Patents Examined by Craig Kim
  • Patent number: 11073041
    Abstract: An aircraft engine having an oil circuit and a transmission that can be supplied with oil via the oil circuit. Oil fed to the transmission can be directed out of the transmission into an oil reservoir, from which oil can be introduced directly back into the transmission via a hydraulic line path. According to the invention, the oil fed to the oil reservoir can only be fed to the hydraulic line path below a defined filling level of the oil reservoir. When the defined filling level of the oil reservoir is reached, oil can also be introduced into a further hydraulic line path.
    Type: Grant
    Filed: November 26, 2018
    Date of Patent: July 27, 2021
    Assignee: Rolls-Royce Deutschland Ltd & Co KG
    Inventors: Stephan Uhkoetter, Uwe Kracht, Thomas Philip Astley
  • Patent number: 11073284
    Abstract: A combustor wall assembly has a heat shield and a supporting shell with a cooling cavity defined therebetween. A grommet generally includes a wall defining a dilution hole isolated from the cooling cavity, and a flange projecting radially outward from the wall and into the cooling cavity. The flange is space from the heat shield and a cooling channel is defined between the wall and the heat shield that communicates with the cavity for cooling the wall proximate to a combustion chamber.
    Type: Grant
    Filed: December 10, 2018
    Date of Patent: July 27, 2021
    Assignee: Raytheon Technologies Corporation
    Inventor: Jonathan P. Sandoval
  • Patent number: 11067276
    Abstract: An igniter seal arrangement for a combustion chamber. The combustion chamber has a wall having first surface and second surfaces. A boss projects from the first surface, and has a platform on its remote end. The platform has an inner surface spaced from the first surface of the wall to define a chamber between the first surface of the wall and the inner surface of the platform. The platform has an outer surface facing away from the first surface of the wall and an aperture extends through the wall from the outer surface of the platform of the boss to the second surface. First and second L-shape rails extend from the platform and a sealing member has a first edge and a second edge locatable between the outer surface of the platform and the first and second L-shape rails and the sealing member has an aperture to receive an igniter.
    Type: Grant
    Filed: March 15, 2019
    Date of Patent: July 20, 2021
    Assignee: ROLLS-ROYCE plc
    Inventors: Paul A Hucker, Stephen C Harding, Iain Morgan
  • Patent number: 11053862
    Abstract: A fuel injector for a gas turbine engine includes a feed arm defining a conduit extending between an inlet end and an outlet end and a plunger. The plunger is disposed within the conduit and is movable between a plunger first position and a plunger second position. A flow area defined between the plunger and the feed arm is smaller in the plunger first position than in the plunger second position to bias fuel flow through the fuel injector. Fuel systems, gas turbine engines, and methods of controlling fuel flow in gas turbine engine fuel systems are also described.
    Type: Grant
    Filed: September 25, 2017
    Date of Patent: July 6, 2021
    Assignee: Delavan Inc.
    Inventors: Jason A. Ryon, Lev Alexander Prociw
  • Patent number: 11053851
    Abstract: The present invention discloses embodiments for a power augmentation system of a gas turbine engine resulting in performance improvements while also improving efficiency. The invention provides systems and methods for generating a heated air supply by way of mixing compressed air from an electrically-driven process with air drawn from the engine compressor discharge plenum.
    Type: Grant
    Filed: February 10, 2017
    Date of Patent: July 6, 2021
    Assignee: Powerphase International, LLC
    Inventor: Robert J. Kraft
  • Patent number: 11028801
    Abstract: A grating for the formation of a reverse flow of a turbofan engine and comprising fins of a first type having a curved profile whose rounding is oriented aft and whose center of curvature is forward relative to the fin of the first type, fins of a second type having a curved profile whose rounding is oriented aft and whose center of curvature is forward relative to the fin of the second type. In this grating, each fin of one of the two types is inserted between two fins of the other type moving from forward to aft and the cord of the fins of the second type is smaller than the cord of the fins of the first type.
    Type: Grant
    Filed: November 27, 2018
    Date of Patent: June 8, 2021
    Inventors: Christophe Bourdeau, Quentin Vaucouloux, Romain Cusset
  • Patent number: 11022072
    Abstract: A divergent flap seal includes a flap seal body with a spine, the flap seal body manufactured of a non-metallic material. A mount is engaged with the spine at the dovetail interface and a resilient member at the dovetail interface.
    Type: Grant
    Filed: February 23, 2017
    Date of Patent: June 1, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Truc Luong, Keegan M. Martin
  • Patent number: 11008938
    Abstract: A low emission, high efficiency Gas Turbine engine operating on a combination of Natural Gas and Bio Gas as fuel, driving either a high efficiency turbo-blower or a high efficiency Turbo Pump system combined with heat recovery systems and in other embodiments is provided a generator of electricity or providing evaporate cooling from using the remaining waste heat in the exhaust gas.
    Type: Grant
    Filed: September 14, 2018
    Date of Patent: May 18, 2021
    Assignee: APGN INC.
    Inventor: Omar Hammoud
  • Patent number: 10995635
    Abstract: A gas turbine engine component assembly is provided. The gas turbine engine comprises: a first component having a first surface and a second surface opposite the first surface; a second component having a first surface and a second surface, the first surface of the first component and the second surface of the second component defining cooling channel therebetween in fluid communication with the cooling hole for cooling the second surface of the second component; and a particulate mitigation device extending from the first surface of the second component a selected distance wherein the particulate mitigation device has an opening therethrough in fluid connection with the cooling channel, and wherein the selected distance is selected to reduce the amount of particulate entering the cooling channel.
    Type: Grant
    Filed: November 30, 2017
    Date of Patent: May 4, 2021
    Inventor: Scott H. Lamson
  • Patent number: 10982594
    Abstract: A bleed valve control system for mounting to a support structure adjacent to a fan air plenum within an aircraft includes a bleed valve module, a pneumatic valve controller, and a fan air duct. The bleed valve module includes a pipe, a plurality of bleed valves connected to the pipe, and a plurality of pneumatic actuators connected to the bleed valves. The pneumatic valve controller includes a plurality of electrical control elements and a cooling shroud. The cooling shroud is attached to the pipe and at least partially surrounds the plurality of electrical control elements. The fan air duct connects the cooling shroud to the fan air plenum such that fan air flows through the cooling shroud to cool the plurality of electrical control elements.
    Type: Grant
    Filed: November 26, 2018
    Date of Patent: April 20, 2021
    Assignee: Hamilton Sundstrand Corporation
    Inventors: Donald E. Army, John M. Maljanian, Gregory L. DeFrancesco
  • Patent number: 10969101
    Abstract: The present invention provides a main nozzle of a combustor, a plurality of the main nozzles are to be installed on an outer peripheral side of a pilot nozzle of the combustor at an interval in a circumferential direction of the pilot nozzle, the main nozzle includes a main nozzle body extending in an axial line; a swirl vane protruded from an outer peripheral surface of the main nozzle body in a radial direction of the axial line, and is configured to allow a fluid flowing downstream in a direction of the axial line to swirl around the axial line; and temperature sensors installed on the main nozzle body so as to be disposed on a tangential line to a mean line of the swirl vane drawn between a vane ventral surface and a vane dorsal surface of the swirl vane, at a downstream end portion of the swirl vane.
    Type: Grant
    Filed: December 15, 2017
    Date of Patent: April 6, 2021
    Inventors: Atsushi Moriwaki, Kenji Miyamoto, Keijiro Saito
  • Patent number: 10968831
    Abstract: A modular gas turbine system for on-shore LNG plants is disclosed. The module comprises a base plate having a top side and a bottom side and supports on the top side thereof at least a gas turbine engine, a control and electrical room wired to the gas turbine engine, at least part of auxiliaries of the gas turbine engine. Additionally, at least one compressor is supported on the base plate and mechanically coupled to the gas turbine engine and driven into rotation by said gas turbine engine.
    Type: Grant
    Filed: September 26, 2016
    Date of Patent: April 6, 2021
    Inventor: Marco Giancotti
  • Patent number: 10961915
    Abstract: A system for starting a gas turbine engine includes a rotor drive system and a hydraulic motor system operatively connected to the rotor drive system. A gas turbine engine is operatively connected to the hydraulic motor system for starting the gas turbine engine. A method for starting an engine includes initiating single-engine-operation on a multi-engine aircraft. Single-engine operation includes operating a first engine and powering down a second engine. The method includes running a hydraulic motor system. The hydraulic motor system is driven by the rotor drive system and is operatively connected to the second engine. The method includes identifying a need to start the second engine and starting the second engine using the hydraulic motor system.
    Type: Grant
    Filed: April 13, 2016
    Date of Patent: March 30, 2021
    Inventors: Joseph L. Simonetti, Mark D. Bystry, Jr., Michael P. Strauss, Michael J. DeVita
  • Patent number: 10955139
    Abstract: Disclosed are a fuel nozzle assembly, and a fuel nozzle module and gas turbine having the same. The fuel nozzle assembly includes a fuel nozzle, a shroud spaced apart from the fuel nozzle and defining a flow path between an inner wall and the fuel nozzle, a rim formed around the shroud to guide air, and a turning guide spaced apart from the rim to distribute the air. The turning guide includes a turning separator spaced apart from the rim to extend in a circumferential direction of the rim, and inner separators extending in a radial direction of the rim to interconnect opposite circumferential ends of the turning separator and an outer surface of the fuel nozzle. The fuel nozzle assembly prevents air pockets, and ensures uniform supply of air, thereby preventing a local increase in combustion temperature inside the fuel nozzle and reducing generation of NOx.
    Type: Grant
    Filed: April 25, 2018
    Date of Patent: March 23, 2021
    Assignee: Doosan Heavy Industries & Construction Co., LTD.
    Inventor: Jongho Uhm
  • Patent number: 10954859
    Abstract: A combustor assembly for a gas turbine engine according to an example of the present disclosure includes, among other things, a combustion chamber, and a fuel injector assembly in communication with the combustion chamber that has a swirler body situated about a nozzle to define an injector passage that converges to a throat. The throat is defined at a distance from the combustion chamber. The nozzle includes a primary fuel injector along a first fuel injector axis and at least one secondary plain jet fuel injector axially forward of the primary fuel injector.
    Type: Grant
    Filed: July 25, 2017
    Date of Patent: March 23, 2021
    Inventors: Zhongtao Dai, Lance L. Smith, Jeffrey M. Cohen
  • Patent number: 10954856
    Abstract: A turbomachine comprises an inter-flow compartment extending radially between first and second intermediate walls, gas bypass ducts passing through the second intermediate wall and communicating with evacuation outlets opening up into a secondary gas flow; an oil reservoir arranged in the inter-flow compartment, and a surface air-oil heat exchanger communicating with the oil reservoir for fluid circulation. Circumferentially in relation to the inter-flow compartment, the surface air-oil heat exchanger extends at least partially between the evacuation outlets which pass through the first intermediate wall.
    Type: Grant
    Filed: December 20, 2016
    Date of Patent: March 23, 2021
    Assignee: Safran Aircraft Engines
    Inventors: Bruna Manuela Ramos, Carmen Gina Ancuta
  • Patent number: 10948190
    Abstract: A combustion chamber (18) of a thermodynamic cycle turbine with a recuperator, for electrical energy production, comprising a casing (56) housing a flame tube (64) with a perforated diffuser for passage of the hot compressed air, a primary zone (ZP) that receives part of the hot compressed air flow and where combustion takes place, and a dilution zone (ZD) where the burnt gases from the primary zone mix with the remaining part of the hot compressed air flow, said chamber further comprising an injection means (76) for injecting at least one fuel. The flame tube carries a flame stabilizer (82) comprising perforated diffuser (88), at least one combustion gas recirculation passage (98) and a mixing tube (94).
    Type: Grant
    Filed: September 13, 2016
    Date of Patent: March 16, 2021
    Assignee: IFP Energies nouvelles
    Inventors: Hubert Baya Toda, Jean-Baptiste Michel, Julien Thiriot, Thomas Valin
  • Patent number: 10934938
    Abstract: A gas turbine engine has an inner housing surrounding a compressor, a combustor, and a turbine, with an inlet leading into the compressor, and a cooling sleeve defined radially outwardly of the inlet to the compressor for receiving cooling air radially outward of the compressor inlet. The cooling sleeve extends along a length of the engine, and radially outwardly of the inner housing, with the cooling air in the cooling sleeve being ejected at a downstream end to mix with products of combustion downstream of the turbine. An aircraft is also disclosed.
    Type: Grant
    Filed: July 22, 2016
    Date of Patent: March 2, 2021
    Assignee: Raytheon Technologies Corporation
    Inventors: Gabriel L. Suciu, Wesley K. Lord, Jesse M. Chandler, Steven H. Zysman
  • Patent number: 10928068
    Abstract: An annular Helmholtz damper for a gas turbine can combustor, the annular Helmholtz damper having an axis; an inner wall and an outer wall concentrically arranged with respect to the axis to define an annular damping volume arranged around a can combustor; a front and rear circumferential plates for closing the annular damping volume upstream and downstream; at least one intermediate circumferential plate arranged between the front and the rear plates for dividing the annular damping volume in a main and a secondary volume; and a plurality of intermediate drain holes passing the intermediate circumferential plate and configured for draining collected liquid from the main volume to the secondary volume.
    Type: Grant
    Filed: September 20, 2017
    Date of Patent: February 23, 2021
    Inventors: Jost Imfeld, Paul Marlow
  • Patent number: 10926883
    Abstract: An aircraft includes a first engine that generates first bleed air flow and a second engine that generates second bleed air flow. The aircraft further includes an aircraft environmental control system (ECS) with a bleed manifold to collect the first bleed air flow and the second bleed air flow, and one or more air cycle machines to perform air conditioning consuming bleed air flow from the bleed manifold. The ECS balances the first bleed air flow and the second bleed air flow output from the first engine and second engine, respectively, based on a bleed manifold pressure of the bleed manifold.
    Type: Grant
    Filed: March 21, 2018
    Date of Patent: February 23, 2021
    Inventors: Jeffry K. Kamenetz, Erin G. Kline, Jeffrey Ernst, James Joyce, Kevin R. DeRoy