Patents Examined by Brian Christopher Delrue
  • Patent number: 11939881
    Abstract: A platform of a gas turbine rotor blade according to one embodiment includes a groove portion recessed from an end surface on a trailing edge side toward a leading edge side. A bottom portion of the groove portion overlaps at least a blade-shaped portion when viewed from a radial direction.
    Type: Grant
    Filed: March 23, 2023
    Date of Patent: March 26, 2024
    Assignee: MITSUBISHI HEAVY INDUSTRIES, LTD.
    Inventors: Ryo Murata, Yuji Komagome, Naoya Tatsumi, Hiroki Kitada, Shunsuke Torii
  • Patent number: 11933634
    Abstract: A compressor variable angle measurement system for guiding the positioning variable vanes supported on a penny of a compressor of a gas turbine engine. The system comprising a gauge assembly that is connectable to a computing device. the gauge assembly comprises a base plate and a clamp arm. The gauge assembly is configured to removably grip a variable vane between three vane contact portions of the baseplate and the vane contact portion of the clamp arm and on the leading edge vane engaging portion and the trailing edge vane engaging portion of the base plate, the stagger angle of the variable vane with respect to the radial setting pin being determined by the computing device from measurements made by an inertial measurement unit.
    Type: Grant
    Filed: August 10, 2022
    Date of Patent: March 19, 2024
    Inventor: Nicholas Howarth
  • Patent number: 11933346
    Abstract: A screw assembly, including: a removable shoulder screw including: a first screw shaft portion; a second screw shaft portion; a first threaded portion; and a first shaft edge between the first screw shaft portion and the second screw shaft portion, wherein the second screw shaft portion is between the first screw shaft portion and the first threaded portion, and wherein a diameter of the second screw shaft portion is smaller than the diameter of the first screw shaft portion; and a first removable shoulder including a first removable shoulder opening and a first removable shoulder edge, wherein the first removable shoulder opening has a diameter less than the diameter of the first screw shaft portion and is configured to engage the second screw shaft portion, and wherein the first removable shoulder edge is configured to engage the first shaft edge.
    Type: Grant
    Filed: May 12, 2023
    Date of Patent: March 19, 2024
    Assignee: NOKIA SOLUTIONS AND NETWORKS OY
    Inventor: Fabien Letourneau
  • Patent number: 11927109
    Abstract: The present invention relates to a blade for a gas turbine, in particular of an aircraft engine, having a blade airfoil, which has a blade-root-side first profile section and a blade-tip-side second profile section, which is spaced apart from the first profile section in a radial direction, from the first profile section to the second profile section, by a blade airfoil height, wherein a stagger angle of the blade airfoil changes with a height in the radial direction over the first profile section at least over certain portions, wherein, in a first region between a first height and a second, greater height, the change in the stagger angle over the height does not decrease with increasing height at least over certain portions.
    Type: Grant
    Filed: December 8, 2020
    Date of Patent: March 12, 2024
    Assignee: MTU Aero Engines AG
    Inventors: Sergio Elorza Gomez, Tobias Froebel, Nina Wolfrum, Sebastian Mann
  • Patent number: 11920608
    Abstract: An axial fan includes a hub having a rotation shaft and configured to be driven to rotate and blades provided to the hub. The blades each have a front edge portion and a rear edge portion. A first blade section is a section of a portion between the front edge portion and the rear edge portion of each of the blades along a direction in which the blades rotate, and the first blade section is an area of each of the blades that is further inward than an outer periphery edge portion that is a most radially outer periphery in each of the blades. In the first blade section, the blades each have a projection portion and a first recess portion. The projection portion projects from a portion of a pressure surface of each of the blades. The first recess portion recedes from a portion of the pressure surface that is between the projection portion and the rear edge portion.
    Type: Grant
    Filed: June 13, 2019
    Date of Patent: March 5, 2024
    Assignee: Mitsubishi Electric Corporation
    Inventors: Katsuyuki Yamamoto, Takahide Tadokoro, Takuya Teramoto
  • Patent number: 11913348
    Abstract: A gas turbine engine stator vane combination includes a stator vane body having an airfoil with a leading edge, a trailing edge, a suction side and a pressure side, and having at least one internal cooling channel. The stator vane body is formed of ceramic matrix composite materials. A spar is received within the at least one cooling air channel and formed of a metal. The spar has an outer peripheral surface spaced from an inner peripheral surface of the cooling air channel to define a cooling air path, with the cooling air path having a varying cross-sectional area through the cooling air channel. A gas turbine engine is also disclosed.
    Type: Grant
    Filed: October 12, 2022
    Date of Patent: February 27, 2024
    Assignee: RTX Corporation
    Inventors: Jonas Banhos, James T. Roach
  • Patent number: 11905853
    Abstract: An airfoil assembly defining a primary airflow path for a turbine engine comprising a platform, an airfoil extending from the platform and into at least a portion of the primary airflow path, a secondary airflow path comprising air from the primary airflow path, and a deflector provided within the secondary airflow path.
    Type: Grant
    Filed: April 13, 2021
    Date of Patent: February 20, 2024
    Assignee: GE AVIO S.r.l.
    Inventors: Alberto Buonvino, Luca Giacobone, Daniele Coutandin, Ernesto Sozio, Francesco Bertini
  • Patent number: 11898466
    Abstract: A method for coating a turbomachine guide vane including a root and a tip, an extrados face and an intrados face connected to one another by a leading edge and a trailing edge, the method including completely covering one of the faces of the vane with a polymer coating of thickness (e1) provided with grooves, removing the grooves from a part of the polymer coating in such a way that the polymer coating includes a grooved zone and a non-grooved zone, coating the non-grooved zone with a coat of paint of thickness (e3) such that the thickness of the coat of paint superimposed on the non-grooved zone is substantially equal to the thickness (e1) of the grooved zone.
    Type: Grant
    Filed: June 18, 2020
    Date of Patent: February 13, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Célia Iglesias Cano, Vincent Marie Jacques Rémi De Carné-Carnavalet, Antoine Hubert Marie Jean Masson
  • Patent number: 11885237
    Abstract: A turbomachine having an engine centerline and a first rotor. The first rotor having a first annular drum and being connected to a first plurality of blades. At least one blade of the first plurality of blades having a blade root, a blade tip, a first arm, a second arm and a first seal. The first arm extending from the blade root and having a radial retention hook. The second arm extending from the blade tip.
    Type: Grant
    Filed: December 14, 2022
    Date of Patent: January 30, 2024
    Assignee: GE AVIO S.r.l.
    Inventors: Matteo Renato Usseglio, Antonio Giuseppe D'Ettole, Andrea Depalma
  • Patent number: 11885241
    Abstract: A turbine nozzle assembly includes at least one airfoil and an outer endwall coupled to a radial outer end of the at least one airfoil. A mounting rail is coupled to the outer endwall and extends at least partially radially outward from the outer endwall and at least partially circumferentially along the outer endwall. A stress relief structure is defined in the mounting rail. The stress relief structure includes an end opening defined in a radial outer surface of the mounting rail, a slot defined through the rail thickness of the mounting rail and coupled to the end opening, and an oblong opening defined through the rail thickness of the mounting rail and coupled to a radial inner end of the slot. The oblong opening is arranged asymmetrically in a circumferential direction relative to the slot to relieve stress where prevalent in the mounting rail.
    Type: Grant
    Filed: July 28, 2022
    Date of Patent: January 30, 2024
    Assignee: General Electric Company
    Inventors: Lauren Elizabeth Rogers, William Scott Zemitis, Kristen Barbara Coletti
  • Patent number: 11879431
    Abstract: There is provided a method (40) of correcting blade pitch in a wind turbine (10) having a tower (12) and a plurality of rotor blades (18). The method (40) comprises: receiving (410) sensor output data from one or more wind turbine sensors (141), the sensor output data including data indicative of excitation of the tower (12) for a plurality of different pitch angles of a particular one of the blades (18); determining (420) a corrected pitch reference of the particular blade (18), the corrected pitch reference corresponding to a minimum tower excitation based on the received sensor output data; and, sending (430) the corrected pitch reference to a pitch actuator system (24) of the particular blade (18).
    Type: Grant
    Filed: July 7, 2020
    Date of Patent: January 23, 2024
    Assignee: Vestas Wind Systems A/S
    Inventors: Karthik Krishnan Jamuna, Igor Kelbas, Selvavignesh Vedamanickam, Maxime Coulange, Jiji Nallathambi Kumaradhas, Jesper Errboe Askov, Karl H. Svendsen, Edgar Anahua, Nikolaj Sig Overgaard
  • Patent number: 11879339
    Abstract: A control valve composed of sectors of stationary blades, which are externally connected to a stator, includes an inner platform divided into an outer portion formed of sectors and associated, by radial slide connections, with an inner portion in the form of a ring which is continuous over a circumference, which carries an abradable seal. Springs ensure the radial position of the crown, and the concentricity thereof to the rest of the machine. The diameter of the crown is essentially determined by the temperature of the gases which pass in front of it. The independence of the radial thermal deformations is ensured by slides composed of sliding sleeves.
    Type: Grant
    Filed: March 22, 2021
    Date of Patent: January 23, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Joao Antonio Amorim, Vahe Kupelian
  • Patent number: 11873737
    Abstract: A system is provided for a gas turbine engine. This gas turbine engine system includes a flowpath wall and a deflector. The flowpath wall includes a surface and an opening to a blind aperture. The surface forms a peripheral boundary of an internal engine flowpath. The opening is disposed in the surface. The blind aperture extends vertically into the flowpath wall from the opening. The deflector projects vertically out from the flowpath wall into the internal engine flowpath. The deflector is configured to deflect gas flowing within the internal engine flowpath over the opening.
    Type: Grant
    Filed: July 22, 2022
    Date of Patent: January 16, 2024
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Tahereh Mirmohammadi Ghoojdi
  • Patent number: 11873731
    Abstract: A gas turbine engine comprises a fan mounted to rotate about a main longitudinal axis; an engine core, comprising in axial flow series a compressor, a combustor, and a turbine coupled to the compressor through a shaft; a reduction gearbox that receives an input from the shaft and outputs drive to the fan so as to drive the fan at a lower rotational speed than the shaft; wherein the compressor comprises a first stage at an inlet and a second stage, downstream of the first stage, comprising respectively a first rotor with a row of first blades and a second rotor with a row of second blades, the first and second blades comprising respective leading edges, trailing edges and tips, and wherein the ratio of a maximum leading edge radius of the first blades to a maximum leading edge radius of the second blades is greater than 2.8.
    Type: Grant
    Filed: February 27, 2023
    Date of Patent: January 16, 2024
    Assignee: ROLLS-ROYCE plc
    Inventors: Ian J. Bousfield, Duncan A. Macdougall
  • Patent number: 11873730
    Abstract: An apparatus is provided for a gas turbine engine. This engine apparatus includes an airfoil extending spanwise along a span line from a base to a tip. The airfoil extends laterally between a pressure side and a suction side. The airfoil extends longitudinally along a camber line from a leading edge to a trailing edge. The airfoil includes a first section and a second section arranged longitudinally between the first section and the trailing edge along the camber line. An angle between the camber line and a reference plane changes according to a slope as the airfoil extends longitudinally along the camber line. The slope in the second section is greater than the slope in the first section.
    Type: Grant
    Filed: November 28, 2022
    Date of Patent: January 16, 2024
    Assignee: RTX CORPORATION
    Inventors: Michael M. Joly, Gorazd Medic
  • Patent number: 11873726
    Abstract: A strut provided in an exhaust diffuser and having an airfoil-shaped cross-section is provided. The strut may include a cut portion configured to be formed in a trailing edge in a span direction. The cut portion is configured to provide a stepped portion in at least a portion of the trailing edge.
    Type: Grant
    Filed: May 10, 2023
    Date of Patent: January 16, 2024
    Assignee: DOOSAN ENERBILITY CO., LTD.
    Inventors: Ik Sang Lee, Willy Hofmann
  • Patent number: 11867081
    Abstract: A turbine blade for a gas turbine engine has an airfoil including leading and trailing edges joined by spaced-apart pressure and suction sides to provide an external airfoil surface extending from a platform in a spanwise direction to a tip. The external airfoil surface is formed in substantial conformance with multiple cross-sectional profiles of the airfoil defined 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.
    Type: Grant
    Filed: January 26, 2023
    Date of Patent: January 9, 2024
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Abdulhalim Twahir, Panagiota Tsifourdaris, Daniel Lecuyer, Masoud Roshan Fekr, Stephane Bigras
  • Patent number: 11867078
    Abstract: A turbocharger turbine wheel can include a hub that includes a rotational axis, a backdisk and a nose, where the rotational axis defines an axial coordinate (z) in a cylindrical coordinate system that includes a radial coordinate (r) and an azimuthal coordinate (?) in a direction of intended rotation about the rotational axis; and blades that extend outwardly from the hub, where each of the blades includes a leading edge and a trailing edge, where the leading edge includes a lower axial point defined by a first theta angle and an upper axial point defined by a second theta angle, where the first theta angle is greater than the second theta angle with respect to the direction of intended rotation of the turbine wheel.
    Type: Grant
    Filed: June 11, 2022
    Date of Patent: January 9, 2024
    Assignee: Garrett Transportation I Inc.
    Inventors: Penny Li, Annie Li, Daniel Wood
  • Patent number: 11859516
    Abstract: A gas turbine engine defining a centerline and a circumferential direction, the gas turbine engine including: a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the turbomachine defining a working gas flowpath and a fan duct flowpath; a primary fan driven by the turbomachine defining a primary fan tip radius R1 and a primary fan hub radius R2; a secondary fan located downstream of the primary fan and driven by the turbomachine, at least a portion of an airflow from the primary fan configured to bypass the secondary fan, the secondary fan defining a secondary fan tip radius R3 and a secondary fan hub radius R4, wherein the secondary fan is configured to provide a fan duct airflow through the fan duct flowpath during operation to generate a fan duct thrust, wherein the fan duct thrust is equal to % Fn3S of a total engine thrust during operation of the gas turbine engine at a rated speed during standard day operating conditions; wherein a ra
    Type: Grant
    Filed: August 26, 2022
    Date of Patent: January 2, 2024
    Assignee: General Electric Company
    Inventor: David Marion Ostdiek
  • Patent number: 11859515
    Abstract: There is provided apparatuses and methods for a gas turbine engine. The embodiments include a core section with a flow path. The flow path includes a stator vane array having outlet vanes. Each outlet vane has a trailing edge. A strut has a leading edge that is upstream of the trailing edges. Alternatively, the flow path includes a stator vane array having inlet vanes. Each inlet vane has a leading edge. The strut has a trailing edge that is downstream of the leading edges. There also is increased spacing between adjacent vanes and rotor blades.
    Type: Grant
    Filed: March 4, 2022
    Date of Patent: January 2, 2024
    Assignee: General Electric Company
    Inventors: Tsuguji Nakano, Darek Zatorski, Andrew Breeze-Stringfellow