Patents Examined by Carlos A Rivera
  • Patent number: 10502225
    Abstract: The present invention is directed to a centrifugal fan assembly (19) for the debris collection arrangement (100) of a road cleaning machine (10). The assembly (19) comprises a casing (101), a rotatable impeller (103) and a wall (107). The casing (101) comprises a volute portion (30) connected to an outlet passageway (31), a corner (106) being formed therebetween. The impeller (103) comprises a plurality of blades (25) and is located in the volute portion (30) proximate the corner (106). The wall (107) separates the outlet passageway (31) into a first and second passageway (36, 37) and extends to an inner end (102) proximate the impeller (103). The inner end (102) is positioned, and the impeller (103) is arranged, such that when a blade (25) passes the inner end (102) a second pressure wave is formed that destructively interferes with a first pressure wave formed by a blade (25) passing the corner (106).
    Type: Grant
    Filed: March 18, 2015
    Date of Patent: December 10, 2019
    Assignee: Johnston Sweepers Limited
    Inventors: Gareth Knopp, Michael Sandford, Stephen Catchpole
  • Patent number: 10502235
    Abstract: In a fan case having an annular outer wall with a plurality of fan case bolt holes there through, bushings are inserted into the fan case bolt hole and are dimensioned to define an annular gap between the bolt hole inner surface and the bushing outer surface. An adhesive material disposed within each annular gap between the bushing and the corresponding fan case bolt hole, with the adhesive material forming a liquid shim separating the bushing outer surface from the bolt hole inner surface.
    Type: Grant
    Filed: August 22, 2014
    Date of Patent: December 10, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Thomas J. Robertson, Mark W. Costa
  • Patent number: 10502073
    Abstract: A rotor assembly is provided. The rotor assembly includes a plurality of blades spaced circumferentially. An airfoil of each blade includes a pressure side, a suction side, a pressure side nub extending from the pressure side, and a suction side nub extending from the suction side. An airfoil length is greater than one of (i) 40 inches, wherein the rotor is configured for operation at about 3600 rpm, and (ii) 48 inches, wherein the rotor is configured for operation at about 3000 rpm. The rotor assembly also includes a plurality of sleeves. Each of the sleeves extends from a first end to a second end. The first end is coupled to the pressure side nub of a first of the blades and the second end is coupled to the suction side nub of an adjacent second of the blades.
    Type: Grant
    Filed: March 9, 2017
    Date of Patent: December 10, 2019
    Assignee: General Electric Company
    Inventors: Robert Edward Deallenbach, John James Ligos, Kristopher John Frutschy
  • Patent number: 10502091
    Abstract: Aspects of the disclosure are directed to a sync ring assembly associated with an engine, comprising: a sync ring, and a clevis coupled to the sync ring, where the clevis includes a rib that resists a deflection of the sync ring assembly when the engine is operated, and where the clevis is made of titanium.
    Type: Grant
    Filed: December 12, 2016
    Date of Patent: December 10, 2019
    Assignee: United Technologies Corporation
    Inventors: James F. McGuire, II, Venkata Reddy Chimalamarri, Seetharama Reddy Katta Jayakumar
  • Patent number: 10502084
    Abstract: The invention relates to a module for a gas turbine comprising a rotationally symmetrical outer casing of a first material having a first linear thermal expansion coefficient, a rotationally symmetrical component for guiding hot gas of a second material having a linear thermal expansion coefficient which is lower than the first coefficient, at least one annular structure arranged radially within the component, and at least three struts having a radially inner end secured on the outer casing and a radially outer end secured on the annular structure. The component also comprises at least one first fixing which is free in radial direction and fixed in axial direction and arranged between the component and the outer casing and/or the annular structure, as well as at least three second fixings having an elastic effect in radial, axial and/or circumferential direction and being arranged between the component and the strut and/or the annular structure.
    Type: Grant
    Filed: October 18, 2016
    Date of Patent: December 10, 2019
    Assignee: MTU AERO ENGINES AG
    Inventors: Werner Humhauser, Hermann Klingels, Rudolf Stanka, Alois Eichinger
  • Patent number: 10495353
    Abstract: Systems, methods, and devices relating to a mechanism which can be used in gas cooling devices, pneumatic motors, turbines and other pressurized gas devices. A rotatable rotor is provided along with a number of hollow conduits that radially radiate from an exit port at the center of the rotor. The pressurized gas is injected into the mechanism at the inlet port(s). The gas enters the conduits and travels from the inlet port(s) to the exit port(s). In doing so, the gas causes the rotor to rotate about its central axis while the gas cools. This results in a colder gas at the exit port(s) than at the inlet port(s) due to an enhanced extraction of work, while maintaining a very low flow rate at the cold outlet.
    Type: Grant
    Filed: August 28, 2015
    Date of Patent: December 3, 2019
    Inventors: Jeliazko Polihronov, Anthony Straatman
  • Patent number: 10494935
    Abstract: A blade track for a gas turbine engine includes segments and joints that couple the segments together. Each segment extends part-way around a central axis of the engine and the joints couple together adjacent segments to form a full hoop.
    Type: Grant
    Filed: April 8, 2016
    Date of Patent: December 3, 2019
    Assignees: Rolls-Royce North American Technologies Inc., Rolls-Royce Corporation, Rolls-Royce plc
    Inventors: Aaron D. Sippel, Daniel K. Vetters, Jun Shi, David J. Thomas, Andrew J. Eifert, Peter Broadhead
  • Patent number: 10494115
    Abstract: A system and a method for the automatic starting of the engines of a twin-engine aircraft. When a first engine is made by the pilots of the aircraft to follow an automatic starting procedure, this engine follows the conventional four-phase starting cycle. The rotor of the high-pressure stage of the second engine is spun up for a predetermined duration and to a speed that is substantially constant and less than the nominal value during the starting cycle for the first engine. Once the starting cycle for the first engine is complete, the second engine is made by the pilots of the aircraft to follow an automatic starting procedure. The starting cycle for the second engine comprises just three phases.
    Type: Grant
    Filed: February 16, 2017
    Date of Patent: December 3, 2019
    Assignees: AIRBUS OPERATIONS SAS, AIRBUS SAS
    Inventors: Patrick Zaccaria, Pierre-Henri Brousse, Alexis Manneville, Paul-Emile Roux, Damien Lozach, Christine Molliet
  • Patent number: 10495092
    Abstract: Disclosed is an impeller for a pump for conveying waste water having a support body which can be rotated about an axis of rotation (A) and on which two blades for conveying are provided, wherein the blades each have an inlet region which extends from an inlet edge up to an apex, wherein the wall thickness increases at its end side remote from the support body in the inlet region from the inlet edge and reaches its maximum value at the apex, wherein the blade converges in the inlet region in an axial direction from the support body to the end side with respect to the wall thickness. A base plate is furthermore proposed for interaction with such an impeller as well as a pump for conveying waste water.
    Type: Grant
    Filed: August 21, 2013
    Date of Patent: December 3, 2019
    Assignee: Sulzer Management AG
    Inventors: Kais Haddad, Horst-Paul Klein
  • Patent number: 10487843
    Abstract: An airfoil member (100) comprising has a substrate (120) along at least a portion of an airfoil (102) of the airfoil member. A sheath (122) has a channel (144) receiving a portion (160) of the substrate. A scrim (200) is between the substrate and the sheath. A spacer (220) is between the sheath and the substrate and has a plurality of spaced-apart portions (232, 234) with gaps between the spaced-apart portions.
    Type: Grant
    Filed: August 4, 2014
    Date of Patent: November 26, 2019
    Assignee: United Technologies Corporation
    Inventors: Lee M. Drozdenko, James O. Hansen, Maria C. Kirejczyk, Scot A. Webb, Jesse C. Meyer, Brandon A. Gates, Richard B. Bergethon, Michael A. Morden
  • Patent number: 10486785
    Abstract: A propeller assembly that includes a hub having an outer radial surface and a plurality of wedge retaining members removably coupled to the hub. The plurality of wedge retaining members are spaced circumferentially about the outer radial surface such that a dovetail slot is defined between adjacent wedge retaining members. The assembly also includes at least one propeller blade including a root portion having a dovetail profile. The root portion is coupled to the hub and positioned within the dovetail slot. The plurality of wedge retaining members are configured to restrict radial movement of the root portion within the dovetail slot.
    Type: Grant
    Filed: October 17, 2016
    Date of Patent: November 26, 2019
    Assignee: General Electric Company
    Inventors: Nicholas Joseph Kray, Peggy Lynn Baehmann, Stefaan Guido Van Nieuwenhove
  • Patent number: 10486805
    Abstract: A control horn arrangement includes a control horn body with an inboard end and an opposed outboard end. The control horn body defines a torque tube axis which extends between the inboard and outboard end of the control horn body. An inner flange and an outer flange are disposed on the outboard end of the control horn body. The inner flange and the outer flange extend about the torque tube axis and define between one another a receptacle to fix a torque tube to the outboard end of the control horn body.
    Type: Grant
    Filed: September 29, 2017
    Date of Patent: November 26, 2019
    Assignee: SIKORSKY AIRCRAFT CORPORATION
    Inventors: Brian Rothermich, Leon M. Meyer
  • Patent number: 10487842
    Abstract: An apparatus for suppressing a surge of a turbo compressor is provided. The apparatus includes a compressor housing having a compressor wheel provided therein and an inlet having air flowing thereinto and protruding from a first opposite to the compressor wheel. A connection module has a first side connected to the compressor housing to communicate with the inlet and a second side that includes an inlet for supplying air. A flexible cone of an elastic material is disposed in the connection module and is formed in a conical shape having sizes of cross-sectional areas of a first side and a second side that are different from each other. A spring member is coupled to an exterior circumferential surface of the flexible cone to provide an elastic force and operated to change a size of a cross-sectional area of the first or second side of the flexible cone.
    Type: Grant
    Filed: November 29, 2017
    Date of Patent: November 26, 2019
    Assignees: Hyundai Motor Company, Kia Motors Corporation
    Inventor: Seok Beom Jin
  • Patent number: 10487672
    Abstract: An airfoil adapted for use in a gas turbine engine is disclosed. The airfoil may include components made from ceramic materials. The airfoil may include insulating material to thermally isolate portions of the airfoil.
    Type: Grant
    Filed: November 20, 2017
    Date of Patent: November 26, 2019
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Daniel K. Vetters, Ted J. Freeman
  • Patent number: 10487661
    Abstract: A power turbine includes a first stage vane having an airfoil with a cold un-coated nominal 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: August 31, 2017
    Date of Patent: November 26, 2019
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Krishan Mohan, Panagiota Tsifourdaris
  • Patent number: 10487795
    Abstract: A hydroelectric power system includes a fluid channel having a bottom surface and side walls configured to form a fluid passage, a upraised curved lip integral with the bottom surface and configured to form a cavity, and a turbine in fluid communication with the fluid channel, the turbine being configured to fit at least partially within the cavity of the upraised curved lip. A method includes creating a spatial fluid flow of the fluid traveling through the fluid channel with the upraised curved lip and creating electrical power via the turbine with the fluid passing over the upraised curved lip.
    Type: Grant
    Filed: December 23, 2014
    Date of Patent: November 26, 2019
    Inventor: Soheil Nashtahosseini
  • Patent number: 10487666
    Abstract: A gas turbine engine component includes a wall having first and second wall surfaces, a cooling hole extending through the wall and a convexity. The cooling hole includes an inlet located at the first wall surface, an outlet located at the second wall surface, a metering section extending downstream from the inlet and a diffusing section extending from the metering section to the outlet. The diffusing section includes a first lobe diverging longitudinally and laterally from the metering section and a second lobe adjacent the first lobe and diverging longitudinally and laterally from the metering section. The convexity is located near the outlet.
    Type: Grant
    Filed: August 15, 2016
    Date of Patent: November 26, 2019
    Assignee: United Technologies Corporation
    Inventors: JinQuan Xu, Glenn Levasseur
  • Patent number: 10487689
    Abstract: An aircraft turbine casing configured to carry a set of ring sectors that partly delimits a conduit inside which a gas flow passes through the turbine, including a dynamic mechanism adjusting radial position of ring sectors, an upstream radial lug that connects an upstream end of each ring sector to the casing, and a downstream radial lug that connects a downstream end of each ring sector to the casing. The upstream lug is made as a single piece with the casing and is directly connected to the upstream end of each ring sector.
    Type: Grant
    Filed: March 6, 2012
    Date of Patent: November 26, 2019
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Damien Bonneau, Jean-Christophe Marc Cordier, Fabrice Marcel Noel Garin
  • Patent number: 10487751
    Abstract: A gas turbine engine includes a compressor section having multiple stages, a combustor section fluidly connected to the compressor section, a turbine section fluidly connected to the combustor section, and a bleed structure radially outward of the stages. The bleed structure includes a body structure having a first set of openings radially outward of a first stage and a second set of openings radially outward of a second stage. The bleed structure further includes a circumferential sleeve configured to cover the first set of openings in a first position and configured to cover the second set of openings in a second position. An actuator is coupled to the circumferential sleeve and is configured to articulate the sleeve between the first and second positions.
    Type: Grant
    Filed: October 2, 2017
    Date of Patent: November 26, 2019
    Assignee: United Technologies Corporation
    Inventor: Enzo DiBenedetto
  • Patent number: 10480526
    Abstract: An axial flow fan according to the present invention includes a plurality of blades, each of the blades including: a leading edge formed in front in a direction of rotation of the axial flow fan; an inner circumferential edge formed at an inner circumference of the blades; and an outer circumferential edge formed at an outer circumference of the blades, the outer circumferential edge configured to be at downstream of a fluid, forced to move by the axial flow fan, than the inner circumferential edge, the blade being reflexed toward upstream of the fluid at a portion adjacent to the outer circumferential edge, and having a local angle-decrease section having a blade inlet angle ? at the leading edge decreasing from neighborhood, the local angle-decrease section being formed at a side of the leading edge and being located closer to the outer circumferential edge than to the inner circumferential edge.
    Type: Grant
    Filed: November 2, 2015
    Date of Patent: November 19, 2019
    Assignee: Mitsubishi Electric Corporation
    Inventors: Seiji Nakashima, Takahide Tadokoro, Shuhei Mizutani, Yutaka Aoyama