Integrally Shaped Or Blended Into Hub Patents (Class 416/234)
  • Patent number: 10578320
    Abstract: An axial fan includes: a cutout in a rear edge part of each of the plurality of blades, the rear edge part being opposite to a front edge part of the each of the plurality of blades in a rotational direction of the each of the plurality of blades, the cutout extending from the rear edge part toward the front edge part such that the cutout divides the rear edge part into an outer rear edge part and an inner rear edge part; a rib in a blade surface of the each of the plurality of blades, the rib extending from the hub toward an outer circumference of the each of the plurality of blades along the front edge part; and a first thickness-reduced part adjacent to an end of the rib, the end of the rib being closer to the outer circumference, the each of the plurality of blades being thinned in the first thickness-reduced part.
    Type: Grant
    Filed: May 30, 2017
    Date of Patent: March 3, 2020
    Assignee: FUJITSU GENERAL LIMITED
    Inventor: Hirotaka Sawada
  • Patent number: 10267338
    Abstract: An impeller includes a hub rotated about an up-down axis and inclined blades disposed circumferentially on a hub's outer circumferential surface. The outer circumferential surface includes a first surface including a portion axially overlapping the blade above its joined portion to the blade, a second surface including a portion axially overlapping the blade below the joined portion, and a connecting portion connecting a rotating-direction rear end of the first outer circumferential surface and a rotating-direction front end of the second outer circumferential surface. The connecting portion is arranged forward of a rotating-direction blade front edge. A distance from the axis to a first point, positioned at the rotating-direction rear end of the first outer circumferential surface, is not shorter than that from the axis to a second point, positioned at the rotating-direction front end of the second outer circumferential surface and at the same axial position as the first point.
    Type: Grant
    Filed: July 25, 2017
    Date of Patent: April 23, 2019
    Assignee: Nidec Corporation
    Inventors: Hidenobu Takeshita, Yasuyuki Kaji, Guiling Zhang
  • Patent number: 10202185
    Abstract: A fan section comprises a fan rotor having a plurality of blades and a spinner positioned forwardly of the fan rotor. The fan rotor is driven through a gear reduction. The spinner includes a spinner body having an outer surface with a forward end and a rearward end. A conical line extends between the forward end to the rear end. A first radius is measured from a centerline of the spinner at substantially 0.25 of a length of the spinner to the conical line. A second radius is also measured at substantially 0.25 of the length and extends outwardly to the outer surface of the spinner. A ratio of the second radius to the first radius is less than or equal to about 2.0. A gas turbine engine is also disclosed.
    Type: Grant
    Filed: May 12, 2015
    Date of Patent: February 12, 2019
    Assignee: United Technologies Corporation
    Inventor: Frederick M. Schwarz
  • Patent number: 9950388
    Abstract: There is proposed a method of producing an integrally bladed rotor, preferably a so-called “blisk” for a turbomachine, the method including the steps of: providing a rotor disc having a plurality of spaced-apart radial protrusions formed integrally around its perimeter; and forming a respective aerofoil-shaped blade extending radially generally outwardly from each of the protrusions via laser deposition. Each protrusion preferably extends radially outwardly from a circumferential body part of the rotor disc by a distance which is greater than the radially inward penetration of a heat-affected zone arising from the laser deposition used to form the respective blade.
    Type: Grant
    Filed: November 17, 2015
    Date of Patent: April 24, 2018
    Assignee: ROLLS-ROYCE plc
    Inventor: Nigel James David Chivers
  • Patent number: 9874221
    Abstract: A compressor apparatus includes: a rotor having: a disk mounted for rotation about a centerline axis, an outer periphery of the disk defining a flowpath surface; an array of airfoil-shaped axial-flow compressor blades extending radially outward from the flowpath surface, wherein the compressor blades each have a root, a tip, a leading edge, and a trailing edge, wherein the compressor blades have a chord dimension and are spaced apart by a circumferential spacing, the ratio of the chord to the circumferential spacing defining a blade solidity parameter; and an array of airfoil-shaped splitter blades alternating with the compressor blades, wherein the splitter blades each have a root, a tip, a leading edge, and a trailing edge; wherein at least one of a chord dimension of the splitter blades at the roots thereof and a span dimension of the splitter blades is less than the corresponding dimension of the compressor blades.
    Type: Grant
    Filed: December 29, 2014
    Date of Patent: January 23, 2018
    Assignee: General Electric Company
    Inventors: Anthony Louis DiPietro, Jr., Gregory John Kajfasz
  • Patent number: 9447789
    Abstract: A fan assembly including a housing, a supporting member, a driving device and a passive impeller. The supporting member is disposed in the housing, and the driving device is disposed on the supporting member. The passive impeller includes a first hub and a plurality of first passive blades encircling the first hub. The active impeller includes a second hub and a plurality of active blades encircling the second hub and actuated to rotate by the driving device. In an axial direction, the first hub is disposed between the driving device and the second hub, and through rotation of the active impeller, airflow is produced which actuates the passive impeller to rotate.
    Type: Grant
    Filed: May 25, 2012
    Date of Patent: September 20, 2016
    Assignee: DELTA ELECTRONICS, INC.
    Inventors: Shun-Chen Chang, Bo-Chun Chen
  • Patent number: 9327067
    Abstract: An impeller for a pump is disclosed herein. The impeller can include a hub having a fixed end and a free end. The impeller can also have a plurality of blades supported by the hub. Each blade can have a fixed end coupled to the hub and a free end. The impeller can have a stored configuration and a deployed configuration, the blades in the deployed configuration extending away from the hub, and the blades in the stored configuration being compressed against the hub.
    Type: Grant
    Filed: May 13, 2013
    Date of Patent: May 3, 2016
    Assignee: THORATEC CORPORATION
    Inventors: Zijing Zeng, Phyllis Yuen, Michael R. Butler
  • Patent number: 9279222
    Abstract: A snow thrower impeller includes a layer of material comprising blade support walls and blades extending from the blade support walls.
    Type: Grant
    Filed: February 13, 2012
    Date of Patent: March 8, 2016
    Assignee: Briggs & Stratton Corporation
    Inventors: Samuel J. Gerrits, Daniel L. Steinike, James W. Mast
  • Patent number: 9033674
    Abstract: Provided is a propeller fan including a hub having an oval shape in an axial direction, a plurality of wings that extend from the hub, and at least one reinforcement rib that extends from the hub and is formed closer to a leading edge of each of the plurality of wings. Through this configuration, the propeller fan has blowing efficiency and stiffness, and the weight and material cost of the propeller fan can be reduced.
    Type: Grant
    Filed: June 28, 2013
    Date of Patent: May 19, 2015
    Assignee: SAMSUNG ELECTRONICS CO., LTD.
    Inventors: Keun Jeong Jang, Byung Ghun Kim, Jong Moon Kim, Young Jae Kim, Hyeong Joon Seo
  • Patent number: 8998582
    Abstract: An impeller for a centrifugal pump includes a radially inner hub, and a plurality of blades extending straight and along a direction that is perpendicular to a rotational axis of the impeller. The blades extend from a radially outer end to a radially inner end, and define a generally frusto-conical envelope. A flow control feature is formed between the radially inner end of the blades and the hub. The flow control feature has a curved upper surface.
    Type: Grant
    Filed: November 3, 2011
    Date of Patent: April 7, 2015
    Assignee: Sundyne, LLC
    Inventors: Scott R. Wait, John E. Sidelko
  • Publication number: 20150071789
    Abstract: An impeller for a torque converter is provided. The impeller includes an impeller shell including an inner circumference, an outer circumference and a radial extension extending radially outward from the inner circumference. The radial extension includes an axially extending groove formed therein. The impeller also includes an impeller hub welded to the impeller shell by a weld. The weld is radially inside of the axially extending groove. The axially extending groove is 5 to 10 millimeters from the weld. A method of forming an impeller for a torque converter is also provided.
    Type: Application
    Filed: September 10, 2014
    Publication date: March 12, 2015
    Inventors: Michael Resh, David Burky, JR.
  • Patent number: 8961129
    Abstract: A method for connecting metallic components, in particular components of a gas turbine, including: corresponding connecting surfaces of the components being connected by means of inductive HF pressure welding, and that during or after a sufficiently great heating of the connecting surfaces, the first component is moved by a definite path toward the second component, and is pressed against it and held there.
    Type: Grant
    Filed: March 14, 2007
    Date of Patent: February 24, 2015
    Assignee: MTU Aero Engines GmbH
    Inventors: Herbert Hanrieder, Alexander Gindorf
  • Patent number: 8951009
    Abstract: A system, in certain embodiments, includes an impeller having a plurality of impeller blades coupled to an impeller hub body, wherein each impeller blade is sculpted having a nonlinear profile extending from a hub intersect surface of the impeller blade to a shroud intersect surface of the impeller blade.
    Type: Grant
    Filed: May 23, 2011
    Date of Patent: February 10, 2015
    Assignee: Ingersoll Rand Company
    Inventors: Chester V. Swiatek, Mikhail Grigoriev, James Hitt
  • Patent number: 8944748
    Abstract: A fluid pump device, in particular for a medical application, is described having a compressible pump housing and rotor, as well as with a drive shaft which runs in a sleeve and on whose end the fluid pump is arranged. In order to utilize all possibilities of a space-saving arrangement of the respective pump housing of the rotor, which is compressible per se, and as the case a bearing arrangement, the mentioned elements are displaceable to one another in the axial direction compared to an operation position. In particular these elements may be end-configured by way of an axial movement of the drive shaft after the assembly.
    Type: Grant
    Filed: April 29, 2010
    Date of Patent: February 3, 2015
    Assignee: ECP Entwicklungsgesellschaft mbH
    Inventor: Reiner Liebing
  • Publication number: 20150030457
    Abstract: An impeller is manufactured by forming, by molding, a first part including a base having a first annular surface with an annular shape in plan view, forming, by molding, a second part including a shroud having a second annular surface with an annular shape having an inner diameter larger than that of the first annular surface in bottom view, and a main blade portion including thin-plate-like inclined portions only extending in a radial direction further inside than an inner circumferential surface of the shroud while inclined with respect to a central axis of the shroud, the inclined portions not overlapping each other in plan view, and joining the first part and the second part together while the first annular surface and the second annular surface to face each other.
    Type: Application
    Filed: February 21, 2013
    Publication date: January 29, 2015
    Inventors: Junya Yamamoto, Shoichi Yoshini
  • Publication number: 20150003992
    Abstract: An axial-flow fan includes a boss and a plurality of blades integrally resin-molded with a hub. An axial hole of the boss has a shaft of a drive motor inserted. The axial hole is formed at an axial center of the hub. The hub includes an outer perimeter cylinder and a lid. The outer perimeter cylinder has an opening formed at the axial center, and the blades are formed so as to project from the outer perimeter cylinder. The lid extends from the outer perimeter cylinder toward the boss so as to cover the opening of the outer perimeter cylinder. The lid connects the boss and the outer perimeter cylinder together. Reinforcing ribs are integrally resin-molded together with the hub and the boss on both axial-direction sides of the lid. The reinforcing ribs reinforce the connection between the hub and the boss.
    Type: Application
    Filed: December 26, 2012
    Publication date: January 1, 2015
    Applicant: DAIKIN INDUSTRIES, LTD.
    Inventors: Azumi Kojima, Yuuta Yokoyama
  • Publication number: 20140341748
    Abstract: An axial-flow fan includes a hub and a plurality of blades integrally resin-molded to the hub at a plurality of joints, The plurality of blades are formed so as to project from an outer perimeter edge of the hub. Each joint has at least one first blade thinned-out part formed so that at least one radial rib extending radially toward an outer perimeter side is formed.
    Type: Application
    Filed: October 5, 2012
    Publication date: November 20, 2014
    Inventors: Azumi Kojima, Yuuta Yokoyama
  • Patent number: 8834129
    Abstract: An integrally bladed disk includes a rotor disk and circumferentially spaced first and second blades. The rotor disk has a rim the periphery of which forms a flow surface. The first and second blades extend integrally outward from the rim. The rim defines a trench in the flow surface between the first and second blades aft of a leading edge of the rim. The trench extends axially forward and rearward of a leading edge of the first blade.
    Type: Grant
    Filed: February 21, 2013
    Date of Patent: September 16, 2014
    Assignee: United Technologies Corporation
    Inventors: Roland R. Barnes, Cagdas Yilmaz
  • Patent number: 8821122
    Abstract: An integrally bladed rotor disk (20) for a turbine, including rotor blades (40), which are joined in a substance-to-substance bond to a disk element (30), and a sealing device (60) for preventing or reducing the extent to which cooling air is able to flow from a high-pressure side (12) of the rotor disk (20) through openings (24) on the rotor disk (20) to a low-pressure side (14) of the rotor disk (20).
    Type: Grant
    Filed: February 1, 2010
    Date of Patent: September 2, 2014
    Assignee: MTU Aero Engines GmbH
    Inventors: Hans-Peter Borufka, Frank Stiehler, Hernan Victor Arrieta, Patrick Prokopczuk, Joachim Lorenz
  • Patent number: 8770941
    Abstract: Efficient impeller or propeller wherein at least one blade in a set of blades on a hub of said impeller is oriented with respect to the tilted plane rotated clockwise or counter clockwise in an axis perpendicular to the longitudinal axis of said impeller. At least one blade in a set of blades of the multi-set impeller may have the same or different sizes or the same or different tilted plane angle compared to at least one blade of the adjacent set or the blade of one set may have the same or different angle as viewed from the second end of the impeller from a reference plane along the longitudinal axis of the impeller compared to the angle of at least one blade of the adjacent set. The invention also includes: blade arrangement for multi-set impeller, inner hub length variations, and hub shapes for better efficiency and utility.
    Type: Grant
    Filed: June 30, 2010
    Date of Patent: July 8, 2014
    Inventor: Mike Richard John Smith
  • 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: 8647063
    Abstract: Provided is a multi-element rotor blade, including a primary element and at least one complimentary element, each having an aerodynamic profile. The primary element is joined by fastening elements to the at least one complimentary element such that the at least one complimentary element is adjacent to the primary element in a chordwise direction perpendicular to an axis of rotation of the blade and perpendicular to a longitudinal length of the blade. The at least one complimentary element is disposed closer to a blade root end of the primary element than to an opposite end of the primary element.
    Type: Grant
    Filed: March 13, 2007
    Date of Patent: February 11, 2014
    Assignee: Tecsis Tecnologia Sistemas Avançados S.A.
    Inventor: Bento Massahiko Koike
  • Publication number: 20140003933
    Abstract: An axial flow fan includes: an impeller, a hub of which is attached to a rotation shaft of a rotation driving device; and a venturi casing that surrounds an outer circumference in a radial direction of the impeller and includes a suction port and a discharge port facing each other in an axial direction of the rotation shaft. A positive pressure surface of a plurality of blades integrally attached to the hub includes a plurality of step portions that is curved so as to comply with a curved shape of a front edge portion in a rotation direction of the blades.
    Type: Application
    Filed: March 28, 2013
    Publication date: January 2, 2014
    Applicant: SANYO DENKI CO., LTD.
    Inventor: SANYO DENKI CO., LTD.
  • Publication number: 20130323072
    Abstract: The invention relates to an axial fan for delivering cooling air, in particular for an internal combustion engine of a motor vehicle, comprising fan blades which are fastened to a hub and which have a pressure side and a suction side and a trailing edge and a blade depth, on the pressure side of which fan blades is arranged a hub ramp which rises counter to the direction of rotation of the axial fan, wherein the trailing edge has an outer region situated radially outside the hub ramp and has an inner region situated radially within the hub ramp.
    Type: Application
    Filed: December 1, 2011
    Publication date: December 5, 2013
    Applicant: BEHR GMBH & CO. KG
    Inventors: Uwe Aschermann, Uwe Blass, Frederic Guilbaud
  • Publication number: 20130323071
    Abstract: An example component polishing method includes polishing a component protecting portions of the component during the polishing using a barrier spaced from the component. The barrier is configured to move together with the component during the polishing.
    Type: Application
    Filed: October 19, 2012
    Publication date: December 5, 2013
    Applicant: PRATT & WHITNEY SERVICES PTE LTD.
    Inventors: Chua Boon Beng, Thomas Tan, Kim Wei Cheah, Wai Tuck Chow
  • Publication number: 20130224036
    Abstract: A rotor blade for a gas turbine engine has an airfoil, a base integrally joined to the airfoil, and a root integrally joined to the base and mountable in a slot in a rotor hub of the gas turbine engine. The root has a dovetail including at least one contact face that, when mounted, contacts a surface of the slot to retain the rotor blade in the hub. The root includes a neck between the base and the dovetail, and a groove in the neck for redirecting stress in the rotor blade. In certain embodiments, the groove is at a distance from the at least one contact face, has a length less than a length of the dovetail, and/or has an initial non-zero depth at the side of a trailing edge of the airfoil and tapers to a zero depth in the direction of the leading edge of the airfoil.
    Type: Application
    Filed: February 27, 2012
    Publication date: August 29, 2013
    Inventors: Olivier Jacques Louis LAMICQ, Fernando Manuel Ibarra Esparragoza, Paul Francis Norton, Jeremiah Wesley Key
  • Patent number: 8480368
    Abstract: A process of fabricating a rotating component and components formed thereby. The process includes fabricating preforms corresponding to portions of the component. Each preform has an interface surface at which the preforms can be joined to locate a first of the portions in a radially outward direction from a second of the portions. The preforms are then inertia welded together to form a profile having a solid-state weld joint containing a finer-grained material than other portions of the profile. The profile is then forged with dies to produce a forging. At least one of the dies has a recess into which the finer-grained material from the weld joint is expelled during forging to purge a joint region of the forging between the forging portions of the finer-grained material. The joint region contains grains distorted in an axial direction of the forging.
    Type: Grant
    Filed: February 5, 2010
    Date of Patent: July 9, 2013
    Assignee: General Electric Company
    Inventors: Ronald Gene Tolbert, Eric Scott Huron, David Paul Mourer, Douglas Gerard Konitzer
  • Patent number: 8465260
    Abstract: A combination fan propeller structure including a hub and at least one first blade assembly. The hub includes a top section and an annular section extending from the top section. The annular section has a free end distal from the top section. The first blade assembly has at least one connection section for connecting with the free end to form the fan propeller structure.
    Type: Grant
    Filed: February 22, 2010
    Date of Patent: June 18, 2013
    Assignee: Beijing AVC Technology Research Center Co., Ltd.
    Inventors: Jen-Chieh Wu, Chiang-Han Chen
  • Patent number: 8403645
    Abstract: An integrally bladed disk includes a rim and blades. The blades are circumferentially spaced and extend integrally outward from the rim to define a flow path therebetween. The periphery of the rim forms a flow surface and includes a trench that is disposed adjacent the blades.
    Type: Grant
    Filed: September 16, 2009
    Date of Patent: March 26, 2013
    Assignee: United Technologies Corporation
    Inventors: Roland R. Barnes, Cagdas Yilmaz
  • Patent number: 8376707
    Abstract: An impeller includes a hub, and a plurality of blades supported by the hub, the blades being arranged in at least two blade rows. The impeller has a deployed configuration in which the blades extend away from the hub, and a stored configuration in which at least one of the blades is radially compressed, for example by folding the blade towards the hub. The impeller may also have an operational configuration in which at least some of the blades are deformed from the deployed configuration upon rotation of the impeller when in the deployed configuration. The outer edge of one or more blades may have a winglet, and the base of the blades may have an associated indentation to facilitate folding of the blades.
    Type: Grant
    Filed: March 25, 2011
    Date of Patent: February 19, 2013
    Assignees: Thoratec Corporation, The Penn State Research Foundation
    Inventors: Mark W. McBride, Thomas M. Mallison, Gregory P. Dillon, Robert L. Campbell, David A. Boger, Stephen A. Hambric, Robert F. Kunz, James P. Runt, Justin M. Walsh, Boris Leschinsky
  • Patent number: 8366378
    Abstract: Blade assemblies are provided in a number of forms. These blade assemblies may have blades secured to disks (blisk), rings (bling) and drums (blum). The blades and/or the rotor elements formed by these rings, drums or disks can fragment and it is necessary to contain such fragments within a casing. Impact energy has a significant effect upon the necessary thickness of the casing to ensure containment. By providing blades as well as rotor elements which incorporate discontinuities which provide flexing under impact, energy is absorbed prior to further fragmentation upon impact engagement with a casing surface; flexing is about the discontinuity. In such circumstances casings may be thinner and therefore significant weight savings achieved with regard to aircraft incorporating gas turbine engines having blade assemblies with discontinuities.
    Type: Grant
    Filed: August 26, 2009
    Date of Patent: February 5, 2013
    Assignee: Rolls-Royce PLC
    Inventors: Peter Rowland Beckford, Simon Read, Ian Colin Deuchar Care
  • Patent number: 8366399
    Abstract: A blade or vane includes a platform 130 and an airfoil 132 extending from the platform. The airfoil has a pressure surface offset in a first direction D1 from a part span mean camber line 148, a suction surface offset in a second direction D2 from the part span mean camber line, and a base 146 that is laterally enlarged in the first direction for reducing secondary flow losses.
    Type: Grant
    Filed: May 2, 2006
    Date of Patent: February 5, 2013
    Assignee: United Technologies Corporation
    Inventors: Eunice Allen-Bradley, Eric A. Grover, Thomas J. Praisner
  • Publication number: 20120237357
    Abstract: The invention relates to a rotor for an axial flow pump for conveying a fluid having an axis of rotation and having an impeller blade which has at least one part surface which extends transversely to the axis of rotation and beyond it, wherein the impeller blade has throughgoing webs or a network of webs which connect a different marginal regions of the impeller blades to one another. A good compressibility is hereby achieved in the radial direction with high stability during operation.
    Type: Application
    Filed: September 22, 2010
    Publication date: September 20, 2012
    Applicant: ECP ENTWICKLUNGSGESELLSCHAFT MBH
    Inventors: Joerg Schumacher, Daniel Roehn
  • Patent number: 8267646
    Abstract: A method is disclosed for assembling a multi-stage compressor or a multi-stage turbine for use in a gas-turbine engine. The method comprises the steps of assembling a rotor drum so as to comprise a plurality of rotor discs 17, 18, and then releasably connecting a plurality of static components 38 to the assembled rotor drum 19, thus forming an intermediate structure. The intermediate structure is then inserted within an outer casing 50, preferably by lowering the outer casing 50 over the intermediate structure, whereafter the static components 38 are fixed to the outer casing 50. The static components 38 are then released from their connection to the rotor drum 19 in order to permit rotation of the drum 19 relative to the static components 38 and the outer casing 50.
    Type: Grant
    Filed: June 19, 2009
    Date of Patent: September 18, 2012
    Assignee: Rolls-Royce PLC
    Inventor: Daniel Robertson
  • Fan
    Patent number: 8235672
    Abstract: A fan includes a hub and a plurality of blades formed on the hub with a rake angle. In an axial direction of the hub, no part of a trailing edge of any of the blades is disposed past an air outlet end of the hub at more than a distance approximately equal to 25% of a diameter of the hub.
    Type: Grant
    Filed: July 21, 2008
    Date of Patent: August 7, 2012
    Assignee: LG Electronics Inc.
    Inventors: Seok Ho Choi, Deok Huh
  • Patent number: 8221086
    Abstract: A propeller has a hub 1 with a pair of blades 3 extending therefrom. Each blade 3 has a root, a tip, a first blade portion 10a extending between the root and tip and a second blade portion 10b extending between the root and tip adjacent and substantially parallel to said first blade portion 10a. The first and second blade portions 10a, 10b each have an arcuate concave face 11a, 11b, the radius of curvature of the concave face 11a of said first blade section 10a being greater than the radius of curvature of the concave face 11b of the second blade section 10b. The concave faces of said first and second portions 10a, 10b facing in substantially opposite directions such that, in use, said concave face 11a of said first blade portion 10a faces rearwards and said concave face 11b of the second blade portion 10b faces forwards.
    Type: Grant
    Filed: June 5, 2008
    Date of Patent: July 17, 2012
    Inventor: Alan Edward Watts
  • Patent number: 8147208
    Abstract: An impeller with an axial inlet in relation to an impeller axis for pressurizing a fluid has: a nose section that has a nose section central hub and multiple nose vane sections, each nose vane section extending from a leading edge to a generally radial nose section interface plane; a tail section that has a tail section central hub and multiple tail vane sections, each tail vane section extending from a generally radial tail section interface plane to a vane tip; a coupling that joins the nose section central hub to the tail section central hub and aligns each one of the nose vane sections with a corresponding one of the tail vane sections with an axial gap between the radial nose section interface plane and the radial tail section interface plane.
    Type: Grant
    Filed: February 25, 2009
    Date of Patent: April 3, 2012
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Behzad Hagshenas, Anthony C. Jones
  • Patent number: 8147207
    Abstract: An airfoil for use as rotor blades in compressors for turbomachines, such as gas turbine engines. The airfoil includes increased forward sweep and forward dihedral effective to reduce losses generated by interaction of tip clearance flow, secondary flows and passage shocks.
    Type: Grant
    Filed: September 4, 2008
    Date of Patent: April 3, 2012
    Assignee: Siemens Energy, Inc.
    Inventors: John Orosa, Matthew Montgomery
  • Publication number: 20120063910
    Abstract: A blade for a rotor of a wind turbine is divided into a root region closest to the hub and an airfoil region with a lift generating profile furthest away from the hub. A transition region has a profile gradually changing in the radial direction from the circular or elliptical profile of the root region to the lift generating profile of the airfoil region, and includes at least a first longitudinal segment extending along at least 20% of a longitudinal extent of the airfoil region. A base part has an inherent non-ideal twist, such as no twist, or a reduced twist compared to a target blade twist, so that an axial induction factor of the first base part at a design point deviates from a target axial induction factor. A number of flow altering devices are arranged so as to adjust the aerodynamic properties of the first longitudinal segment.
    Type: Application
    Filed: May 18, 2010
    Publication date: March 15, 2012
    Applicant: LM GLASFIBER A/S
    Inventors: Peter Fuglsang, Stefano Bove, Lars Fuglsang
  • Publication number: 20120057984
    Abstract: A blade for a rotor of a wind turbine is divided into a root region closest to the hub and an airfoil region with a lift generating profile furthest away from the hub and a transition region. A base part of the transition region has an axial induction factor, which without flow altering device deviates at least 5% from a target axial induction factor. A number of first flow altering devices are arranged so as to adjust the aerodynamic properties of a longitudinal segment of the transition region to substantially meet the target axial induction factor.
    Type: Application
    Filed: May 18, 2010
    Publication date: March 8, 2012
    Applicant: LM GLASFIBER A/S
    Inventors: Peter Fuglsang, Stefano Bove, Lars Fuglsang
  • Patent number: 8128375
    Abstract: The monocrystalline turbomachine blade according to the invention that is cast and directionally solidified, is disclosed. The blade includes an airfoil with a leading edge, a pressure face, a suction face, a trailing edge, a skeleton and having a longitudinal axis, the faces and having a neck line, respectively a pressure face neck and a suction face neck relative to the adjacent blade in the turbomachine rotor of which it forms an element; an endpiece of the airfoil, such as a heel or a platform, having an airfoil end face, on the stream side, forming an angle with the axis ZZ; and a connection zone between the airfoil and the airfoil end face. The connection zone forms a fattening of the airfoil. The connection zone extends about the leading edge between a point P1 situated on the suction face of the airfoil upstream of the suction face neck and a point P3 situated on the pressure face of the airfoil upstream of the pressure face neck.
    Type: Grant
    Filed: December 12, 2008
    Date of Patent: March 6, 2012
    Assignee: SNECMA
    Inventors: Patrick Joseph Marie Girard, Jean-Claude Marcel Auguste Hanny, Renaud Martet, Olivier Charles Henri Massy, Philippe Jean-Pierre Pabion, Stephanie Dominique Roger
  • Patent number: 8123486
    Abstract: A system for manufacturing an integrally bladed rotor is provided. This system includes a ring component, wherein the ring component further includes at least one metal matrix composite and a continuous radially outwardly facing blade conical surface; an airfoil component, wherein the at least one airfoil component has been created from a single, unitary piece of material and further includes a plurality of individual airfoil blades and a continuous radially inwardly facing blade conical surface; and inertia welding means for frictionally engaging under an axially applied weld load the ring component and the airfoil component to effect an inertia weld therebetween along the conical surfaces.
    Type: Grant
    Filed: June 8, 2010
    Date of Patent: February 28, 2012
    Assignee: General Electric Company
    Inventors: Charles W. Carrier, Chen-yu J. Chou
  • Patent number: 8113788
    Abstract: Disclosed is a surface of the blade having a cylindrical root portion, an airfoil portion and a transition portion connecting the root portion with the airfoil portion, wherein the blade comprises a shoulder at the border between the transition portion to the airfoil portion, wherein the blade comprises an element which is arranged substantially at the root portion and/or at the transition portion which creates a slot between the element and the surface of the blade.
    Type: Grant
    Filed: January 8, 2009
    Date of Patent: February 14, 2012
    Assignee: Siemens Aktiengesellschaft
    Inventor: Henrik Stiesdal
  • Patent number: 8100663
    Abstract: The invention concerns a rotor blade of a wind power installation and a wind power installation. One advantage of the present invention is to provide a rotor blade having a rotor blade profile, and a wind power installation, which has better efficiency than hitherto. A rotor blade of a wind power installation, wherein the rotor blade has a thickness reserve approximately in the range of between 15% and 40%, preferably in the range of between about 23% and 28%, and wherein the greatest profile thickness is between about 20% and 45%, preferably between about 32% and 36%.
    Type: Grant
    Filed: March 19, 2010
    Date of Patent: January 24, 2012
    Inventor: Aloys Wobben
  • Patent number: 8091177
    Abstract: A fan includes a hub and blades. A first edge of each blade is proximate an open end of the hub. A first rib is coupled to the hub and substantially aligned with a first plane intersecting the central axis and an intersection of the first edge of the first blade with the hub. The first plane is angularly spaced from a reference plane intersecting the central axis and an intersection of the first edge of the second blade with the hub. An angular spacing between the first plane and the reference plane defines one sector. A second rib is aligned with a second plane angularly positioned between the first plane and the reference plane at a location less than or equal to about (1/nR?0.05) sectors from the first plane, in which nR equals the number of ribs divided by the number of blades.
    Type: Grant
    Filed: May 13, 2010
    Date of Patent: January 10, 2012
    Assignee: Robert Bosch GmbH
    Inventors: F. Raymond Coté, Mark D. Caplan, Sebastian Hansen
  • Patent number: 8043063
    Abstract: A frequency mistuned integrally bladed rotor (IBR) for a gas turbine engine comprises a hub and a circumferential row of blades of varying frequency projecting integrally from the hub. Each blade in the row alternate with another blade having a different pressure surface definition but similar suction surface, leading edge and trailing edge definitions.
    Type: Grant
    Filed: March 26, 2009
    Date of Patent: October 25, 2011
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Frank Kelly, Kari Heikurinen, Edward Fazari, Yuhua Wu
  • Publication number: 20110182745
    Abstract: An integrally bladed rotor for a gas turbine engine includes at least one discontinuity formed in an outer face of an outer rim. The discontinuity reduces hoop stress in the outer rim.
    Type: Application
    Filed: December 28, 2007
    Publication date: July 28, 2011
    Inventors: Gabriel L. Suciu, James W. Norris
  • Patent number: 7980812
    Abstract: A low pressure turbine rotor disk for a small twin spool gas turbine engine in which the rotor disk includes a forward side cavity large enough to allow for the bearing assembly that rotatably supports the rotor disk to fit within the cavity in order to shorten the axial distance between the bearings that support the inner rotor shaft on which the turbine rotor disk is secured. Minimizing the bearings spacing allows for a high critical speed for the inner rotor shaft and therefore allows for the small twin spool gas turbine engine to operate at this small scale. The turbine rotor disk also includes a plurality of axial aligned cooling air holes to allow for cooling air from the bearings to flow out from the aft end of the rotor disk. The inner surface of the cavity is an annular surface that forms a seal with knife edges extending outward from the bearing support plate also located within the cavity.
    Type: Grant
    Filed: October 19, 2007
    Date of Patent: July 19, 2011
    Assignee: Florida Turbine Technologies, Inc.
    Inventors: Ryan C. McMahon, Jack W. Wilson, Jr.
  • Patent number: 7959413
    Abstract: A fan includes an impeller and a motor. The impeller includes a hub and a plurality of blades. The hub has a top portion, a connection portion, and at least one airflow-guiding portion. The top portion is connected to the connection portion. The blades are disposed around the connection portion. The motor is disposed corresponding to the impeller and used to drive the impeller to rotate. The airflow-guiding portion is disposed between two adjacent blades.
    Type: Grant
    Filed: January 19, 2007
    Date of Patent: June 14, 2011
    Assignee: Delta Electronics, Inc.
    Inventors: Shihhua Ho, Shihying Huang, Tsung Yu Lei, Chung-kai Lan, Huan-Chi Chen, Wen-Shi Huang
  • Patent number: 7927068
    Abstract: An impeller includes a hub, and a plurality of blades supported by the hub, the blades being arranged in at least two blade rows. The impeller has a deployed configuration in which the blades extend away from the hub, and a stored configuration in which at least one of the blades is radially compressed, for example by folding the blade towards the hub. The impeller may also have an operational configuration in which at least some of the blades are deformed from the deployed configuration upon rotation of the impeller when in the deployed configuration. The outer edge of one or more blades may have a winglet, and the base of the blades may have an associated indentation to facilitate folding of the blades.
    Type: Grant
    Filed: June 9, 2008
    Date of Patent: April 19, 2011
    Assignees: Thoratec Corporation, The Penn State Research Foundation
    Inventors: Mark W. McBride, Thomas M. Mallison, Gregory P. Dillon, Robert L. Campbell, David A. Boger, Stephen A. Hambric, Robert F. Kunz, James P. Runt, Justin M. Walsh, Boris Leschinsky