Vibration Damping Features Patents (Class 416/500)
  • Patent number: 9840916
    Abstract: A blade (1) for a turbomachine, including a turbine blade (1.1) which has a channel (1.5), an impact chamber (2) having a constricted cross section being situated in the channel for the purpose of accommodating a single impulse body (3) is provided.
    Type: Grant
    Filed: May 21, 2014
    Date of Patent: December 12, 2017
    Assignee: MTU Aero Engines AG
    Inventors: Frank Stiehler, Andreas Hartung
  • Patent number: 9588007
    Abstract: An online real time steam or gas turbine engine rotor balancing system is incorporated in a rotor balance plane. A selectively displaceable balancing weight is coupled to the rotor and is selectively displaced by a motor that is coupled to the balancing weight. The motor selectively displaces the balancing weight along a displacement path that is in the balance plane. A turbine engine rotor vibration monitoring system monitors rotor vibration in real-time. A control system is coupled to rotor vibration monitoring system and the motor, for determining in real time a desired balance weight displacement position to counteract the monitored rotor vibration. The controller selectively causes the motor to displace the balancing weight to the desired displacement position. The motor power source is an inductive power source or a permanent magnet generator.
    Type: Grant
    Filed: June 12, 2014
    Date of Patent: March 7, 2017
    Assignee: SIEMENS ENERGY, INC.
    Inventors: Edward David Thompson, David R. Tiffany, Benjamin E. Bassford, IV
  • Patent number: 9151165
    Abstract: A damper body extends between an axial first end, an opposing axial second end, a first lateral side, and an opposing second lateral side. A first pair of lugs are disposed at the first axial end and a second pair of lugs are disposed at the second axial end. In the first lug pair, a lug has an axially outermost foot which extends laterally beyond a lateral wall. The second lug pair has a lug with an axial outermost point with a foot extending laterally beyond a lateral wall. The foot on the first axial end and the foot on the second axial end are on opposed lateral sides.
    Type: Grant
    Filed: October 22, 2012
    Date of Patent: October 6, 2015
    Assignee: United Technologies Corporation
    Inventors: Brandon S. Donnell, Yafet Girma, Gina C. O'Dell
  • Patent number: 8985956
    Abstract: The present application provides a compressive stress system for a gas turbine engine. The compressive stress system may include a first bucket attached to a rotor, a second bucket attached to the rotor, the first and the second buckets defining a shank pocket therebetween, and a compressive stress spring positioned within the shank pocket.
    Type: Grant
    Filed: September 19, 2011
    Date of Patent: March 24, 2015
    Assignee: General Electric Company
    Inventor: Nicholas Alvin Hogberg
  • 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: 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: 8951013
    Abstract: A device for damping of vibratory energy in the blades of rotor assemblies during operation where the blades have a shroud attached thereto with at least one sealing rail extending radially outward from the shroud to an outer diameter surface. A damper element is attached to the turbine blade sealing rail extending radially inward from the rail outer diameter surface along rail sides to maintain the damper element out of the flow of gas and positioned at a radial location on the blade for damping.
    Type: Grant
    Filed: October 24, 2011
    Date of Patent: February 10, 2015
    Assignee: United Technologies Corporation
    Inventors: Jeff H. Miller, Steven P. Grota
  • Patent number: 8951014
    Abstract: A gas turbine engine blade comprises a dovetail, a shank extending from the dovetail, an airfoil, and a platform between the shank and the airfoil. The platform comprises a side wall extending between an upstream side and a downstream side of the platform. A first pin channel extends from the upstream side of the sidewall and a second pin channel, co-axial with the first pin channel, extends from the downstream side of the sidewall. The first channel includes a radial notch at the upstream longitudinal end of the first pin channel.
    Type: Grant
    Filed: March 15, 2011
    Date of Patent: February 10, 2015
    Assignee: United Technologies Corporation
    Inventors: Christopher Corcoran, Seth J. Thomen
  • Patent number: 8944764
    Abstract: A main rotor arrangement for an UAV-helicopter. A rotor mast defines a vertical axis of rotation. A hub is for attachment of rotor blades. The hub is mounted to the rotor mast in a tiltable way so as to reduce loads acting on the rotor blades during operation of the UAV-helicopter. A damping assembly is configured to damp the tilting of the hub.
    Type: Grant
    Filed: June 10, 2009
    Date of Patent: February 3, 2015
    Assignee: SAAB AB
    Inventors: Per-Erik Cardell, Kjell Stenbom
  • Patent number: 8932019
    Abstract: A fan wheel (1) is designed as a radial or diagonal fan, comprising a top plate (2) with an inlet port (4), a base plate (6) and a plurality of fan blades (8) distributed around the inlet port (4) and around an axis of rotation (Z). Blade ducts extend (10) respectively between the adjacent fan blades (8). The blade ducts lead radially or diagonally outward from the area of the inlet port (4) and form blow-out ports in the outer region. The blade ducts (10) are designed, with respect to their effective flow cross-section, as large enough that during operation, a turbulent flow with a Reynolds number markedly greater than 2300 is achieved. The top plate (2) or the base plate (6) or both feature a rotationally asymmetrical geometry with a continuous profile, at least in angular sections encompassing the fan blades (8).
    Type: Grant
    Filed: February 24, 2011
    Date of Patent: January 13, 2015
    Assignee: EMB-PAPST Mulfingen GmbH & Co. KG
    Inventors: Katrin Bohl, Marc Schneider, Jürgen Schöne
  • 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: 8920893
    Abstract: An aerofoil has first and second panels spaced apart from each other to provide a cavity, the cavity containing a damping material, the first panel has at least one protrusion extending therefrom within the cavity towards the second panel, the protrusion having a proximal end and a distal end, wherein the proximal end is secured to the first panel and the distal end is slidably mounted to the second panel.
    Type: Grant
    Filed: December 14, 2009
    Date of Patent: December 30, 2014
    Assignee: Rolls-Royce PLC
    Inventor: Oliver M. Strother
  • Patent number: 8915718
    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 faced 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 a cavity in the airfoil body. A damper member is enclosed in the cavity. The damper member includes a first end and a second end. The first end is connected in a first joint to the first sidewall at a first longitudinal location and the second end is connected in a second joint to the second sidewall at a second, different longitudinal location.
    Type: Grant
    Filed: April 24, 2012
    Date of Patent: December 23, 2014
    Assignee: United Technologies Corporation
    Inventors: Gregory M. Dolansky, Tracy A. Propheter-Hinckley, Benjamin T. Fisk
  • Patent number: 8911210
    Abstract: A vibration-damping shim configured to be interposed between a platform of a fan blade and a fan disk, including a radially external surface fitted with plates in contact with the fan blade platform, and a radially internal surface formed by an upstream surface, configured to be facing the disk, and a downstream surface separated from the upstream surface by a break in alignment. The upstream surface includes a zone protruding radially towards the interior, initiated at some distance from its upstream end.
    Type: Grant
    Filed: August 9, 2010
    Date of Patent: December 16, 2014
    Assignee: SNECMA
    Inventors: Laurent Bilz, Fabrice Marois, Patrick Jean-Louis Reghezza, Julien Tran
  • Patent number: 8905715
    Abstract: A bucket for a turbomachine rotor wheel includes an airfoil portion, a shank portion and a dovetail mounting portion, the shank portion including opposite sides, one of the sides formed with a substantially axially-oriented groove extending between forward and aft ends of the shank portion. The other one of the opposite sides is formed with at least one substantially radially-oriented groove. The substantially axially-oriented groove is adapted to receive an elongated damper pin, and the at least one substantially radially-oriented groove is adapted to receive an elongated radial seal pin.
    Type: Grant
    Filed: March 17, 2011
    Date of Patent: December 9, 2014
    Assignee: General Electric Company
    Inventors: Bradley Boyer, Matthew D. Collier
  • Patent number: 8899928
    Abstract: A device (10) for reducing the vibration of a rotorcraft main rotor (1) provided with a hub (2) and a plurality of blades, said device having a support (20) together with at least one weight element (30). Said weight element (30) is fastened to said support (20) by connection means (40), and said weight element (30) is connected to said connection means (40) by guide means (50) for guiding said weight element (30) in movement in circular translation in a filter plane (P1) that is movable perpendicularly to an elevation axis (AX) of said device (10), said connection means (40) including resilient return means (41) serving to allow said filter plane (P1) to move in elevation while keeping the filter plane (P1) perpendicular to said elevation axis (AX) under the effect of said vibration.
    Type: Grant
    Filed: April 19, 2011
    Date of Patent: December 2, 2014
    Assignee: Airbus Helicopters
    Inventors: Vincent Girard, Arnaud Varin D'Ainvelle
  • Patent number: 8894353
    Abstract: A turbine blade system including a first turbine blade and a second turbine blade being arranged adjacent to each other shall be suited to allow a particularly secure and reliable operation of a turbine. To this end, the turbine blades are in contact in a first surface area and separated from each other in a second surface area, wherein the first turbine blade includes a pocket containing a damping piece in the second surface area.
    Type: Grant
    Filed: January 12, 2010
    Date of Patent: November 25, 2014
    Assignee: Siemens Aktiengesellschaft
    Inventors: James McCracken, Christoph Hermann Richter
  • Patent number: 8882469
    Abstract: The present invention provides a structural element, in particular for an aircraft or spacecraft, comprising a core, the material density of which varies, at least in portions, in order to optimize the natural vibration behavior of the structural element. The present invention further provides a method for producing a structural element, in particular for an aircraft or spacecraft, comprising the following steps: providing a structural element which has a core; determining the natural vibration behavior of the structural element; and varying the material density of the core of the structural element, at least in portions, in such a way that the natural vibration behavior of the structural element is optimized. The present invention provides still further an aircraft or spacecraft and a rotor blade, in particular for a wind turbine, comprising such a structural element.
    Type: Grant
    Filed: July 25, 2011
    Date of Patent: November 11, 2014
    Assignee: Airbus Operations GmbH
    Inventors: Ichwan Zuardy, Karim Grase, Wolfgang Voege, Axel Herrmann
  • Patent number: 8876479
    Abstract: A damper pin for coupling platforms of adjacent turbine blades includes a first flat longitudinal end region, a second flat longitudinal end region and a reduced cross sectional area. The reduced cross sectional area is separated from the first flat longitudinal end region by a first main body region and the reduced cross sectional area is separated from the second flat longitudinal end region by a second main body region. The cross sectional area of the reduced cross sectional area is less than the cross sectional area of each of the first and second main body regions.
    Type: Grant
    Filed: March 15, 2011
    Date of Patent: November 4, 2014
    Assignee: United Technologies Corporation
    Inventors: Seth J. Thomen, Christopher Corcoran
  • Patent number: 8876472
    Abstract: A turbine wheel including: a plurality of first and second blades, at least one of the first blades being adjacent to at least one of the second blades; a disk presenting an axis of rotation and a periphery having the blades mounted thereat, each of the blades including a head solid with a root engaged in a housing that opens to the periphery of the disk, each of the blades including a keying mechanism including a respective shelf arranged between the head and the root of the blade, the shelves of the first blades presenting an azimuth length different from the azimuth length of the shelves of the second blades; and a damper device arranged at least between the adjacent blades, the damper device being arranged between the shelves of the blades and the periphery of the disk.
    Type: Grant
    Filed: March 31, 2010
    Date of Patent: November 4, 2014
    Assignee: Turbomeca
    Inventors: Marc Dijoud, Jean-Philippe Ousty
  • Patent number: 8870547
    Abstract: The present invention provides a structural element, in particular for an aircraft and spacecraft, comprising a core, the rigidity of which varies at least in portions for optimising the aeroelastic characteristics of the structural element The present invention also provides a method for producing a structural element, in particular for an aircraft and spacecraft, which comprises the following steps: provision of a structural element comprising a core; determination of the aeroelastic behavior of the structural element; and variation, at least in portions, of the rigidity of the core of the structural element such that the aeroelastic behavior of the structural element is optimised. The present invention further provides an aircraft and spacecraft comprising a structural element of this type, and a rotor blade, in particular for a wind turbine, comprising a structural element of this type.
    Type: Grant
    Filed: August 12, 2011
    Date of Patent: October 28, 2014
    Assignee: Airbur Operations GmbH
    Inventors: Karim Grase, Ichwan Zuardy, Marianne Jacoba Reijerkerk
  • Patent number: 8851844
    Abstract: A stationary blade and a steam turbine capable of reducing self-excited vibrations with a simple configuration are provided. A stationary blade has a cavity, extending in a blade-width direction, formed therein and slits communicating between the cavity and the outside. A wave-shaped plate spring that is in sliding contact with at least one of a pressure-side member and a suction-side member is provided between the pressure-side member, which is a portion on the pressure side of the cavity, and the suction-side member, which is a portion on the suction side of the cavity. When the stationary blade is elastically deformed, the wave-shaped plate spring causes friction between itself and at least one of the pressure-side member and the suction-side member. This friction attenuates relative positional displacement between the pressure-side member and the suction-side member. Thus, self-excited vibrations occurring at the stationary blade can be reduced.
    Type: Grant
    Filed: October 24, 2008
    Date of Patent: October 7, 2014
    Assignee: Mitsubishi Heavy Industries, Ltd.
    Inventors: Hiroyuki Yamashita, Yasutomo Kaneko, Hiroharu Ooyama
  • 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: 8851851
    Abstract: Large diameter axial Super Low Noise flow fans and commercial air cooled apparatuses incorporating such fans are provided. The large diameter axial flow fan is mounted on the air cooled apparatus for generating an axial air flow in the air cooled apparatus for accomplishing the cooling. The fan has a diameter of at least four feet. The fan has plurality of blades. Each blade includes a leading edge opposite a trailing edge. The entire of the leading edge of each of the blades is linear and forward swept, and each blade includes a metallic outer surface.
    Type: Grant
    Filed: April 5, 2011
    Date of Patent: October 7, 2014
    Assignee: Moore Fans LLC
    Inventor: John D. Moore
  • Patent number: 8840361
    Abstract: A fan blade (10) for a turbofan aero engine comprises a blade body including a root (10c) for engagement with a rotor, and a tip, wherein the tip is provided with a winglet (14).
    Type: Grant
    Filed: September 2, 2011
    Date of Patent: September 23, 2014
    Assignee: Rolls-Royce PLC
    Inventor: Kristofer J. Bottome
  • Patent number: 8834099
    Abstract: A gas turbine engine comprises a fan and a turbine section having a first turbine rotor. The first turbine rotor drives a compressor rotor. A gear reduction effects a reduction in the speed of the fan relative to an input speed from a fan drive turbine rotor. The compressor rotor has a number of compressor blades in at least one of a plurality of rows of the compressor rotor. The blades operate at least some of the time at a rotational speed. The number of compressor blades in at least one row and the rotational speed are such that the following formula holds true for at least one row of the compressor rotor: (the number of blades×the rotational speed)/(60 seconds/minute)?5500 Hz; and the rotational speed being in revolutions per minute. A compressor module and a method of designing a gas turbine engine are also disclosed.
    Type: Grant
    Filed: January 21, 2014
    Date of Patent: September 16, 2014
    Assignee: United Technoloiies Corporation
    Inventors: David A. Topol, Bruce L. Morin
  • Patent number: 8821125
    Abstract: A turbine blade, airfoil configuration, and rotor stage are disclosed in which through the airfoil profile disclosed in Table 1, a modification in airfoil flutter and swirl are achieved. Through the airfoil configuration, the swirl and improved platform sealing configuration, result in the turbine blades having the airfoil profile with an increased performance output from the turbine.
    Type: Grant
    Filed: February 6, 2012
    Date of Patent: September 2, 2014
    Assignee: Alstom Technology Ltd.
    Inventors: Adam Lee Hart, Adam John Fredmonski, Douglas James Dietrich, Samer Abdel-Wahab, Stephen Wayne Fiebiger, Kuo-Ting Hsia, W. David Day, Richard Ramirez
  • Patent number: 8807925
    Abstract: A fan blade has a main body extending between a leading edge and a trailing edge. Channels are formed into the main body from at least one open side. A plurality of ribs extend across the main body intermediate the channels. The fan blade has a dovetail, and an airfoil extends radially outwardly from the dovetail. The ribs having a thickness defined as measured from said leading edge toward said trailing edge. The ribs have break-edges at ends of the thickness that extend away from an outer face of the rib.
    Type: Grant
    Filed: September 23, 2011
    Date of Patent: August 19, 2014
    Assignee: United Technologies Corporation
    Inventors: Christopher S. McKaveney, James R. Murdock
  • Patent number: 8807924
    Abstract: A fan blade has a main body extending between a leading edge and a trailing edge. Channels are formed into the main body from at least one open side. A plurality of ribs extend across the main body intermediate the channels. The fan blade has a dovetail, and an airfoil extending radially outwardly from the dovetail. The channels have a termination end adjacent a radially inner end of the ribs. The termination end is formed along a complex fillet with a first radius of curvature formed at the termination end, and a second radius of curvature merging into sides of the ribs. The second radius of curvature is greater than the first radius of curvature.
    Type: Grant
    Filed: September 23, 2011
    Date of Patent: August 19, 2014
    Assignee: United Technologies Corporation
    Inventors: Christopher S. McKaveney, James R. Murdock
  • Patent number: 8801367
    Abstract: A fan blade has a main body extending between a leading edge and a trailing edge. Channels are formed into the main body from an open side extending toward an opposed closed side. A plurality of ribs extending across the main body intermediate the channels, the fan blade has a dovetail, and an airfoil extending radially outwardly from said dovetail. A bottom surface of the channels is defined at the closed side of the channels. Sides of the channel merge into sides of the ribs, with a compound fillet at the bottom surface. A first radius of curvature is used along the bottom, and merging into at least a second radius of curvature at the sides. The first radius of curvature is larger than the second radius of curvature.
    Type: Grant
    Filed: September 23, 2011
    Date of Patent: August 12, 2014
    Assignee: United Technologies Corporation
    Inventors: Michael A. Weisse, Christopher S. McKaveney
  • 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
  • Patent number: 8790086
    Abstract: A turbine has blade assemblies disposed about a rotor. Each of the blade assemblies have an airfoil and a bucket. Pockets are defined at trailing and leading sides of the bucket, with damper pin slots at an ends thereof. The damper pin slot at the trailing side has a depth sufficient for fully receiving a damper pin. The damper pin slot at the trailing side of a first adjacent blade assembly is positioned relative to the damper pin slot at the leading side of a second adjacent blade assembly to allow the damper pin to move. At each side of the pocket at the trailing side is a seal pin slot with seal pins therein. The seal pin slots extend beyond a line that is aligned with an inner edge of the damper pin slot at the trailing side, wherein the seal pins overlap the damper pin.
    Type: Grant
    Filed: November 11, 2010
    Date of Patent: July 29, 2014
    Assignee: General Electric Company
    Inventors: Mark Steven Honkomp, Matthew Durham Collier, Jason Douglas Herzlinger
  • Patent number: 8784058
    Abstract: The invention relates to an engine fan device for a vehicle, characterized in that the engine fan device (10) has at least one or more receiving contours (24, 30, 50), in which one or more balancing elements (28) can be received, wherein at least one receiving contour (24) has at least two planes (26), and/or wherein at least two receiving contours (24) each have at least one plane (26), wherein both planes (26) are different from each other.
    Type: Grant
    Filed: July 8, 2009
    Date of Patent: July 22, 2014
    Assignee: Robert Bosch GmbH
    Inventors: Tobias Schneider, Markus Liedel, Thomas Helming, Heidrun Schied
  • Patent number: 8764398
    Abstract: A concentrated-mass device including a main oscillating mass held radially in a horizontal plane by main resilient means inside a casing suitable for being secured to the hub is provided. The device includes a secondary main oscillating mass suspended by secondary resilient means inside a recess in said main oscillating mass to oscillate along a vertical axis perpendicular to the horizontal plane, the secondary oscillating mass being constrained to move in translation together with the main oscillating mass in the horizontal plane.
    Type: Grant
    Filed: April 19, 2010
    Date of Patent: July 1, 2014
    Assignee: Airbus Helicopters
    Inventors: Vincent Girard, Stéphane Mazet
  • Patent number: 8763360
    Abstract: A fan blade comprises a main body extending between a leading edge and a trailing edge. Channels are formed into the main body, with a plurality of ribs extending intermediate the channels. The fan blade has a dovetail, and an airfoil extending radially outwardly from the dovetail. Material is deposited within the channels, with one type of material being selected to provide additional stiffness to the fan blade, and a second type of material being selected for having good damping characteristics. A method and gas turbine engine are is also disclosed.
    Type: Grant
    Filed: November 3, 2011
    Date of Patent: July 1, 2014
    Assignee: United Technologies Corporation
    Inventor: James R. Murdock
  • Patent number: 8721266
    Abstract: A cooling fan includes a frame and a rotor received in the frame. The rotor includes a hub, blades extending outwardly and radially from the hub, and a cover plate connected with the hub. The hub includes a top wall and a sidewall extending from a circumference of the top wall. The top wall of the hub defines a plurality of blind holes on an outer surface thereof, and the blind holes are shaded by the cover plate.
    Type: Grant
    Filed: December 31, 2010
    Date of Patent: May 13, 2014
    Assignee: Hon Hai Precision Industry Co., Ltd.
    Inventors: Yao-Ting Chang, Chao-Ke Wei
  • Patent number: 8714913
    Abstract: A gas turbine engine has a fan and a turbine having a fan drive turbine rotor. The fan drive turbine rotor drives a compressor rotor. A gear reduction effects a reduction in the speed of the fan relative to an input speed from the fan drive turbine rotor that drives the compressor rotor. The compressor rotor has a number of compressor blades in at least one of a plurality of rows of the compressor rotor. The blades operate at least some of the time at a rotational speed. The number of compressor blades in at least one row and the rotational speed are such that the following formula holds true for at least one row of the compressor rotor turbine: (number of blades×rotational speed)/60 s?5500 Hz, and the rotational speed is in revolutions per minute. A method of designing a gas turbine engine and a compressor module are also disclosed.
    Type: Grant
    Filed: September 3, 2013
    Date of Patent: May 6, 2014
    Assignee: United Technologies Corporation
    Inventors: David A. Topol, Bruce L. Morin
  • Patent number: 8701286
    Abstract: A method is provided of rotationally balancing a rotating part. A rotor hub or ring and a plurality of rotor blades for assembly onto the hub or ring are provided, each blade having an unfilled internal cavity. The respective masses and moment weights of the blades with filled internal cavities are then predicted. Next, the rotor blades are assembled onto the hub or ring to form the rotating part. The relative positions of the assembled blades are determined on the basis of their predicted masses and moment weights with filled internal cavities. The internal cavities of the assembled rotor blades are then filled.
    Type: Grant
    Filed: May 24, 2011
    Date of Patent: April 22, 2014
    Assignee: Rolls-Royce PLC
    Inventor: Oliver M. Strother
  • Patent number: 8696316
    Abstract: A compressor wheel (20) for an air boost device and a method for designing the wheel are provided. The compressor wheel (20) comprises a hub (24) and a plurality of blades (22, 23) connected to the hub (24). The plurality of blades (22, 23) have a ratio (f/N) of natural frequency to maximum rotational speed of less than 4.0 and are made from a titanium alloy. The plurality of blades (22, 23) can comprise a plurality of full blades (22) and a plurality of splitter blades (23).
    Type: Grant
    Filed: November 14, 2008
    Date of Patent: April 15, 2014
    Assignee: Borg Warner Inc.
    Inventors: David Decker, Stephen Roby
  • Patent number: 8672623
    Abstract: A stator vane assembly includes: inner and outer vane supports, and vanes extending radially between the supports. The supports have openings for receiving the ends of the vanes, and each vane is connected to the supports by a vane boot. Each vane boot has: a rim portion shaped to locate the boot within the corresponding opening in the vane support, the rim portion engaging with the inner surface defining the opening, an abutting portion for abutting against the vane support in the region surrounding the opening, and a vane pocket for accommodating the end of the vane. The vane pockets of the vane boots are shaped so as to position the vane with a predetermined stagger angle.
    Type: Grant
    Filed: March 9, 2010
    Date of Patent: March 18, 2014
    Assignee: Rolls-Royce PLC
    Inventor: Cedric B Harper
  • Patent number: 8672262
    Abstract: A vibration isolator includes an upper housing and a lower housing; an upper reservoir housing defining a upper fluid chamber; a lower reservoir housing defining a lower fluid chamber; a piston spindle resiliently coupled to the upper housing with an upper elastomer member, the piston spindle being resiliently coupled to the lower housing with a lower elastomer member; an elongated portion having a tuning passage; and a tuning fluid disposed there within. The vibration isolator cancels vibratory forces at an isolation frequency. The vibration isolator is utilized in a pylon system for mounting a transmission in an aircraft. The vibration isolator is located between a pylon structure and a roof structure. The isolator includes a spherical bearing assembly that is located near a waterline location of a rotational axis of a drive shaft.
    Type: Grant
    Filed: January 10, 2012
    Date of Patent: March 18, 2014
    Assignee: Textron Innovations Inc.
    Inventor: Maurice D. Griffin
  • Patent number: 8672626
    Abstract: A system for creating a seal between a damper and a platform of a turbine engine component includes a turbine engine component having an airfoil portion, a platform, and a fir tree for joining the turbine engine component to a rotor, a damper located in an area beneath the platform, a seal having a sealing surface which seats against an underside of the platform, which seal has a seal retention feature which bends into contact with an underside of the damper, and which seal with the seal retention feature has a center of gravity which allows the seal retention feature to bend up as result of rotational movement of the rotor. A method for creating the seal is also described.
    Type: Grant
    Filed: April 21, 2010
    Date of Patent: March 18, 2014
    Assignee: United Technologies Corporation
    Inventors: Lynn M. Boy, Tracy A. Propheter-Hinckley, Malcolm C. Staddon
  • Patent number: 8668458
    Abstract: A fan including a hub part, a blade part and a vibration-absorbing boss, all constituent elements of which are injection molded, thereby reducing production costs. The fan has a minimized contact area between the vibration-absorbing boss and the hub part to prevent the vibration-absorbing boss from being deformed by high-temperature heat during insert injection molding of the hub part and the blade part while assuring sufficient strength of the hub part.
    Type: Grant
    Filed: June 17, 2011
    Date of Patent: March 11, 2014
    Assignee: Samsung Electronics Co., Ltd.
    Inventors: Min Gi Cho, Jin Baek Kim, Seong Ho Kil, Young Jae Kim, Byung Ghun Kim
  • Patent number: 8668456
    Abstract: A turbomachine blade having features arranged to initiate bending of the leading edge towards the pressure surface upon impact of a foreign object on the leading edge. The features may be features weaker than the material of the leading edge located on the pressure surface side of a mid-thickness line. By causing the leading edge to bend towards the pressure surface on impact the volume of the foreign object, typically a bird, that passes over the suction surface is reduced.
    Type: Grant
    Filed: October 6, 2011
    Date of Patent: March 11, 2014
    Assignee: Rolls-Royce PLC
    Inventors: Nicholas M. Merriman, Simon Read
  • Patent number: 8657581
    Abstract: A blade comprises a lightweight core, a composite material disposed on the core, and a skin located on the composite material. The composite material comprises fibers incorporated into a thermoplastic resin matrix in the form of a prepreg sheet or wet layup. The rotor blade may also comprise a front edge member attached along at least a portion of a leading edge of the core, a rear edge member attached along at least a portion of a trailing edge of the core, and a skin located over the core, the front edge member, and the rear edge member. The rotor blade may also comprise a spar extending through the core along a longitudinal axis of the rotor blade, and a skin located over the core and the spar. The edge members and the spars may be fabricated from thermoplastic material.
    Type: Grant
    Filed: August 30, 2010
    Date of Patent: February 25, 2014
    Assignee: Gordon Holdings, Inc.
    Inventors: Edward Pilpel, Benjamin Pilpel
  • Patent number: 8651822
    Abstract: A wind turbine rotor blade including outer skin materials made of fiber-reinforced plastic, a crossbeam material, and a trailing edge sandwich material disposed closer to a trailing edge than a trailing edge end of the crossbeam material, wherein a reinforcing material is provided on an inner surface of the outer skin material on a front side located closer to the trailing edge than a trailing edge end of the trailing edge sandwich material.
    Type: Grant
    Filed: March 24, 2011
    Date of Patent: February 18, 2014
    Assignee: Mitsubishi Heavy Industries, Ltd.
    Inventors: Kouji Esaki, Shinichi Hori
  • 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: 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: 8632301
    Abstract: A gas turbine engine has a fan, a compressor section having a low pressure portion and a high pressure portion, a combustor section, and a turbine having a low pressure portion. The low pressure turbine portion drives the low pressure compressor portion and the fan. A gear reduction effects a reduction in the speed of the fan relative to a speed of the low pressure turbine and the low pressure compressor portion. At least one of the low pressure turbine portion and low pressure compressor portion has a number of blades in each of a plurality of rows. The blades operate at least some of the time at a rotational speed. The number of blades and the rotational speed are such that the following formula holds true for at least one of the blade rows of the at least one of the low pressure turbine portion and/or the low pressure compressor sections: (number of blades×rotational speed)/60?5500. The rotational speed is an approach speed in revolutions per minute.
    Type: Grant
    Filed: September 28, 2012
    Date of Patent: January 21, 2014
    Assignee: United Technologies Corporation
    Inventors: David A. Topol, Burce L. Morin