Patents Examined by William H. Rodriguez
  • Patent number: 10995958
    Abstract: Disclosed are a pilot fuel injector, and a fuel nozzle and a gas turbine having the same. The pilot fuel injector is mounted on the fuel nozzle to uniformize the flow of the introduced air and to enable uniform mixing with the fuel, so that a fuel mixed air having a high mixing rate is provided to the combustion chamber. The mixing rate of the fuel mixed air directed to the combustion chamber is increased, thereby suppressing the generation of nitrogen oxides and preventing the flame stagnation.
    Type: Grant
    Filed: January 15, 2019
    Date of Patent: May 4, 2021
    Inventors: Borys Shershnyov, Yunyoung Doh
  • Patent number: 10989144
    Abstract: An injector element for injecting a mixture of at least a first propellant and a second propellant into a combustion chamber. The injector element includes a first tubular wall defining a first duct for injecting the first propellant, and a second wall surrounding the first wall and defining, between the first and second walls, a second duct for injecting the second propellant. The first wall includes a first electrode for igniting the mixture by electric discharge.
    Type: Grant
    Filed: January 26, 2017
    Date of Patent: April 27, 2021
    Assignee: ARIANEGROUP SAS
    Inventors: Jean-Luc Le Cras, Laurent Gomet
  • Patent number: 10968836
    Abstract: A distribution method for a gas turbine engine distributes fuel based on a calculated ratio of air flow burnt to total air flow through all combustion zones in the gas turbine engine. This ratio is used to achieve a predetermined flame temperature in the gas turbine engine.
    Type: Grant
    Filed: July 7, 2016
    Date of Patent: April 6, 2021
    Assignee: SIEMENS ENERGY GLOBAL GMBH & CO. KG
    Inventors: Brian John Price, Michael Johnson, Charles Fallaha, Jeremy Blackburn, Louis Demers
  • Patent number: 10961910
    Abstract: In a combustion cylinder, an outer-side region of a cooling part on an outer side with regard to a reference line orthogonal to a radial direction and an axial direction of a gas turbine and passing through a center of a combustor basket, and an inner-side region of the cooling part on an inner side with regard to the reference line are set. A connection angle at an intersection between an extension line of an outer surface of the combustor basket along the axial direction and an inner surface of a combustor transition piece is set. First regions are set at positions near the reference line, and second regions, with a larger connection angle than the first regions, are set at positions farther from the reference line than the first regions. The second regions are set to have a higher flow rate of a cooling medium than the first regions.
    Type: Grant
    Filed: October 28, 2016
    Date of Patent: March 30, 2021
    Assignee: MITSUBISHI POWER, LTD.
    Inventors: Kenji Sato, Kentaro Tokuyama
  • Patent number: 10948188
    Abstract: A fuel injector for a combustor of a gas turbine engine is disclosed herein. The fuel injector includes a fuel delivery system for receiving and distributing fuel and an injector body. The injector body includes a primary fuel gallery, a pilot fuel gallery, a primary perforated plate, and a pilot distributor plate. The primary fuel gallery is formed as an annular cavity in the injector body and extends around an assembly axis. The primary fuel gallery and the pilot fuel gallery are in flow communication with the fuel delivery system. The primary perforated plate is disposed within the primary fuel gallery and divides the primary fuel gallery. The primary perforated plate having a first perforation to restrict flow. The pilot distributor plate is disposed within the center body assembly and radially inward of the first portion of the primary gallery, adjacent to portions of the tube stem. The pilot distributor plate having a pilot distributor passage to restrict flow.
    Type: Grant
    Filed: December 12, 2018
    Date of Patent: March 16, 2021
    Assignee: Solar Turbines Incorporated
    Inventors: Christian Di Norscia, Edouard Bahous, Michael J. Ramotowski, Ram Srinivasan
  • Patent number: 10941709
    Abstract: The gas turbine engine can have a gas path extending in serial flow communication across a compressor, a combustion chamber, and a turbine, the turbine having at least one multistage turbine section having a front toward the combustion chamber and a rear opposite the front, a plenum radially outward of the gas path, and a plurality of aperture sets interspaced from one another between the front and the rear, the aperture sets providing fluid flow communication from the plenum to the gas path, and a cooling air path having an outlet fluidly connected to the plenum at the rear of the plenum.
    Type: Grant
    Filed: September 28, 2018
    Date of Patent: March 9, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Ion Dinu, Mohammed Ennacer, René Paquet
  • Patent number: 10941938
    Abstract: In accordance with at least one aspect of this disclosure, a fuel injector can include an annular body defining a gas fuel inlet therein, and a structure extending radially outward from the annular body and configured to extend into an air circuit. The structure can include a gas channel defined within the structure at least partially along a radial length of the structure. The gas channel is in fluid communication with the gas fuel inlet where the structure meets the annular body. The structure also includes a slot opening defined at least partially along a radial length of the structure and configured to fluidically connect the gas channel and the air circuit to all gas fuel to effuse into the air circuit.
    Type: Grant
    Filed: February 22, 2018
    Date of Patent: March 9, 2021
    Assignee: Delavan Inc.
    Inventors: Andy W. Tibbs, Gregory A. Zink, Thomas J. Ocken, Lev Alexander Prociw
  • Patent number: 10934940
    Abstract: The present application provides a combustor. The combustor may include a fuel supply line, a fuel nozzle, and a number of flow-device pathways connecting the fuel supply line and the fuel nozzle. The flow-device pathways may include a counter-swirl configuration.
    Type: Grant
    Filed: December 11, 2018
    Date of Patent: March 2, 2021
    Assignee: GENERAL ELECTRIC COMPANY
    Inventor: Homayoon Feiz
  • Patent number: 10934030
    Abstract: A rocket fueling system includes an insulated jacket configured to removably couple to at least a portion of a rocket and form an enclosed space between the insulated jacket and the at least the portion of the rocket. The rocket fueling system also includes a cryogen inlet in the insulated jacket. The cryogen inlet is configured to receive a cryogen into an interior chamber of the insulated jacket. The rocket fueling system further includes a cryogen outlet in the insulated jacket. The cryogen outlet is configured to provide the cryogen from the interior chamber in the insulated jacket to the at least the portion of the rocket in the enclosed space. The rocket fueling system still further includes a gas outlet in the insulated jacket configured to exhaust the cryogen from the enclosed space, and a flammable gas sensor configured to detect a flammable gas at the gas outlet.
    Type: Grant
    Filed: July 21, 2016
    Date of Patent: March 2, 2021
    Assignee: The Boeing Company
    Inventors: Daniel A. Watts, David S. Jenkins
  • Patent number: 10927764
    Abstract: The gas turbine engine fuel manifold assembly includes a fuel manifold, and fuel nozzles secured to the fuel manifold and in fluid communication therewith. A fuel inlet connector has a body secured to the fuel manifold, and is in-line therewith. The fuel inlet connector has at least one connector outlet fluidly connected to the fuel manifold. The at least one connector outlet defines a fuel flow direction having a main component in a circumferential direction relative to the axis.
    Type: Grant
    Filed: September 26, 2018
    Date of Patent: February 23, 2021
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Oleg Morenko, Ryan Miskie
  • Patent number: 10920669
    Abstract: A modular gas turbine system is disclosed. The system includes a base plate and a gas turbine engine mounted on the base plate. The gas turbine engine is drivingly coupled to a rotating load mounted on the base plate. A supporting frame extends above the base plate. A first bridge crane and a second bridge crane are movably supported on the supporting frame.
    Type: Grant
    Filed: February 16, 2017
    Date of Patent: February 16, 2021
    Assignee: NUOVO PIGNONE TECNOLOGIE SRL
    Inventors: Marco Giancotti, Andrea Righeschi, Luciano Guidotti, Michele Cecarini
  • Patent number: 10914471
    Abstract: A combustor has a structure enabling selective control of the amount of air supplied to the liner and the transition piece and includes a liner having one end connected to a fuel injector, the liner comprising an inner liner surrounded by an outer liner having a first opening that is elongated in a circumferential direction of the outer liner and is configured to introduce cooling air into an annular space between the inner liner and the outer liner; a liner sliding cover configured to adjust an opening degree of the first opening; and a transition piece connected at one end to the other end of the liner and connected to a turbine at the other end, the transition piece having an effusion hole configured to supply cooling air to a combustion chamber, the effusion hole having an opening area that is less than the opening degree of the first opening.
    Type: Grant
    Filed: October 22, 2018
    Date of Patent: February 9, 2021
    Assignee: Doosan Heavy Industries Construction Co., Ltd
    Inventors: Muhwan Chon, Donggon Lee
  • Patent number: 10914233
    Abstract: In a power generation system, exhausted fuel gas exhausted from a solid oxide fuel cell (SOFC) is used as a fuel of a first combustor or a second combustor of a gas turbine, and at the same time, a part of compressed air compressed by a compressor of the gas turbine is used to drive the SOFC. The gas turbine includes the first combustor for burning fuel gas which is different from the exhausted fuel gas, a first turbine configured to be driven by combustion gas supplied from the first combustor, the second combustor for burning at least a part of the exhausted fuel gas, and a second turbine coupled with the first turbine and configured to be driven by combustion gas supplied from the second combustor.
    Type: Grant
    Filed: September 21, 2018
    Date of Patent: February 9, 2021
    Assignee: MITSUBISHI POWER, LTD.
    Inventors: So Manabe, Kentaro Fujii
  • Patent number: 10914236
    Abstract: A heat exhaust system for an on-aircraft electric generator, includes: a fuel pump which is driven by electric power generated by an electric generator installed in an aircraft, and which measures and supplies fuel to an engine of the aircraft; a first heat exchanger which releases heat generated by the electric generator into the fuel supplied to the engine; a fuel flow rate determiner which determines a flow rate of the fuel supplied to the engine by the fuel pump; an electric generator output determiner which determines an output from the electric generator; and a heat release controller which controls heat release at the first heat exchanger by using at least one of the flow rate of the fuel determined by the fuel flow rate determiner and the output determined by the electric generator output determiner as a control parameter.
    Type: Grant
    Filed: October 31, 2018
    Date of Patent: February 9, 2021
    Assignee: IHI Corporation
    Inventors: Noriko Morioka, Hitoshi Oyori
  • Patent number: 10895157
    Abstract: A gas turbine engine component includes a hot side surface that is configured for exposure to a hot gas flow path, a second surface that is opposite the hot side surface and not exposed to the hot gas flow path, and an effusion cooling aperture positioned along the hot side surface. The effusion cooling aperture includes a recessed portion including a void area beginning at the hot side surface and extending inwardly therefrom, a forward surface, an entirety of which is angled at 90 degrees or greater than 90 degrees with respect to the hot side surface, defining a forward end of the recessed portion, an inward surface, angled with respect to the hot side surface, and connecting the forward surface to the hot side surface, and an overhang portion connected with the hot side surface and extending aftward from the forward surface and over the void area.
    Type: Grant
    Filed: April 24, 2017
    Date of Patent: January 19, 2021
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Rodolphe Dudebout, Paul Yankowich
  • Patent number: 10895384
    Abstract: A fuel injector assembly for a gas turbine engine is generally provided. The first fuel injector includes a first centerbody surrounding a first walled fuel injection circuit. A first fuel injection port is extended at least partially radially through the first centerbody in fluid communication with the first walled fuel injection circuit. The first centerbody defines a cooling circuit surrounding the first walled fuel injection circuit. The first centerbody defines a plurality of cooling openings at a downstream end of the first centerbody. The plurality of cooling openings is in fluid communication with the cooling circuit. The first centerbody defines an axially extended cooling outlet at the downstream end of the first centerbody.
    Type: Grant
    Filed: November 29, 2018
    Date of Patent: January 19, 2021
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Randall Charles Boehm, Gregory Allen Boardman, Ajoy Patra, David Albin Lind, Pradeep Naik, Ranjeet Kumar Mishra
  • Patent number: 10890113
    Abstract: Embodiments of the invention involve the application of a disk-in-tube type of “wet” or “dry” ESP (electrostatic precipitation) technology for the capture/removal of airborne particles entering a gas turbine compressor. This provides an effective method of particulate removal without the inefficiencies associated with conventional filtering techniques. Embodiments of the innovative approach also eliminate the inlet airstream blocking effect of a conventional filter, thus making its use and operation adaptable to different operating environments and processes that require clean input air streams (including industrial manufacturing processes, power generators, combined turbine and fluid recapture systems for use in heating and cooling, etc.).
    Type: Grant
    Filed: December 1, 2016
    Date of Patent: January 12, 2021
    Assignee: AIRTECH INNOVATIONS, LLC
    Inventor: Steven A. Jaasund
  • Patent number: 10890328
    Abstract: A transition piece can include: an inner transition piece including an inlet and an outlet; an outer transition piece surrounding the inner transition piece with a flow passage; an outlet fin-pin flow guide disposed on the inner transition piece and located closer to the outlet than the inlet; a first bottom fin disposed at a bottom portion of the inner transition piece; and a second bottom fin disposed at the bottom portion of the inner transition piece, wherein the first bottom fin and the second bottom fin are arranged to be inclined to each other at an acute angle.
    Type: Grant
    Filed: November 29, 2018
    Date of Patent: January 12, 2021
    Assignee: Doosan Heavy Industries Construction Co., Ltd
    Inventors: Jung Jin Choi, Yunyoung Doh, Donggon Lee
  • Patent number: 10883718
    Abstract: An air intake swirler for a turbomachine injection system includes an upstream wall and a downstream wall, both of revolution about an axis of the air intake swirler, and fins distributed about the axis and connecting the upstream wall to the downstream wall so as to delimit, between the upstream wall and the downstream wall, air inlet channels each having an inlet and an outlet. The swirler includes two aerodynamic deflectors that respectively extend the downstream walls radially outward and that have a concavity oriented upstream. The aerodynamic deflectors extend radially facing the respective inlets of the air inlet channels and thus make it possible to limit the loss of pressure of the air supplied to the air inlet channels.
    Type: Grant
    Filed: April 28, 2017
    Date of Patent: January 5, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Romain Nicolas Lunel, Guillaume Aurelien Godel, Haris Musaefendic, Christophe Pieussergues, Francois Pierre Georges Maurice Ribassin
  • Patent number: 10883447
    Abstract: An aircraft propulsion assembly including a bypass turbojet having a stationary inter-compressor casing positioned upstream from a space between passages, a nacelle including at its downstream end an inner wall that defines the outside of the space between passages and the inside of the bypass stream flow passage, and an outer wall arranged around the inner wall and that defines the outside of the bypass stream flow passage, at least a portion of the inner wall being suitable for moving between a maintenance position and a working position, and a thrust-reverser including a downstream element of the outer wall that is movable in translation between a retracted position and a thrust-reversal position in which it allows bypass stream deflector elements to be deployed in a radial direction, the deployment of the stream deflector elements being controlled by guide rods.
    Type: Grant
    Filed: February 3, 2017
    Date of Patent: January 5, 2021
    Assignees: SAFRAN AIRCRAFT ENGINES, SAFRAN NACELLES
    Inventors: Carmen Gina Ancuta, Kevin Morgane Lemarchand, Olivier Kerbler, Melody Seriset