Patents Examined by Carlos A Rivera
  • Patent number: 10968747
    Abstract: In accordance with one aspect of the disclosure, an airfoil is disclosed. The airfoil may include a platform and a blade extending from the platform. The blade may have a root proximate the platform and a tip radially outward from the platform. The root may have a greater thickness than a cross-section at about a quarter-span of the blade or greater.
    Type: Grant
    Filed: December 18, 2013
    Date of Patent: April 6, 2021
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Eric D. Gray, Razvan Virgil Florea, Mark B. Stucky, Ray-Sing Lin
  • Patent number: 10865709
    Abstract: An on-board Flex-Fuel H2 reforming apparatus provides devices and the methods of operating these devices to produce a combustible reformate containing H2 and CO from hydrocarbons and bio-fuels. For this generator, one or more parallel autothermal reformers are used to convert the fuels into the reformate over Pt group metal catalysts, and the produced reformate is then cooled, compressed and stored in vessels at a pressure between 1 to 100 atmospheres. The reformate from the storage vessels is used either as the sole fuel or is mixed with other fuels as the fuel mixture for a lean burn engine/gas turbine. For this system, the pressure of the storage vessels and the flow control curves are used directly to control the amount of the reformers' reformate flow output.
    Type: Grant
    Filed: April 11, 2016
    Date of Patent: December 15, 2020
    Inventor: Herng Shinn Hwang
  • Patent number: 10865653
    Abstract: A magnetic seal system adapted for use between a support structure and a rotatable shaft. The seal system includes a rotating annular seal assembly surrounding the shaft and rotating therewith, which includes an annular seal, and a non-rotating biasing assembly sealingly mounted to the support structure around the shaft and axially engaging the annular seal assembly. The biasing assembly includes an annular magnet unit axially displaceable relative to the shaft and supported surrounding the shaft. The annular magnet unit exerting an attracting force on the annular seal assembly to biasingly displace the annular magnet unit towards the annular seal. A bias member unit is also provided for non-magnetically biasing the annular magnet unit axially relative to the shaft towards the annular seal. Adjacent contacting surfaces between the annular seal and the annular magnet unit biasingly contact one another to form a sealing interface therebetween.
    Type: Grant
    Filed: March 18, 2016
    Date of Patent: December 15, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Julien De La Bruere Terreault, Dany Blais
  • Patent number: 10859036
    Abstract: There is provided an actuator for an aircraft thrust reverser, comprising a first member, a second member movable relative to the first member, a third member movable relative to the first member and the second member, and a lock system configured to selectively lock the second member to the third member in a first stage of actuation, and the first member to the second member in a second, separate stage of actuation.
    Type: Grant
    Filed: June 25, 2018
    Date of Patent: December 8, 2020
    Assignee: GOODRICH ACTUATION SYSTEMS LIMITED
    Inventors: Antony Morgan, Andrew Hawksworth
  • Patent number: 10859267
    Abstract: An oxidation resistant coating system for a turbine engine component includes a cathodic arc coating applied to a surface of the engine component, a thin APS metallic coating applied to a surface of the cathodic arc coating, and a ceramic top coating applied to a surface of the thin APS metallic coating to improve lifetime of the engine components.
    Type: Grant
    Filed: December 12, 2014
    Date of Patent: December 8, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Brian S. Tryon, Alexander W. Williams, Stephen K. Kramer, Kevin W. Schlichting, Jessica L. Serra
  • Patent number: 10844815
    Abstract: The power turbine system includes two power turbines communicating with an ion transport membrane (ITM) reactor. Heavy liquid fuel is atomized and burned within the reactor to drive the first turbine, with the first turbine producing useful power. Exhaust from the first turbine is recycled back into the reactor. The reactor includes a series of concentric cylindrical ion transport membranes that separate atmospheric and exhaust gases into suitable components for combustion therein, with at least some of the gases being “cracked” to alter their molecular structure for further combustion to power the second turbine. The second turbine drives a compressor to supply air to the reactor. At least one of the ITMs precludes atmospheric nitrogen from the combustion processes, with the resulting exhaust including pure water and carbon dioxide. The carbon dioxide is either recycled into the reactor to facilitate fuel atomization, or compressed for sequestration.
    Type: Grant
    Filed: December 4, 2018
    Date of Patent: November 24, 2020
    Assignee: KING FAHD UNIVERSITY OF PETROLEUM AND MINERALS
    Inventors: Medhat A. Nemitallah, Mohamed A. Habib
  • Patent number: 10844814
    Abstract: The power turbine system includes two power turbines communicating with an ion transport membrane (ITM) reactor. Heavy liquid fuel is atomized and burned within the reactor to drive the first turbine, with the first turbine producing useful power. Exhaust from the first turbine is recycled back into the reactor. The reactor includes a series of concentric cylindrical ion transport membranes that separate atmospheric and exhaust gases into suitable components for combustion therein, with at least some of the gases being “cracked” to alter their molecular structure for further combustion to power the second turbine. The second turbine drives a compressor to supply air to the reactor. At least one of the ITMs precludes atmospheric nitrogen from the combustion processes, with the resulting exhaust including pure water and carbon dioxide. The carbon dioxide is either recycled into the reactor to facilitate fuel atomization, or compressed for sequestration.
    Type: Grant
    Filed: December 4, 2018
    Date of Patent: November 24, 2020
    Assignee: KING FAHD UNIVERSITY OF PETROLEUM AND MINERALS
    Inventors: Medhat A. Nemitallah, Mohamed A. Habib
  • Patent number: 10844807
    Abstract: A system for actuating a blocker door of a thrust reverser, in which a drag link assembly is removed from the airflow through the engine during flight. The assembly couples the door to a sleeve so that translation of the sleeve between deployed and stowed positions moves the door to open and closed positions, respectively. The assembly includes a drag link track having a channel extending between first and second track ends, and a drag link having a link end which is slidable in the track channel between the first and second track ends. During deployment, translation of the sleeve causes the second link end to slide within the channel toward the second track end which causes the door to open, and during stowage, translation of the sleeve causes the second link end to slide within the channel toward the first track end which causes the door to close.
    Type: Grant
    Filed: June 27, 2018
    Date of Patent: November 24, 2020
    Assignee: Spirit AeroSystems, Inc.
    Inventor: Alexander Jon Carr
  • Patent number: 10837316
    Abstract: A strut shield collar can include: a tubular portion including a tubular inside surface and a tubular outside surface; a flange portion extended from the tubular portion toward an outside of the tubular portion and including a flange inside surface; and a grid type mesh formed on at least one of the tubular inside surface and the flange inside surface, wherein the grid type mesh comprises a groove portion and a rib portion, and the groove portion is thinner than the rib portion.
    Type: Grant
    Filed: April 24, 2018
    Date of Patent: November 17, 2020
    Assignee: Doosan Heavy Industries Construction Co., Ltd
    Inventor: Chad Garner
  • Patent number: 10823422
    Abstract: A trapped vortex combustor for use in a gas turbine engine defines a radial direction, an axial direction, and a circumferential direction. The trapped vortex combustor includes an outer vortex chamber wall defining a forward end, and a dome attached to, or formed integrally with, the outer vortex chamber wall at the forward end of the outer vortex chamber wall. The dome and outer vortex chamber wall define at least in part a combustion chamber having an outer trapped vortex chamber. The dome includes an air chute defining an airflow direction. The radial direction and axial direction of the trapped vortex combustor define a reference plane extending through the air chute, the airflow direction of the air chute defining an angle greater than zero with the reference plane.
    Type: Grant
    Filed: October 17, 2017
    Date of Patent: November 3, 2020
    Assignee: General Electric Company
    Inventors: Arthur Wesley Johnson, Joseph Zelina, Eric John Stevens, Clayton Stuart Cooper, Beverly Stephenson Duncan, Juntao Zhang
  • Patent number: 10815899
    Abstract: A gas turbine engine has an in-line mounted accessory gear box (AGB) and an accessory drivingly connected to the AGB, the accessory being oriented transversally to the engine centerline.
    Type: Grant
    Filed: November 15, 2016
    Date of Patent: October 27, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Lazar Mitrovic, Jean Dubreuil, Eric Durocher, Keith Morgan, Michel Desjardins
  • Patent number: 10816207
    Abstract: A fuel nozzle for a gas turbine engine includes a stem having a monolithic stem body extending longitudinally between a first end and a second end. The monolithic stem body has a radially outer surface and at least one helical fuel passage extending through the monolithic stem body and disposed inwardly from the radial outer surface. The at least one helical fuel passage extends helically through the monolithic stem body about a passage axis extending between the first and second ends.
    Type: Grant
    Filed: February 14, 2018
    Date of Patent: October 27, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventor: Michael A. Fryer
  • Patent number: 10808648
    Abstract: A nacelle assembly according to an exemplary aspect of the present disclosure includes, among other things, a core nacelle defined at least partially about a core engine, a fan nacelle mounted at least partially around the core nacelle to define a fan bypass flow path, and a variable area fan nozzle in communication with the fan bypass flow path. The variable area fan nozzle has a first fan nacelle section and a second fan nacelle section downstream of the first fan nacelle section. The first fan nacelle section and the second fan nacelle section are axially movable relative to one another to define an auxiliary port to vary a fan nozzle exit area and adjust fan bypass airflow. The auxiliary port is defined between the first fan nacelle section and the second fan nacelle section. The first fan nacelle section comprises a first acoustic system which provides an acoustic impedance configured to attenuate a noise characterized by a leading edge of the second fan nacelle section.
    Type: Grant
    Filed: August 29, 2014
    Date of Patent: October 20, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Jonathan Gilson, Andre M. Hall, Oliver V. Atassi, Ramons A. Reba
  • Patent number: 10794283
    Abstract: A gas turbine engine includes a fan, a compressor, a combustor, a turbine, a bypass duct, and a bearing compartment assembly. The bearing compartment assembly includes a fluid pump, a compartment, a fluid line between the fluid pump and the compartment, and a damper check valve located in the fluid line. The damper check valve is a unitary, monolithic component that is configured to restrict a reverse flow from the compartment to the fluid pump substantially more than the damper check valve restricts a standard flow from the fluid pump to the compartment.
    Type: Grant
    Filed: June 27, 2017
    Date of Patent: October 6, 2020
    Assignee: United Technologies Corporation
    Inventor: William G. Sheridan
  • 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
  • Patent number: 10774740
    Abstract: The invention relates to a gas turbine assembly which substantially includes at least one compressor, at least one first burner, at least one second burner that is connected downstream of the first burner, and at least one turbine that is connected downstream of the second burner. At least the first and second burner form a component of a tubular or quasi-tubular combustion chamber element in the flow direction of the combustion path of the burners. The combustion chamber element being closed or quasi-closed and extending between the compressor and the turbine. The combustion chamber elements are arranged around the rotor of the gas turbine assembly in the shape of a ring.
    Type: Grant
    Filed: October 8, 2013
    Date of Patent: September 15, 2020
    Assignee: ANSALDO ENERGIA SWITZERLAND AG
    Inventors: Robert Marmilic, Jaan Hellat, Ewald Freitag, Adnan Eroglu
  • Patent number: 10767597
    Abstract: A thrust reverser system of a nacelle is provided. The thrust reverser system may include a pressure shell, a blocker door, and a drag link. The blocker door may be pivotably coupled to the pressure shell. The drag link may include a first segment pivotably coupled to a second segment and a third segment pivotably coupled to the second segment and the blocker door.
    Type: Grant
    Filed: June 28, 2018
    Date of Patent: September 8, 2020
    Assignee: ROHR, INC.
    Inventor: Bryce Tyler Kelford
  • Patent number: 10739001
    Abstract: A combustor for a gas turbine engine including a combustor liner support shell with a furrow formed therein; a forward liner panel mounted to the support shell via a multiple of studs, the forward liner panel including a forward liner panel rail the extends into the furrow; and an aft liner panel mounted to the support shell via a multiple of studs downstream of the forward liner panel, the aft liner panel including an aft liner panel rail that extends into the furrow.
    Type: Grant
    Filed: February 14, 2017
    Date of Patent: August 11, 2020
    Assignee: Raytheon Technologies Corporation
    Inventor: Steven W. Burd
  • Patent number: 10731602
    Abstract: A thrust reverser system includes a thrust reversal cascade and a reverser door which are accommodated in a housing situated outside a secondary flow duct. The system also includes connection parts the presence of which combined with the action of the actuator gives rise simultaneously to: displacement rearwards of the cascade in the direction of a nacelle opening, cleared by a nacelle cowling entrained rearwards together with the cascade; and a combined movement of the reverser door relative to the cascade, leading to displacement of the front end of the door rearwards along the cascade, and to pivoting of this door, such as to give rise to plunging of its rear end into the secondary flow duct.
    Type: Grant
    Filed: June 6, 2018
    Date of Patent: August 4, 2020
    Assignee: Airbus Operations S.A.S.
    Inventor: Olivier Pautis
  • Patent number: 10724473
    Abstract: A system for actuating a blocker door of a thrust reverser, in which a drag link assembly is removed from the airflow through the engine during flight. The assembly couples the door to a sleeve so that translation of the sleeve between deployed and stowed positions moves the door to open and closed positions, respectively. The assembly includes a telescoping drag link having one end rotatably coupled with a drag link anchor and another end coupled with the door. During deployment and stowage, translation of the sleeve causes the door to move and the link to extend or collapse and rotate until it contacts a stop element of the anchor, and then rotate in the opposite direction as the door opens or closes, respectively. A channel may be provided in the door to accommodate the link. The anchor may include a spring which exerts a rotational force on the link.
    Type: Grant
    Filed: June 27, 2018
    Date of Patent: July 28, 2020
    Assignee: Spirit AeroSystems, Inc.
    Inventor: Alexander Jon Carr