Axially Extending Shroud Ring Or Casing Patents (Class 416/189)
  • Patent number: 10851676
    Abstract: An exhaust diffuser includes: an internal cylinder; an external cylinder that forms an exhaust passage between the internal cylinder and the external cylinder, the exhaust passage expanding from front to rear; and at least one tubular strut that couples the internal cylinder and the external cylinder together. The external cylinder includes: a front conical portion that is positioned forward of the tubular strut; and an outer flaring portion that starts flaring at a positon forward of the tubular strut at an inclination angle that is greater than an inclination angle of the front conical portion. The internal cylinder includes: a front straight portion that faces the front conical portion and the outer flaring portion; and an inner flaring portion that starts flaring at a position between a maximum width portion and a trailing edge of the tubular strut.
    Type: Grant
    Filed: August 30, 2016
    Date of Patent: December 1, 2020
    Assignee: KAWASAKI JUKOGYO KABUSHIKI KAISHA
    Inventors: Takuya Ikeguchi, Koji Terauchi, Keiji Oikaze, Naoto Sakai
  • Patent number: 10844770
    Abstract: A cooling fan module is provided. The cooling fan module may include a frame, a fan assembly, a number of guide vanes, and a cylindrical deflector. The frame may include a sidewall that defines an opening and an outer periphery. The fan assembly may be disposed within the opening and include fan blades extending from a hub and terminating at a fan ring. The fan ring may have a curved profile. The number of guide vanes may be disposed radially around the opening. The cylindrical deflector may extend axially from the sidewall and radially surround the number of guide vanes. The cylindrical deflector may be disposed radially between the number of guide vanes and the outer periphery.
    Type: Grant
    Filed: December 4, 2018
    Date of Patent: November 24, 2020
    Assignee: Brose Fahrzeugteile GmbH & Co. Kommanditgesellschaft, Würzburg
    Inventors: Tao Hong, William Brehmer, Attila Simofi-Ilyes, Derek Mudge
  • Patent number: 10837457
    Abstract: A gas turbine engine blade root shim for use between a composite blade root and a wall of a slot in a rotor includes a longitudinally extending base having distal first and second transversely spaced apart ends, first and second longitudinally extending legs acutely angled inwardly towards the base from the first and second ends, and one or more apertures disposed through each of the longitudinally extending first and second legs. Apertures may include rectangular slots having rounded edges along the first and second outwardly facing surfaces of the first and second legs respectively and/or rounded corners between the first and second outwardly facing surfaces and the first and second inwardly facing surfaces of the first and second legs. Low coefficient of friction coatings may be disposed on outwardly facing surfaces, of the legs. Coatings may include polytetrafluoroethylene powder dispersed in a resin binder and other coatings having polytetrafluoroethylene.
    Type: Grant
    Filed: November 17, 2014
    Date of Patent: November 17, 2020
    Assignee: General Electric Company
    Inventors: Nicholas Joseph Kray, Qiang Li
  • Patent number: 10815786
    Abstract: A gas turbine that includes a rotor blade that includes an airfoil. The airfoil is defined between a pressure face and a laterally opposed suction face, the pressure face and the suction face extending axially between opposite leading and trailing edges and radially between an outboard tip and a connection with a root of the rotor blade. The airfoil may include non-integral portions in which: a base portion of the airfoil is made from a first material; and a top portion of the airfoil is made from a second material. The airfoil may include a dovetail joint connecting the top portion to the base portion. The dovetail joint may include a dovetail extending from the top portion being received within a complementary dovetail groove formed in the base portion.
    Type: Grant
    Filed: December 28, 2018
    Date of Patent: October 27, 2020
    Assignee: General Electric Company
    Inventors: Matthew Troy Hafner, John McConnell Delvaux, James Zhang, Jeffrey Clarence Jones, Peter de Diego
  • Patent number: 10787917
    Abstract: A multi-piece disk for use in a turbine of a gas turbine engine. The multi-piece disk includes a fore disk segment and an aft disk segment coupled with the fore disk segment for movement with the fore disk segment. The fore disk segment and the aft disk segment are formed to define slots that extend through the disk segments and are configured to receive turbine blades therein.
    Type: Grant
    Filed: May 4, 2018
    Date of Patent: September 29, 2020
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce High Temperature Composites Inc.
    Inventors: Ted J. Freeman, Christopher Barrett
  • Patent number: 10760488
    Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan section having a plurality of fan blades. The plurality of fan blades has a peak tip radius Rt and an inboard leading edge radius Rh at a first inboard boundary of a first flowpath. A core engine includes a first turbine configured to drive a first compressor, and a fan drive turbine configured to drive the fan section. A method of designing a gas turbine engine is also disclosed.
    Type: Grant
    Filed: February 2, 2016
    Date of Patent: September 1, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Frederick M. Schwarz, William G. Sheridan
  • Patent number: 10697308
    Abstract: Various embodiments of the invention include turbine buckets and systems employing such buckets. Various particular embodiments include a turbine bucket having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; a base connected with a first end of the airfoil along the suction side, pressure side, trailing edge and the leading edge; and a tip shroud connected with a second end of the airfoil along the suction side, the pressure side, the trailing edge and the leading edge, the tip shroud including a tip shroud fillet connecting the airfoil and the tip shroud and having a non-uniform thickness across an axial length of the airfoil.
    Type: Grant
    Filed: October 25, 2018
    Date of Patent: June 30, 2020
    Assignee: General Electric Company
    Inventors: Neil Ristau, Zachary James Taylor, David Wayne Weber
  • Patent number: 10683759
    Abstract: A turbine rotor blade including an airfoil having a tip shroud, the tip shroud having leading and trailing edges, the leading edge having a leading edge profile including first and second scalloped sections substantially in accordance with X and Y coordinate values in a Cartesian coordinate system at points 1-6 and 11-25, respectively, as set forth in Table I, where X and Y are distances in inches from an origin and, when points 1-6 and points 11-25 are connected by smooth, continuing arcs, the points define the first and second scalloped sections, respectively, of the leading edge profile of the tip shroud.
    Type: Grant
    Filed: March 23, 2018
    Date of Patent: June 16, 2020
    Assignee: General Electric Company
    Inventors: William Scott Zemitis, Jacob Charles Perry, II, Melbourne James Myers, Ajay Gangadhar Patil, Richard Ryan Pilson
  • Patent number: 10641290
    Abstract: A ducted fan for an aircraft or other vehicle includes aerodynamic features to selectably move the thrust vector of the ducted fan from the axis of rotation of the ducted fan, providing additional and redundant control authority to a control system. The control system may apply the aerodynamic features asymmetrically about the circumference of the duct and may apply the aerodynamic features differentially among a plurality of ducted fans. The aerodynamic features may include a morphing leading edge portion, an air dam, vanes and trailing edge control surfaces.
    Type: Grant
    Filed: September 19, 2017
    Date of Patent: May 5, 2020
    Assignee: Piasecki Aircraft Corporation
    Inventors: John W. Piasecki, Frederick W. Piasecki
  • Patent number: 10605099
    Abstract: A rotor blade (16) for a turbine of a gas turbine that includes an airfoil (25). The airfoil may have a leading edge, a trailing edge, an outboard tip, and an inboard end where the airfoil attaches to a root configured to couple the turbine blade to a rotor disc. The airfoil (25) may include a tip shroud (55) at an outboard tip. The rotor blade may have a cooling configuration that includes: elongated cooling channels (33) for receiving and directing a coolant through the airfoil (25); and branching passages (75) formed through the tip shroud (55), each of which elongates between a connection with one of the cooling channels (33) and an outlet port (37) formed on a surface of the tip shroud (55). The branching passages (75) may have a canted orientation relative the outboard surface of the tip shroud (55).
    Type: Grant
    Filed: July 31, 2015
    Date of Patent: March 31, 2020
    Assignee: General Electric Company
    Inventors: Zachary James Taylor, Lucas Seth Wedmore, Hiteshkumar Rameshchandra Mistry
  • Patent number: 10532806
    Abstract: The present invention discloses a low-noise novel thruster, in which a rotor casing is located at an air inlet side of a stator casing, at an inner middle portion of the rotor casing a rotor core is provided which is driven to rotate by a driving module; a rotor core is provided at in inner middle portion of the stator casing; the rotor casing is of a streamlined cylindrical structure with unequal diameter, and the main body of the rotor blade is parallel with the axial direction, and provided with a smooth curve in the rotating direction of the blade adjacent to an edge portion of an air inlet side. The present application provides a new thruster, which has same energy consumption and safety as propellers, but at a significantly greater thrust than the propeller, the more significant the advantage is at higher speeds.
    Type: Grant
    Filed: March 13, 2018
    Date of Patent: January 14, 2020
    Inventor: Yanjin Nan
  • Patent number: 10519783
    Abstract: A method for modifying an airfoil shroud located at a tip of an airfoil is provided. A locating step locates a reference location in a first end edge. The reference location includes a portion of a fillet. A seal rail extends circumferentially along a radially outer surface of the airfoil shroud. The fillet extends along the radially outer surface and is positioned directly adjacent to the seal rail. A forming step forms a compound relief cut in the fillet without performing a weld process on the airfoil shroud to remove the reference location. The compound relief cut has a first cut having a first radius extending from the seal rail towards the first end edge, and a second cut having a second radius extending from an end of the first cut to the first end edge. Modifying the airfoil shroud is complete following forming the compound relief cut.
    Type: Grant
    Filed: December 22, 2016
    Date of Patent: December 31, 2019
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Richard Gordon Rollings, Kevin Leon Bruce, William Scott Zemitis
  • Patent number: 10422340
    Abstract: According to present embodiments or aspects thereof, a composite booster spool with separable composite blades is provided. The blades are inserted radially from within the inner circumference of the spool and extend outwardly through the spool. The system provides a reduced weight assembly as compared to prior art metallic or composite/metallic combination systems. Additionally, the blades are separable which results in a more field-serviceable assembly over a fully integral system wherein the blades and spool are integrally formed from composites or combination of metal and composites.
    Type: Grant
    Filed: May 6, 2015
    Date of Patent: September 24, 2019
    Assignee: General Electric Company
    Inventors: Nicholas Joseph Kray, Suresh Subramanian, Phani Nandula, Dong-Jin Shim, Todd Alan Anderson, Mark Ernest Vermilyea
  • Patent number: 10370978
    Abstract: An airfoil comprises one or more internal cooling circuits. The cooling circuits can be fed with a flow of cooling fluid from one or more cooling air inlet passages in fluid communication with the cooling circuits. The cooling circuits can further comprise a leading edge cooling circuit defined by a supply passage, a pin bank passage divided into one or more sub-circuits by pin banks disposed within the pin bank passage, and at least first and second cooling passages. The cooling circuits can provide the cooling fluid flow within the airfoil to cool the airfoil, as well as provide a cooling fluid to a plurality of film holes to create a cooling film on the external surface of the airfoil.
    Type: Grant
    Filed: October 15, 2015
    Date of Patent: August 6, 2019
    Assignee: General Electric Company
    Inventors: Matthew Lee Krumanaker, Steven Robert Brassfield, Robert Frederick Bergholz, Aaron Ezekiel Smith, Weston Nolan Dooley
  • Patent number: 10227879
    Abstract: A fluid transfer assembly for use in a gas turbine engine includes a rotor shaft, a stationary assembly circumscribing the rotor shaft, and a rotating component coupled to the rotor shaft and positioned radially inward of the stationary assembly. The rotating assembly includes a hub coupled to the rotor shaft, a plurality of rotor blades coupled to the hub, and a shroud coupled to the plurality of rotor blades.
    Type: Grant
    Filed: February 11, 2016
    Date of Patent: March 12, 2019
    Assignee: General Electric Company
    Inventors: Thomas Ory Moniz, Joseph George Rose
  • Patent number: 10190423
    Abstract: A turbine blade for a gas turbine engine comprises a platform, a blade root, an airfoil portion defining pressure and suction sides, and a shroud provided at a tip of the airfoil portion opposite to the blade root. The shroud includes a body having a radially outer face opposite to the airfoil portion, upstream and downstream generally parallel fins extending outwardly from the outer face, and two ribs extending outwardly from the outer face. Each of the fins has an end disposed toward the pressure side and another end disposed toward the suction side. The ribs extend from and connecting the upstream fin to the downstream fin at locations other than the ends of the upstream and downstream fins. The ribs converge toward the downstream fin at an angle of between about 10 and about 45 degrees. A shroud for a blade is also presented.
    Type: Grant
    Filed: December 15, 2016
    Date of Patent: January 29, 2019
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Ghislain Plante, Remy Synnott, Jaideep Gahlawat
  • Patent number: 10155575
    Abstract: A diffuser-type endplate propeller driving a hull and including a propeller hub and a plurality of blades is provided. The propeller hub has an axis of rotation and is connected to a transmission shaft of the hull. A blade has a blade-body and an endplate. The blade-body is connected to the propeller hub and extends outward from the propeller hub to the corresponding endplate, the endplate bends from the corresponding blade-body to extend towards a stern of the hull, and the endplate has a leading edge and a trailing edge. A cylindrical surface is imaginarily formed by the leading edges while the diffuser-type endplate propeller is rotated about the axis. Each of the endplates has a first tangent plane at the leading edge thereof, the cylindrical surface has a second tangent plane at the leading edge. An included angle is measured from the second tangent plane to the first tangent plane.
    Type: Grant
    Filed: January 3, 2018
    Date of Patent: December 18, 2018
    Assignee: National Taiwan Ocean University
    Inventor: Young-Zehr Kehr
  • Patent number: 10131073
    Abstract: A fiber preform for a vane module of an intermediate casing of a turbine engine, the preform being obtained by three-dimensional weaving. The preform includes first longitudinal segment presenting opposite first and second ends and suitable for forming a first vane; a second longitudinal segment presenting first and second opposite ends and suitable for forming a second vane; and a first transverse segment connecting together the first and second longitudinal segments by their first ends, and suitable for forming a first transverse vane portion such as a flange or a platform.
    Type: Grant
    Filed: November 12, 2013
    Date of Patent: November 20, 2018
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Matthieu Gimat, Dominique Coupe, Yann Marchal, Thierry Papin
  • Patent number: 10099434
    Abstract: An airfoil structure is presented. The airfoil structure includes an outer casing substantially surrounding a composite core. The composite core includes a plurality of fiber bands, each of the plurality of fiber bands is placed at a predetermined position and orientation at a time, wherein the plurality of fiber bands are interwoven in an in-plane and out-of-plane orientation by interleaving each of the plurality of fiber bands placed in a plane with one or more of the plurality of fiber bands of an adjacent plane to define an interleaved structure. A method for manufacturing an airfoil structure including the composite core is also presented.
    Type: Grant
    Filed: September 16, 2014
    Date of Patent: October 16, 2018
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Todd Alan Anderson, Nicholas Joseph Kray, Gregory Carl Gemeinhardt, Michael Harvey Schneider
  • Patent number: 10001128
    Abstract: A fan impeller includes a plurality of fan blade assembly members, each one of the fan blade assembly members respectively includes a metal ring bracket and a plurality of metal blades, one end of each one of the metal blades is respectively connected to the corresponding metal ring bracket and the plurality of metal blades of each one of the fan blade assembly members arranged radially to circumference the corresponding metal ring bracket. The metal ring brackets are configured to stack with each other and the metal blades are arranged in a radial centric row, a width of at least one portion of each one of the metal blades is not smaller than a distance between any two adjacent metal blades along a fan impeller circumferential direction. Accordingly, metal blades of a greater width can be densely arranged on the fan impeller.
    Type: Grant
    Filed: May 5, 2015
    Date of Patent: June 19, 2018
    Assignee: COOLER MASTER CO., LTD.
    Inventors: Chen-Yang Lin, Kuo-Chun Hung
  • Patent number: 9914515
    Abstract: Barrel extension assemblies for structural modification of a propeller barrel on a marine propeller include a ring housing having a ring housing interior, the ring housing adapted to detachably engage an interior surface of the propeller barrel at a trailing barrel edge for structural modification of the propeller barrel. Barrel extension methods for modifying performance of a marine vessel are also disclosed.
    Type: Grant
    Filed: September 8, 2015
    Date of Patent: March 13, 2018
    Inventor: Charles S. Powers
  • Patent number: 9903206
    Abstract: An impeller includes a hub and a plurality of blades. The blades are disposed around an outer periphery of the hub. Each of the blades includes a connecting end, a sweep-back part and a sweep-forward part. The connecting end is coupled with the hub. The sweep-back part is disposed at an edge of the blade and extended from the connecting end. An extending direction of the sweep-back part is opposed to a rotating direction of the impeller. The sweep-forward part is extended from the sweep-back part. An extending direction of the sweep-forward part is the same as the rotating direction of the impeller.
    Type: Grant
    Filed: October 12, 2011
    Date of Patent: February 27, 2018
    Assignee: DELTA ELECTRONICS, INC.
    Inventors: Po-Hao Yu, Shir-Harn Yeh
  • Patent number: 9765632
    Abstract: Disclosed is a process for producing a blade or vane ring segment for a gas turbine, in particular for an aero engine, and also to a correspondingly produced blade or vane ring segment, the process comprising: forging at least two blanks made of a TiAl material, joining the blanks to form a blade or vane ring by means of an integral connection process, and remachining of the blank composite by material-removing processes.
    Type: Grant
    Filed: August 8, 2013
    Date of Patent: September 19, 2017
    Assignee: MTU AERO ENGINES AG
    Inventor: Karl-Hermann Richter
  • Patent number: 9568015
    Abstract: A centrifugal fan includes a fan frame, a stator assembly and an impeller. The fan frame has a base plate portion, a cover plate portion and a lateral wall portion. The cover plate portion has an air inlet, and the lateral wall portion has an air outlet. The impeller includes a rotating member, a plurality of blades and a connection ring. The rotating member is coupled with the stator assembly. Each blade has a windward edge and a lateral edge. The windward edge faces the air inlet, the lateral edge faces the lateral wall portion, and the connection ring is arranged on the windward edges of the blades. The windward edge has a first coupling edge, and the connection ring has a second coupling edge. A part of the windward edge between the first coupling edge and the lateral edge extends downwards in a curved manner, forming a truncating portion.
    Type: Grant
    Filed: January 10, 2014
    Date of Patent: February 14, 2017
    Assignee: Sunonwealth Electric Machine Industry Co., Ltd.
    Inventor: Alex Horng
  • Patent number: 9551345
    Abstract: A leading edge of a rotating blade of an impeller is formed in an arc recessed in a direction opposite to a rotating direction of the impeller. An angle where an extended line of the recessed arc of the leading edge meets another extended line of a curve of a side edge is set in an acute angle of 30 to 37 degrees in a front view so that a leading tip of the rotating blade may be projected in the rotating direction. An opening angle of a suction-side slant portion of a venturi casing is set in the range of 12 to 17 degrees and an opening angle of a discharge-side slant portion is set in the range of 30 to 35 degrees.
    Type: Grant
    Filed: September 5, 2013
    Date of Patent: January 24, 2017
    Assignee: SANYO DENKI CO., LTD.
    Inventor: Atsushi Yanagisawa
  • Patent number: 9249783
    Abstract: Multiple horizontal axis type rotors are coaxially attached along the upper section of an elongate torque transmitting tower/driveshaft, The tower/driveshaft projects upward from a cantilevered bearing, and is bent downwind, until the rotors become sufficiently aligned with the wind to rotate the entire tower/driveshaft, Power is drawn from the shaft at the base. Surface mount, subsurface mount, and marine installations, including a sailboat, are disclosed. Blade-to-blade lashing, and vertical axis rotor blades may also be included. Vertical and horizontal axis type rotor blades may be interconnected along the length of the tower/driveshaft to form a structural lattice, and the central shaft may even be eliminated. Aerodynamic lifting bodies or tails, buoyant lifting bodies, buoyant rotor blades, and methods of influencing the tilt of the rotors, can help elevate the structure. This wind turbine can have as few as one single moving part.
    Type: Grant
    Filed: September 25, 2013
    Date of Patent: February 2, 2016
    Inventor: Douglas Spriggs Selsam
  • Patent number: 9243610
    Abstract: A fluid powered turbine, such as a wind turbine (10), has a hollow column (12) in which a rotating turbine is housed. A fluid directing structure (14) is supported at or near an end of the column (12) remote from the turbine. The fluid directing structure (14) has a plurality of individual inlet openings (26) spaced around its periphery and is arranged to direct air at each inlet opening into an inner pipe (18). The incoming air is constricted both within the structure (14) and as it exits the column (12) whereby its speed is sufficient to rotate the turbine (20). The structure at the top of the column (12) generally requires no maintenance and maintenance of the turbine (20) is considerably easier than with traditional wind generators as access is easy. As the turbine is enclosed, it is safer than the traditional wind generators and less noisy.
    Type: Grant
    Filed: October 15, 2012
    Date of Patent: January 26, 2016
    Assignee: Funnelhead Limited
    Inventor: Rajeshwar Rao Degala
  • Patent number: 9234521
    Abstract: A ring-type fan includes a frame having a receiving space defined between an air inlet and an air outlet thereof and being provided along an inner side of the air outlet with an inward projected wall portion; an impeller assembly rotatably mounted in the receiving space and including spaced impellers outward extended from a hub, and a ring member connected to radially outer ends of the impellers and externally provided with a circle of stop section, which and the projected wall portion together define an air passage between them; and at least one pressure relief section defining an airflow guide on the frame to communicate with the receiving space and the air passage. Any backflow can be guided out of the frame via the air passage and the pressure relief section without interfering with the inflow of air, allowing the ring-type fan to have upgraded heat dissipation performance.
    Type: Grant
    Filed: May 28, 2012
    Date of Patent: January 12, 2016
    Assignee: Asia Vital Components Co., Ltd.
    Inventor: Wen-Hao Liu
  • Patent number: 9162749
    Abstract: A blade (1) for a tail anti-torque device of a helicopter, said device comprising a ducted rotor (13). The blade (1) has an assembly of sections, a leading edge (2) and a trailing edge (3); a stacking line (4) of the profiles extending at a distance lying in the range 25% to 50% of the chord (C). The stacking line (4) presents a shape that is curved having successively from the root (5) to the end (6) of the blade a back sweep, a forward sweep, and a last back sweep; and a chord (C) that becomes larger going towards the end (6) of the blade (1) over at least the end profile (1a).
    Type: Grant
    Filed: October 30, 2014
    Date of Patent: October 20, 2015
    Assignee: Airbus Helicopters
    Inventors: Marc Gervais, Benoit Gresle, Sebastein Finck, Laurent Sudre
  • Patent number: 9097262
    Abstract: A fan includes an impeller having a plurality of blades. Each of the plurality of blades has a trailing edge portion positioned rearmost in a rotation direction and a leading edge portion positioned foremost in the rotation direction. A curved line interconnects the trailing edge portion and the leading edge portion at the shortest distance on an imaginary cylindrical surface. Each of the blades includes a lower surface facing downward in the direction of the center axis and an upper surface facing upward in the direction of the center axis. In the fan, L1/L2 decreases from a radial inner side toward a radial outer side, where L1 denotes the longest distance on the imaginary cylindrical surface between the curved line and a camber line and L2 denotes a length of the curved line.
    Type: Grant
    Filed: July 31, 2012
    Date of Patent: August 4, 2015
    Assignee: Nidec Corporation
    Inventor: Junji Tsukida
  • Publication number: 20150118079
    Abstract: A turbocharger (5) comprising a housing (10) including a compressor shroud (14) and a turbine shroud (12). A compressor wheel (18) is disposed in the compressor shroud (14) and includes a plurality of compressor blades (45, 46). Each compressor blade (45, 46) includes a leading edge (50, 51) and a compressor shroud contour edge (54, 55), wherein each compressor shroud contour edge (54, 55) is in close confronting relation to the compressor shroud (14). A turbine wheel (16) is disposed in the turbine shroud (12) and includes a plurality of turbine blades (26). Each turbine blade (26) includes a leading edge (30) and a turbine shroud contour edge (34), wherein each turbine shroud contour edge (34) is in close confronting relation to the turbine shroud (12). At least one of the compressor shroud (14) and turbine shroud (12) includes a plurality of grooves (70, 72) extending cross-wise with respect to the corresponding compressor or turbine shroud contour edges (34, 54, 55).
    Type: Application
    Filed: April 11, 2013
    Publication date: April 30, 2015
    Inventors: Stephanie Dextraze, David G. Grabowska
  • Patent number: 9004864
    Abstract: A wind turbine having a set of curved blades mounted on a central rotatable hub. Each of the blades has a defined pitch angle, to a rotational axis of the hub, along the blade from the hub to the tip. A curve is provided on the wind contact surface along each of the blades over the blade surface from the leading edge of the blade to the trailing edge of the blade by an amount between about 6 and about 24 degrees. The defined pitch angle from any point along the leading edge of the blade being defined by the arc-sine of a ratio of blade velocity to apparent wind velocity, with a variance of ±30 percent of the complementary angle to the arc-sine; and apparatus for varying the velocity of the blade to control power output so that it is within fifteen percent of maximum obtainable power of the blade most distant from the hub.
    Type: Grant
    Filed: August 30, 2011
    Date of Patent: April 14, 2015
    Inventor: Kean W. Stimm
  • Patent number: 8992163
    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: January 11, 2013
    Date of Patent: March 31, 2015
    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
  • Publication number: 20150071782
    Abstract: A fan impeller for the conveyance of a gaseous fluid includes several blades arranged with constant angular spacing around a rotation axis. At least one blade has a boundary zone and an inner zone, together with a bead extending between them along a curved path and/or the boundary zone is determined by a first blade surface and the inner zone is determined by a second blade surface, which are arranged with varying geometry.
    Type: Application
    Filed: September 10, 2014
    Publication date: March 12, 2015
    Inventors: Henning BÄHREN, Christian HORNHARDT, Matthias WOLF, Yingan XIA
  • Publication number: 20150064011
    Abstract: An impeller includes a fan frame, a hub, a plurality of axial blades and a plurality of wind guiding blades. The fan frame has a wind inlet, a wind outlet and an inner ring-shaped oblique surface, wherein the wind inlet is opposite to the wind outlet, and the inner ring-shaped oblique surface is formed at an inner side wall of the fan frame and adjacent to the wind inlet. The hub is disposed in the fan frame. The axial blades are connected to the inner side wall of the fan frame and the hub. The wind guiding blades protrude from the inner ring-shaped oblique surface.
    Type: Application
    Filed: September 1, 2014
    Publication date: March 5, 2015
    Inventors: Shiman Xu, Jiasheng Lai, Wen-Chun Hsu
  • Publication number: 20150064010
    Abstract: The present application provides a turbine bucket. The turbine bucket may include an airfoil and a tip shroud attached to the airfoil. The tip shroud may include a cooling core and an enhanced cooling surface.
    Type: Application
    Filed: August 28, 2013
    Publication date: March 5, 2015
    Applicant: General Electric Company
    Inventors: Xiuzhang James Zhang, Melbourne James Myers, Robert Joseph Testa, Jr., Haiping Wang
  • Patent number: 8967972
    Abstract: A turbine blade is provided and includes a tip end carrying a shroud and at least one fin, which extends radially away from the shroud. The fin includes a first sidewall and a second sidewall, which are spaced apart, arranged parallel to each other, and are connected to the shroud, and a cutting edge, which is connected to the first and second sidewalls. The cutting edge thereby creates a hollow space between the sidewalls, the shroud, and the cutting edge, and further extends radially away from the first and second sidewalls. Also provided is a method of manufacturing the blade by casting the blade as single piece with the hollow fin or by forging the blade; and machining the fin to create the first and second sidewalls and cutting edge thereby opening the hollow space between said sidewalls and the cutting edge.
    Type: Grant
    Filed: November 2, 2012
    Date of Patent: March 3, 2015
    Assignee: ALSTOM Technology Ltd.
    Inventors: Herbert Brandl, Igor Tsypkakyin, Philipp Indlekofer
  • Fan
    Patent number: 8961109
    Abstract: A fan includes a frame, rotor supported by this frame and having a central hub and a number of blades and a drive mechanism for rotatably driving the rotor, in addition to a ring to which the end zones of the blades are connected. The ring is assembled from two part-rings of the same form which each include a circular strip of sheet material, the free ends of which are mutually connected to form the outer surface of a truncated cone, and a third part-ring which mutually connects the inner edges of the first two part-rings. The end zones of the blades are connected to the third part-ring. The ring has a diameter of more than about 1.50 m. The number of blades amounts to at least eight. The blades are hollow and include a framework structure which is provided with a skin connected thereto.
    Type: Grant
    Filed: October 6, 2008
    Date of Patent: February 24, 2015
    Assignee: Bronswerk Heat Transfer B.V.
    Inventor: Augustinus Wilhelmus Maria Bertels
  • Patent number: 8920126
    Abstract: An object is to provide a turbine and a turbine rotor blade in which it is possible to ensure the strength of the turbine rotor blade and to improve the performance thereof. The turbine includes: rotor blades that rotate about a rotational axis in a main flow channel of a casing; stator vanes that are disposed in the casing; a tip shroud that is disposed at a radially-outward end of each of the rotor blades and whose length in the direction along the rotational axis is reduced as the distance from the rotor blade increases; and a cavity portion that is formed at a position in the casing facing the rotor blades and in which the tip shroud is accommodated. An inclination angle of the inner periphery of the tip shroud is larger than an average inclination angle that is an inclination angle of the inner periphery of the casing, averaged from the trailing edge of the stator vanes disposed at the upstream side of a main flow to the cavity portion disposed at the downstream side of the main flow.
    Type: Grant
    Filed: December 7, 2009
    Date of Patent: December 30, 2014
    Assignee: Mitsubishi Heavy Industries, Ltd.
    Inventor: Koichiro Iida
  • Patent number: 8918995
    Abstract: A method of repairing a damaged notch fillet radius of a turbine blade shroud includes a replacement notch fillet radius and a hardface nugget. The damaged notch fillet radius is blended out and a hardface structure positioned proximate the damaged notch fillet radius is removed. A replacement notch fillet radius is formed with weld filler and the hardface nugget is welded to at least a portion of the replacement notch fillet radius.
    Type: Grant
    Filed: March 25, 2011
    Date of Patent: December 30, 2014
    Assignee: United Technologies Corporation
    Inventor: Timothy A. Milleville
  • Patent number: 8915717
    Abstract: The impeller wheel is rotatably supported about a central axis and has a hub on which vanes are arranged. The vane has across its radial length at least similar profiled sections, viewed in cylindrical section through the vane. The radial outermost profiled section which is positioned on a cylindrical enveloping surface of the impeller wheel has a greater displacement relative to the neighboring profiled section than this neighboring profiled section to its neighboring profiled section. The impeller wheel can also be provided on the radial outer edge with at least one projecting flow element whose axial height has a maximum in the area of the leading edge and of the trailing edge of the vane. The impeller wheels, while having a simple constructive configuration, provide a great noise reduction in operation of the ventilator.
    Type: Grant
    Filed: August 12, 2011
    Date of Patent: December 23, 2014
    Assignee: Ziehl-Abegg AG
    Inventors: Michael Stephan, Ralf Neumeier, Volker Kress
  • Patent number: 8894366
    Abstract: This wheel comprises a plurality of vanes (2) arranged on a crown (3) and is equipped with a tip-forming member (10) attached to a central region (32) of the crown or hub of the wheel (1), radially inside the vanes (2), the crown defining a wet surface (31) for guiding a flow (E) passing between the vanes. The tip-forming member (10) is provided with at least one opening (121) for diverting a fraction (E1) of the flow towards the internal volume (V10) of this member. This member comprises a frustoconical annular skirt (11) and at least one fin (15) arranged in its internal volume (V10) and able to modify the path of the flow fraction (E1) entering this volume through the opening (121). This fin (15) extends as far as the edge (112) of the skirt (11) which defines an outlet opening (14) of the member (10) for the flow fraction (E1).
    Type: Grant
    Filed: March 4, 2009
    Date of Patent: November 25, 2014
    Assignee: Alstom Renewable Technologies
    Inventors: Farid Mazzouji, Danièle Bazin, Michel Couston, Claude Beral, Jacques Bremond
  • Patent number: 8881397
    Abstract: A method for designing an air cooled turbine airfoil includes selecting a number of different internal cooling air circuits, forming a ceramic core for each of the different cooling air circuits, forming a metal airfoil over each of the ceramic cores, leaching away the ceramic cores, mounting the airfoils in a stage of a turbine, passing a hot gas stream through the turbine, passing cooling air through each of the airfoils, and measuring a pressure and temperature differential across each of the airfoils to determine which cooling air circuit has the best performance.
    Type: Grant
    Filed: October 16, 2012
    Date of Patent: November 11, 2014
    Assignee: Florida Turbine Technologies, Inc.
    Inventor: Adam R Dowd
  • Publication number: 20140314575
    Abstract: Provided is a turbo fan. The turbo fan includes a main plate rotating by a fan motor providing power and a plurality of blades having one ends connected to the main plate, the plurality of blades being disposed along a circumferential direction on the main plate. Each of the plurality of blades includes a first curved part curved in one direction with respect to an extension part and a second curved part curved in the other direction with respect to the extension part. A plurality of projections protruding in one direction from the one end of the blade and a plurality of grooves protruding in the other direction are alternately disposed on the first and second curved parts.
    Type: Application
    Filed: December 31, 2013
    Publication date: October 23, 2014
    Applicant: LG Electronics Inc.
    Inventors: Namjoon Cho, Dongkeun Yang, Youngmin Park
  • 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: 8827649
    Abstract: A fan assembly according to an exemplary embodiment of the present invention includes: a hub; and a plurality of blades including a leading edge corresponding to a side hit by air and a trailing edge corresponding to an opposite side of the leading ledge, the plurality of blades configured to be extended radially from an outer peripheral surface of the hub, wherein each of the plurality of blades includes a first part extended radially from the outer peripheral surface of the hub, a bent part stepped on the end of the first part, and a second part further extended radially on the end of the bent part.
    Type: Grant
    Filed: July 12, 2011
    Date of Patent: September 9, 2014
    Assignee: LG Electronics Inc.
    Inventors: Myoungju Kang, Jindong Kim, Hosan Kim
  • Patent number: 8821123
    Abstract: A double-ducted fan includes a hub, a rotor having a plurality of blades rotatably and coupled to the hub, a first duct, a second duct, and a channel defined between the first duct and second duct. The first duct circumscribes the rotor, and the second duct circumscribes at least a portion of the first duct. The second duct can be oriented axially upward such that there is an axial distance is between the leading edges of the first duct and second duct. The channel can be configured to direct air flow cross-wise to the first duct over a top of the first duct into the inlet side of the fan. The second duct can be movable relative to the first duct to adjust at least a portion of the channel. The length of the first duct can be different from the length of the second duct.
    Type: Grant
    Filed: March 4, 2011
    Date of Patent: September 2, 2014
    Assignee: The Penn State Research Foundation
    Inventors: Cengiz Camci, Ali Akturk
  • Patent number: 8794903
    Abstract: A wind energy systems includes a shroud for each turbine. The shroud is adapted to direct and accelerate wind towards the turbine. A strong adaptable support assembly is provided for securing turbines to a structure. An air glide yaw assembly facilitates rotational movement of the structure allowing the turbines to face oncoming wind. The turbine blades are optimized for use with a shroud.
    Type: Grant
    Filed: March 27, 2012
    Date of Patent: August 5, 2014
    Assignee: Green Energy Technologies, LLC
    Inventors: John W. Fedor, Mark L. Cironi
  • Patent number: 8777554
    Abstract: A fan system is disclosed having a forward fan stage configured to pressurize an airflow and an aft fan stage having a tip-fan configured to pressurize a first portion of a pressurized air flow from the forward fan stage wherein the aft fan stage is driven by a second portion of the pressurized airflow.
    Type: Grant
    Filed: August 27, 2010
    Date of Patent: July 15, 2014
    Assignee: General Electric Company
    Inventor: John Lewis Baughman
  • Publication number: 20140193260
    Abstract: A radial pump for water has a drive motor, a pump chamber and an impeller revolving in the pump chamber. The impeller has a plurality of impeller blades which are designed, at least in regions, to be elastic and have a fixed mounting arranged in a region located near the impeller axis of rotation. They can bend elastically radially outward from this fixed mounting counter to a spring force.
    Type: Application
    Filed: June 22, 2012
    Publication date: July 10, 2014
    Applicant: E.G.O. ELEKTRO-GERAETEBAU GMBH
    Inventors: Volker Block, Tobias Albert