Reverse Curve Surface Patents (Class 416/242)
  • Patent number: 9879539
    Abstract: A method is provided for designing an airfoil. The method includes considering a baseline airfoil having a first camber distribution and a first aerodynamic efficiency; reducing the first camber distribution to result in a reduced camber airfoil with a second camber distribution and a second aerodynamic efficiency such that the second aerodynamic efficiency is approximately equal to the first aerodynamic efficiency; and producing the airfoil with the second camber distribution.
    Type: Grant
    Filed: November 18, 2014
    Date of Patent: January 30, 2018
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventor: Jeff Lentz
  • 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
  • Publication number: 20150044058
    Abstract: A leading edge of a blade has a first curved portion provided with a leading-edge rearmost point, and a trailing edge of the blade has a second curved portion located on the inner circumferential side of the trailing edge and a third curved portion located on the outer circumferential side of the blade on the trailing edge. The third curved portion has a trailing-edge foremost point, and the second curved portion has a trailing-edge rearmost point. The trailing edge and a first concentric circle, which is one of concentric circles having as their center an axis of rotation and passes through the leading-edge rearmost point, intersect each other at a first intersection. The first intersection is located between the trailing-edge rearmost point and the trailing-edge foremost point.
    Type: Application
    Filed: July 31, 2014
    Publication date: February 12, 2015
    Inventors: Shingo HAMADA, Seiji NAKASHIMA, Takashi IKEDA, Takahide TADOKORO, Takuya KODAMA, Takashi KOBAYASHI, Hiroshi YOSHIKAWA, Hiroaki MAKINO
  • Publication number: 20150030441
    Abstract: A fan blade structure applied to a centrifugal fan is provided. The fan blade structure includes a wheel hub and an annular vane. The wheel hub includes a plurality of connecting brackets, and the annular vane includes multiple crests and troughs which interlace to form a continuous curved surface. The continuous curved surface has an outer ring surface and an inner ring surface. The connecting brackets are connected to the inner ring surface and drive the annular vane to rotate.
    Type: Application
    Filed: December 4, 2013
    Publication date: January 29, 2015
    Applicant: ASUSTeK COMPUTER INC.
    Inventors: Ming-Hsiu WU, Sung-Chuan HUANG, Yi-Chi LAI, Ta-Ching KUAN
  • 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
  • Publication number: 20140363306
    Abstract: An axial-flow fan has a blade with a recessed part that is recessed toward a front edge formed in a rear edge of the blade. A rounded stress-relieving part is formed in a positive pressure surface side and a negative pressure surface side of a front-edge-side edge part of the recessed part as seen in a cross-sectional view of the blade.
    Type: Application
    Filed: December 26, 2012
    Publication date: December 11, 2014
    Inventors: Azumi Kojima, Yuuta Yokoyama
  • Publication number: 20140356154
    Abstract: The present disclosure provides a subsonic rotor and/or stator blade profile of an axial turbomachine compressor, such as a turbojet. The blade comprises a leading edge with an S-shaped lateral profile in its mid-plane. Specifically, the profile includes, from its inner end to the outer end, a first convex portion including the foremost point of the blade, and a second concave portion including the rearmost area of the blade. This profile enables the fluid flow between 20% and 80% of the blade's length to be redistributed. This so-called “sweep” profile increases the performance of the stage with such blades because it reduces blade tip vortex losses as well as secondary losses.
    Type: Application
    Filed: May 15, 2013
    Publication date: December 4, 2014
    Applicant: Techspace Aero S.A.
    Inventor: Vasiliki Iliopoulou
  • Publication number: 20140348660
    Abstract: A blade cascade of a continuous-flow machine is disclosed. The blade cascade has at least one side wall that is constructed in a wave-like manner in the peripheral direction and has at least one elevation and at least one depression. At least a profile-like rib is integrated in or combined with the side wall, which has a blade profile with a pressure side and with an opposite suction side. A continuous-flow machine with such a blade cascade is also disclosed.
    Type: Application
    Filed: May 23, 2014
    Publication date: November 27, 2014
    Applicant: MTU Aero Engines AG
    Inventors: Yavuz GUENDOGDU, Jochen Gier, Karl Engel
  • Publication number: 20140294595
    Abstract: Rotor blade assemblies for wind turbines are provided. In one embodiment, a rotor blade assembly includes a rotor blade having exterior surfaces defining a pressure side, a suction side, a leading edge, and a trailing edge each extending between a tip and a root. The rotor blade further defines a span and a chord. A span-wise portion of the pressure side includes along a chord-wise cross-section a plurality of inflection points. The plurality of inflection points include a first inflection point and a second inflection point, the first and second inflections points positioned within approximately 50% of the chord from the leading edge.
    Type: Application
    Filed: March 28, 2013
    Publication date: October 2, 2014
    Applicant: General Electric Company
    Inventor: General Electric Company
  • Patent number: 8814495
    Abstract: A wind blade device for rotating a wind turbine is provided. The wind turbine generates wind-generated electric power in residential, business, industrial, and electric utility applications. The wind blade device comprises a drive shaft mountable to the wind turbine. A first wing extends from one side of the drive shaft and a second wing extends from an opposite side of the drive shaft. At least a portion of the first wing distant from the drive shaft is curved in a first direction and at least a portion of the second wing distant from the drive shaft is curved in a second direction. The first wing and the second wing maximize surface area to the wind and receive the wind from any direction.
    Type: Grant
    Filed: December 30, 2010
    Date of Patent: August 26, 2014
    Inventor: Douglas Soucy
  • 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
  • Publication number: 20140227102
    Abstract: A rotor blade for a compressor of a turbomachine is disclosed, the rotor blade having an airfoil having a leading edge, a trailing edge, an airfoil tip, as well as a pressure side and a suction side extending therebetween, provision being made for a profile variation on the pressure side, the profile variation extending into the trailing edge and into the airfoil tip. Also disclosed are a compressor and a turbomachine.
    Type: Application
    Filed: June 1, 2012
    Publication date: August 14, 2014
    Applicant: MTU Aero Engines AG
    Inventor: Harald Schoenenborn
  • Publication number: 20140219805
    Abstract: A fan blade for a gas turbine engine includes: a straight axial dovetail, an airfoil, and a transition section disposed between the dovetail and the airfoil, the fan blade having opposed pressure and suction sides, and further including at least one shoulder protruding from a nominal surface of a selected one of the pressure and suction sides, wherein the at least one shoulder includes a boss defining a side face, and an upper section extending radially outward from the boss and tapering inward to join a nominal surface of the selected side.
    Type: Application
    Filed: September 10, 2012
    Publication date: August 7, 2014
    Inventors: Jorge Orlando Lamboy, Nicholas Joseph Kray, Gerald Alexander Pauley, Qiang Li, Daniel Allen Wilkin, II, Tod Winton Davis
  • Patent number: 8757982
    Abstract: A wind turbine includes a rotor having a hub and at least one blade having a torsionally rigid root, an inboard section, and an outboard section. The inboard section has a forward sweep relative to an elastic axis of the blade and the outboard section has an aft sweep.
    Type: Grant
    Filed: January 23, 2008
    Date of Patent: June 24, 2014
    Assignee: General Electric Company
    Inventor: Kyle Kristopher Wetzel
  • Patent number: 8753086
    Abstract: An impeller includes a substantially cylindrical cup portion arranged to rotate about a center axis, a plurality of blades fixed to an outer circumferential surface of the cup portion for unitary rotation with the cup portion to draw air from one axial side and discharge the air to the other axial side, and an annular connector portion arranged to interconnect the blades. The connector portion has a substantially cylindrical shape in a position spaced apart about 70% to about 90% of the radial length of the blades from the base of each of the blades on the outer circumferential surface of the cup portion, and the ratio of a total axial height of the connector portion to a total radial gap between the outer circumferential surface of the cup portion and the inner circumferential surface of the connector portion is equal to or smaller than about 0.9.
    Type: Grant
    Filed: February 14, 2011
    Date of Patent: June 17, 2014
    Assignee: Nidec Servo Corporation
    Inventors: Asahi Higo, Seung-Sin Yoo, Osamu Sekiguchi, Taro Tanno
  • 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: 8678745
    Abstract: The invention relates to a Wells turbine, comprising a hub having a plurality of rotor blades having a drop-shaped symmetrical profile originating from a leading edge; the rotor blades have a threading line, whose course in the rotation plane of the Wells turbine deviates in relation to a radial beam associated with the respective rotor blade at least in parts of the radial extension of the rotor blade, the threading line comprising at least one curved area.
    Type: Grant
    Filed: January 31, 2009
    Date of Patent: March 25, 2014
    Assignee: Voith Patent GmbH
    Inventors: Raphael Arlitt, Thomas Carolus, Ken Tease
  • Patent number: 8668461
    Abstract: Wind turbine rotor blade with a longitudinal axis, a blade tip, a blade root, a leading edge, a trailing edge and a cross-section arranged orthogonally to the longitudinal axis and changing from the blade root to the blade tip, is the cross-section being formed at the blade root and in the middle of the rotor blade by an aerodynamic profile, and an imaginary reference plane arranged with respect to the rotor blade which includes the longitudinal axis of the rotor blade, wherein, in a cross-section, an angle ?3 is defined between the reference plane and a straight line, which connects the longitudinal axis with the trailing edge, and describes the position of the trailing edge, wherein the angle ?3 increases with decreasing distance from the blade root in a first longitudinal portion of the rotor blade and decreases with decreasing distance from the blade root in a second longitudinal portion.
    Type: Grant
    Filed: July 9, 2010
    Date of Patent: March 11, 2014
    Assignee: Nordex Energy GmbH
    Inventor: Gunter Fischer
  • Patent number: 8668462
    Abstract: Wind turbine rotor blade with a blade tip, a blade root, a leading edge, a trailing edge, a pressure side, a suction side and a cross-section, which changes from the blade tip to the blade root, the longitudinal portion being arranged between the blade root and the middle of the rotor blade, has the following: a convex pressure side portion, which extends from the leading edge up to a pressure-side inflection point, a concave pressure side addition portion, which connects with the pressure-side inflection point with a continuous curvature and extends up to the trailing edge, a convex suction side portion, which extends from the leading edge up to a suction-side kink or inflection point, and a suction side addition portion, which extends from the suction side kink or inflection point up to the trailing edge.
    Type: Grant
    Filed: July 9, 2010
    Date of Patent: March 11, 2014
    Assignee: Nordex Energy GmbH
    Inventors: Gunter Fischer, Hermann Rochholz
  • Publication number: 20140037459
    Abstract: An airfoil for a gas turbine engine comprises a radially extending body having a transverse cross-section. The transverse cross-section comprises a leading edge, a trailing edge, a pressure side and a suction side. The pressure side extends between the leading edge and the trailing edge with a predominantly concave curvature. The suction side extends between the leading edge and the trailing edge with a predominantly convex curvature. The suction side includes an approximately flat portion flanked by forward and aft convex portions. In another embodiment, the suction side includes a series of local curvature changes that produce inflection points in the convex curvature of the suction side spaced from the trailing edge.
    Type: Application
    Filed: August 3, 2012
    Publication date: February 6, 2014
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Andrew S. Aggarwala, Eunice Allen-Bradley, Eric A. Grover, Ricardo Trindade
  • Publication number: 20140023516
    Abstract: A diagonal impeller for a diagonal fan (11), comprising a carrier plate (33) over the outer periphery of which a plurality of vanes (36) are distributed, wherein the vanes (36) have a leading edge (81) and a trailing edge (82), which are interconnected by outer edges (84) formed at the vane end (37), and the leading edge (81) and the trailing edge (82) extend in a manner directed radially outwardly and inclined upstream, wherein a vane face of the vane (36) is three-dimensionally twisted and the vane (36) is inclined in the direction of rotation relative to the meridian line, such that the leading edge (81) is oriented ahead of the trailing edge (82), and wherein an outer leading corner region (86) formed by the leading edge (81) and the outer edge (84) is inclined in an increased manner in the direction of rotation and/or a trailing corner region (88) formed between the trailing edge (82) and the outer edge (84) is inclined in an increased manner against the direction of rotation. (See FIG. 1).
    Type: Application
    Filed: January 31, 2013
    Publication date: January 23, 2014
    Applicant: ruck Ventilatoren GmbH
    Inventor: Gerhard Ruck
  • Patent number: 8613592
    Abstract: A guide blade of a turbomachine, in particular of a compressor, a blade of the guide blade without an inner shroud having a flow inlet edge, a flow outlet edge, a suction side, and a pressure side. The blade is formed by a plurality of blade sections stacked one on top of the other in the radial direction, and the centers of gravity of the blade sections extend along a stacking axis. The blade sections are stacked one on top of the other in the radial direction in such a way that, in a radially inner section of the blade adjacent to a radially outer section of the blade, the stacking axis has its single inflection point in its radial curvature, namely, between a first, radially inner subsection of the radially inner section in which the stacking axis has a concave curvature toward the pressure side, and a second, radially outer subsection of the radially inner section in which the stacking axis has a concave curvature toward the suction side.
    Type: Grant
    Filed: April 7, 2011
    Date of Patent: December 24, 2013
    Assignee: MTU Aero Engines GmbH
    Inventor: Sergio Elorza Gomez
  • Publication number: 20130336774
    Abstract: The invention relates to a centrifugal pump (1) comprising a pump housing (2) which is provided with an axial inlet (6), an outlet (5) and a rotor (7) which is attached in the pump housing (2) such that it can rotate about an axial rotation axis A. The rotor (7) is provided with a central boss (9), a shaft shield (11) fastened to the boss (9), a suction shield (12) attached so as to be axially set apart from the shaft shield (11), which suction shield (12) has an axial supply (14) aligned with the axial inlet (6) of the pump housing (2), and a plurality of rotor blades (15) which are fastened between the shields (11, 12). The radial inner ends (18) of the rotor blades (15) are connected to the suction shield (12) by a substantial perpendicular connection.
    Type: Application
    Filed: December 1, 2011
    Publication date: December 19, 2013
    Applicant: IHC HOLLAND IE B.V.
    Inventors: Cornelis Hendrik van den Berg, Hasan Hüseyin Bugdayci, Erwin Cornelis Johannes Bijvoet, Mattheus Abraham Manneke
  • Patent number: 8602739
    Abstract: A wind turbine rotor blade with an airfoil profile having an upwind side, a downwind side is provided. A stall inducing device is located at the upwind side of the airfoil profile.
    Type: Grant
    Filed: July 17, 2008
    Date of Patent: December 10, 2013
    Assignee: Siemens Aktiengesellschaft
    Inventors: Peder Bay Enevoldsen, Søren Hjort, Jesper Laursen, Anders Vangsgaard Nielsen, Rune Rubak
  • Publication number: 20130323065
    Abstract: A fan rotor blade has a rotor blade leading edge. On a hub side of the rotor blade leading edge, a vertical hub section is formed. From a top end of the vertical hub section to a mid-span side of the rotor blade leading edge, a backward tilt mid-span section is formed. From a top end of the backward tilt mid-span section to a tip end of the rotor blade leading edge, a forward tilt tip section is formed. From a hub end of the rotor blade leading edge to a base end of the vertical hub section, a backward tilt hub section is formed. The backward tilt hub section is backwardly tilted so that a top end thereof is positioned behind a base end thereof.
    Type: Application
    Filed: December 16, 2011
    Publication date: December 5, 2013
    Applicant: IHI Corporation
    Inventor: Takeshi Murooka
  • Patent number: 8579593
    Abstract: An airfoil (10) is provided with a tip (12) having an opening (14) to a center channel (24). A damping element (16) is inserted within the opening of the center channel, to reduce an induced vibration of the airfoil. The mass of the damping element, a spring constant of the damping element within the center channel, and/or a mounting location (58) of the damping element within the center channel may be adjustably varied, to shift a resonance frequency of the airfoil outside a natural operating frequency of the airfoil.
    Type: Grant
    Filed: November 6, 2009
    Date of Patent: November 12, 2013
    Assignee: Siemens Energy, Inc.
    Inventors: Christian X. Campbell, John J. Marra
  • Publication number: 20130224039
    Abstract: The present invention relates to a rotor for a vertical wind power station comprising a plurality of planar rotor elements (2A, 2B, 2C) that are arranged around a hub region (3), wherein the rotor elements (2A, 2B, 2C) have a helical axis which is parallel or inclined relative to an axis of rotation (4) of the rotor (1) and around which the rotor elements (2A, 2B, 2C) are twisted in a spiraling manner, the rotor elements (2A, 2B, 2C) having concave and convex surface regions smoothly merging into each other and having different radii of curvature along the helical axis.
    Type: Application
    Filed: April 6, 2012
    Publication date: August 29, 2013
    Inventor: Josef Moser
  • Publication number: 20130224040
    Abstract: A turbomachine blade with a localized dihedral feature has a high order polynomial shaped curve region.
    Type: Application
    Filed: April 24, 2012
    Publication date: August 29, 2013
    Inventor: Joseph C. Straccia
  • Patent number: 8517690
    Abstract: The invention relates to an aerodynamic profile for the root of a wind turbine blade having a double leading edge, including a leading edge (13), a trailing edge (15) and suction and pressure sides (17, 19) between the leading edge (13) and the trailing edge (15). The profile (5, 5?, 5?) has a relative thickness in the 30%-50% range in at least one section (37) of the root region (31). In addition, the convex portion (21) of the pressure side (19) is configured such that the curvature thereof decreases from a value C0 at the leading edge (13) to a value C1 at a first point P1 and subsequently increases to a value C2 at a second point P2, after which it decreases to a value 0 at the end of the convex portion (21).
    Type: Grant
    Filed: November 10, 2008
    Date of Patent: August 27, 2013
    Assignee: Gamesa Innovation & Technology, S.L.
    Inventors: Gideon Nagy, Ignacio Romero Sanz, Mario Jimenez De Lago
  • Publication number: 20130189116
    Abstract: A swept wind turbine blade (20) includes a blade body (24) extending along a length between a root (26) and a tip (28) of the blade (20). A pitch axis (36) extends through the root (26) of the blade (20). A reference line (48) defines a deviation from the pitch axis (36) and corresponds to a swept shape of the blade (20) along its length. The reference line (48) has a zero sweep at the root (26), a zero slope at the root (26), and a positive curvature (66) along a segment within 25% of the length from the root (26) to the tip (28) of the blade (20).
    Type: Application
    Filed: January 25, 2012
    Publication date: July 25, 2013
    Inventors: John M. Obrecht, Lasse Gilling, Henrik Fredslund Hansen, Scott J. Johnson, Ryan A. Sievers
  • Patent number: 8480372
    Abstract: A system including an airfoil portion of an unshrouded turbine bucket, which includes a pressure-side surface and suction-side surface each extending from a root surface to a tip surface and joined at a leading edge and a trailing edge, the pressure-side surface having a generally concave shape and the suction-side surface having a generally convex shape; the airfoil portion having an increasing stagger angle in a span-wise direction from the root surface to the tip surface and an increasingly loaded suction-side surface as the suction-side surface approaches the tip surface and the tip surface approaches the leading edge, the airfoil portion having a resultant lean in a direction of the suction-side surface as the leading edge approaches the tip surface, and the pressure-side surface and the suction-side surface each having a locally reduced or reversed curvature in a direction of the pressure-side surface at their intersection with the tip surface.
    Type: Grant
    Filed: November 6, 2008
    Date of Patent: July 9, 2013
    Assignee: General Electric Company
    Inventor: Scott Matthew Sparks
  • Patent number: 8464426
    Abstract: A method of designing an airfoil for a gas turbine engine according to one embodiment of this disclosure can include localizing a sweep angle at a leading edge of a tip region of the airfoil, and localizing a dihedral angle at the tip region of the airfoil. The dihedral angle can be applied by translating the airfoil in direction normal to a chord of the airfoil.
    Type: Grant
    Filed: April 2, 2012
    Date of Patent: June 18, 2013
    Assignee: United Technologies Corporation
    Inventors: Jody Kirchner, Yuan Dong, Sanjay S. Hingorani
  • Patent number: 8439645
    Abstract: A two-stage high pressure turbine includes a second stage blade having an airfoil with a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.
    Type: Grant
    Filed: March 30, 2010
    Date of Patent: May 14, 2013
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: Panagiota Tsifourdaris
  • Patent number: 8393872
    Abstract: An airfoil is provided and includes a pressure surface and a suction surface. Radially corresponding surface characteristics of the pressure and suction surfaces at a spanwise local portion of the airfoil are formed to cooperatively define at least one of a camber line and a thickness distribution plot of the airfoil as having a radius of curvature with at least two sign changes. The number of sign changes decreases along a radial dimension of the airfoil measured from the spanwise local portion.
    Type: Grant
    Filed: October 23, 2009
    Date of Patent: March 12, 2013
    Assignee: General Electric Company
    Inventor: Kevin Richard Kirtley
  • Publication number: 20130028747
    Abstract: A fan propeller comprises blades (14), each of which has a general profile of the aircraft wing type, with a leading edge (28) and a trailing edge (30), a neutral axis (32) and a span (36) between the leading edge (28) and the trailing edge (30). According to one embodiment, the blade (14) has, on at least part of its length, a profile shaped such that the neutral axis (32) makes possible a point of contraflexure (34), and has two opposite concavities, i.e. a positive concavity (C1) between the leading edge (28) and the point of contraflexure (34), and a negative concavity (C2) between the point of contraflexure (34) and the trailing edge (30). Application to motor vehicles.
    Type: Application
    Filed: November 8, 2010
    Publication date: January 31, 2013
    Applicant: VALEO SYSTEMES THERMIQUES
    Inventors: Manuel Henner, Bruno Demory
  • Patent number: 8337164
    Abstract: An object is to provide a turbomolecular pump with rotor and stator blades alternatively arranged that can prevent collision between the adjacent rotor and stator blades due to air inrush, which may take place due to vacuum break in a system operation, prevent excessive centrifugal force to a hub portion of a rotor, and further enhance pumping performance. A blade cross sectional profile taken along the circumferential direction of each of the rotor blades of a rotor blade stage has an upstream portion curved convexly backward in a rotational direction of the rotor and a downstream portion curved convexly forward in the rotational direction of the rotor, thereby forming the blade cross sectional profile into an S-shape or inversed S-shape.
    Type: Grant
    Filed: July 9, 2009
    Date of Patent: December 25, 2012
    Assignee: Osaka Vacuum, Ltd.
    Inventors: Tetsuro Ohbayashi, Takeshi Shoji
  • Patent number: 8277192
    Abstract: An airfoil profile is formed such that a passage width ratio, represented in a dimensionless manner, of an inter-blade passage width of vane root cross-section to an outlet throat width substantially monotonously decreases from a blade inlet toward a blade outlet. The blade has a blade airfoil profile shape in an envelope within a range of .+?.2.0 mm in a direction normal to any surface location of an airfoil profile portion. The airfoil profile portion has a reference airfoil contour represented in Cartesian coordinates wherein Z is a distance representing a sectional height from a root of the airfoil profile portion. The contours represented by X and Y at each section Z are joined smoothly with one another in a blade height direction to form a complete shape of the airfoil profile portion.
    Type: Grant
    Filed: January 23, 2008
    Date of Patent: October 2, 2012
    Assignee: Hitachi, Ltd.
    Inventors: Nobuaki Kizuka, Hidetaro Murata, Hidetoshi Kuroki, Kenji Nanataki
  • Patent number: 8272838
    Abstract: An impeller includes an impeller body which rotates about a rotation axis, and a vane which is provided at the impeller body. The impeller body receives force asymmetric with respect to the rotation axis in driving and rotation in a fluid in a manner that radially inward fluid force, which is generated due to arrangement of the vane, acts on a predetermined point in a peripheral direction. In the impeller body, a filled space filled, in a fluid, with the fluid is formed.
    Type: Grant
    Filed: July 28, 2009
    Date of Patent: September 25, 2012
    Assignee: Shinmaywa Industries, Ltd.
    Inventors: Kazuki Takeuchi, Hiroshi Kanki, Motonobu Tarui, Nobukazu Tanaka
  • Publication number: 20120201692
    Abstract: A rotor of a turbomachine compressor, including a bladed rotor disk fitted at its radially external end with a wall forming the inner end of an annual flow channel of a primary gas flow, and formed from multiple angular sectors, each of which is delimited between two blades of the disk which are consecutive in a circumferential direction and includes a bulging portion which is convex in the axial direction and in the circumferential direction, together with, upstream from the bulging portion, a troughed portion which is concave in the axial direction and in the circumferential direction and which has a base which is roughly punctiform.
    Type: Application
    Filed: October 1, 2010
    Publication date: August 9, 2012
    Applicants: CENAERO, SNECMA
    Inventors: Eric Jacques Boston, Alexandre Franck Arnaud Chartoire, Vasiliki Iliopoulou, Ingrid Lepot, Thierry Jean-Jacques Obrecht
  • 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: 8215916
    Abstract: The axial flow fan includes a plurality of blades disposed around and rotating together with the rotation shaft, the blades each including a leading edge, a trailing edge, a leading edge portion proximate the leading edge, a trailing edge portion proximate the trailing edge, a suction surface, a pressure surface, the suction surface having a curved shape; wherein the blade trailing edge portion has a constant thickness; and the trailing edge is formed in a semi-circle which is bi-sected by a mean camber line of the air foil.
    Type: Grant
    Filed: May 2, 2008
    Date of Patent: July 10, 2012
    Assignee: Mitsubishi Electric Corporation
    Inventors: Kiyonori Koga, Shoji Yamada
  • Patent number: 8192153
    Abstract: A circumferential row of aerofoil members span an annular duct for carrying a flow of compressible fluid. The duct is centered on the axis of a turbomachine. Pressure and suction surfaces of neighboring aerofoil members bound respective sectoral passages which receive the flow of compressible fluid. The row of aerofoil members includes at least one radial endwall to which the tangent to the trailing edge of each aerofoil member at midspan is substantially orthogonal. Each aerofoil member has reverse compound lean. Each aerofoil member further has a leading edge which has a position at the endwall which is upstream of its position at midspan. The endwall at each sectoral passage has a non-axisymmetrical cross-section formed by a region that, in meridional section, is convexly profiled immediately adjacent the pressure surface and a region that, in meridional section, is concavely profiled immediately adjacent the suction surface.
    Type: Grant
    Filed: February 25, 2008
    Date of Patent: June 5, 2012
    Assignee: Rolls-Royce PLC
    Inventors: Neil William Harvey, Mark Richard Stokes, David Andrew Bagshaw
  • Patent number: 8182232
    Abstract: A wind turbine blade having an aerodynamic profile (5) with a leading edge (11), a trailing edge (13) and suction and pressure sides (17, 19) between the leading edge (11) and the trailing edge (13) which has, on at least one part of the wind turbine blade, a Trailing Edge Region (TER), the transversal section of which increases in the direction of the trailing edge (13). Said trailing edge region (TER) preferably has a divergent form with a curved concave surface on its lower part.
    Type: Grant
    Filed: May 29, 2007
    Date of Patent: May 22, 2012
    Assignee: Gamesa Innovation & Technology, S.L.
    Inventor: Mark Olaf Slot
  • Patent number: 8167567
    Abstract: A rotor blade for a gas turbine engine includes an airfoil that extends in span between a root and a tip region. A leading edge and a trailing edge of the airfoil section extend between a chord line of the airfoil. A sweep angle is defined at the leading edge of the airfoil section, and a dihedral angle is defined relative to the chord line of the airfoil section. The sweep angle and the dihedral angle are localized at the tip region of the airfoil section.
    Type: Grant
    Filed: December 17, 2008
    Date of Patent: May 1, 2012
    Assignee: United Technologies Corporation
    Inventors: Jody Kirchner, Yuan Dong, Sanjay S. Hingorani
  • Patent number: 8133012
    Abstract: Sectional profiles close to a tip 124 and a part between a midportion 125 and a hub 123 are shifted to the upstream of an operating fluid flow in a sweep direction. Accordingly, an S shape is formed in which the tip 124 and the part between the midportion 125 and the hub 123 protrude. As a result, it is possible reduce various losses due to shook, waves, thereby forming a transonic airfoil having an excellent aerodynamic characteristic.
    Type: Grant
    Filed: September 11, 2007
    Date of Patent: March 13, 2012
    Assignee: Mitsubishi Heavy Industries, Ltd.
    Inventors: Naonori Nagai, Junji Iwatani
  • Patent number: 8096777
    Abstract: A mixed flow turbine or radial turbine suppresses a rapid increase in load applied on a leading edge of a blade, and can reduce incidence loss. The mixed flow turbine or radial turbine includes a hub, and a plurality of blades provided on an outer circumference surface of the hub at substantially equal intervals. The camber line of the blade section is convex-curved to the rotational direction side as seen entirely from a leading edge side toward trailing edge side. On a leading edge section of the blade, there is provided an inflected section that is inflected so that a camber line in a sectional surface along the outer circumference surface is concave-curved to the rotational direction side.
    Type: Grant
    Filed: February 9, 2007
    Date of Patent: January 17, 2012
    Assignee: Mitsubishi Heavy Industries, Ltd.
    Inventors: Takao Yokoyama, Hirotaka Higashimori, Motoki Ebisu, Takashi Shiraishi
  • Patent number: 8092189
    Abstract: Radial cross sections of front sides in rotational direction of impellers attached to a pump shaft obliquely to a circumferential direction from an upstream side toward a downstream side have concave shapes protruding toward the upstream side, and radial cross sections of rear sides in rotational direction of the impellers have concave shapes protruding toward the downstream side.
    Type: Grant
    Filed: January 4, 2007
    Date of Patent: January 10, 2012
    Assignee: Hitachi Plant Technologies, Ltd.
    Inventors: Takanori Ishii, Akira Manabe, Yasuhiro Inoue
  • Patent number: 8079823
    Abstract: A fan blade comprises an airfoil having an upper surface with region that has a generally elliptical curvature. In some examples, the lower surface has a convex region and a concave region. The curvature of the concave region corresponds with the generally elliptical curvature of the upper surface; while the curvature of the convex region is defined by a substantially constant radius. Some examples also include a trailing edge flap region, which may itself include a first flap portion and a second flap portion. When mounted to a rotating hub member fan, blades with elliptical curvatures may provide air movement at significant efficiencies.
    Type: Grant
    Filed: September 20, 2007
    Date of Patent: December 20, 2011
    Assignee: Delta T Corporation
    Inventor: Richard Michael Aynsley
  • Patent number: RE43710
    Abstract: A swept turbomachinery blade for use in a cascade of such blades is disclosed. The blade (12) has an airfoil (22) uniquely swept so that an endwall shock (64) of limited radial extent and a passage shock (66) are coincident and a working medium (48) flowing through interblade passages (50) is subjected to a single coincident shock rather than the individual shocks. In one embodiment of the invention the forwardmost extremity of the airfoil defines an inner transition point (40) located at an inner transition radius rt-inner. The sweep angle of the airfoil is nondecreasing with increasing radius from the inner transition radius to an outer transition radius rt-outer, radially inward of the airfoil tip (26), and is nonincreasing with increasing radius between the outer transition radius and the airfoil tip.
    Type: Grant
    Filed: June 5, 2001
    Date of Patent: October 2, 2012
    Assignee: United Technologies Corp.
    Inventors: David A. Spear, Dennis N. Kantor, legal representative, Bruce P. Biederman, John A. Orosa
  • Patent number: RE45689
    Abstract: A swept turbomachinery blade for use in a cascade of such blades is disclosed. The blade (12) has an airfoil (22) uniquely swept so that an endwall shock (64) of limited radial extent and a passage shock (66) are coincident and a working medium (48) flowing through interblade passages (50) is subjected to a single coincident shock rather than the individual shocks. In one embodiment of the invention the forwardmost extremity of the airfoil defines an inner transition point (40) located at an inner transition radius rt-inner. The sweep angle of the airfoil is nondecreasing with increasing radius from the inner transition radius to an outer transition radius rt-outer, radially inward of the airfoil tip (26), and is nonincreasing with increasing radius between the outer transition radius and the airfoil tip.
    Type: Grant
    Filed: May 21, 2010
    Date of Patent: September 29, 2015
    Assignee: United Technologies Corporation
    Inventors: David A. Spear, Dennis N. Kantor, Bruce P. Biederman, John A. Orosa