Concave Surface Patents (Class 416/243)
  • Patent number: 10844731
    Abstract: A cantilevered vane, for use with a rotary disc of a gas turbine, includes a root supported in a dovetail slot formed in a circumferential surface of the rotary disc; and an airfoil protruding a predetermined height from the root and having a J-shaped cross-section throughout a front-wing portion and a rear-wing portion of the airfoil. The airfoil includes a straight portion vertically extending upward from the root by a predetermined height; and a curved portion integrally formed with an upper end of the straight portion to cantilever toward one side of the airfoil, the curved portion being inclined at a predetermined angle with respect to the straight portion. Cooling fluid flows through a first channel formed in the straight portion and a second channel formed in the curved portion. The first channel includes front-wing and rear-wing channels for guiding the cooling fluid to the front-wing and rear-wing portions.
    Type: Grant
    Filed: May 10, 2018
    Date of Patent: November 24, 2020
    Assignee: Doosan Heavy Industries Construction Co., Ltd
    Inventor: Seol Baek
  • Patent number: 10808538
    Abstract: A turbine rotor blade having an airfoil that includes a pressure side portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a pressure side as set forth in Table I. The Cartesian coordinate values of X, Y, and Z are non-dimensional values from 0% to 100% convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil defined along the Z axis. The X and Y values of the pressure side are coordinate values that, when connected by smooth continuing arcs, define pressure side sections of the pressure side portion of the nominal airfoil profile at each Z coordinate value. The pressure side sections may be joined smoothly with one another to form the pressure side portion.
    Type: Grant
    Filed: October 31, 2018
    Date of Patent: October 20, 2020
    Assignee: General Electric Company
    Inventors: Melbourne James Myers, Sylvain Pierre, Michael Gordon Sherman, Luke C Sponseller, Zhirui Dong, Le Trong Tran
  • Patent number: 10746025
    Abstract: Suction surfaces of blades of this radial turbine each have: a leading edge side of blade tip including a leading edge and the boundary between the suction surface and the tip; and a trailing edge side of blade tip including a trailing edge and the boundary between the suction surface and the tip. The leading edge side of blade tip forms a concave curved surface which is recessed towards the side opposite to the rotation side in a radial view. The trailing edge side of blade tip forms a convex curved surface which protrudes towards the rotation side in a radial view.
    Type: Grant
    Filed: March 2, 2016
    Date of Patent: August 18, 2020
    Assignee: MITSUBISHI HEAVY INDUSTRIES ENGINE & TURBOCHARGER, LTD.
    Inventors: Toyotaka Yoshida, Takao Yokoyama
  • Patent number: 10724383
    Abstract: A modified J-type cantilevered vane reduces rubbing of an airfoil and enhances the vibration stability of a vane hub and the fluidity of fluid. The cantilevered vane includes a root attachment inserted into a slot formed in an inner circumferential surface of a casing of a gas turbine, and an airfoil vertically extending from the root attachment to a predetermined height. The airfoil includes a linear part extending in a radial direction from the inner circumferential surface of the casing toward a rotating shaft of the gas turbine, and a curved part integrally formed with the linear part, the curved part including a bend beginning from one end of the linear part and curving in a circumferential direction of the rotating shaft. Overall, the linear part and the curved part are biased in the circumferential direction, since the airfoil has a J-shaped X-axis profile and a C-shaped Y-axis profile.
    Type: Grant
    Filed: September 19, 2018
    Date of Patent: July 28, 2020
    Assignee: Doosan Heavy Industries Construction Co., Ltd.
    Inventor: Seol Baek
  • Patent number: 10689993
    Abstract: A turbine nozzle having an airfoil that includes a pressure side portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a pressure side as set forth in Table I. The Cartesian coordinate values of X, Y, and Z are non-dimensional values from 0% to 100% convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil defined along the Z axis. The X and Y values of the pressure side are coordinate values that, when connected by smooth continuing arcs, define pressure side sections of the pressure side portion of the nominal airfoil profile at each Z coordinate value. The pressure side sections may be joined smoothly with one another to form the pressure side portion.
    Type: Grant
    Filed: November 15, 2018
    Date of Patent: June 23, 2020
    Assignee: General Electric Company
    Inventors: Sylvain Pierre, Bryan David Lewis, Debdulal Das, Stephen Walter Newman
  • Patent number: 10669853
    Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.
    Type: Grant
    Filed: August 31, 2018
    Date of Patent: June 2, 2020
    Assignee: General Electric Company
    Inventors: Robin Charles Payne, Luis Vega
  • Patent number: 10590773
    Abstract: Disclosed is a blade/vane cascade segment of a blade/vane cascade of a turbomachine, which comprises at least two blade/vane elements defining an axial cascade width, and a stage with a stage surface, as well as a stage edge on the inflow side. The stage surface has an elevation extending up to the pressure side of a first blade/vane element and a depression extending up to the suction side of the other blade/vane. At least one highest point of the elevation and at least one lowest point of the depression each lie at least 30% and at most 60% of the axial cascade width downstream of the inflow edges of the blade/vane elements. In this case, the elevation and the depression each come close to the stage edge on the inflow side.
    Type: Grant
    Filed: February 2, 2018
    Date of Patent: March 17, 2020
    Assignee: MTU Aero Engines AG
    Inventors: Markus Brettschneider, Inga Mahle
  • Patent number: 10442510
    Abstract: A floating wind turbine assembly, configured to self-stabilize in water without a fixed anchor. The floating wind turbine assembly has a wind turbine, joined to a turbine shaft. A beam anchor is joined to the turbine shaft. A hollow moving mass, arranged around the beam anchor, such that the hollow moving mass can be moved up or down the beam anchor. The hollow moving mass includes a pump, having a pump first end connected to the water with a first pump hose and a pump second end arranged within the hollow moving mass with a second pump hose.
    Type: Grant
    Filed: October 31, 2018
    Date of Patent: October 15, 2019
    Assignee: Upy Designs LLC.
    Inventors: Carlos Prieto, Laura Nunez, Meir Messingher Lang, Daniel Curiel
  • Patent number: 10287886
    Abstract: A system is provided, including an airfoil. The airfoil includes a first suction portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a suction side as set forth in TABLE I to a maximum of three decimal places, wherein the X and Y values of the suction side are coordinate values that couple together to define suction side sections of the first suction portion of the nominal airfoil profile at each Z coordinate value, the suction side sections of the first suction portion of the nominal airfoil profile are coupled together to define the first suction portion, the airfoil includes an airfoil length along a Z axis, the first suction portion comprises a first portion length along the Z axis, the first portion length is less than or equal to the airfoil length, and the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances.
    Type: Grant
    Filed: September 22, 2016
    Date of Patent: May 14, 2019
    Assignee: General Electric Company
    Inventors: Paul Griffin Delvernois, Patrick Daniel Noble
  • Patent number: 9759227
    Abstract: An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in a scalable TABLE 1, wherein the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y, and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.
    Type: Grant
    Filed: September 4, 2015
    Date of Patent: September 12, 2017
    Assignee: General Electric Company
    Inventors: Edward Charles Schurr, Svitlana Kalmyk
  • Patent number: 9719591
    Abstract: A continuously variable transmission cooling fan includes a moveable sheave cover attached to a drive clutch assembly of a continuously variable transmission, with a plurality of fan blades molded into the moveable sheave cover and arranged around the perimeter of the moveable sheave cover. Each fan blade may have a different length, curvature and angle of position than the adjacent fan blades. The continuously variable transmission cooling fan also may include a plurality of openings in the moveable sheave cover located radially inwardly from the fan blades.
    Type: Grant
    Filed: October 28, 2015
    Date of Patent: August 1, 2017
    Assignee: DEERE & COMPANY
    Inventors: Jeremie A. Wade, Nathan Yolitz, Hany K. Nakhla, Shankar Narayana
  • Patent number: 9638041
    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; and a base connected with a first end of the airfoil along the suction side, pressure side, trailing edge and the leading edge, the base including a non-axisymmetric contour proximate a junction between the base and the airfoil.
    Type: Grant
    Filed: October 23, 2013
    Date of Patent: May 2, 2017
    Assignee: General Electric Company
    Inventors: Lee Larned Brozyna, Matthew Durham Collier, Christopher William Kester, Alexander Stein
  • Patent number: 9022744
    Abstract: A turbine engine blade having a plurality of blade sections stacked along a radial axis between a root and a tip. Each section extends along a longitudinal axis between a leading edge and a trailing edge, and along a tangential axis between a pressure-side face and a suction-side face. Each section presents a camber line, a deviation defined for each section as the difference between an angle between the tangent to the camber line at the leading edge and the longitudinal axis, and an angle between the tangent to the camber line at the trailing edge and the longitudinal axis. The minimum deviation is at the root of the blade, and the maximum deviation is present at sections situated in the range 0.3H to 0.8H, where H is the height of the blade measured from its root to its tip.
    Type: Grant
    Filed: June 20, 2012
    Date of Patent: May 5, 2015
    Assignee: SNECMA
    Inventors: Renaud Gabriel Constant Royan, Renaud Martet, Jean-Michel Guimbard
  • Publication number: 20150118061
    Abstract: A radial compressor has at least one compressor stage. The compressor stage includes: an impeller having moving blades on a rotor side arranged in a flow channel of the compressor stage. The flow channel is bounded by a hub contour and a housing contour or cover disc contour. Each moving blade has a flow inlet edge and a flow outlet edge. In the region of the compressor stage on the hub contour of the flow channel, initially a curvature change from a first concave curvature into a convex curvature and following this a curvature change from the convex curvature into a second concave curvature is formed; and/or on the housing contour or cover disc contour of the flow channel, initially a curvature change from a first convex curvature into a concave curvature and following this a curvature change from the concave curvature into a second convex curvature is formed.
    Type: Application
    Filed: October 30, 2014
    Publication date: April 30, 2015
    Inventors: André Hildebrandt, Thomas Ceyrowsky
  • Patent number: 9017036
    Abstract: A turbomachine blade with a localized dihedral feature has a high order polynomial shaped curve region.
    Type: Grant
    Filed: April 24, 2012
    Date of Patent: April 28, 2015
    Assignee: United Technologies Corporation
    Inventor: Joseph C. Straccia
  • Patent number: 9017037
    Abstract: A rotor blade comprises an airfoil extending radially from a root section to a tip section and axially from a leading edge to a trailing edge, the leading and trailing edges defining a curvature therebetween. The curvature determines a relative exit angle at a relative span height between the root section and the tip section, based on an incident flow velocity at the leading edge of the airfoil and a rotational velocity at the relative span height. In operation of the rotor blade, the relative exit angle determines a substantially flat exit pressure ratio profile for relative span heights from 75% to 95%, wherein the exit pressure ratio profile is constant within a tolerance of 10% of a maximum value of the exit pressure ratio profile.
    Type: Grant
    Filed: January 24, 2012
    Date of Patent: April 28, 2015
    Assignee: United Technologies Corporation
    Inventors: Constantine Baltas, Dilip Prasad, Edward J. Gallagher
  • Patent number: 8974189
    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: December 8, 2011
    Date of Patent: March 10, 2015
    Assignee: Airbus Helicopters
    Inventors: Marc Gervais, Benoit Gresle, Sébastien Finck, Laurent Sudre
  • Patent number: 8944750
    Abstract: A turbine vane for a gas turbine engine with an airfoil portion including a perimeter wall having first, second, and third sets of cooling holes defined therethrough, including the holes numbered HA-1 to HA-13, HB-1 to HB-13 and PA-1 to PA-9, respectively, and located such that a central axis thereof extends through the respective point 1 and point 2 having a nominal location in accordance with the X, Y, Z Cartesian coordinate values set forth in Table 3.
    Type: Grant
    Filed: December 22, 2011
    Date of Patent: February 3, 2015
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Marc Tardif, Sri Sreekanth, Stephen Conway
  • Patent number: 8939708
    Abstract: A universal spherical reaction turbine for any flowing fluid at any depths or elevation that is capable of unidirectional rotation under reversible flow conditions. The turbine includes a rotatable shaft that is adapted to rotate about an axis of rotation; turbine blade support members that are fixedly attached to the rotatable shaft and a plurality of meridian turbine blades. The meridian turbine blades are fixedly attached to diametrically-opposite points that define a geometrical north-south meridian axis that is oriented at a skew angle to the axis of rotation of the rotatable shaft. The skew angle is greater than zero and less than 180 degrees, and, more preferably, between 25 and 35 degrees. The skewing ensures that those turbine blades that are attached to the diametrically-opposite points move on a helical trajectory with respect to the axis of rotation.
    Type: Grant
    Filed: May 28, 2010
    Date of Patent: January 27, 2015
    Assignee: Northeastern University
    Inventor: Alexander M. Gorlov
  • Patent number: 8936435
    Abstract: A wind turbine blade includes a root region. A first extension (LEX) is attached to the leading edge side of the root region while a trailing edge strake (TES) is attached to the trailing edge side of the root region. The LEX and TES each include an outer profile that becomes more pronounced relative to their respective locations in the root region as the root region of the wind turbine blade morphs from a substantially cylindrical shape to a substantially airfoil shape. The LEX provides both optimal angle of attack and lift generation in the root region, while the TES mitigates airflow separation and enhances airfoil lift in the root region.
    Type: Grant
    Filed: December 16, 2011
    Date of Patent: January 20, 2015
    Assignee: General Electric Company
    Inventors: Anurag Gupta, Arathi Kamath Gopinath
  • 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: 8911215
    Abstract: A compressor blade for an axially permeated compressor, preferably of a stationary gas turbine is provided. The camber line of the blade tip side profile of the blade of the compressor blade includes at least two inflection points for reducing radial gap losses. By means of two inflection points, there is a concavely designed suction side contour segment in a segment from 35% to 50% for the suction side contour, and a convexly implemented pressure side contour segment for the pressure side contour. It is possible by means of the geometry to generate low-loss gap vortices, in order to increase the overall efficiency of an axial compressor including the compressor blades.
    Type: Grant
    Filed: August 10, 2010
    Date of Patent: December 16, 2014
    Assignee: Siemens Aktiengesellschaft
    Inventors: Christian Cornelius, Georg Kröger, Eberhard Nicke
  • Patent number: 8905704
    Abstract: A wind turbine comprising a drive shaft; at least one vane connected to the drive shaft; and a torque converter attached to the vane, the torque converter comprising an airfoil, the torque converter being adapted to capture air for use in aiding the vane to rotate. Certain embodiments include the vane comprising a first surface and a second surface positioned opposite to the first surface, the first surface comprising a plurality of wind disrupters. Certain embodiments include a plurality of vanes rotatably connected to the drive shaft, the plurality of vanes comprising a plurality of strakes adapted to capture air and direct air to the drive shaft. Yet certain embodiments include a first air scoop connected to the vane, the first air scoop comprising a first air scoop portion at an angle relative to the vane.
    Type: Grant
    Filed: January 24, 2012
    Date of Patent: December 9, 2014
    Assignee: Sauer Energy, Inc.
    Inventor: Dieter Sauer
  • Patent number: 8899925
    Abstract: A wind/water turbine has a basic configuration in which both ends of blades which are in rotational symmetry are fixed to support plates, the blades have vanes, one of the vertical sides of the vanes is attached to a vane rotating shaft, and the free opposite sides each rotate freely in a sector extending as far as the adjacent vane rotating shafts on either side. The vanes are arranged such that when the blades of the wind/water turbine are convex, moving against the water flow/airflow, the vanes are pressed by the water flow/airflow and are opened, thereby reducing the rotational resistance, and when the blades have pivoted further and are concave, the spaces between the vane rotating shafts are closed, the water/air pressure is received over the entire surface of the blade, and thus a pivoting force that is increased corresponding to the reduction in rotation resistance is obtained.
    Type: Grant
    Filed: June 7, 2011
    Date of Patent: December 2, 2014
    Inventor: Yoshiji Tamatsu
  • Publication number: 20140348661
    Abstract: A blade row for a turbomachine is disclosed. The blade row has an inner lateral wall and an outer lateral wall for bordering a hot gas channel in the turbomachine through which hot gas passes. At least one of the lateral walls has a rounded lateral wall front edge, which is provided with a circumferentially asymmetrical edge contouring that is elliptical or is comprised of one or more segments of a circle.
    Type: Application
    Filed: May 23, 2014
    Publication date: November 27, 2014
    Applicant: MTU Aero Engines AG
    Inventors: Inga MAHLE, Martin Pernleitner, Karl Engel
  • Patent number: 8882470
    Abstract: A rotor according to a preferred embodiment of the invention has at least one blade arranged at a hub of the rotor, wherein the blade has a curvature between its leading edge and its trailing edge which curvature has a first convex surface and an opposite second concave surface, wherein the first surface is to be arranged against the direction of the wind striking the blades. The convex profile of the first surface and the concave profile of the opposite second surface are spaced by the thickness of the blade which is preferably constant. The hub is arranged at the rotational axis.
    Type: Grant
    Filed: July 12, 2011
    Date of Patent: November 11, 2014
    Inventor: Fritz Unger
  • Patent number: 8876485
    Abstract: The present application provides a turbine nozzle including an airfoil shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches. The X and Y values are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances may be joined smoothly with one another to form a complete airfoil shape.
    Type: Grant
    Filed: November 28, 2011
    Date of Patent: November 4, 2014
    Assignee: General Electric Company
    Inventors: Ross James Gustafson, Aaron Gregory Winn
  • Patent number: 8864440
    Abstract: A vertical axis omni-wind turbine having a wind sail centrally mounted to a turbine drive shaft, the wind sail consisting of three generally identical vanes paced 120 degrees apart. The vanes each have a generally concave surface for capturing impinging wind thrust with an opposite generally convex surface to provide minimal wind resistance. The resulting disparate wind resistance causes a stronger reaction on the concave side of a vane which in turn provides rotation about the vertical oriented drive shaft. The turbine has omni-wind characteristics in that regardless of the wind direction an adequate portion of the concave surface of a rotor blade will always be exposed to impinging wind. The subsequent drive shaft rotation is transmitted to an electrical turbine.
    Type: Grant
    Filed: May 27, 2011
    Date of Patent: October 21, 2014
    Assignee: Sauer Energy, Incc.
    Inventor: Dieter Sauer, Jr.
  • Patent number: 8845296
    Abstract: A turbine bucket is provided including a bucket airfoil having an airfoil shape, the bucket airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein the Z values are non-dimensional values from 0% to 100% convertible to Z distances in inches by multiplying the Z values by a height of the airfoil in inches and adding the radius of the airfoil base, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the profile sections at the Z distances being joined smoothly with one another to form a complete airfoil shape.
    Type: Grant
    Filed: September 19, 2011
    Date of Patent: September 30, 2014
    Assignee: General Electric Company
    Inventors: Matthew Durham Collier, Gayathri Puram, Paul Kendall Smith, Jacob Charles Perry, II
  • Publication number: 20140265335
    Abstract: An electrical generation system. A floating vessel is anchored in flowing water. Inlets in the hull of the vessel capture flowing water and direct the water to one or more turbines. The system is designed so that all flows are two-dimensional to the extent possible. The latter feature greatly simplifies both design and construction.
    Type: Application
    Filed: March 15, 2013
    Publication date: September 18, 2014
    Inventor: Bruno Peter Andreis
  • Patent number: 8834121
    Abstract: A blade front edge of a turbo fan has, between a main-plate-side blade front edge and a shroud-side blade front edge, a projecting blade front edge which distances away from a blade rear edge (located in a rotation direction A) as it furthers away from a main plate, which curves to a position away from a rotation center, and, in a range close to the main plate, a main-plate-side front-edge skirt portion which distances away from the blade rear edge and inclines away from the rotation center as it becomes closer to the main plate. On the other hand, a main-plate-side blade rear edge, which is a range close to the main plate of the blade rear edge, is substantially perpendicular to the main plate and a shroud-side blade rear edge, which is a range close to a shroud, is inclined so as to gradually distance away from the blade front edge (behind in the rotation direction A) as it furthers away from the main plate.
    Type: Grant
    Filed: March 16, 2010
    Date of Patent: September 16, 2014
    Assignee: Mitsubishi Electric Corporation
    Inventors: Takashi Ikeda, Takahide Tadokoro, Masahiko Takagi, Makoto Kurihara
  • 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
  • Publication number: 20140241901
    Abstract: An impeller for increasing the pressure of a fluid circulating in an annular fluid path, the impeller comprising: a plurality of centrifugal compressor vanes circumferentially interspaced around the axis of the annular fluid path, the plurality of compressor vanes extending from an axially-oriented inlet to a radially-oriented outlet, and each having an inner edge and a free edge, the free edge of the plurality of compressor vanes coinciding with an outer limit of the annular fluid path, and a hub having a solid-of-revolution shape centered around an axis, the hub having an outer hub surface forming an inner limit to the annular fluid path and to which the inner edge of the plurality of centrifugal vanes is secured, the outer hub surface having a portion which leans forward, forming an axial recess therein.
    Type: Application
    Filed: February 25, 2013
    Publication date: August 28, 2014
    Applicant: Pratt & Whitney Canada Corp.
    Inventor: PRATT & WHITNEY CANADA CORP.
  • Patent number: 8814525
    Abstract: The profile (1-4) of a rotor blade (5) of a wind power plant is characterized in that the main camber line runs beneath the chord at least in sections in the direction of the pressure side (8). The profile is further characterized in that the profile (1-4) has a relative profile thickness of greater than 45% with a position of maximum thickness of less than 50%, wherein a lift coefficient (ca) of greater than 0.9, particularly greater than 1.4 is achieved in turbulent flow.
    Type: Grant
    Filed: September 10, 2009
    Date of Patent: August 26, 2014
    Assignee: Senvion SE
    Inventors: Marc Petsche, Matthias Korjahn, Bert Gollnick
  • Publication number: 20140234120
    Abstract: A blade comprises a first blade surface, a second blade surface forming the reverse surface of the first blade surface, a front edge portion connected to the front end of the first blade surface and the front end of the second blade surface and formed in a curved shape convex toward the travelling direction, and a back edge portion connected to the back end of the first blade surface and the back end of the second blade surface extending toward the opposite of the travelling direction, and formed in an acute angle, and the blade is formed to be curved in an arc viewed from the side of the travelling direction.
    Type: Application
    Filed: February 18, 2014
    Publication date: August 21, 2014
    Applicant: TECHNOLOGY OF NATURAL PROVIDENCE, INC
    Inventors: Kunihiko AIHARA, Junko AIHARA
  • Publication number: 20140234108
    Abstract: In order to optimise a rotor (1) for a wind turbine (2), comprising a hub (6) which is rotatable about an axis of rotation (15) and a number of rotor blades fixed to the hub (6), at least one rotor blade having at least one curved portion (8) having a curve in the upstream direction, so as to increase the performance of wind turbines (2), it is proposed for a base portion (7) of the curved rotor blade (5), extending from the hub end, to be arranged with the longitudinal axis (14) thereof at a wind correction angle (11) in the upstream direction to a plane (16) orthogonal to the axis of rotation (15).
    Type: Application
    Filed: May 31, 2012
    Publication date: August 21, 2014
    Applicant: DeWind Europe GmbH
    Inventor: Thomas Nägler
  • Patent number: 8807950
    Abstract: The present application provides a turbine nozzle including an airfoil shape. The airfoil shape may have a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1. The Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches. The X and Y values are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The airfoil profile sections at Z distances may be joined smoothly with one another to form a complete airfoil shape.
    Type: Grant
    Filed: November 28, 2011
    Date of Patent: August 19, 2014
    Assignee: General Electric Company
    Inventors: Craig Allen Bielek, Veeraporn Kullatham, Mary Holloway
  • Patent number: 8807951
    Abstract: A blade for a gas turbine engine, according to an exemplary aspect of the present disclosure includes, among other things, a platform and an airfoil that extends from the platform. The airfoil extends in span between a root and a tip region and in chord between a leading edge and a trailing edge. A sweep angle is defined at the leading edge and a dihedral angle is defined relative to the chord of the airfoil. The sweep angle and the dihedral angle are localized at the tip region and extend over a distance of the airfoil equivalent to about 10% to about 40% of the span.
    Type: Grant
    Filed: May 21, 2013
    Date of Patent: August 19, 2014
    Assignee: United Technologies Corporation
    Inventors: Jody Kirchner, Yuan Dong, Sanjay S. Hingorani
  • Patent number: 8790088
    Abstract: A compressor having a compressor blade with a blade tip portion configured to reduce stresses in the blade tip of the compressor blade is provided. The compressor blade includes a first and second faces extending to the blade tip portion. The blade tip portion includes a blade tip, a first recess extending between the first face and the blade tip, and a second recess extending between the second face and the blade tip.
    Type: Grant
    Filed: April 20, 2011
    Date of Patent: July 29, 2014
    Assignee: General Electric Company
    Inventors: John David Dyer, Madhusudan Rao Pothumarthi, Lynn M. Naparty, Michael Ericson Friedman
  • Patent number: 8777564
    Abstract: Airfoils according to embodiments of this invention result in a hybrid controlled flow concept that reduces leakage loss by creating a different vortexing concept near endwall regions of the airfoils than at the core region of the airfoils. Specifically, a turbine static nozzle airfoil is disclosed having a variable, non-linear, throat dimension, s, divided by a pitch length, t, distribution (“s/t distribution”) across its radial length. In one embodiment, a plurality of static nozzle airfoils are provided, with each static nozzle airfoil configured such that a throat distance between adjacent static nozzle airfoils is larger proximate the hub regions of the airfoils than proximate the core regions of the airfoils, and the throat distance between adjacent static nozzle airfoils is smaller proximate the tip regions of the airfoils than proximate the core regions.
    Type: Grant
    Filed: May 17, 2011
    Date of Patent: July 15, 2014
    Assignee: General Electric Company
    Inventors: Xiaoqiang Zeng, Jonathon Edward Slepski
  • Publication number: 20140186186
    Abstract: The invention relates to a hydraulic machine having an impeller wheel that comprises a plurality of impeller blades; having a spiral housing that encloses the impeller wheel and that is open toward said impeller wheel by a circumferential slit formed by two circumferential edges; having a traverse ring, comprising two traverse ring decks that are connected to one another by tension anchors; wherein the spiral housing is composed of segments that meet in the flow direction and that are welded to each other, the ends of which segments stand on the respective traverse ring deck and are welded to said deck; wherein at the meeting point between two segments that are adjacent to one another and one traverse ring deck a stiffening element is provided that protrudes into the inner space of the spiral housing; and wherein the extension of the stiffening element into the inner space of the spiral housing is so small that the flow is not affected in a significant manner.
    Type: Application
    Filed: July 26, 2012
    Publication date: July 3, 2014
    Applicant: Voith Patent GmbH
    Inventors: Sebastian Hyneck, Gerhard Wengert
  • Patent number: 8757967
    Abstract: An axial flow turbine includes in axial flow series a low pressure turbine section and a turbine exhaust system. The low pressure turbine section includes a final low pressure turbine stage having a circumferential row of static aerofoil blades followed in axial succession by a circumferential row of rotating aerofoil blades. Each aerofoil blade has a radially inner hub region and a radially outer tip region. The K value, being equal to the ratio of the throat dimension (t) to the pitch dimension (p), of each static aerofoil blade of the final low pressure turbine stage varies along the height of the static aerofoil blade, between the hub region and the tip region, according to a substantially W-shaped distribution.
    Type: Grant
    Filed: January 23, 2012
    Date of Patent: June 24, 2014
    Assignee: Alstom Technology Ltd
    Inventors: Brian Robert Haller, Gursharanjit Singh
  • Patent number: 8757983
    Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y,Z? given in Table 1, in which the coordinate Z? is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.
    Type: Grant
    Filed: June 29, 2011
    Date of Patent: June 24, 2014
    Assignee: SNECMA
    Inventors: Patrick Girard, Olivier Kueny, Pierre Marche, Ludovic Pintat
  • Publication number: 20140154068
    Abstract: An airfoil array is disclosed. The airfoil array may include an endwall, and a plurality of airfoils radially projecting from the endwall. Each airfoil may have a first side and an opposite second side extending axially in chord between a leading edge and a trailing edge. The airfoils may be circumferentially spaced apart on the endwall thereby defining a plurality of flow passages between adjacent airfoils. The airfoil array may further include a convex profiled region extending from the endwall adjacent to the first side of at least one of said plurality of airfoils near the leading edge of the at least one of said plurality of airfoils, and a concave profiled region in the endwall and extending across said at least one of said plurality of flow passages.
    Type: Application
    Filed: October 30, 2012
    Publication date: June 5, 2014
    Applicant: United Technologies Corporation
    Inventor: United Technologies Corporation
  • Patent number: 8740570
    Abstract: A turbine bucket is provided including a bucket airfoil having an airfoil shape, the bucket airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape.
    Type: Grant
    Filed: November 28, 2011
    Date of Patent: June 3, 2014
    Assignee: General Electric Company
    Inventors: Alexander Stein, Bradley Taylor Boyer, Xiaoyong Fu, Randall Richard Good, William Scott Zemitis
  • Patent number: 8734116
    Abstract: A turbine bucket is provided including a bucket airfoil having an airfoil shape, the bucket airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape.
    Type: Grant
    Filed: November 28, 2011
    Date of Patent: May 27, 2014
    Assignee: General Electric Company
    Inventors: Paul Kendall Smith, Spencer Aaron Kareff, Srinivasa Govardhan Jayana
  • Patent number: 8734115
    Abstract: When cold and in the non-coated state, the aerodynamic profile is substantially identical to a nominal profile determined by the Cartesian coordinates X,Y,Z? given in Table 1, in which the coordinate Z? is the quotient D/H where D is the distance of the point under consideration from a first reference plane P0 situated at the base of the nominal profile, and H is the height of said profile measured from the first reference plane to a second reference plane P1. The measurements D and H are taken radially relative to the axis of the turbine, while the X coordinate is measured in the axial direction of the turbine.
    Type: Grant
    Filed: June 28, 2011
    Date of Patent: May 27, 2014
    Assignee: SNECMA
    Inventors: Jean Bleuzen, Jean-Michel Guimbard, Pierre Marche, Renaud Martet
  • Patent number: 8714930
    Abstract: A turbine bucket is provided including a bucket airfoil having an airfoil shape, the bucket airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape.
    Type: Grant
    Filed: September 12, 2011
    Date of Patent: May 6, 2014
    Assignee: General Electric Company
    Inventors: Jason Douglas Herzlinger, Craig Allen Bielek, Jonathan Glenn Reed, Holly Renae Davis, Luis Manuel Herrera, Ariel Caesar Prepena Jacala, William Scott Zemitis
  • Patent number: 8702398
    Abstract: A rotor blade having an airfoil for a compressor is described. The airfoil has an airfoil root, an airfoil tip located at a spanwise distance from the airfoil root, a leading edge extending from the airfoil root to the airfoil tip, an inner span region (“S1”) between the airfoil root and a first height location on the airfoil leading edge, a midspan region (“S2”) between the first height location and a second height location on the airfoil leading edge located radially outward from the first height location; an outer span region (“S3”) between the second height location and the airfoil tip, wherein the airfoil has a normalized camber profile such that the normalized camber increases in the outer span region in a spanwise direction towards the tip and is more than 2.2 in the outer span region.
    Type: Grant
    Filed: March 25, 2011
    Date of Patent: April 22, 2014
    Assignee: General Electric Company
    Inventors: Andrew Breeze-Stringfellow, David Scott Clark, Brent F. Beacher
  • Patent number: 8684698
    Abstract: An airfoil for a compressor is described. The airfoil has a root, an airfoil tip, a leading edge, a trailing edge, airfoil pressure and suction sides extending between the leading edge and the trailing edge. The airfoil has an inner span region and an outer span region and the trailing edge has a dihedral profile such that the trailing edge dihedral angle decreases in at least a portion of the inner span region and the outer span region.
    Type: Grant
    Filed: March 25, 2011
    Date of Patent: April 1, 2014
    Assignee: General Electric Company
    Inventors: Andrew Breeze-Stringfellow, David Scott Clark, Brent F. Beacher