Patents Examined by William H. Rodriguez
  • Patent number: 10443852
    Abstract: A lobe lance is disclosed for a gas turbine combustor which includes a plurality of N (N?4) lobe fingers, each configured as a streamlined body with two lateral surfaces. A plurality of nozzles for injecting a gaseous and/or liquid fuel mixed with air are provided whereby lobes running between the nozzles are provided for improving the mixing quality and reducing pressure loss in said combustor. The lobes of each lobe finger have one of two opposite orientations with respect to said flow direction, and the lobes of all lobe fingers follow a predetermined pattern of orientation across the lobe fingers at least one pair of neighboring lobe fingers has the same lobe orientation resulting in a grouped lobe arrangement ( . . . LL . . . or . . . RR . . . ) such that at least two of the vortices generated by the lobe shape downstream of the lobe fingers combine.
    Type: Grant
    Filed: November 20, 2015
    Date of Patent: October 15, 2019
    Assignee: ANSALDO ENERGIA SWITZERLAND AG
    Inventors: Yang Yang, Michael Düsing
  • Patent number: 10443542
    Abstract: The present disclosure relates to a system for locking the position of the flaps of a thrust reverser of a turbojet nacelle, said flaps being controlled by actuators, each one swinging about a tranverse pivot in order to partially close off the air stream so as to guide it forwards, further including locks for locking the flaps in an intermediate opening position, between the closed position and the open position.
    Type: Grant
    Filed: October 3, 2016
    Date of Patent: October 15, 2019
    Assignee: AIRCELLE
    Inventors: Corentin Hue, Rodolphe Denis, Denis Guillois, Sarah Tissot
  • Patent number: 10443510
    Abstract: A method using an inverse three-way valve model with feed-forward fuel flow control is provided for controlling liquid fuel flow in a turbine power generation system to achieve a bump-less driven watts (dwatt) power output during fuel mode transitions between passive mode and active mode operations of a three-way check valve that delivers liquid fuel to the turbine combustor nozzles. The method utilizes an inverse fluid flow model for a three-way check valve which is based upon a valve position surrogate for the three-way check valve to develop a calculated estimate of a fuel spike/dwatt oscillation likely to occur during mode transitions of the three-way check valve and to produce a feed-forward control used to modulate a fuel path bypass valve within the turbine fuel supply circulation system that provides the liquid fuel to the three-way valve during transfers of valve operation between passive and active mode operations.
    Type: Grant
    Filed: July 14, 2016
    Date of Patent: October 15, 2019
    Assignee: General Electric Company
    Inventors: Omprakash Pobbati, Sunil Unnikrishnan, Pradeep Kumar Vavilala, James Frederick Den Outer
  • Patent number: 10443429
    Abstract: A gas turbine engine comprises a core engine housing. A nacelle is positioned radially outwardly of the core engine housing. An outer bypass housing is positioned outwardly of the nacelle. There is at least one accessory to be cooled positioned in a chamber radially between the core engine housing and the nacelle. A manifold delivers cooling air into the chamber, and extends ng circumferentially about a central axis of the core engine. The nacelle has an asymmetric flow cross-section across a circumferential extent.
    Type: Grant
    Filed: January 20, 2015
    Date of Patent: October 15, 2019
    Assignee: United Technologies Corporation
    Inventors: Gabriel L. Suciu, Jesse M. Chandler, Federico Papa
  • Patent number: 10436115
    Abstract: A gas turbine engine has a core engine with a compressor section and a turbine section. The compressor section includes a low pressure compressor and a high pressure compressor. A cooling air system taps compressed air and passes the compressed air through a heat exchanger. Cooling air passes over the heat exchanger to cool the compressed air, which is returned to the core engine to provide a cooling function. The heat exchanger is mounted through a flexible mount allowing movement between a static structure and the heat exchanger.
    Type: Grant
    Filed: August 22, 2016
    Date of Patent: October 8, 2019
    Assignee: United Technologies Corporation
    Inventors: Paul W. Duesler, Frederick M. Schwarz
  • Patent number: 10436445
    Abstract: An assembly for controlling a gap between a liner and a stationary nozzle within a gas turbine includes an annular liner having an aft frame that is disposed at an aft end of the liner, and a mounting bracket that is coupled to the aft frame. The assembly further includes a turbine having an outer turbine shell and an inner turbine shell that at least partially defines an inlet to the turbine. A stationary nozzle is disposed between the aft frame and the inlet. The stationary nozzle includes a top platform portion having a leading edge that extends towards the aft frame and a bottom platform portion. A gap is defined between the aft end of the aft frame and the leading edge of the top platform portion. The mounting bracket is coupled to the outer turbine shell, and stationary nozzle is coupled to the inner turbine shell.
    Type: Grant
    Filed: March 18, 2013
    Date of Patent: October 8, 2019
    Assignee: General Electric Company
    Inventors: Christopher Paul Willis, Richard Martin DiCintio, Patrick Benedict Melton, Lucas John Stoia
  • Patent number: 10436114
    Abstract: A gas turbine engine has a combustor supported in a gas generator case. A baffle apparatus is attached to the gas generator case, surrounding an upstream section of the combustor to create at least one passage for directing an air flow discharged from a compressor diffuser to pass therethrough for cooling the combustor. The at least one passage extends from an upstream end of the combustor and has a passage exit immediately upstream of a dilution hole in the combustor. The baffle apparatus is configured to increase a velocity of the air flow entering the at least one passage and passing over the combustor.
    Type: Grant
    Filed: August 26, 2015
    Date of Patent: October 8, 2019
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Bhawan B. Patel, Oleg Morenko
  • Patent number: 10429073
    Abstract: A combustor cap module is provided with a retention system to facilitate assembly and disassembly. The combustor cap module further includes a cap face assembly having a cooling plate; a cylindrical sleeve including a connecting surface for attaching the cap face assembly to the retention assembly; and a coupling member mounted in a downstream fuel nozzle opening in the cooling plate. The retention system includes a support plate having an inner panel that defines an upstream fuel nozzle opening. The coupling member extends through the upstream fuel nozzle opening, such that its upstream end extends upstream of the support plate. A retaining ring at least partially encircles the upstream end of the coupling member and is engaged by a spring plate that is removably secured to the support plate at multiple locations. A method for assembling a combustor cap module is also provided.
    Type: Grant
    Filed: November 22, 2016
    Date of Patent: October 1, 2019
    Assignee: General Electric Company
    Inventors: Charles Lewis Davis, III, Scott Robert Simmons, David Kenton Felling
  • Patent number: 10428742
    Abstract: A gas turbine engine and method of operation are provided. The gas turbine engine may include a variable geometry component operably driven by a component actuator. The component actuator may be in fluid communication with a primary line having a valve associated therewith. The method may include determining a demand pressure associated with actuating the variable geometry component using the component actuator. The method may also include adjusting a position of the valve based on the demand pressure to generate a fuel pressure at the component actuator that is greater than or equal to the demand pressure.
    Type: Grant
    Filed: June 7, 2016
    Date of Patent: October 1, 2019
    Assignee: General Electric Company
    Inventor: Frederick Ehrwulf van Alen
  • Patent number: 10422283
    Abstract: A fuel injection device for a gas turbine can include streamlined bodies arranged adjacent to one another in a circumferential direction. Each streamlined body can have a fuel nozzle on its trailing edge. The streamlined bodies can be split into at least a first group of streamlined bodies and a second group of streamlined bodies. All the streamlined bodies in the first group being the same and being different from the streamlined bodies in the second group. The first group of streamlined bodies includes at least two streamlined bodies adjacent to one another. Alternatively, the streamlined bodies are clustered in sets of two adjacent streamlined bodies. As yet another alternative, the streamlined bodies can be arranged such that the fuel injection device has a maximum of four-fold rotational symmetry in the plane perpendicular to the central axis.
    Type: Grant
    Filed: February 11, 2016
    Date of Patent: September 24, 2019
    Assignee: ANSALDO ENERGIA SWITZERLAND AG
    Inventors: Yang Yang, Nicolas Noiray, Michael Dusing
  • Patent number: 10415432
    Abstract: A power plant includes a gas turbine including a turbine extraction port that is in fluid communication with a hot gas path of the turbine and an exhaust duct that receives exhaust gas from the turbine outlet. The power plant further includes a first gas cooler having a primary inlet fluidly coupled to the turbine extraction port, a secondary inlet fluidly coupled to a coolant supply system and an outlet in fluid communication with the exhaust duct. The first gas cooler provides a cooled combustion gas to the exhaust duct which mixes with the exhaust gas to provide an exhaust gas mixture to a heat exchanger downstream from the exhaust duct. The power plant further includes a fuel heater in fluid communication with the outlet of the first gas cooler.
    Type: Grant
    Filed: December 15, 2015
    Date of Patent: September 17, 2019
    Assignee: General Electric Company
    Inventors: Alston Ilford Scipio, Sanji Ekanayake, Joseph Philip Klosinski, Paul Robert Fernandez, David Clayton Poole
  • Patent number: 10415476
    Abstract: A power plant includes a first gas turbine and a second gas turbine. The first gas turbine includes a turbine extraction port that is in fluid communication with a hot gas path of the turbine and an exhaust duct that receives exhaust gas from the turbine outlet. The power plant further includes a first gas cooler having a primary inlet fluidly coupled to the turbine extraction port, a secondary inlet fluidly coupled to a coolant supply system and an outlet in fluid communication with the exhaust duct. The first gas cooler provides a cooled combustion gas to the exhaust duct which mixes with the exhaust gas to provide an exhaust gas mixture to a first heat exchanger downstream from the exhaust duct. At least one of a compressor and a turbine of the second gas turbine are in fluid communication with the outlet of the first gas cooler.
    Type: Grant
    Filed: December 15, 2015
    Date of Patent: September 17, 2019
    Assignee: General Electric Company
    Inventors: Joseph Philip Klosinski, Alston Ilford Scipio, Sanji Ekanayake, Paul Robert Fernandez
  • Patent number: 10415507
    Abstract: A method of regulating pressure within a first propellant tank of a rocket engine having a first propellant tank containing a first propellant and a second propellant tank containing a second propellant, and a regulator device for regulating pressure within the first tank, the regulator device comprising a gas generator and a heat exchanger co-operating with the gas generator so as to vaporize at least part of the first propellant prior to reintroducing it into the first tank (16), the gas generator and the heat exchanger both being fed with the first propellant by a single first motor-driven pump, while the gas generator is fed with the second propellant by a single second motor-driven pump, wherein the flow rate of the first motor-driven pump is controlled as a function of a first parameter, while the flow rate of the second motor-driven pump is controlled as a function of a second parameter.
    Type: Grant
    Filed: October 25, 2016
    Date of Patent: September 17, 2019
    Assignee: ARIANEGROUP SAS
    Inventors: Valentin Hue, Serge Le Gonidec
  • Patent number: 10400673
    Abstract: A system for a gas turbine includes a control system comprising a processor. The processor is configured to receive a signal indicating spray intercooling fluid demand of the gas turbine. The processor is configured to determine a rate of change of the spray intercooling fluid demand. The processor is configured to control flow of a nitrogen oxide (NOX) minimization fluid that reduces NOX emissions from the gas turbine based at least in part on the rate of change of the spray intercooling fluid demand.
    Type: Grant
    Filed: June 20, 2016
    Date of Patent: September 3, 2019
    Assignee: General Electric Company
    Inventors: Roman Freidl, Eugene Damankah
  • Patent number: 10400710
    Abstract: A third stream duct producing a third air stream at reduced pressure that is exhausted through a separate nozzle that is concentric with the main or primary engine nozzle. The third stream exhaust air from the separate concentric nozzle is exhausted to a location at which pressure is ambient or sub-ambient. The location at which the third stream air is exhausted contributes to the thrust of the aircraft. The airstream from the third air duct is exhausted through an exhaust nozzle of the third duct that is positioned at the interface between the aft of the airframe and the leading edge of the engine outer flaps. This location is a low pressure region that has a recirculation zone. The exhaust of third stream air to this low pressure region substantially reduces or eliminates this recirculation zone and associated boat tail drag, thereby improving the efficiency of the engine.
    Type: Grant
    Filed: May 7, 2013
    Date of Patent: September 3, 2019
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: David Lynn Dawson, Erin Lee Lariviere, Brian Joseph Petersen, Robert Jerome Ellerhorst
  • Patent number: 10400711
    Abstract: The present invention relates to an igniter assembly, including a blast tube provided with a supporting part formed in a cylindrical shape, and an aft-closure part having front and rear sides through which igniter combustion gas is emitted, an igniter disposed adjacent to the rear side of the aft-closure part and storing ignition pellet therein, and a blast tube stopper formed in a shape surrounding the supporting part, accommodating the igniter, and coupled to the rear side of the aft-closure part, wherein the aft-closure part includes a plurality of holes through which igniter combustion gas is emitted.
    Type: Grant
    Filed: January 12, 2018
    Date of Patent: September 3, 2019
    Assignee: AGENCY FOR DEFENSE DEVELOPMENT
    Inventors: Sangyoun Lee, Seunggyo Jang, Hyonam Lee
  • Patent number: 10393067
    Abstract: A gas turbine engine includes a spool configured to rotate about an axial centerline. The spool includes a fan rotor and a cold turbine rotor. The fan rotor is rotatably driven by the cold turbine rotor. A cold turbine inlet passage is configured to direct an airflow along a radial inward trajectory to the cold turbine rotor.
    Type: Grant
    Filed: August 25, 2016
    Date of Patent: August 27, 2019
    Assignee: United Technologies Corporation
    Inventors: Daniel Bernard Kupratis, Francis R. Moon, Arthur W. Utay
  • Patent number: 10393030
    Abstract: Pilot fuel injectors for combustors of gas turbine engines are provided. The pilot fuel injectors include a swirler having an exit into a combustion chamber of the combustor and a nozzle located within the swirler. The nozzle includes a primary fuel circuit configured to atomize fuel dispensed therethrough and a secondary fuel circuit having a first sub circuit having at least one injection aperture a first injection depth from the exit of the swirler and a second subcircuit having at least one second injection aperture located at a second injection depth from the exit of the swirler, wherein the first injection depth is greater than the second injection depth.
    Type: Grant
    Filed: October 3, 2016
    Date of Patent: August 27, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventor: William Proscia
  • Patent number: 10385805
    Abstract: A variable geometry exhaust nozzle arrangement includes a plurality of hingable exhaust petals defining a perimeter of an exhaust duct and an annular ring slidably engagable against a radially outer surface of each petal. The annular ring is coupled to a plurality of circumferentially spaced actuator arrangements, each including first and second circumferentially spaced parallel actuator arms pivotably coupled to the annular ring at a first end and to a slide arrangement at a second end. Each slide arrangement is mounted for linear sliding movement relative to the annular ring, such that sliding movement of each slide arrangement causes pivoting of the first and second actuator arms to thereby translate the annular ring in one or both of a longitudinal direction and a lateral direction.
    Type: Grant
    Filed: October 4, 2017
    Date of Patent: August 20, 2019
    Assignee: ROLLS-ROYCE plc
    Inventor: Jack F Colebrooke
  • Patent number: 10385728
    Abstract: A turbine stator vane assembly for a gas turbine engine is disclosed and includes an airfoil rotatable about an axis transverse to an engine longitudinal axis. The airfoil includes outer walls defining an inner chamber between a pressure side and a suction side of the airfoil. At least one spindle supports rotation of the airfoil and includes a feed opening for communicating cooling air into the inner chamber. An inlet defines a passage between the feed opening and the inner chamber and includes a protrusion of the outer wall on at least one of the pressure side and suction side of the airfoil.
    Type: Grant
    Filed: November 3, 2014
    Date of Patent: August 20, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Thomas N. Slavens, Eric A. Grover, John D. Teixeira