapierre, Jerome Paul Marceau Mace, Patrick Jean-Louis Reghezza, Nicolas Christian Triconnet
  • Patent number: 8562301
    Abstract: A turbine blade assembly has a turbine blade with a root section and an airfoil section. The root section has one of a radially extending groove or flange, and a retainer element has the other of the groove and the flange. The groove receives the flange to hold the retainer element and the blade together. The retainer element has axial ends extending radially inwardly to secure a turbine blade assembly within a disk slot in a turbine rotor disk. A method is also disclosed.
    Type: Grant
    Filed: April 20, 2010
    Date of Patent: October 22, 2013
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Shihming Jan, David Carlton Hansen
  • Publication number: 20130259695
    Abstract: Wedging blades attached to the disk of a rotor having slots. According to the invention, each wedging 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: Application
    Filed: May 24, 2013
    Publication date: October 3, 2013
    Inventors: Olivier BELMONTE, Jean-Luc Christian Yvon Goga, Jean-Noel Mahieu
  • Patent number: 8545181
    Abstract: A turbine blade assembly, which can be used for a gas turbine is provided. The turbine blade assembly includes turbine blades with platforms, gaps between the platforms of adjacent turbine blades and seals. Each seal covers the gap between the platforms of two adjacent turbine blades wherein the platforms are provided with slots extending in the downstream flow direction. The turbine blades have root cavities, wherein the seal covers at least the whole length of the root cavities of two adjacent turbine blades. The seal is formed from a strip and the seal is placed in two opposed slots formed in each of the platforms of two adjacent turbine blades and open towards the respective downstream ends.
    Type: Grant
    Filed: August 31, 2007
    Date of Patent: October 1, 2013
    Assignee: Siemens Aktiengesellschaft
    Inventor: Scott Charlton
  • Patent number: 8535013
    Abstract: A fan assembly of a gas turbine engine, the fan assembly includes an array of radially extending blades defining gaps therebetween and an annulus filler located within at least one gap. The annulus filler includes at least two individual bodies arranged circumferentially adjacent one another with at least one adjacent a blade, one of the bodies includes a flexible wall arranged to centrifuge outwardly against the other body thereby urging both bodies against the blades and securing them during engine operation.
    Type: Grant
    Filed: March 30, 2009
    Date of Patent: September 17, 2013
    Assignee: Rolls-Royce PLC
    Inventors: Ian Colin Deuchar Care, Dale Edward Evans
  • Patent number: 8529209
    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: June 24, 2008
    Date of Patent: September 10, 2013
    Assignee: SNECMA
    Inventors: Olivier Belmonte, Jean-Luc Christian Yvon Goga, Jean-Noël Mahieu