Self-shifting Or Selectively Adjustable Mass Patents (Class 416/145)
  • Patent number: 11365643
    Abstract: A sealing flange sector for a turbomachine rotor disc includes a radially outer part which is configured to bear at least partly against blades of the turbomachine rotor disc to ensure sealing between the blades and a radially inner part configured to bear on an annular strip mounted on a face of the turbomachine rotor disc, the radially inner part having a first groove disposed radially outwardly of a second groove. The first groove includes at least one foolproofing element.
    Type: Grant
    Filed: January 13, 2020
    Date of Patent: June 21, 2022
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Pierre-Alain Francis Claude Sebrecht, Nishanth Thomas Rajaratnam
  • Patent number: 11346324
    Abstract: The present invention provides a method of erecting a wind turbine on a wind turbine site. The wind turbine comprises a turbine tower and a nacelle. The method comprises the following steps: providing a plurality of tower sections being arrangeable upon each other in a vertical orientation in a tower structure to form the turbine tower, providing at least two damper units configured to dampen oscillations of the turbine tower, attaching one of the at least two damper units to one of the plurality of the tower sections on an outside thereof, and subsequently arranging said tower section in the tower structure, attaching a subsequent one of the at least two damper units to another one of the plurality of the tower sections on an outside thereof, and subsequently arranging said tower section in the tower structure, while the previous one of the at least two damper units is still attached to the previous one of the plurality of tower sections.
    Type: Grant
    Filed: June 26, 2019
    Date of Patent: May 31, 2022
    Assignee: Vestas Wind Systems A/S
    Inventors: Rasmus Sanderhoff Johansen, Søren Bøgelund Madsen, Jes Grøn Andersen, Jakob Anders Sørensen
  • Patent number: 11333127
    Abstract: A protective cover for a leading-edge of a wind turbine rotor blade is provided. The protective cover is pre-formed into a curved shape to accommodate at least a part of a leading-edge section including the leading-edge of the wind turbine rotor blade to be protected. The protective cover includes a pressure side section, a suction side section and a centerline in-between the pressure side section and the suction side section. The centerline runs in longitudinal direction of the protective cover. Thickness of the protective cover in a cross section of the protective cover in transverse direction has a thickness distribution corresponding to a standardized normal distribution.
    Type: Grant
    Filed: February 27, 2019
    Date of Patent: May 17, 2022
    Assignee: SIEMENS GAMESA RENEWABLE ENERGY A/S
    Inventors: Kasper Koops Kratmann, Oriol Ferret Gasch
  • Patent number: 11299992
    Abstract: Rotor blades and turbomachines are provided. The rotor blade includes a main body having a shank, an airfoil extending radially outwardly from the shank, and a platform. The main body further includes a pressure-side slash face and a suction-side slash face. Each of the pressure-side slash face and the suction-side slash face includes a damper land and defines a slot. The damper land is disposed radially inward from the slot.
    Type: Grant
    Filed: March 25, 2020
    Date of Patent: April 12, 2022
    Assignee: General Electric Company
    Inventors: Martin James Jasper, Charles Wesley Wells
  • Patent number: 11267561
    Abstract: A vibration attenuator for a rotor of an aircraft has a track housing adapted for rotation relative to the rotor and configured for rotation at a second angular velocity greater than a first angular velocity of the rotor. A track is located within the track housing and has a reaction surface, a pair of weights being configured for movement within the track and in contact with the reaction surface. A stop assembly has a pair of stops spaced 180 degrees apart, the stops separating the weights from each other, and each weight being allowed to travel within the track between the stops. A motor rotates the track housing relative to the rotor. The weights are free to travel relative to each other between a minimum-force configuration, in which the weights are positioned 180 degrees apart, and a maximum-force configuration, in which both weights are adjacent one of the stops.
    Type: Grant
    Filed: October 25, 2019
    Date of Patent: March 8, 2022
    Assignee: Textron Innovations Inc.
    Inventors: David Heverly, Frank Bradley Stamps, Jouyoung Jason Choi, Michael R. Smith, Thomas C. Parham
  • Patent number: 11254424
    Abstract: A balance weight assembly for a rotor blade of a rotorcraft. The balance weight assembly includes a balance weight pocket formed by a balance weight tray and a cover. The balance weight tray has an upper surface including a lip region extending outwardly from a projected region with an outboard boss. A balance weight receiving cavity is recessed from the upper surface and contains a plurality of balance weights. The projected region is disposed within an opening in a hollow blade spar such that the outboard boss of the balance weight tray has a contact relationship with an outboard surface of the opening. The cover is coupled to the balance weight tray such that the lip region of the balance weight tray and at least a portion of the cover have a clamping relationship with the blade spar, thereby coupling the balance weight pocket to the blade spar.
    Type: Grant
    Filed: September 30, 2019
    Date of Patent: February 22, 2022
    Assignee: Textron Innovations Inc.
    Inventors: Tyler Wayne Baldwin, Jared Mark Paulson, Colin John Thomas, Paul Branson Sherrill, Bryan Huber
  • Patent number: 10920607
    Abstract: A blade for a propulsion apparatus. The blade includes a body having opposed pressure and suction sides. The blade extends in span between a root and a tip and the blade extends in chord between a leading edge and a trailing edge. The blade includes a fracture structure that is defined within the body and positioned such that it is spaced-away from the tip. The fracture structure includes at least one chamber. A first fracture wall is disposed between the at least one chamber and the pressure side, and a second fracture wall is disposed between the at least one chamber and the suction side. The fracture structure is configured to fail when a predetermined force is applied to the tip such that the tip separates from the remainder of the body.
    Type: Grant
    Filed: September 28, 2018
    Date of Patent: February 16, 2021
    Assignee: General Electric Company
    Inventors: Nitesh Jain, Kishore Budumuru, Nicholas Joseph Kray, Daniel Edward Mollmann
  • Patent number: 10899441
    Abstract: The present disclosure provides various embodiments of a multicopter-assisted launch and retrieval system generally including: (1) a multi-rotor modular multicopter attachable to (and detachable from) a fixed-wing aircraft to facilitate launch of the fixed-wing aircraft into wing-borne flight; (2) a storage and launch system usable to store the modular multicopter and to facilitate launch of the fixed-wing aircraft into wing-borne flight; and (3) an anchor system usable (along with the multicopter and a flexible capture member) to retrieve the fixed-wing aircraft from wing-borne flight.
    Type: Grant
    Filed: May 21, 2020
    Date of Patent: January 26, 2021
    Assignee: Hood Technology Corporation
    Inventors: Andreas H. von Flotow, Corydon C. Roeseler, Daniel Pepin Reiss
  • Patent number: 10858122
    Abstract: A method for monitoring the health of propellers in an aircraft is provided. The method includes receiving pressure waves generated by at least one rotating propeller and analysing data corresponding to the received pressure waves to detect tonal noise which is within a selected frequency range. If tonal noise at harmonics of the propeller rotational frequency within the selected frequency range is detected within the selected frequency range, it is established that the health of at least one propeller may be impaired and an alert is created for inspection and maintenance to take place.
    Type: Grant
    Filed: September 8, 2017
    Date of Patent: December 8, 2020
    Assignee: RATIER-FIGEAC SAS
    Inventors: Abdellah El Haloui, Bruno Petellaz
  • Patent number: 10767504
    Abstract: A flexible damper (24) for turbine blades (10) includes a plurality of segments (32) positioned together in a substantially linear pattern, each segment (32) having a first side (46), a second side (48), a top side (50), a bottom side (52), a length (56), a width (54), and a thickness (58).
    Type: Grant
    Filed: January 12, 2016
    Date of Patent: September 8, 2020
    Assignee: SIEMENS AKTIENGESELLSCHAFT
    Inventors: Nicholas F. Martin, Jr., David J. Wiebe
  • Patent number: 10696388
    Abstract: The present disclosure provides various embodiments of a multicopter-assisted launch and retrieval system generally including: (1) a multi-rotor modular multicopter attachable to (and detachable from) a fixed-wing aircraft to facilitate launch of the fixed-wing aircraft into wing-borne flight; (2) a storage and launch system usable to store the modular multicopter and to facilitate launch of the fixed-wing aircraft into wing-borne flight; and (3) an anchor system usable (along with the multicopter and a flexible capture member) to retrieve the fixed-wing aircraft from wing-borne flight.
    Type: Grant
    Filed: February 13, 2017
    Date of Patent: June 30, 2020
    Assignee: Hood Technology Corporation
    Inventors: Andreas H. von Flotow, Corydon C. Roeseler, Daniel Pepin Reiss
  • Patent number: 10640157
    Abstract: An assembly of subassemblies having a mating bond interface for a motor vehicle is provided. The assembly includes a first subassembly of molded composite material and a second subassembly of molded composite material. An adjustable mating interface couples the subassemblies together. The interface includes a groove and a flange disposed on the first subassembly and bonded within the groove. The groove is sized and shaped relative to the size and shape of the flange to allow a bonding position of the flange within the groove to be adjusted during assembly of the subassemblies so that the mating interface is adjustable.
    Type: Grant
    Filed: October 23, 2018
    Date of Patent: May 5, 2020
    Assignee: Global IP Holdings, LLC
    Inventors: Scott Allen Grajek, Jesse Brian Straight, Dustin Martin Fowler, Shane Caird Morse
  • Patent number: 10611501
    Abstract: There is described herein a propeller balancing system and method that selects at least a portion of received propeller vibration data by comparing received aircraft data collected concurrently with the propeller vibration data with at least one customizable flight criterion, and identifying the portion of the vibration data acquired at a time when the aircraft data meets the at least one customizable flight criterion. The selected portion of the propeller vibration data is analyzed to assess a vibration level of the propeller and a balancing need is signaled when the vibration level reaches a threshold.
    Type: Grant
    Filed: June 1, 2017
    Date of Patent: April 7, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Richard Brian Wirth, Robert Winchcomb, Bruce Calvert, Robert Wigny
  • Patent number: 10584597
    Abstract: A damper pin for damping adjacent turbine blades coupled to a rotor shaft includes an elongated body having a center portion that is disposed between a first end portion and a second end portion. The first end portion, center portion and second end portion at least partially define a generally arcuate top portion of the elongated body. At least a portion of the top portion may be configured to contact with a groove that is defined between the adjacent turbine blades. The first end portion and the second end portion have substantially semi-cylindrical cross sectional shapes and the center portion has a cylindrical cross sectional shape. A bottom portion of the elongated body diverges radially outwardly from the first end portion to the center portion and from the second end portion to the center portion.
    Type: Grant
    Filed: September 3, 2015
    Date of Patent: March 10, 2020
    Assignee: General Electric Company
    Inventors: Spencer A. Kareff, Sheo Narain Giri
  • Patent number: 10562617
    Abstract: A vibration attenuation system for attenuating vibrations in a mast of an aircraft includes a weight attached to the mast but free to orbit about the mast. The weight can be comprised of one or more weight assemblies. Embodiments can include a single weight, or plural weight assemblies wherein each weight assembly can include a mechanical interconnecting mechanism so that each weight assembly receives feedback regarding the position and movement of one or more other weight assemblies. Each weight can be associated with a spring that urges the weight towards a neutral position. Rotation of the mast can cause the weight to orbit about the mast and self-excite such that the weight acts against the urging of the spring towards an attenuating position.
    Type: Grant
    Filed: November 13, 2016
    Date of Patent: February 18, 2020
    Assignee: BELL HELICOPTER TEXTRON INC.
    Inventors: Jouyoung Jason Choi, David Heverly, Michael Seifert, Michael Smith, Frank Brad Stamps, Thomas Parham, Jr., Amarjit Olenchery Kizhakkepat
  • Patent number: 10526901
    Abstract: A turbomachine blade assembly including a turbomachine blade (1), in particular for a gas turbine, and at least one tuning element container including a housing (10) attached to the turbomachine blade and an insert (20) disposed in a recess (11) of this housing. A wall (20; 21) of the insert spaces apart two first cavities (31), which each accommodate at least one tuning element (40) provided for impacting contact with the housing (10) and the insert (20).
    Type: Grant
    Filed: March 14, 2017
    Date of Patent: January 7, 2020
    Assignee: MTU Aero Engines AG
    Inventors: Markus Schlemmer, Gerhard-Heinz Roesele, Andreas Hartung
  • Patent number: 10479494
    Abstract: A rotorcraft tail rotor comprising at least two blade elements, each blade element being suitable for pivoting about a collective pitch variation axis Z in order to vary the collective pitch of each blade element of the tail rotor, each blade element including at least one compensation weight comprising a projection emerging substantially perpendicularly to a main inertia axis of the blade element, the main inertia axis being parallel to a longitudinal direction of the blade element. In the invention, the tail rotor is wherein the compensation weight includes a deformable portion that is movable relative to the projection in a plane P that is parallel to the main inertia axis of the blade element.
    Type: Grant
    Filed: November 24, 2015
    Date of Patent: November 19, 2019
    Assignee: AIRBUS HELICOPTERS
    Inventors: Bernard Certain, Jeremy Jouve
  • Patent number: 10415391
    Abstract: The present disclosure relates generally a gas turbine engine and a rotor therefor. The rotor may include a symmetric rim thereon to prevent the propagation of induced vibratory responses. The rim may have one or more sloping surfaces to prevent the re-attachment of boundary layer flow.
    Type: Grant
    Filed: May 1, 2015
    Date of Patent: September 17, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Loc Quang Duong, Xiaolan Hu, Nagamany Thayalakhandan, Benjamin E. Fishler
  • Patent number: 10287897
    Abstract: A rotor blade assembly for a rotor of a gas turbine engine having an axis of rotation includes a shank portion formed from a ceramic matrix composite (CMC) material. The rotor blade assembly also includes a platform portion formed from a substantially similar CMC material as that of the shank portion. The platform portion is coupled to the shank portion. The platform portion and the shank portion cooperate to at least partially define two opposing side portions of the rotor blade assembly. The opposing side portions are angularly separated with respect to the axis of rotation. The rotor blade assembly further includes a damper retention apparatus. The damper retention apparatus is coupled to the shank portion. The damper retention apparatus includes at least one angled bracket apparatus extending toward a circumferentially adjacent rotor blade assembly.
    Type: Grant
    Filed: September 8, 2011
    Date of Patent: May 14, 2019
    Assignee: General Electric Company
    Inventors: Anthony Reid Paige, II, Michael James Verrilli, Joshua Brian Jamison, Mark Eugene Noe, Paul Izon, Mark Willard Marusko
  • Patent number: 10150201
    Abstract: The present invention relates to the field of grinding machines. In one of its embodiments, this disclosure presents a grinding machine casing (30) for a grinding machine (100). The grinding machine casing (30) comprises a first casing part (10), which is mounted to a second casing part (20). The first casing part (10) is provided with a set of brackets. Each bracket of a set of brackets comprises a hole which is adapted to receive a cylindrical end of a support bar (60) such that the support bar (60) can be releasably connected to the first casing part (10). Still further, one bracket in each set of brackets comprises a hole, the cross-section of which is non-circular.
    Type: Grant
    Filed: February 20, 2015
    Date of Patent: December 11, 2018
    Assignee: Tormek AB
    Inventor: Håkan Persson
  • Patent number: 10151204
    Abstract: An airfoil includes an airfoil body that has a leading edge and a trailing edge and a first sidewall and a second sidewall that is spaced apart from the first sidewall. The first sidewall and the second sidewall join the leading edge and the trailing edge between a radially outer end and a radially inner end. The first sidewall and the second sidewall at least partially define a cavity extending radially in the airfoil body. A damper member has a free radially inner end in the cavity and a free radially outer end in the cavity. The damper member is free-floating in the cavity.
    Type: Grant
    Filed: February 12, 2016
    Date of Patent: December 11, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: David P. Houston, Tracy A. Propheter-Hinckley, Benjamin T. Fisk, Anita L. Tracy
  • Patent number: 10087763
    Abstract: A rotor comprises a disk having a rim. The rim has an axial face facing one of a forward or rearward direction. The rim defines a circumferential groove. A damper engages with the rim at both the axial face and the circumferential groove. The disk includes a rotor hub having a hub inner surface facing a longitudinal axis about which the rotor hub rotates. The rim is spaced radially outwardly relative to the hub inner surface. The axial face extends radially inwardly from the rim to the hub inner surface. The circumferential groove is formed within the hub inner surface. The damper comprises a split ring damper with a first leg mounted within the circumferential groove and a second leg that extends from the first leg, surrounds a radial lip of the hub inner surface, and extends radially outwardly to contact the axial face. An integrally bladed rotor is also disclosed.
    Type: Grant
    Filed: August 31, 2015
    Date of Patent: October 2, 2018
    Assignee: United Technologies Corporation
    Inventors: Yehia M. El-Aini, Gary A. Davis
  • Patent number: 10001016
    Abstract: A turbomachine blade having a main body (10) that includes a plane, first attachment surface (100) having a first rim contour (110), a cover (20; 21, 22) that has a plane, second attachment surface (200) having a second rim contour (210) that is welded to the first attachment surface, and a tuning body configuration having at least one tuning body (30; 31-33) for contacting an inner wall (220) of the cover by impact therewith, a gap (s) being formed between the first and the second rim contour.
    Type: Grant
    Filed: July 9, 2015
    Date of Patent: June 19, 2018
    Assignee: MTU Aero Engines AG
    Inventors: Frank Stiehler, Andreas Hartung
  • Patent number: 9982559
    Abstract: The present invention relates to a blade or vane for a turbomachine, having at least one impulse element housing with a first impact cavity, in which an impulse element is arranged with play of movement, wherein the impulse element housing has at least one second impact cavity, which is in alignment with the first impact cavity in a first matrix direction and in which an impulse element is arranged with play of movement, and has at least one third impact cavity, which is in alignment with the first impact cavity in a second matrix direction crosswise to the first matrix direction and in which an impulse element is arranged with play of movement.
    Type: Grant
    Filed: November 17, 2015
    Date of Patent: May 29, 2018
    Assignee: MTU AERO ENGINES AG
    Inventors: Andreas Hartung, Hermann Klingels, Patrick Wackers, Manfred Feldmann, Frank Stiehler, Markus Schlemmer
  • Patent number: 9604722
    Abstract: A rotorcraft may include an airframe and a rotor connected to the airframe. The rotor may include a hub and a rotor blade connected to the hub to extend radially away therefrom. The rotor blade may include biasing fibers, oriented to increase the twist of the rotor blade in response to an increase in the speed of rotation of the rotor corresponding to a mission, task, or maneuver.
    Type: Grant
    Filed: January 22, 2015
    Date of Patent: March 28, 2017
    Assignee: Groen Aeronautics Corporation
    Inventor: David L. Groen
  • Patent number: 9458836
    Abstract: A wind turbine comprises a wind-driven rotor for converting wind energy to a mechanical driving force, a power converter for converting the driving force to exploitable power, and a drive train for rotatably transmitting the driving force from the wind-driven rotor to the power converter. The drive train includes: at least one rotatable driving element configured to provide at least one torsional resonance frequency in the drive train; a first detuner having at least one first mass element with a first mass inertia and at least one first elastic element with first elastic properties; and a second detuner having at least one second mass element with a second mass inertia and at least one second elastic element with second elastic properties. The first and second mass elements and first and second elastic elements are arranged to rotate during operation of the wind turbine. The torsional resonance frequency is influenced by the first and second mass inertias and the first and second first elastic properties.
    Type: Grant
    Filed: July 1, 2011
    Date of Patent: October 4, 2016
    Assignee: VESTAS WIND SYSTEMS A/S
    Inventors: Steffen Muraszewski, Jørgen Jakobsen
  • Patent number: 9404373
    Abstract: A turbine-blade retaining structure in which deformation of end portions of locking pieces exposed through an insertion window portion in the axial direction is prevented, and the occurrence of a crack in a welded portion is prevented. At least one of the end portions of adjacent locking pieces exposed through the insertion window portion is provided with a thick-plate portion that expands in the disc-thickness direction so as to be inside the insertion window portion.
    Type: Grant
    Filed: January 28, 2013
    Date of Patent: August 2, 2016
    Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.
    Inventors: Keita Kimura, Yuki Enomoto, Tatsuya Furukawa
  • Patent number: 9371733
    Abstract: In a moving blade system for a turbomachine, in particular a gas turbine, having at least one moving blade (1), the moving blade system having at least one cavity (3) in which at least one tuning mass (2) is movably situated, the tuning mass and/or the cavity is/are adapted in such a way that the tuning mass rests against an inner wall (3.1) of the cavity in a predefined first operating state of the turbomachine and at least temporarily moves away from the inner wall in a second predefined operating state of the turbomachine.
    Type: Grant
    Filed: November 5, 2011
    Date of Patent: June 21, 2016
    Assignee: MTU Aero Engines GmbH
    Inventor: Andreas Hartung
  • Patent number: 9297258
    Abstract: A balance weight for a turbine rotor includes: a block-like centerbody; a pair of resilient spring arms extending laterally from opposite sides of the centerbody, the centerbody and the spring arms collectively defining an arcuate shape; at least one locating structure extending from a radially outer surface of the balance weight; and a limit tab extending radially inward from a distal end of each of the spring arms.
    Type: Grant
    Filed: April 20, 2012
    Date of Patent: March 29, 2016
    Assignee: General Electric Company
    Inventors: Nathan Tyler Woods, Aaron Todd Williams, Robert Patrick Tameo, Michael Thomas, Charles Eric Lavender
  • Patent number: 9285013
    Abstract: A vehicle wheel is provided with a plurality of tube's distributed at various radial angles from the center and oriented generally transversely of the central plane of the wheel and generally parallel to the wheel's axis of rotation. The azimuthal and longitudinal imbalance of a mounted tire including the wheel is determined. To balance the mounted tire both azimuthally and longitudinally, one or more weights are inserted into one or more tubes disposed on the wheel at appropriate azimuthal locations. The weights are placed longitudinally of the tubes in the plane of central mass of the mounted tire, and are secured in that position within the tube by any of a variety of means such as thread locking fluid, friction, or plugs.
    Type: Grant
    Filed: July 12, 2012
    Date of Patent: March 15, 2016
    Inventor: Jeff Swain
  • Patent number: 9181806
    Abstract: An airfoil includes an airfoil body that defines a longitudinal axis. The airfoil body includes a leading edge and a trailing edge and a first sidewall and a second sidewall that is spaced apart from the first sidewall. The first sidewall and the second sidewall join the leading edge and the trailing edge and at least partially define at least one longitudinally elongated cavity in the airfoil body. A plurality of loose particles is enclosed in the at least one longitudinally elongated cavity.
    Type: Grant
    Filed: April 24, 2012
    Date of Patent: November 10, 2015
    Assignee: United Technologies Corporation
    Inventors: Tracy A. Propheter-Hinckley, Gregory M. Dolansky, Benjamin T. Fisk, Robert J. Treen
  • Patent number: 9074479
    Abstract: A damping system for damping vibrations of a rotor blade of a rotor of a turbomachine is disclosed. A damping element is guided on a support such that the damping element is radially outwardly movable during a rotation of the rotor and is contactable with a lower platform area of a rotor blade. A circumferential contact surface is formed by an elevation on the lower platform area, where the circumferential contact surface is a limit stop for a movement of the damping element.
    Type: Grant
    Filed: April 15, 2011
    Date of Patent: July 7, 2015
    Assignee: MTU Aero Engines GmbH
    Inventors: Hans Peter Borufka, Andreas Hartung, Patrick Prokopczuk, Frank Stiehler
  • Publication number: 20150132131
    Abstract: A balancing apparatus for a rotary element is provided and includes a central hub portion and radial elements extending outwardly from the central hub portion. The balancing apparatus includes a conduit extending along the radial elements via the central hub portion, a mass movable within the conduit between the radial elements via the central hub portion and a mass balancing system which directs a movement of the mass within the conduit into and out of the central hub portion and along the radial elements.
    Type: Application
    Filed: November 8, 2013
    Publication date: May 14, 2015
    Applicant: Sikorsky Aircraft Corporation
    Inventors: William A. Welsh, Joseph John Andrews
  • Publication number: 20150132132
    Abstract: A balancing apparatus for a rotary element is provided and includes a central hub portion and radial elements extending outwardly from the central hub portion. The balancing apparatus includes a conduit extending along the radial elements via the central hub portion, a mass movable within the conduit between the radial elements via the central hub portion and a mass balancing system which directs a movement of the mass within the conduit into and out of the central hub portion and along the radial elements.
    Type: Application
    Filed: October 13, 2014
    Publication date: May 14, 2015
    Inventor: William A. Welsh
  • Publication number: 20150093245
    Abstract: A method for controlling helicopter ground resonance and air resonance motions as well as centrifugal force switching dampers are disclosed. A helicopter lead-lag damper (30) has a first ground resonance motion damping rate stage (FDR) and a second air resonance motion damping rate stage (SDR). The damper (30) includes a centrifugal force switch (52). The damper (30) is oriented relative to the rotary wing rotation axis (26) and helicopter blade (24). An in-flight rotation rate of the centrifugal force switching damper (30) actuates the centrifugal force switch (52) with the damper switching from the first ground resonance motion damping rate stage (FDR) to the second air resonance motion damping rate stage (SDR).
    Type: Application
    Filed: April 5, 2013
    Publication date: April 2, 2015
    Inventors: Zachary Fuhrer, Mark Jolly, Conor M. Marr
  • Patent number: 8961139
    Abstract: An aircraft system/method for propeller balancing.
    Type: Grant
    Filed: October 14, 2010
    Date of Patent: February 24, 2015
    Assignee: LORD Corporation
    Inventors: Askari Badre-Alam, David Boswell, Donald Morris, Wayne Winzenz
  • Patent number: 8961140
    Abstract: An aircraft system and method with a first counterweight rotating balancing rotor mass concentration, and a second counterweight rotating balancing rotor mass concentration to balance a first aircraft propeller. The system includes an inboard electromagnetic coil driver with a first inboard electromagnetic coil, and a second inboard electromagnetic coil, the inboard electromagnetic coil driver and the first counterweight balancing rotor and the second counterweight balancing rotor centered around the aircraft propeller shaft rotating machine member. The system/method utilizes a first control system controller to control the coils and position the mass concentrations to balance the first aircraft propeller. The system/method includes a third counterweight rotating balancing rotor mass concentration, and a fourth counterweight rotating balancing rotor mass concentration to balance a second aircraft propeller which positioned and controlled by a second control system controller.
    Type: Grant
    Filed: October 14, 2011
    Date of Patent: February 24, 2015
    Assignee: LORD Corporation
    Inventors: Askari Badre-Alam, David Boswell, Donald Morris, Wayne Lee Winzenz
  • Patent number: 8955409
    Abstract: A rotating assembly includes a shaft having a driven end and a driving end. At least one rotating member coupled to the driven end. A support member is operatively connected to the at least one rotating member. A dynamic balancing system is operatively coupled to the support member. The dynamic balancing system includes a first balancing weight rotatably mounted to the support member. The first balancing weight is operatively connected to a first motor. A second balancing weight is rotatably mounted to the support member. The second balancing weight is operatively connected to a second motor. A controller is operatively connected to the first and second motors. The controller is configured and disposed to signal each of the first and second motors to rotate and to establish a desired position of the first balancing weight and the second balancing weight relative to at least one rotating member.
    Type: Grant
    Filed: October 12, 2012
    Date of Patent: February 17, 2015
    Assignee: Hamilton Sundstrand Corporation
    Inventor: Paul A. Carvalho
  • Patent number: 8920125
    Abstract: A vibration suppressor system includes an annular electric motor system which independently controls rotation of at least two masses about the axis of rotation to reduce in-plane vibration of the rotating system. A method of reducing vibrations in a rotary-wing aircraft includes independently controlling a relative angular position of a multiple of independently rotatable masses to reduce vibrations of a main rotor system.
    Type: Grant
    Filed: February 22, 2013
    Date of Patent: December 30, 2014
    Assignee: Sikorsky Aircraft Corporation
    Inventor: William A. Welsh
  • Patent number: 8882464
    Abstract: An aircraft propeller taper bore insert apparatus includes a tapered outer surface, the outer surface dimensioned and configured to fit within and be of substantially a same size and shape as an aircraft propeller taper bore or an aircraft propeller balancing tube, and an inner surface, the inner surface defining an inner cavity configured to receive a balancing medium, the inner surface comprising a plurality of retention formations arranged thereon, and the plurality of retention formations being configured to support the balancing medium.
    Type: Grant
    Filed: August 12, 2011
    Date of Patent: November 11, 2014
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Blair A. Smith, David J. Grulke
  • Publication number: 20140286772
    Abstract: A vibration attenuator for an aircraft has at least one weight mounted in a rotating system of a rotor hub of the aircraft, each weight being rotatable about an axis of rotation of the hub relative to the hub and to each other weight. Drive means are provided for rotating each weight about the axis of rotation at a selected speed for creating oscillatory shear forces that oppose and attenuate rotor-induced vibrations having a selected frequency. A vertically oriented vibration attenuator is configured to oppose and attenuate vertical rotor induced oscillatory forces that would otherwise travel vertical down the rotor mast and into the airframe.
    Type: Application
    Filed: July 2, 2013
    Publication date: September 25, 2014
    Applicant: Textron Innovations Inc.
    Inventors: David A. Popelka, Frank B. Stamps
  • Publication number: 20140169961
    Abstract: A propeller rotor has a hub mounting a plurality of blades and a drive shaft for driving the hub and the blades about a central axis. A motor to change its position is operably connected to drive at least one counterweight. A sensor senses vibration on the propeller rotor and communicates with a controller. The controller controls the motor to change a position of the counterweight in response to a sensed imbalance. A method of operating a propeller rotor is also disclosed.
    Type: Application
    Filed: December 13, 2012
    Publication date: June 19, 2014
    Applicant: HAMILTON SUNDSTRAND CORPORATION
    Inventors: Mark A. Plickys, Paul A. Carvalho
  • Publication number: 20140086750
    Abstract: An enclosure for carrying an adjustable payload. The enclosure is beneficially used on a rotorcraft blade or other similar structure. The enclosure has a first element having a first flange and an upper element. The first element has an upper surface which has a first angle with respect to a lower surface of the first flange in a direction extending from an inboard direction to an outboard direction. The upper element has a lower surface which has a second angle with respect to an upper surface of said upper element in a direction extending from an inboard direction to an outboard direction, the lower surface being in contact with the upper surface of said first element, the second angle being in a direction which is opposite to the direction of said first angle. The first element and the upper element define a cavity for holding a payload.
    Type: Application
    Filed: September 25, 2012
    Publication date: March 27, 2014
    Applicant: THE BOEING COMPANY
    Inventors: Matthew Howard Cawthorne, Christopher James Cline, Dinesh Panneerselvam, Frank Joseph Gill, III, Russell Eddy Fay
  • Patent number: 8672625
    Abstract: A vibration-resistant wind turbine and process for operation is provided. The wind turbine has a rotor with at least two blades, each of which includes an inclinometer arrangement with at least two axes, and an evaluating unit. The evaluating unit determines the bending and/or twisting of the blade relative to the longitudinal axis of the blade on the basis of signals from the inclinometer arrangement for each blade during operation. Each rotor blade further has at least one liquid tank which is capable of receiving or transferring liquid from or to a liquid reservoir via a transfer mechanism in response to the determined bending and/or twisting of the rotor blades to reduce vibration caused by imbalances, thereby extending the service life of the wind turbine.
    Type: Grant
    Filed: February 16, 2010
    Date of Patent: March 18, 2014
    Assignee: Prüftechnik Dieter Busch AG
    Inventors: Edwin Becker, Marcel Kenzler, Johann Loesl
  • Patent number: 8668457
    Abstract: A trim balance for a gas turbine engine having a hollow rotatable rotor shaft includes an elongate support rod adapted for longitudinal accommodation within and mounting on an interior surface of the rotor shaft and one or more apertured balance weights supported on the support rod which extends through the weight apertures and a weight retainer for retaining the weights on the support rod.
    Type: Grant
    Filed: October 29, 2010
    Date of Patent: March 11, 2014
    Assignee: United Technologies Corporation
    Inventor: Christopher M. Juh
  • Patent number: 8632308
    Abstract: Rotary wing system with a rotating blade rotating about a rotation axis. The system includes a fluid damper with a damper fluid for controlling a troublesome motion. The fluid damper has an inboard end and an outboard end, the damper inboard end attached to a first rotary wing system inboard member proximate the rotation axis and the outboard end attached to a second rotary wing system outboard member distal from the rotation axis. The fluid damper contains a damper fluid volume in at least a first working chamber which is worked by a relative motion between said first rotary wing system inboard member and said second rotary wing system outboard member to control the troublesome motion.
    Type: Grant
    Filed: November 25, 2009
    Date of Patent: January 21, 2014
    Assignee: Lord Corporation
    Inventor: Donald D. Russell
  • Patent number: 8631578
    Abstract: A balancing weight clip with a mass adapted to balance a rotor assembly of a gas turbine engine, includes a weight portion, a first flange engaging portion and a second flange engaging portion extending from the weight portion, each being engageable with a sidewall of at least one recess located on an edge of a flange of a disc of the rotor assembly. Each flange engaging portion is provided with a hook engageable with a mating groove provided on a face of the flange. At least one of the first and second flange engaging portions is resiliently biased so that the first and second flange engaging portions are elastically moveable away from one another to removably secure the balancing weight clip to the flange and engage each hook with the mating groove.
    Type: Grant
    Filed: October 1, 2009
    Date of Patent: January 21, 2014
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: David F. Glasspoole, Francois Caron
  • Patent number: 8579589
    Abstract: The invention provides a mechanism for attenuating torque pulsations between an engine (2) and a rotor (1) of a rotorcraft. Torsion means (5) are interposed between the driving and driven shafts and comprise a torsion shaft (6) axially engaged with the drive shaft (3) and the driven shaft (4) an inlet shaft (9) and an outlet shaft (10) respectively engaged with the drive and driven shafts (3, 4) a lever system (7) that extends radially relative to the torsion shaft (6) and that has the inlet and outlet shafts (9, 10) hinged thereto via points (11, 12) that are spaced apart; and a mass (8) carried by said lever arm (7) at its free end (13) radially farthest away from the axis along which the torsion shaft (6) extends.
    Type: Grant
    Filed: October 4, 2010
    Date of Patent: November 12, 2013
    Assignee: Eurocopter
    Inventors: Thomas Manfredotti, Jerome Chemin
  • Publication number: 20130294913
    Abstract: A turbine blade is provided comprising: a root; an airfoil comprising an external wall extending radially from the root and having a radially outermost portion; and a damping structure. The external wall may comprise first and second side walls joined together to define an inner cavity of the airfoil. The damping structure may be positioned within the airfoil inner cavity and coupled to the airfoil so as to define a tuned mass damper.
    Type: Application
    Filed: May 4, 2012
    Publication date: November 7, 2013
    Inventors: CHRISTIAN X. CAMPBELL, Stephen J. Messmann
  • Patent number: 8573935
    Abstract: A rotor for a helicopter, having: a hub rotating about an axis and in turn having a number of blades; and an at least partly hollow drive shaft connectable to a drive of the helicopter and connected functionally to the hub to rotate the hub about the axis; the rotor also having vibration damping means in turn having a mass, and an elastically deformable member connected to the mass and supported by the shaft; the member extending at least partly inside the shaft, and being elongated parallel to the axis; and the mass vibrating, in use, at such a frequency as to oppose transmission to the shaft of the vibration produced by rotation of the hub and blades.
    Type: Grant
    Filed: June 19, 2008
    Date of Patent: November 5, 2013
    Assignee: Agusta S.p.A.
    Inventor: Santino Pancotti