Unsymmetrical Impeller Or Dissimilar Working Members Patents (Class 416/203)
  • Patent number: 10738627
    Abstract: A fan exit guide vane assembly for a gas turbine engine includes a plurality of guide vanes having a pressure side and a suction side extending between a leading edge and a trailing edge. The vanes further include a span extending between a root and tip with a stagger angle defined as an angle between a longitudinal axis parallel to an engine axis of rotation and a line connecting the leading edge and the trailing edge that is less than about 15°.
    Type: Grant
    Filed: January 15, 2018
    Date of Patent: August 11, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Edward J. Gallagher, Glen E. Potter, Barry M. Ford
  • Patent number: 10590775
    Abstract: An airfoil of a turbine engine includes pressure and suction sides and extends in a radial direction from a 0% span position to a 100% span position. The airfoil has a relationship between a stagger angle and span position that defines a curve with a stagger angle that is greater than 32° from 90% span to 100% span.
    Type: Grant
    Filed: February 12, 2015
    Date of Patent: March 17, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Edward J. Gallagher, Lisa I. Brilliant, Joseph C. Straccia, Stanley J. Balamucki, Mark A. Stephens, Kate Hudon
  • Patent number: 10487840
    Abstract: A temperature destratification assembly can include an outer housing. An impeller can be positioned within the outer housing between the inlet and outlet of the outer housing. The impeller can have an impeller hub and a plurality of impeller blades extending radially outward from the impeller hub. The assembly can include an impeller motor configured to rotate the impeller blades about an axis of rotation. A stator can be positioned within the outer housing between the impeller and the outlet of the outer housing. The stator can include a plurality of vanes. The stator vanes can include an upstream edge at the upstream end of the stator, a first surface extending from the upstream edge to the downstream edge of the vane, and a second surface opposite the first surface and extending from the upstream edge to the downstream edge of vane. A plurality of the vanes can have a downstream edge at the outlet of the outer housing.
    Type: Grant
    Filed: July 12, 2017
    Date of Patent: November 26, 2019
    Assignee: Airius IP Holdings, LLC
    Inventor: Raymond B. Avedon
  • Patent number: 10458426
    Abstract: A fan for a gas turbine engine includes: an annular casing; a disk disposed inside the casing and mounted for rotation about an axial centerline, the disk including a row of fan blades extending radially outwardly therefrom; each of the fan blades including an airfoil having circumferentially opposite pressure and suction sides extending radially in span from a root to a tip, and extending axially in chord between spaced-apart leading and trailing edges, with the airfoils defining corresponding flow passages therebetween for pressurizing air; the row including no more than 21 and no less than 13 of the fan blades; and wherein each of the fan blades has a solidity defined by a ratio of the airfoil chord over a circumferential pitch of the fan blades, measured at 60% of a radial distance from the root to the tip, of less than about 1.6.
    Type: Grant
    Filed: September 15, 2016
    Date of Patent: October 29, 2019
    Assignee: General Electric Company
    Inventors: Daniel Allen Wilkin, II, Andrew Breeze-Stringfellow
  • Patent number: 10378384
    Abstract: When in a cold state and in a non-coated state, the aerodynamic profile for an arm of a structural casing of a turbine having a hub and a shroud is substantially identical to a nominal profile determined by specific Cartesian coordinates X,Y, Zadim. The coordinate Zadim is the quotient D/H where D is a 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: February 22, 2017
    Date of Patent: August 13, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Maxime Didier Delabriere, Pascal Pierre Routier, Pierre Hervé Marche, Vincent Nicolas Leonardon
  • Patent number: 10215194
    Abstract: A compressor rotor for a gas turbine engine is described which includes sets of blades having different airfoil thickness distributions, each including a frequency modifier forming a thickness differential relative to a baseline blade thickness. The frequency modifiers provide different natural vibration frequencies for each of the blades, and facilitate modifying natural vibration frequency separation between adjacent blades of the compressor rotor.
    Type: Grant
    Filed: December 21, 2015
    Date of Patent: February 26, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Ignatius Theratil, Krishna Prasad Balike, Richard Ivakitch, Sean Michael Kelly, Peter Townsend, Ronald Dutton, Paul Stone, Robert Venditti, Daniel Fudge, Milica Kojovic, Aldo Abate
  • Patent number: 10137982
    Abstract: An aerial vehicle includes one or more propeller units operable to provide thrust for takeoff or hover flight and one or more propulsion units operable to provide thrust for forward flight. At least one propeller unit includes a shaft coupled to a motor, and a first propeller blade and a second propeller blade that are both connected to the shaft. The second propeller blade is located substantially opposite the first propeller blade, and the second propeller blade has a surface area substantially perpendicular to an axis of rotation that is greater than a corresponding surface area of the first propeller blade. While the aerial vehicle is in forward flight in a first direction and the motor is turned off, the first propeller blade and the second propeller blade are each configured to orient in a second direction that is substantially parallel to the first direction, such that the first propeller blade is oriented substantially upwind of the second propeller blade.
    Type: Grant
    Filed: May 7, 2015
    Date of Patent: November 27, 2018
    Assignee: Wing Aviation LLC
    Inventors: Parsa Dormiani, James Ryan Burgess
  • Patent number: 9926058
    Abstract: A propeller having a means for creating fluid flow in a non-axial direction and redirecting it in an axial direction.
    Type: Grant
    Filed: May 25, 2017
    Date of Patent: March 27, 2018
    Inventor: Gregory Charles Sharrow
  • Patent number: 9527578
    Abstract: One aspect of the present invention provides a propeller for an aircraft. The propeller comprises a propeller hub, a spinner for streamlining the propeller and a plurality of composite propeller blades mounted to the propeller hub. The propeller blades are arranged to rotate together in the same rotational direction in at least two parallel planes substantially perpendicular to an axis of rotation of the propeller. The propeller has a reduced sized spinner with an improved aerodynamic profile that can be better matched to an engine nacelle and also has reduced drag.
    Type: Grant
    Filed: July 26, 2011
    Date of Patent: December 27, 2016
    Assignee: GE AVIATION SYSTEMS LIMITED
    Inventor: Michael Fedor Towkan
  • Patent number: 9462914
    Abstract: A food processor having a standing surface at the bottom, a rear side and a front side, wherein the front side, starting from the highest location of the food processor, is formed obliquely and contains a holder for a cooking vessel. Freely projecting rod parts are formed in an upper region of the food processor, wherein the front ends of the rod parts are arranged on the same horizontal plane and are set back. To improve handling further, it is proposed that the set-back amount should correspond to 25% to 50% of the largest extent of the food processor as seen in the depthwise direction in the standing-surface region of the food processor. The amount also corresponds to approximately half the horizontal distance between the longitudinal centre axes of the rod parts. The contour of the front side is always rounded in the region of the rod parts.
    Type: Grant
    Filed: October 3, 2014
    Date of Patent: October 11, 2016
    Assignee: Vorwerk & Co. Interholding GmbH
    Inventors: Uwe Kemker, Uwe Caldewey, Georg Hackert, Frank Starflinger
  • Patent number: 9145897
    Abstract: A blade structure for centrifugal fan includes a hub, a first blade unit, and a second blade unit. The hub has a connection section formed therearound and the connection section has a first side and an opposite second side. The first and the second blade unit are radially outward extended from the first and the second side, respectively, of the connection section. By providing the first and the second blade unit around the hub of a centrifugal fan, the air flows and air pressure produced by the centrifugal fan can be largely increased at effectively reduced noise.
    Type: Grant
    Filed: October 4, 2011
    Date of Patent: September 29, 2015
    Assignee: ASIA VITAL COMPONENTS CO., LTD.
    Inventor: Chun-Ming Wu
  • Patent number: 9121284
    Abstract: A vane having a cambered airfoil body is frequency-tuned via a number of cavities formed in a surface of the vane. At least some of the cavities are filled with a nonmetallic filler material, and the remainder of the cavities are left unfilled. A cover is affixed to the vane so as to cover at least the unfilled cavities. In an embodiment, the filling and covering of cavities is performed in a manner that excludes the frequency modes of the guide vane from a precluded band, e.g., an engine excitation band.
    Type: Grant
    Filed: January 27, 2012
    Date of Patent: September 1, 2015
    Assignee: United Technologies Corporation
    Inventor: Andrew Pope
  • Patent number: 9097125
    Abstract: A new, more economical design for intentionally frequency mistuned turbine blades for more efficient turbine engines is disclosed. A rotating disk of a turbine engine includes first turbine blades that alternate between second turbine blades. The second turbine blades are thicker than the first turbine blades, within manufacturing tolerances, in sections from about their mean line to their airfoil tip. The first and second turbine blades can be cast using two different molds, resulting in an economical manufacturing method. As such, the natural frequency of the second turbine blades is about 3% less than the natural frequency of the first turbine blades. As a result of the intentional difference in natural frequencies of the two different turbine blades, the rotating disk does not experience flutter instability.
    Type: Grant
    Filed: August 17, 2012
    Date of Patent: August 4, 2015
    Assignee: MAPNA Group
    Inventors: Gholamreza Ghorbani Zarimahalleh, Reza Torabideh, Hamid Motamedi Zoka, Arash Jahangiri Zad
  • Patent number: 9046109
    Abstract: A centrifugal blower in a cooling system of an electronic device having asymmetrical blade spacing with acceptable balance. The asymmetrical blade spacing is determined according to a set of desired acoustic artifacts that are favorable and balance that is similar to that found with equal fan blade spacing. In one embodiment, the fan impeller can include sixty one fan blades.
    Type: Grant
    Filed: August 29, 2012
    Date of Patent: June 2, 2015
    Assignee: Apple Inc.
    Inventors: Connor R. Duke, Jesse T. Dybenko
  • Patent number: 9046108
    Abstract: A centrifugal blower in a cooling system of an electronic device having asymmetrical blade spacing with acceptable balance. The asymmetrical blade spacing is determined according to a set of desired acoustic artifacts that are favorable and balance that is similar to that found with equal fan blade spacing. In one embodiment, the fan impeller can include thirty one fan blades.
    Type: Grant
    Filed: August 29, 2012
    Date of Patent: June 2, 2015
    Assignee: Apple Inc.
    Inventors: Connor R. Duke, Jesse T. Dybenko
  • Publication number: 20150110629
    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: Application
    Filed: October 23, 2013
    Publication date: April 23, 2015
    Applicant: General Electric Company
    Inventors: Lee Larned Brozyna, Matthew Durham Collier, Christopher William Kester, Alexander Stein
  • Patent number: 8997486
    Abstract: A compressor wheel for use with turbochargers or superchargers for forced air induction of internal combustion engines includes a base having a hub portion, and a plurality of blades extending from the base, each blade having a length defined by the distance between opposite axial extremities of the blade, the plurality of blades including at least three different types of blades, each having a substantially different length.
    Type: Grant
    Filed: March 23, 2012
    Date of Patent: April 7, 2015
    Assignee: Bullseye Power LLC
    Inventor: David M. Hall
  • Patent number: 8967525
    Abstract: A helicopter with a longitudinal axis and with a tail portion (1) with a transverse duct (6) and a drive shaft (23) inside a drive shaft fairing (14) for an aerodynamic and acoustic optimized counter-torque device (2) supported within said transverse duct (6).
    Type: Grant
    Filed: June 4, 2013
    Date of Patent: March 3, 2015
    Assignee: Airbus Helicopters Deutschland GmbH
    Inventors: Sascha Schneider, Dieter Schimke, Christian Wehle
  • Patent number: 8961107
    Abstract: A heat-dissipation fan including a base and an impeller disposed at the base, wherein the impeller includes a plurality of first blades, a plurality of second blades and a plurality of connection ribs. Each of the first blades and each of the second blades are arranged alternately. Each of the connection ribs comprises a first edge, a second edge and a third edge. The first edge is connected with the first blade, the second edge is connected with the second blade, the third edge is connected with the first edge and the second edge, and the third edge and the second blade are spaced apart to form a first vent. The first edge comprises a first length, the second edge comprises a second length, and the first length is larger than the second length.
    Type: Grant
    Filed: May 17, 2012
    Date of Patent: February 24, 2015
    Assignee: ADDA Corp.
    Inventors: Yen-Min Su, Kao-Chuan Huang, Chi-Ping Lai, Jiun-Shian Guo
  • Patent number: 8961141
    Abstract: A bladed rotor includes a blade lock mountable to a rotor hub adjacent to a multiple of blade slots. The blade lock includes at least one interface feature adjacent to a first of the multiple of blade slots. A first rotor blade includes a blade feature which interfaces with the interface feature to permit the first rotor blade to be axially mounted within the first of the multiple of blade slots but not within a remainder of the multiple of blade slots.
    Type: Grant
    Filed: August 29, 2011
    Date of Patent: February 24, 2015
    Assignee: United Technologies Corporation
    Inventors: Carney R. Anderson, Peter V. Tomeo
  • Patent number: 8938975
    Abstract: An inner combustion chamber casing of a turbomachine, which is intended to be placed downstream of a centrifugal compressor, is provided. The casing has the shape of a disc, pierced by a central circle, and includes on its disc at least one guide vane of the drawn-off air. The guide vane extends longitudinally over the disc between the periphery of the disc and the central circle and spreads out axially from the disc so as to form with the downstream face of the centrifugal compressor a guide channel for the air which is drawn off upon exit from the said compressor. The guide vane has a curved shape orienting in a radial direction at the level of its most central end.
    Type: Grant
    Filed: June 7, 2011
    Date of Patent: January 27, 2015
    Assignee: SNECMA
    Inventors: Laurent Donatien Behaghel, Frederic Dallaine, Delphine Leroux, Benjamin Philippe Pierre Pegouet
  • Fan
    Patent number: 8899930
    Abstract: A fan, for a ventilation assembly has blades extending from a cup-shaped central hub. The hub has an annular side wall and a bottom wall defining a receptacle for an electric motor. The hub has internal ribs for ventilation of the motor. Each rib has a longitudinal portion which extends along the side wall, a radial portion which extends along the bottom wall and an intermediate portion having an arcuate, transversely protruding profile. The longitudinal portion has a profile whose spacing from the side wall of the hub increases, from a minimum value remote from the bottom wall to a maximum value adjacent the bottom wall.
    Type: Grant
    Filed: January 25, 2012
    Date of Patent: December 2, 2014
    Assignee: Gate S.R.L.
    Inventors: Piergiorgio Innocenti, Davide Parodi
  • Patent number: 8876472
    Abstract: A turbine wheel including: a plurality of first and second blades, at least one of the first blades being adjacent to at least one of the second blades; a disk presenting an axis of rotation and a periphery having the blades mounted thereat, each of the blades including a head solid with a root engaged in a housing that opens to the periphery of the disk, each of the blades including a keying mechanism including a respective shelf arranged between the head and the root of the blade, the shelves of the first blades presenting an azimuth length different from the azimuth length of the shelves of the second blades; and a damper device arranged at least between the adjacent blades, the damper device being arranged between the shelves of the blades and the periphery of the disk.
    Type: Grant
    Filed: March 31, 2010
    Date of Patent: November 4, 2014
    Assignee: Turbomeca
    Inventors: Marc Dijoud, Jean-Philippe Ousty
  • Publication number: 20140322021
    Abstract: This invention relates to a device and method of reducing the azimuthal torque acting on a pulling pod unit or azimuth thruster (1) having a rotary pod housing (2) with a substantially vertical slewing axis (3) and a fixed downwardly directed first fm (4) carried by the pod housing (2) abaft the slewing axis (3), wherein said first fin is in the form of an elongated strip-shaped vane (4) and extends abaft the slewing axis (3) along the pod housing (2) to the vicinity of a rear end (5) thereof.
    Type: Application
    Filed: October 5, 2012
    Publication date: October 30, 2014
    Applicant: Rolls-Royce AB
    Inventors: Anders Ottosson, Rikard Johansson
  • Patent number: 8864471
    Abstract: A rotor for a gas turbine engine includes a plurality of turbine blades extending radially outwardly of a rotor body. A plurality of purge blades are positioned to rotate with the rotor body, and to drive air radially outwardly toward the turbine blades.
    Type: Grant
    Filed: August 12, 2011
    Date of Patent: October 21, 2014
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Loc Quang Duong, Xiaolan Hu
  • Publication number: 20140301852
    Abstract: A blade cascade for a turbomachine, in particular a gas turbine, including multiple identical blade groups which are situated next to each other and which each include a first individual blade (10) having a vane (12) having a blade profile and a first side wall (11), and a second individual blade (20), which differs from the first, having a vane (22) having a blade profile and a second side wall (21), the first and second side walls (11, 21) having different contourings.
    Type: Application
    Filed: April 8, 2014
    Publication date: October 9, 2014
    Applicant: MTU Aero Engines AG
    Inventor: Carsten ZSCHERP
  • Publication number: 20140286752
    Abstract: An impeller which is applied to a fan includes a hub, a plurality of first centrifugal blade and a plurality of second centrifugal blades. The hub is disposed in an accommodating space of the fan. The first centrifugal blades and the second centrifugal blades are connected to the hub. The first centrifugal blades have first ends away from the hub. The second centrifugal blades have second ends away from the hub. A distance between the second end and a center of the hub is larger than that between the first end and the hub center, and the first centrifugal blades and the second centrifugal blades are arranged periodically. Thus, an airflow noise in a constant frequency generated by the impeller can be avoided, and noises in inconstant frequency would not accumulate or generate annoying noise peak.
    Type: Application
    Filed: March 18, 2014
    Publication date: September 25, 2014
    Applicant: ASUSTek COMPUTER INC.
    Inventor: Ing-Jer CHIOU
  • 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: 8834130
    Abstract: A blade for a rotor of a wind turbine having a substantially horizontal rotor shaft, the rotor comprising a hub, from which the blade extends substantially in a radial direction when mounted to the hub. The blade comprises a main blade part having a profiled contour comprising a pressure side and a suction side as well as a leading edge and a trailing edge with a chord extending between the leading edge and the trailing edge. The profiled contour generates a lift when being impacted by an incident airflow. The profiled contour is divided in the radial direction into a root region with a substantially circular or elliptical profile closest to the hub, the substantially circular or elliptical profile having a diameter, an airfoil region with a lift generating profile furthest away from the hub, and a transition region between the root region and the airfoil region.
    Type: Grant
    Filed: April 2, 2009
    Date of Patent: September 16, 2014
    Inventors: Peter Fuglsang, Stefano Bove
  • Publication number: 20140212268
    Abstract: A boomerang wind blade includes a blade body having a protruding front edge and a recess rear edge. Both sides of the center of the blade body are two wing parts bent at an angle. The wing shape of one wing part is round at the front edge and tapering towards the rear edge. The wing shape of the other wing part is round at the rear edge and tapering towards the front edge. The device with a boomerang wind blade has a shaft fixed to the center of the two wing parts of the blade body to rotate as the blade body is driven by wind. The device also has at least one generator coupled with the shaft to generate electrical power.
    Type: Application
    Filed: January 30, 2013
    Publication date: July 31, 2014
    Applicant: NATIONAL PENGHU UNIVERSITY OF SCIENCE AND TECHNOLOGY
    Inventor: FU-NENG KU
  • Patent number: 8764397
    Abstract: A rotor system is provided wherein coaxial, closely spaced multi-bladed rotors counter-rotate at extremely low RPMs while their pitches are controlled to account for wind gusts and velocity conditions, thereby eliminating many of the deficiencies of conventional helicopters. The embodiments can dramatically decrease the power required to lift a given quantity of weight, even beyond the level required by a typical airplane.
    Type: Grant
    Filed: January 16, 2007
    Date of Patent: July 1, 2014
    Inventor: Michael Brian Wittig
  • Patent number: 8702395
    Abstract: The present invention discloses a hub fin device for improving the efficiency of a propeller. The hub fin device can include a propeller having a hub and a plurality of propeller blades that extend radially outward from the hub. Each of the plurality of propeller blades has a trailing edge region. A fin can also be included and located in the trailing edge region of at least one of the plurality of propeller blades. The fin extends radially outward from the hub and reduces or eliminates a hub vortex that is normally present during operation of the propeller.
    Type: Grant
    Filed: September 10, 2009
    Date of Patent: April 22, 2014
    Assignee: The Penn State Research Foundation
    Inventor: Walter S. Gearhart
  • Patent number: 8684694
    Abstract: The invention relates to a wheel (R) of the Francis type that comprises a ring (1) with revolution symmetry about the rotation axis (Z) of the wheel (R), and curved blades (21, 22) connected to the ring (1) and each having an outer peripheral edge (212, 222) and an inner central edge (211, 221). The connection points (B21, B22) between the ring (1) and the inner central edges (211, 221) of the blades (21, 22) are located on a same circle (C20) centered on the axis (Z). The connection points (A21, A22) between the ring (1) and the outer peripheral edges (212, 222) of the blades (21, 22) are located on at least two distinct circles (C21, C22) (D21, D22) centered on the axis (Z).
    Type: Grant
    Filed: February 13, 2009
    Date of Patent: April 1, 2014
    Assignee: Alstom Renewable Technologies
    Inventors: Farid Mazzouji, Michel Henri Couston, Jean Bernard Houdeline, Sylvain Lavigne, Claire Segoufin
  • Patent number: 8684659
    Abstract: The invention concerns a moving blade system for a moving blade sequence of a continuous-flow machine, in particular a thermal gas turbine with at least two moving blade segments, of which each moving blade segment encompasses at least two moving blades that are disposed, in reference to a rotation axis of the moving blade sequence, at least primarily radially between a radially interior and a radially exterior shroud band and are coupled to the shroud bands, wherein at least the radially exterior shroud bands of the two moving blade segments encompass contact surfaces that correspond to one another, wherein radial equilibrium axes of neighboring moving blades of the at least two moving blade segments are disposed in a tilted manner by respectively axially an angle (?a, ?b) relative to their respective base inclination, wherein the angles (?a, ?b) in regard to the base inclination feature opposite signs.
    Type: Grant
    Filed: August 1, 2009
    Date of Patent: April 1, 2014
    Assignee: MTU Aero Engines AG
    Inventor: Alexander Böck
  • Patent number: 8678752
    Abstract: A system, including a rotary machine including: a stator, a rotor configured to rotate relative to the stator, wherein the rotor comprises a plurality of blades having a non-uniform spacing about a circumference of the rotor.
    Type: Grant
    Filed: October 20, 2010
    Date of Patent: March 25, 2014
    Assignee: General Electric Company
    Inventors: John McConnell Delvaux, Brian Denver Potter
  • Patent number: 8672630
    Abstract: A fan-turbine rotor assembly includes one or more turbine ring rotors. Each turbine ring rotor is cast as a single integral annular ring. By forming the turbine as one or more rings, leakage between adjacent blade platforms is minimized which increases engine efficiency. Assembly of the turbine ring rotors to the diffuser ring includes axial installation and radial locking of each turbine ring rotor.
    Type: Grant
    Filed: January 16, 2012
    Date of Patent: March 18, 2014
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, James W Norris, Craig A. Nordeen, Brian Merry
  • Patent number: 8672614
    Abstract: Exhaust apparatus for exhausting “dirty” exhaust gases accept a core flow of such exhaust gases and combine that with an annularly-surrounding “rooftop” flow of ambient air for diluting the exhaust gases as well as expelling the diluted flow in a forcibly expelled plume in order to ensure that the “effective” expulsion distance of the expelled diluted flow is at least the physical length of the exhaust apparatus plus the gains gotten from efflux velocity and flowrate.
    Type: Grant
    Filed: February 2, 2009
    Date of Patent: March 18, 2014
    Assignee: Loren Cook Company
    Inventor: Erich R. Fitzpatrick
  • Patent number: 8657558
    Abstract: Methods, apparatus, and products are disclosed for improving the airflow exiting a blower that has one or more adjustable guide vanes that are affixed to the blower at one or more pivot points located in an outlet of the blower that include: determining a rotational speed of an impeller in the blower and adjusting a position of at least one of the adjustable guide vanes in dependence upon the rotational speed of the impeller.
    Type: Grant
    Filed: April 8, 2010
    Date of Patent: February 25, 2014
    Assignee: International Business Machines Corporation
    Inventors: Michael S. June, Jason A. Matteson, Mark E. Steinke
  • Patent number: 8651814
    Abstract: An axial flow fan includes a hub rotatable about a central axis. The hub includes a front face and a cylindrical portion. A plurality of apertures is provided in the front face of the hub, each aperture at least partially defined by a first surface oriented non-parallel with the front face. A plurality of ribs is provided, each rib aligned with one of the plurality of apertures such that a free edge of the rib at least partially overlaps the respective one of the plurality of apertures. The fan further includes a plurality of lips, each lip coupled to the front face of the hub and aligned with one of the plurality of apertures that is not aligned with one of the plurality of ribs, each lip having a second surface, adjacent the first surface of a respective aperture, that at least partially overlaps the respective aperture.
    Type: Grant
    Filed: March 7, 2012
    Date of Patent: February 18, 2014
    Assignee: Robert Bosch GmbH
    Inventors: Dana F. Nicgorski, Adam H. Sterne, Michael Strupp
  • Publication number: 20140044546
    Abstract: A bladed rotor for a turbomachine, in particular a gas turbine, having a plurality of blades distributed around the circumference thereof; the blade distribution being made up of a natural-number sector count of first angular sectors and second angular sectors; a first blade count of first blades being arranged in the first angular sectors, and a second blade count of second blades being arranged in the second angular sectors, said second blade count being different from said first blade count; and the sector count being odd (Z=2n+1, n=1, 2, 3, . . . ) and/or greater than two (Z>2).
    Type: Application
    Filed: July 25, 2013
    Publication date: February 13, 2014
    Applicant: MTU Aero Engines AG
    Inventors: Johann GEPPERT, Peter Eibelshaeuser
  • Patent number: 8640984
    Abstract: A ducted fan for a helicopter includes a transverse duct and a counter-torque device supported within the duct. The counter-torque device includes a rotor rotatably mounted within the duct and a stator fixedly mounted within the duct downstream from the rotor. The rotor includes a rotor hub having a rotor axis, and rotor blades extending from the hub. The Rotor blades have a modulated angular distribution about the rotor axis. The stator includes a stator hub, and a plurality of stator vanes distributed around the stator hub. The stator vanes are angularly modulated around the stator hub.
    Type: Grant
    Filed: August 7, 2012
    Date of Patent: February 4, 2014
    Assignee: Bell Helicopter Textron Inc.
    Inventors: John M. Kebrle, James R. Andrews, Justin Daw, Jim Hurdle, Paul Sherrill, Jimmy C. Narramore, Sidney Xue, Charles Hollimon, Dudley Smith, Bryce Docker, John T. Brieger
  • Patent number: 8641361
    Abstract: Methods, apparatus, and products are disclosed for improving the airflow exiting a blower that has one or more adjustable guide vanes that are affixed to the blower at one or more pivot points located in an outlet of the blower that include: determining a rotational speed of an impeller in the blower and adjusting a position of at least one of the adjustable guide vanes in dependence upon the rotational speed of the impeller.
    Type: Grant
    Filed: April 8, 2010
    Date of Patent: February 4, 2014
    Assignee: International Business Machines Corporation
    Inventors: Michael S. June, Jason A. Matteson, Mark E. Steinke
  • Patent number: 8608447
    Abstract: A disk for a turbine engine is disclosed herein. The disk includes a rotatable body extending along a longitudinal axis between a forward side and an aft side. The disk also includes a plurality of slots disposed about a periphery of the body. Each of the slots extends between the forward and aft sides along a respective slot axis. The sides of each of the slots are asymmetrical relative to one another in a cross-section normal to the slot axis.
    Type: Grant
    Filed: February 19, 2009
    Date of Patent: December 17, 2013
    Assignee: Rolls-Royce Corporation
    Inventors: Joseph Benjamin LaBelle, Christopher Hall, Samuel J. LaCombe, James C. Muskat
  • Patent number: 8579591
    Abstract: A compressor impeller includes a hub, main blades and splitter blades. The main blades are equally spaced around the circumference of the hub. Each splitter blade is equally spaced between two adjacent main blades. Each main blade and splitter blade has suction and pressure surfaces formed in substantial compliance with normalized Cartesian coordinate values of X, Y, and Z set forth in Tables 1-4. When connected by smooth, continuing arcs, the normalized Cartesian coordinates form complete main blade and splitter blade shapes that are substantially matched by the main blade and splitter blade shapes of the compressor impeller.
    Type: Grant
    Filed: October 28, 2010
    Date of Patent: November 12, 2013
    Assignee: Hamilton Sundstrand Corporation
    Inventors: John Chen Chiang Ho, Bo Zheng, Timothy M. Hollman, Kevin K. Taft, Jang Y. Jo, Anthony C. Jones
  • Patent number: 8579575
    Abstract: A wind turbine has a spindle, a first fan device and a second fan device. The first fan device is rotatably mounted around the spindle and has a first pivot hole and at least two first blades. The first pivot hole is formed through a center of the first fan device and is mounted around the spindle. The at least two first blades are radially mounted on and protrude from an external surface of the first fan device. The second fan device is rotatably mounted around the spindle, abuts with the first fan device and has a second pivot hole and at least two second blades. The second pivot hole is formed through a center of the second fan device and is mounted around the spindle. The at least two second blades are mounted on and protrude from an external surface of the second fan device.
    Type: Grant
    Filed: June 14, 2010
    Date of Patent: November 12, 2013
    Inventor: Shun-Tsung Lu
  • Patent number: 8540490
    Abstract: An apparatus includes a first set of blades and a second set of blades disposed downstream relative to the first set of blades. The first set of blades includes a first subset of blades, wherein each blade among the first subset of blades comprises one or more first geometric parameters. The second set of blades includes a second subset of blades, wherein each blade among the second subset of blades comprises one or more second geometric parameters different from the one or more first geometric parameters.
    Type: Grant
    Filed: September 28, 2011
    Date of Patent: September 24, 2013
    Assignee: General Electric Company
    Inventors: Kishore Ramakrishnan, Trevor Howard Wood
  • Patent number: 8529190
    Abstract: A wind turbine rotor with a vertical rotation axis connected to a hub having at least two horizontal supports, on the ends of which are tightly fixed blades, each consisting of two wings joined together, with a symmetrical or concavo-convex airfoil with the airfoil's chord lengths and thickness diminishing toward both wing ends. The rotor blade's upper and lower wings are radially deflected from the central zone outwards. The chord length of both wing ends and the chord length in the central zone are approximately inversely proportional to the radii of its location in relation to the axis of the rotor's rotation. The deflecting angle of the lower wing can be greater than the deflecting angle of the upper wing or the length of the lower wing can be greater than the length of the upper wing. These specifications provide uniform wind power consumption along the wing's length, increasing the efficiency of a wind turbine and its service life.
    Type: Grant
    Filed: March 31, 2010
    Date of Patent: September 10, 2013
    Assignee: Anew Institute Sp. z o.o.
    Inventor: Anatoliy Naumenko
  • Patent number: 8512000
    Abstract: A turbocharger for or in a motor vehicle has a rotor with an intermediate blade disposed between two primary blades. The intermediate blade, at least in some regions, has an angular progression that differs from the primary blades.
    Type: Grant
    Filed: February 27, 2008
    Date of Patent: August 20, 2013
    Assignee: Continental Automotive GmbH
    Inventors: Tobias Dettmann, Andre Kaufmann
  • Publication number: 20130121833
    Abstract: An airfoil comprises a leading edge, a trailing edge, and pressure and suction surfaces defined therebetween. An inner platform is coupled to a root section of the airfoil, with a curvilinear gusset extending along a lower surface of the inner platform, opposite the root section. An outer platform is coupled to a tip section of the airfoil, with a multi-lobed gusset extending along an upper surface of the inner platform, opposite the tip section.
    Type: Application
    Filed: November 14, 2011
    Publication date: May 16, 2013
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: John P. Lucashu, Gregory E. Reinhardt, John C. Ditomasso
  • Publication number: 20130108466
    Abstract: A spacer for a gas turbine engine includes a rotor ring defined along an axis of rotation, the rotor ring defines a forward circumferential flange which defines a first thickness and an aft circumferential flange which defines a second thickness, the first thickness different than the second thickness. A plurality of core gas path seals which extend from the rotor ring opposite the ramped interface.
    Type: Application
    Filed: October 28, 2011
    Publication date: May 2, 2013
    Inventors: Gabriel L. Suciu, Stephen P. Muron, Christopher M. Dye, Ioannis Alvanos, Brian D. Merry