Patents Examined by Carlos A Rivera
  • Patent number: 10711796
    Abstract: A multistage centrifugal compressor is described. The compressor comprises a casing and a shaft rotatingly supported in the casing by at least a first bearing and a second bearing. At least one in-between-bearing impeller is mounted on the shaft, between the first bearing and the second bearing. An overhung impeller is mounted at one end of the shaft. A first diaphragm arrangement is further located in the casing. The first diaphragm arrangement comprises return a channel assembly with a plurality of stationary return channel blades defining a plurality of return vanes for redirecting compressed gas from an exit location of the overhung impeller to an inlet location of the in-between-bearings impeller. The first diaphragm arrangement houses one of the first bearing and second bearing.
    Type: Grant
    Filed: September 2, 2014
    Date of Patent: July 14, 2020
    Assignee: NUOVO PIGNONE SRL
    Inventors: Vittorio Michelassi, Ismail Hakki Sezal, Christian Aalburg
  • Patent number: 10704394
    Abstract: A flow passage forming plate includes a plate main body, a peripheral wall, and a ledge. The plate main body has a gas path surface facing a side of a gas flow passage, and an inner surface facing the opposite side from the gas path surface. The peripheral wall protrudes along a peripheral edge of the plate main body, from the inner surface toward an opposite-flow-passage side. The ledge protrudes along an inner wall surface of the peripheral wall, from the inner surface toward the opposite-flow-passage side. The ledge receives an impingement plate having a plurality of through-holes. The ledge is disposed only in a part of an inner wall surface of the peripheral wall.
    Type: Grant
    Filed: November 17, 2016
    Date of Patent: July 7, 2020
    Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.
    Inventors: Tadakazu Sakaguchi, Hiroshi Shimizu, Shinji Yoshida, Yoshio Fukui, Masamitsu Kuwabara
  • Patent number: 10697636
    Abstract: An assembly is provided for a turbine engine. A combustor wall of the turbine engine assembly includes a shell and a heat shield. The combustor wall defines a quench aperture through the shell and the heat shield. The heat shield defines an effusion outlet a distance from the quench aperture equal to between about twenty-five times and about seventy-five times a width of the effusion outlet.
    Type: Grant
    Filed: December 4, 2014
    Date of Patent: June 30, 2020
    Assignee: Raytheon Technologies Corporation
    Inventors: Frank J. Cunha, Stanislav Kostka, Jr., Randal G. McKinney
  • Patent number: 10683809
    Abstract: The present disclosure is directed to a system for bleeding air from a compressed gas path of a gas turbine engine. The system includes an impeller positioned at a downstream end of a compressor in the gas turbine engine. The impeller includes an impeller hub, an impeller arm coupled to the impeller hub, and a plurality of circumferentially spaced apart impeller vanes extending radially outwardly from the impeller arm. The impeller arm defines an impeller arm aperture extending therethrough. A vortex spoiler is positioned radially inwardly from the impeller arm and defines a vortex spoiler passage extending radially therethrough. Bleed air flows from the compressed gas path radially inwardly through both the impeller arm aperture and the vortex spoiler passage.
    Type: Grant
    Filed: May 10, 2016
    Date of Patent: June 16, 2020
    Assignee: General Electric Company
    Inventors: Daniel Waslo, Michael Richardson-Bach
  • Patent number: 10677195
    Abstract: A gas turbine engine includes a first shaft coupled to a first turbine and a first compressor, a second shaft coupled to a second turbine and a second compressor, and a third shaft coupled to a third turbine and a fan assembly. The turbine engine includes a heat rejection heat exchanger configured to reject heat from a closed loop system with air passed from the fan assembly, and a combustor positioned to receive compressed air from the second compressor as a core stream. The closed-loop system includes the first, second, and third turbines and the first compressor and receives energy input from the combustor.
    Type: Grant
    Filed: April 25, 2018
    Date of Patent: June 9, 2020
    Assignees: Rolls-Royce North American Technologies, Inc., Rolls-Royce Corporation
    Inventors: Michael J. Armstrong, Igor Vaisman
  • Patent number: 10677466
    Abstract: A combustor includes an inlet flow conditioner. The inlet flow conditioner includes a sleeve that circumferentially surrounds a portion of a fuel nozzle assembly and that extends from a forward end of a combustion liner to an inner surface of an end cover. The sleeve defines a plurality of apertures circumferentially spaced about the sleeve. A portion of the inner surface of the end cover and the sleeve define a head end volume of the combustor. An inlet to a premix passage of at least one fuel nozzle of the fuel nozzle assembly is disposed within and is in fluid communication with the head end volume.
    Type: Grant
    Filed: October 13, 2016
    Date of Patent: June 9, 2020
    Assignee: General Electric Company
    Inventors: Jonathan Dwight Berry, Brandon Lamar Bush, Timothy James Purcell, Lucas John Stoia
  • Patent number: 10677264
    Abstract: A gas turbine engine includes a fan section having a single-stage fan, a core turbine engine, and a nacelle at least partially surrounding the fan of the fan section and the core turbine engine. The gas turbine engine also includes an outlet guide vane extending between a casing of the core turbine engine and the nacelle. The gas turbine engine is configured to define an acoustic ratio greater than or equal to 2.3, with the acoustic ratio being a ratio of an axial spacing between the trailing edge of the fan blade and the leading edge of the outlet guide vane at a radial location seventy-five percent (75%) along the span of the fan blade to the axial width of the fan blade also at the radial location seventy-five percent (75%) along the span of the fan blade.
    Type: Grant
    Filed: October 14, 2016
    Date of Patent: June 9, 2020
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Thomas Ory Moniz, Daniel Robert Dwyer, Mark John Laricchiuta, Jeffrey Donald Clements, Brandon Wayne Miller
  • Patent number: 10669941
    Abstract: A gas turbine cooling system includes: a cooling air line that guides compressed air; a cooler that cools the compressed air; a flow rate adjuster that adjusts the flow rate of the cooling air; and a control device. The control device includes: a load change determination unit that determines whether a load indicated by a load command of the gas turbine has changed; a first command generation section that generates a first command indicating such an operation amount of the flow rate adjuster as allows the flow rate of the cooling air to meet a target flow rate; and a second command generation section that, when it is determined that the load indicated by the load command has changed, generates a second command indicating such an operation amount of the flow rate adjuster as allows a change-adapted flow rate higher than the target flow rate to be met.
    Type: Grant
    Filed: December 6, 2016
    Date of Patent: June 2, 2020
    Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.
    Inventors: Satoko Fujii, Tetsuya Yabe, Kazuya Higashi
  • Patent number: 10669970
    Abstract: A thrust reverser system includes two thrust reversal cascades, of which the first cascade is entrained by an actuator, and which are configured to adopt a retracted position in which they are housed in a space located outside the duct. The action of the actuator brings about: rearward displacement of the first cascade in the direction of a nacelle opening; and during part of the rearward displacement of the second cascade, simultaneous pivoting of this second cascade under the action of a control lever, the interaction of which with a fixed guide rail forces the front end of the lever to move radially inwards while the lever is entrained rearwards by the second cascade.
    Type: Grant
    Filed: June 13, 2018
    Date of Patent: June 2, 2020
    Assignee: Airbus Operations S.A.S.
    Inventors: Olivier Pautis, Lionel Czapla
  • Patent number: 10655473
    Abstract: An airfoil for a gas turbine engine includes pressure and suction walls spaced apart from one another and joined at leading and trailing edges to provide an airfoil having an exterior surface that extends in a radial direction to a tip. A tip trench is provided in the tip and wrapping at least a portion of the airfoil from the pressure side wall around the leading edge to the suction side wall. The tip trench is provided by a recess.
    Type: Grant
    Filed: December 13, 2012
    Date of Patent: May 19, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: San Quach, Lane Thornton
  • Patent number: 10655564
    Abstract: An assembly is provided for an aircraft propulsion system with an axial centerline. This assembly includes a nacelle structure and a thrust reverser system. The nacelle structure includes a fan cowl, where a forward cavity extends axially into the nacelle structure from an aft end of the fan cowl. The thrust reverser system includes a sleeve, a cascade structure, a blocker door and a linkage. The sleeve is configured to translate axially along the centerline and relative to the nacelle structure between a forward stowed position and an aft deployed position. The cascade structure, the blocker door and the linkage are at least partially within the forward cavity when the sleeve is in the forward stowed position. The cascade structure is fixedly attached to the sleeve. The linkage extends between and is pivotally attached to the cascade structure and the blocker door.
    Type: Grant
    Filed: May 13, 2016
    Date of Patent: May 19, 2020
    Assignee: Rohr, Inc.
    Inventor: Timothy Gormley
  • Patent number: 10654579
    Abstract: In an aircraft including a gas turbine engine having a compressor including a compressor booster, a turbine, and a nacelle, a system for cooling compressor discharge air provided to the turbine to cool the turbine includes a heat exchanger provided in a nacelle compartment of the gas turbine engine configured to cool the compressor discharge air by exchanging heat from the compressor discharge air to a cooling fluid; and a cooling fluid circuit configured to circulate cooling fluid through the heat exchanger and a heat sink, wherein the heat sink is at least one of an inlet of the nacelle compartment, an inlet of the compressor booster, or outlet guide vanes of the gas turbine engine.
    Type: Grant
    Filed: July 14, 2016
    Date of Patent: May 19, 2020
    Assignee: GENERAL ELECTRIC COMPANY GLOBAL RESEARCH
    Inventor: Carlos Enrique Diaz
  • Patent number: 10648484
    Abstract: A compressor for a turbine engine includes a shroud having a grooved section including a plurality of groove segments extending radially into a shroud surface. A rotor assembly rotatably supported in the shroud includes a rotor hub and a plurality of rotor blades. Each rotor blade extends radially from the rotor hub and terminates at a blade tip, which is spaced from the shroud surface by a tip gap and defines a non-constant clearance region between a leading edge position and a medial chord position along the blade chord at the minimum tip clearance. The rotor blades generate an aft axial fluid flow through the shroud and the grooved section is formed in the shroud surface upstream of the medial chord position within the non-constant clearance region for resisting a reverse axial fluid flow through the tip gap when the compressor section is operated at near stall conditions.
    Type: Grant
    Filed: February 14, 2017
    Date of Patent: May 12, 2020
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Timothy Gentry, Bruce David Reynolds, Nick Nolcheff
  • Patent number: 10641173
    Abstract: In a gas turbine system including a first gas turbine generator, a heat recovery steam generator and a steam turbine generator heat rejection system, the present invention relates to a method for CO2 capture from flue gas in said system, said method including: (a) diverting an amount of heat recovery steam generator flue gas from the CO2 capture plant; and (b) mixing the diverted heat recovery steam generator flue gas with an air stream, forming a combined gas stream, wherein (1) the combined gas stream is fed to a second gas turbine generator; (2) exhaust gas from the second gas turbine generator is mixed with exhaust gas from the first gas turbine generator, forming a combined exhaust gas stream; and (3) the combined exhaust gas stream enters the heat recovery steam generator, with the CO2 content of the combined exhaust gas stream increased through supplementary firing in the heat recovery steam generator.
    Type: Grant
    Filed: April 29, 2016
    Date of Patent: May 5, 2020
    Assignee: BECHTEL POWER CORPORATION
    Inventor: Seyfettin Can Gulen
  • Patent number: 10626730
    Abstract: In a featured embodiment, a gas turbine engine component comprises an airfoil having a leading edge, a trailing edge, and pressure and suction side walls extending from the leading edge to the trailing edge. The airfoil extends from a base to a tip. A shelf is formed in the tip, and extends from the pressure side wall, around the leading edge, to the suction side wall.
    Type: Grant
    Filed: November 5, 2014
    Date of Patent: April 21, 2020
    Assignee: United Technologies Corporation
    Inventors: James T. Auxier, Thomas N. Slavens, Brandon S. Donnell, Yafet Girma
  • Patent number: 10626798
    Abstract: A thermal energy exchange system for cooling air of a gas turbine engine includes a heat exchanger located at a diffuser of the gas turbine engine. The diffuser is positioned axially between a compressor and a combustor of the gas turbine engine. A fuel source is operably connected to the heat exchanger to direct a flow of fuel through the heat exchanger via a fuel pipe and toward a fuel nozzle of the combustor. An airflow inlet directs a cooling airflow through the heat exchanger to reduce an airflow temperature via thermal energy exchange between the cooling airflow and the flow of fuel. An airflow outlet directs the cooling airflow from the heat exchanger toward one or more of components of the turbine to cool the one or more components.
    Type: Grant
    Filed: December 9, 2015
    Date of Patent: April 21, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: James D. Hill, Steven J. Laporte, Wendell V. Twelves, Jr., Stephen K. Kramer, Simon Pickford
  • Patent number: 10619855
    Abstract: A fuel injection system for a gas turbine engine includes a fuel delivery conduit, a nozzle block with a nozzle aperture, and a cavity block with a cavity. The nozzle aperture has a first cross sectional area, and injects fuel received from the fuel delivery conduit into the cavity. The cavity has a second cross sectional area that is greater than the first cross sectional area.
    Type: Grant
    Filed: July 8, 2013
    Date of Patent: April 14, 2020
    Assignee: United Technologies Corporation
    Inventors: Torence P. Brogan, Jeffery A. Lovett, Christopher A. Eckett, May L. Corn
  • Patent number: 10619596
    Abstract: An ejector/mixer for a gas turbine engine includes an annular wall having upstream end adapted to be fastened to an engine case and a downstream end forming a plurality of lobes. A support member interconnects the lobes, and includes an annular blade located radially inwardly of the bight of the lobes. The lobes extend radially inwardly downstream relative to the annular wall and the support member includes an annular blade and has spaced apart joint surfaces spaced apart to coincide with the joint surfaces of a respective lobes. The spaced-apart joint surfaces of the support member being profiled to mate with the corresponding joint surface of the lobes.
    Type: Grant
    Filed: July 20, 2017
    Date of Patent: April 14, 2020
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Franco Di Paola, Guy Lefebvre, Patrick L'Esperance, Gabriel Emard-Parent
  • Patent number: 10618666
    Abstract: An aspect includes a system for pre-start motoring synchronization for multiple engines of an aircraft. The system includes a first engine starting system of a first engine and a controller. The controller is operable to synchronize a motoring time of the first engine starting system with one or more other engine starting systems of one or more other engines of the aircraft by extending the motoring time of the first engine starting system to match, within a synchronization tolerance, the motoring time of the one or more other engine starting systems in a pre-start motoring sequence.
    Type: Grant
    Filed: July 21, 2016
    Date of Patent: April 14, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Matthew D. Teicholz, James W. Dunn, Christopher P. Kmetz, Louis A. Celiberti
  • Patent number: 10619564
    Abstract: A gas turbine includes a compressor, a turbine, an extraction line, and a component introduction line. A compressed air from an intermediate compression stage of the compressor, as an extraction air, is extracted through the extraction line and is introduced to a first component configuring a portion of the turbine casing through the extraction line. The extraction air, which has passed through the first component, is introduced to a second component serving as a component configuring the turbine through the component introduction line. The second component is a low-pressure component, which is disposed under a pressure environment lower than a pressure of the compressed air at an outlet of the intermediate compression stage.
    Type: Grant
    Filed: November 25, 2016
    Date of Patent: April 14, 2020
    Assignee: MITSUBISHI HITACHI POWER SYSTEMS, LTD.
    Inventors: Keita Takamura, Kazumasa Takata