Patents Examined by Cameron A Corday
  • Blast fan
    Patent number: 10837345
    Abstract: A blast fan includes: a tubular frame having a first opening and a second opening to pass airflow through between the first opening and the second opening. The first opening has a first reverse tapered portion expanding from inside to outside of the frame, and the first reverse tapered portion has a surface having first convex portions projecting to the inside of the frame.
    Type: Grant
    Filed: September 26, 2017
    Date of Patent: November 17, 2020
    Assignee: SANYO DENKI CO., LTD.
    Inventors: Yoshihisa Yamazaki, Satoshi Fujimaki, Takashi Kawashima, Souma Araki
  • Turbine bucket cooling
    Patent number: 10815808
    Abstract: Embodiments of the invention relate generally to rotary machines and, more particularly, to the cooling of at least portions of a turbine bucket. In one embodiment, the invention provides a method of cooling at least a portion of a turbine bucket, the method comprising: during operation of a turbine, altering a swirl velocity of purge air between a platform lip extending axially from the platform and an angel wing extending axially from a face of a shank portion of the turbine bucket, wherein altering the swirl velocity of the purge air includes interrupting a flow of the purge air with a plurality of turbulators disposed along at least one of a radially inner surface of the platform lip or the face of the shank portion.
    Type: Grant
    Filed: July 22, 2016
    Date of Patent: October 27, 2020
    Assignee: General Electric Company
    Inventors: Rohit Chouhan, Soumyik Kumar Bhaumik
  • Assembly for releasable locking of a spinner or nosecone to an engine structure
    Patent number: 10808613
    Abstract: Disclosed is an assembly for a gas turbine engine, the assembly includes: a spinner or nosecone comprising a threaded rear portion, an engine structure comprising a threaded front portion, the nosecone being threadingly connected to the engine structure, wherein rotation of the spinner or nosecone about the engine structure in a first direction secures the spinner or nosecone to the engine structure and rotation of the spinner or nosecone about the engine structure in a second direction releases the spinner or nosecone from the engine structure; and a lock ring slidingly connected to the engine structure to slide between: a forward position to engage the spinner or nosecone and block rotation of the spinner or nosecone in the second direction, and a rearward position, where the lock ring is spaced from the spinner or nosecone.
    Type: Grant
    Filed: January 9, 2018
    Date of Patent: October 20, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Anthony R. Bifulco, Joseph M. Wilson, Jason B. Hickman
  • Gas turbine engine blade airfoil profile
    Patent number: 10801327
    Abstract: A turbine blade for a gas turbine engine is disclosed. The turbine blade includes an airfoil including leading and trailing edges joined by spaced-apart pressure and suction sides to provide an exterior airfoil surface extending from a platform in a radial direction to a tip. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil described by a set of Cartesian coordinates set forth in Table 1, the Cartesian coordinates provided by an axial coordinate scaled by a local axial chord, a circumferential coordinate scaled by a local axial chord, and a span location, wherein the local axial chord corresponds to a width of the airfoil between the leading and trailing edges at the span location.
    Type: Grant
    Filed: January 21, 2019
    Date of Patent: October 13, 2020
    Assignee: Raytheon Technologies Corporation
    Inventor: Kevin K. Song
  • Device for generating a dynamic axial thrust to balance the overall axial thrust of a radial rotating machine
    Patent number: 10774839
    Abstract: An impeller wheel assembly for a radial rotating machine, comprises a bladed hub portion of an impeller wheel, with a first radially outward facing, fluid deflecting surface having a curvature profile designed to deflect an axial fluid flow into a radial centrifugal flow, and comprising a deflector portion with a second radially outward facing, fluid deflecting surface. The second radially outward facing surface has a curvature profile designed to deflect a radial centripetal fluid flow into an axial fluid flow.
    Type: Grant
    Filed: December 18, 2013
    Date of Patent: September 15, 2020
    Assignee: THERMODYN SAS
    Inventors: Thomas Alban, Sylvain Guillemin, Manuele Bigi, Guiseppe Iurisci, Stefano Falomi
  • Contouring a blade/vane cascade stage
    Patent number: 10753206
    Abstract: A blade/vane cascade segment of a blade/vane cascade for a turbomachine is disclosed, which comprises a stage with a stage surface as well as a first blade/vane element and a second blade/vane element. The stage surface comprises a first elevation reaching as far as the pressure side of the first blade/vane element and a second elevation reaching as far as the suction side of the second blade/vane element. A furthest downstream point of a boundary of the second elevation has an axial position which differs from the axial position of at least one highest point of the first elevation by a maximum of 10% of an axial cascade span. Furthermore, a blade/vane cascade, a blade/vane channel, a stage, a turbomachine and an aircraft engine are disclosed.
    Type: Grant
    Filed: April 9, 2018
    Date of Patent: August 25, 2020
    Assignee: MTU Aero Engines AG
    Inventors: Markus Brettschneider, Inga Mahle, Fadi Maatouk
  • Quick disconnect coupling for a propeller
    Patent number: 10745108
    Abstract: A coupling is disclosed for connecting a propeller to a motor in an aircraft such as a rotary wing aircraft and the like. The coupling comprises a propeller hub having an inner propeller hub bore defining an axial keyway. A rotatable shaft has an internal shaft bore connected for rotation with the motor. A radial key is slidably located in a radial aperture extending through the rotatable shaft. An actuator is slidably mounted within the internal shaft bore of the rotatable shaft. The radial key is received with the axial keyway for securing the propeller hub to the rotatable shaft. A depression of the actuator retracting the radial key relative to an outer surface of the rotatable shaft for permitting the propeller hub bore to be introduced onto the rotatable shaft.
    Type: Grant
    Filed: May 31, 2017
    Date of Patent: August 18, 2020
    Inventors: Tim Nilson, Daniel Nethery, Austin Holbrook
  • Rotor blade with wheel space swirlers and method for forming a rotor blade with wheel space swirlers
    Patent number: 10738638
    Abstract: The present disclosure is directed to a rotor blade and method for forming the rotor blade. The rotor blade includes a platform having a bottom side radially spaced from a top side and a leading edge portion axially spaced from a trailing edge portion. An airfoil extends radially outwardly from the top side of the platform and a shank extends radially inwardly from the bottom side of the platform. The shank includes a lip that extends axially outwardly from a forward wall of the shank. The lip defines a radially inward surface and a radially outward surface and a plurality of slots. Swirler vane inserts are disposed within respective slots of the plurality of slots. Each swirler vane insert extends radially inwardly from the inward surface of the lip and axially outwardly from the forward wall of the shank.
    Type: Grant
    Filed: September 7, 2016
    Date of Patent: August 11, 2020
    Assignee: General Electric Company
    Inventors: Rohit Chouhan, Soumyik Bhaumik
  • Sealing structure for turbocharger housing
    Patent number: 10731491
    Abstract: Bolt holes 16 are formed in a joint part 14 of a turbine housing 12, with flanged bolts 40 screwed in the bolt holes 16. A flange part 32 of a bearing housing 30 is sandwiched between bearing surfaces 44a of the flanged bolts 40 and an inner end face 14b of the joint part 14. A sealing ring 48 is interposed in an annular space s. Before the flanged bolts 40 are fastened, there is formed a height difference G equivalent to a compression allowance h for the sealing ring 48, between an outer end face 60a of the joint part 14 and a bolt receiving surface 32a of the flange part 32. The flanged bolts 40 are screwed into the bolt holes 16 until the bearing surfaces 44a make tight contact with the outer end face 60a so as to resiliently deform the sealing ring 48.
    Type: Grant
    Filed: July 27, 2016
    Date of Patent: August 4, 2020
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Shingo Shudo, Daigo Watanabe, Takumi Tokiyoshi, Motoki Ebisu
  • Compressor with a thermal shield and methods of operation
    Patent number: 10711641
    Abstract: A compressor includes a compressor bundle and an outer casing. Between the outer casing and the compressor bundle a thermal shield is provided, for reducing thermal stress and visco-plastic deformation of the casing under severe operating conditions.
    Type: Grant
    Filed: May 19, 2014
    Date of Patent: July 14, 2020
    Assignee: NUOVO PIGNONE SRL
    Inventors: Silvio Giachetti, Massimiliano Borghetti, Luca Lombardi
  • Airfoil with geometrically segmented coating section
    Patent number: 10711624
    Abstract: An airfoil includes an airfoil body that has a geometrically segmented coating section. The geometrically segmented coating section includes a wall having an outer side. The outer side has an array of cells, and there is a coating disposed in the array of cells.
    Type: Grant
    Filed: November 17, 2016
    Date of Patent: July 14, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Matthew A. Devore, Adam P. Generale, Tracy A. Propheter-Hinckley
  • Composite aerofoil structure with a cutting edge tip portion
    Patent number: 10669866
    Abstract: An aerofoil structure (26) for a gas turbine engine (10), the aerofoil structure comprising a carbon composite aerofoil portion (38) and a tip portion (48), wherein the tip portion comprises a tip surface (60) configured to face a corresponding casing structure (30), the tip portion further comprising a ridge line (62) extending along at least a portion of the tip surface, wherein the tip surface comprises a first surface (64) and a second surface (66) provided either side of the ridge line, the ridge line being defined by the intersection of the first and second surfaces, wherein the ridge line is configured to cut into the casing structure during an interaction between the aerofoil structure and casing structure.
    Type: Grant
    Filed: December 19, 2013
    Date of Patent: June 2, 2020
    Assignee: ROLLS-ROYCE PLC
    Inventor: Nicholas Michael Merriman
  • System and method to move turbomachinery
    Patent number: 10662816
    Abstract: A system includes a turbine housing, a turbine mount disposed in the turbine housing, and a turbine moving machine disposed at least partially within the turbine housing. The turbine moving machine includes a turbine support configured to couple to a turbine and a first translational portion coupled to the turbine support. The turbine moving machine is configured to move the turbine lengthwise along the first translational portion between a first turbine position within the turbine housing and a second turbine position outside of the turbine housing. The turbine moving machine includes a vertical adjustment assembly configured to raise and lower the turbine.
    Type: Grant
    Filed: April 12, 2016
    Date of Patent: May 26, 2020
    Assignee: General Electric Company
    Inventors: Artemio Josue Aguilar, Juan Carlos Oidor
  • Composite yoke fitting for bearing attachment to rotorcraft blade
    Patent number: 10654567
    Abstract: A rotor blade assembly includes a rotor blade comprising an inboard end and an outboard end. A composite yoke fitting made from a composite material is attached to the rotor blade. The composite yoke fitting includes an outboard portion inserted into the inboard end of the rotor blade, an inboard portion, and a flexure region about which the rotor blade is configured to flex. The inboard portion and the flexure region are outside the rotor blade.
    Type: Grant
    Filed: March 26, 2015
    Date of Patent: May 19, 2020
    Assignee: BELL HELICOPTER TEXTRON INC.
    Inventors: Andrew Haldeman, Frank Bradley Stamps, Drew Sutton
  • Reinforced fan containment case for a gas turbine engine
    Patent number: 10655500
    Abstract: A fan containment case for a gas turbine engine is provided which includes a barrel having an outermost portion, an innermost portion, and an interior portion in-between the outermost portion and the innermost portion. The outermost portion has an outermost band of material made of carbon fiber composite and the innermost portion has an innermost band of material made of carbon fiber composite. The interior portion includes a first interior band and a second interior band adjacent the first interior band. The first interior band is made of poly p-phenylene-2,6-benzobisoxazole (PBO) and the second interior band is made of an aramid material. The innermost portion has an innermost band of material made of carbon fiber composite.
    Type: Grant
    Filed: November 14, 2016
    Date of Patent: May 19, 2020
    Assignee: Rolls-Royce Corporation
    Inventor: Robert W. Heeter
  • Turbine blade sealing structure
    Patent number: 10648352
    Abstract: A turbine blade sealing structure for a ceramic matrix composite component is provided. The turbine sealing structure includes at least one top ply abutting a top portion of a shank. The at least one top ply extends out over the top portion of the shank. The turbine sealing structure includes at least one side ply abutting a side portion of the shank. The at least one side ply extends along a side portion of the shank. The at least one top ply and at least one side ply form an angel wing and a skirt with on the shank of the ceramic matrix composite component.
    Type: Grant
    Filed: June 13, 2013
    Date of Patent: May 12, 2020
    Assignee: General Electric Company
    Inventors: Anthony Reid Paige, Paul Izon, Michael Verrilli, Mark Willard Marusko, Mark Eugene Noe, Joshua Brian Jamison, Andrew John Breslin
  • Composite airfoil with rolled fiberglass reinforced leading edge
    Patent number: 10640197
    Abstract: A composite airfoil is disclosed. In various embodiments, a composite airfoil as disclosed herein includes an outer skin comprising one or more layers of carbon fiber composite material, the outer skin defining an aerodynamic surface having a leading edge; and a reinforcement material comprising a roll of fiberglass reinforced fabric positioned behind the outer skin along at least a portion of the leading edge.
    Type: Grant
    Filed: October 31, 2017
    Date of Patent: May 5, 2020
    Assignee: WISK AERO LLC
    Inventors: Cody Patrick Leuck, Bernard F. Ahyow
  • Fan containment case for a gas turbine engine
    Patent number: 10641287
    Abstract: According to one aspect, a fan containment case for a gas turbine engine is provided which includes a barrel having a first band of material on an outside of the barrel. The first band is made of carbon fiber composite. The barrel further includes a second band of material inboard of the fan case and made of poly p-phenylene-2,6-benzobisoxazole (PBO) composite. The barrel also includes a third band of material made of carbon fiber composite inboard of the second band.
    Type: Grant
    Filed: September 6, 2016
    Date of Patent: May 5, 2020
    Assignee: Rolls-Royce Corporation
    Inventors: Matthew J. Kappes, Robert W. Heeter, Benedict N. Hodgson
  • Piezoelectric damping rings
    Patent number: 10612401
    Abstract: A blisk assembly for vibration dampening includes a disk portion extending circumferentially about a central axis of the blisk, a plurality of blades integrally coupled to the disk, and a piezoelectric damping ring that includes a damping ring and a plurality of piezoelectric elements coupled to the damping ring. The disk portion includes a groove configured to receive the piezoelectric damping ring. As a result of centrifugal forces applied to the piezoelectric damping ring during rotation of the blisk assembly, mechanical energy may be generated at one or more of the plurality of piezoelectric elements, which is converted to electrical energy and transmitted to another one or more of the plurality of piezoelectric elements. Accordingly, the one or more of the piezoelectric elements having received the electricity can convert the electricity to mechanical energy to provide vibration damping.
    Type: Grant
    Filed: January 19, 2017
    Date of Patent: April 7, 2020
    Assignee: Rolls-Royce Corporation
    Inventors: Roy D. Fulayter, Daniel Hoyniak
  • Turbine engines with ceramic vanes and methods for manufacturing the same
    Patent number: 10605086
    Abstract: A vane assembly includes first and second annular metal rings configured to accept a compressed gas flow therebetween. The first and second annular rings each include a cutout portion. The assembly further includes a ceramic matrix composite vane configured as an airfoil having a blunt rounded nose and a flattened and tapered tail. A first radial end of the vane is rigidly disposed on the first annular ring and a second radial end of the vane is slidably disposed within the cutout portion of the second annular ring such that the vane is encompassed by the first and second annular rings. The vane includes a hollow through opening portion extending radially therethrough. Still further, the assembly includes a metallic elongated member disposed within and extending through the hollow portion of vane and through the cutout portion of the first annular ring.
    Type: Grant
    Filed: November 20, 2012
    Date of Patent: March 31, 2020
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: George E. Zurmehly, Milton Ortiz, Kin Poon, Michael Vinup, Ardeshir Riahi