Patents Examined by Andrew Nguyen
  • Part load performance improvement using deformable bore plugs
    Patent number: 9297310
    Abstract: A cooling arrangement for a gas turbine engine. The cooling arrangement comprises a discharge channel for air flow from a compressor, a first cooling channel and at least one aperture providing communication between the flow of air through the discharge channel and the first cooling channel. A restrictor device in the aperture regulates the flow of air between the discharge channel and the first cooling channel. The restrictor device deforms to vary air flowing through the aperture in response to a physical condition of the engine. This physical condition of the engine may be that of the temperature of air flowing through the discharge channel, the restrictor device responding to regulate the flow of air based on that temperature. The restrictor device may be a two-way shape memory alloy.
    Type: Grant
    Filed: October 18, 2012
    Date of Patent: March 29, 2016
    Assignee: General Electric Company
    Inventors: Sheo Narain Giri, Sanjeev Kumar Jha, Bhaskar Pemmi, Harish Bommanakatte, Santhosh Donkada, Krishna Kishore Gumpina, Indrajit Mazumder, Rajarshi Saha
  • Circumferentially retained fairing
    Patent number: 9297312
    Abstract: An assembly for a gas turbine engine includes a frame, a mount, and a fairing. The mount is attached to the frame and the fairing is connected to the mount. The fairing and mount have mating anti-deflection features that engage to prevent circumferential movement of the fairing relative to the frame.
    Type: Grant
    Filed: December 29, 2012
    Date of Patent: March 29, 2016
    Assignee: United Technologies Corporation
    Inventors: Conway Chuong, Jonathan Ariel Scott, Matthew Budnick
  • Gas turbine engine
    Patent number: 9279334
    Abstract: A gas turbine engine with a compressor rotor having compressor impulse blades that delivers gas at supersonic conditions to a stator. The stator includes a one or more aerodynamic ducts that each have a converging portion and a diverging portion for deceleration of the selected gas to subsonic conditions and to deliver a high pressure oxidant containing gas to flameholders. The flameholders may be provided as trapped vortex combustors, for combustion of a fuel to produce hot pressurized combustion gases. The hot pressurized combustion gases are choked before passing out of an aerodynamic duct to a turbine. Work is recovered in a turbine by expanding the combustion gases through impulse blades. By balancing the axial loading on compressor impulse blades and turbine impulse blades, asymmetrical thrust is minimized or avoided.
    Type: Grant
    Filed: July 6, 2012
    Date of Patent: March 8, 2016
    Assignee: Dresser-Rand Company
    Inventors: Shawn P. Lawlor, William Byron Roberts, II
  • Turbomachine combustor nozzle including a monolithic nozzle component and method of forming the same
    Patent number: 9267690
    Abstract: A turbomachine combustor nozzle includes a monolithic nozzle component having a plate element and a plurality of nozzle elements. Each of the plurality of nozzle elements includes a first end extending from the plate element to a second end. The plate element and plurality of nozzle elements are formed as a unitary component. A plate member is joined with the nozzle component. The plate member includes an outer edge that defines first and second surfaces and a plurality of openings extending between the first and second surfaces. The plurality of openings are configured and disposed to register with and receive the second end of corresponding ones of the plurality of nozzle elements.
    Type: Grant
    Filed: May 29, 2012
    Date of Patent: February 23, 2016
    Assignee: General Electric Company
    Inventors: Lucas John Stoia, Patrick Benedict Melton, Thomas Edward Johnson, Christian Xavier Stevenson, John Drake Vanselow, James Harold Westmoreland
  • Rotating fluid pumping system
    Patent number: 9260980
    Abstract: A mechanism such as a rotor of an open rotor gas turbine engine comprises a rotor assembly 100 rotatable about a rotational axis A. The rotor assembly 100 has a fluid pathway 110 including a pump 114 carried by the first rotor assembly 100 for driving fluid along the fluid pathway 110. The fluid may be oil for lubricating components of the mechanism. The fluid is collected by an annular channel-shaped collector 111 and pumped through surface coolers 116 to an outlet pipe 119. From the pipe 119 the fluid migrates along a path 500 under centrifugal force, returning to the collector 111.
    Type: Grant
    Filed: February 3, 2012
    Date of Patent: February 16, 2016
    Assignee: ROLLS-ROYCE plc
    Inventor: Robert E. Leese
  • Gimbal pin for jet propulsion system
    Patent number: 9260194
    Abstract: A thrust reverser actuator gimbal assembly for mounting a thrust reverser actuator to fixed structure of the thrust reverser is disclosed. The thrust reverser actuator gimbal assembly may comprise a gimbal, first and second gimbal pins mounted to the gimbal and defining a first pivot axis, the first and second gimbal pins adapted to form a pivotal joint with the fixed structure of the thrust reverser, third and fourth gimbal pins mounted to the gimbal and defining a second pivot axis normal to the first pivot axis, the third and fourth gimbal pins adapted to form a pivotal joint with the thrust reverser actuator, wherein the first and second gimbal pins each include a shaft and a flange integrally formed together, the flange including a pair of bores for receiving a fastener to fasten the respective gimbal pin to the thrust reverser fixed structure.
    Type: Grant
    Filed: October 24, 2013
    Date of Patent: February 16, 2016
    Assignee: Rohr, Inc.
    Inventors: Jay Francisco, Jimmy Kee
  • Method for automatic closed-loop control of one or more combustion temperatures in a gas turbine installation and method for determination of the water content in the working fluid of a gas turbine installation
    Patent number: 9249738
    Abstract: The invention relates to a method for automatic closed-loop control of one or more combustion temperatures in a gas turbine installation, having the following steps: measurement of a plurality of temperatures of the working fluid of the gas turbine installation at various positions in the gas turbine installation, measurement of a plurality of pressures of the working fluid at different positions in the gas turbine installation, determination of the water content of the working fluid flowing through the gas turbine installation, taking account of the measured values, and setting of at least one combustion temperature for the gas turbine installation as a function of the determined water content.
    Type: Grant
    Filed: February 5, 2008
    Date of Patent: February 2, 2016
    Assignee: ALSTOM TECHNOLOGY LTD
    Inventors: Anton Nemet, Stanka Kokanovic
  • Fluid impingement arrangement
    Patent number: 9243513
    Abstract: A fluid impingement arrangement comprising a supply manifold and at least one nozzle exit coupled to the supply manifold. The nozzle exit is arranged as a Coanda surface having a restriction and has at least one static pressure tapping that cross-connects two regions of the restriction to induce passive oscillation in a fluid jet passing through the nozzle exit.
    Type: Grant
    Filed: October 6, 2011
    Date of Patent: January 26, 2016
    Assignee: ROLLS-ROYCE PLC
    Inventors: Zahid M Hussain, Christopher T J Sheaf, Andrew J Mullender, David MacManus, Brian A Handley
  • Cooling system for engine and aircraft air
    Patent number: 9239005
    Abstract: The combined cooling system uses a single heat exchanger to cool both engine air for use in an engine system and aircraft air for use in an aircraft system. More particularly, a bleed air path leads from the compressor stage to the heat exchanger where it is placed in thermal exchange contact with a flow of cooling air coming from a cooling path. From an outlet end of the heat exchanger, the bleed air splits into two paths: an aircraft air path leading to at least one aircraft system such as an Environmental control system (ECS), a wind de-icing system or the like, and an engine air path leading to at least one engine system such as a buffer air system for pressurizing the bearing cavities.
    Type: Grant
    Filed: November 25, 2011
    Date of Patent: January 19, 2016
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Steven Strecker, Xiaoliu Liu, Adam Logan
  • Fuel metering system electrically servoed metering pump
    Patent number: 9234464
    Abstract: A fuel metering system for supplying fuel to load includes a variable displacement piston pump having an adjustable hanger that is movable to a plurality of positions. The variable displacement piston pump is configured to receive a drive torque and, upon receipt of the drive torque, to supply fuel to the plurality of loads at a flow rate dependent on the position of the adjustable hanger. A hanger actuator is coupled to receive hanger position commands and is operable, in response thereto, to move the adjustable hanger to the commanded position.
    Type: Grant
    Filed: November 13, 2013
    Date of Patent: January 12, 2016
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventor: Dwayne Michael Benson
  • Gas turbine engine with secondary air flow circuit
    Patent number: 9228497
    Abstract: One embodiment of the present invention is a unique gas turbine engine. Another embodiment of the present invention is a gas turbine engine having a unique secondary air flow circuit. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and secondary air flow circuits. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.
    Type: Grant
    Filed: December 28, 2011
    Date of Patent: January 5, 2016
    Assignees: Rolls-Royce Corporation, Rolls-Royce North American Technologies Inc.
    Inventors: Nathan Wesley Ottow, Nathan J. Cooper
  • Laser clad fuel injector premix barrel
    Patent number: 9228498
    Abstract: A fuel injector for a gas turbine engine may include a center body disposed about a longitudinal axis, and a premix barrel positioned radially outwardly from the center body to define an annular passageway between the center body and the premix barrel. The annular passageway may extend from an upstream end that is configured to be fluidly coupled to a compressor to a downstream end that is configured to be fluidly coupled to a combustor. The premix barrel may include a first portion at the upstream end and a second portion at the downstream end. The first portion may include a stainless steel material, and the second portion may include a nickel based superalloy material. The second portion may be coupled to the first portion by a laser clad coupling.
    Type: Grant
    Filed: March 1, 2012
    Date of Patent: January 5, 2016
    Assignee: Solar Turbines Incorporated
    Inventors: Alexander Ilich Krichever, Robert Anthony Corr, II, Peter Barker, Bruno Enriquez Struck, John Preston Montague
  • Fuel metering system electrically servoed metering pump
    Patent number: 9228500
    Abstract: A fuel metering system for supplying fuel to load includes a variable displacement piston pump having an adjustable hanger that is movable to a plurality of positions. The variable displacement piston pump is configured to receive a drive torque and, upon receipt of the drive torque, to supply fuel to the plurality of loads at a flow rate dependent on the position of the adjustable hanger. A hanger actuator is coupled to receive hanger position commands and is operable, in response thereto, to move the adjustable hanger to the commanded position.
    Type: Grant
    Filed: November 13, 2013
    Date of Patent: January 5, 2016
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventor: Dwayne Michael Benson
  • Variable contour nacelle assembly for a gas turbine engine
    Patent number: 9228534
    Abstract: A gas turbine engine includes a compressor section, a combustor section, a turbine section and a nacelle assembly which at least partially surrounds the compressor section, the combustor section and the turbine section. At least a portion of the nacelle assembly includes an adjustable contour. The portion of the nacelle assembly including the adjustable contour is selectively moveable between a first portion and a second position to influence the adjustable contour of the nacelle assembly. A controller identifies an abnormal aircraft operating condition and selectively moves the portion of the nacelle assembly including the adjustable contour between the first position and the second position in response to detecting the abnormal aircraft operating condition.
    Type: Grant
    Filed: July 2, 2007
    Date of Patent: January 5, 2016
    Assignee: United Technologies Corporation
    Inventors: Ashok K. Jain, Michael Winter
  • Gas turbine engine fuel heating system
    Patent number: 9222415
    Abstract: A fuel heating system for a gas turbine engine comprises a first heat exchanger, a second heat exchanger, a fuel pump and a valve. The first heat exchanger produces a heated air flow. The second heat exchanger receives the heated air flow from the first heat exchanger. The fuel pump provides a fuel flow. The valve is coupled to the fuel pump to intermittently include the second heat exchanger in the fuel flow based on a temperature of the fuel flow. A method of heating fuel in a gas turbine engine comprises providing fuel to a gas turbine engine with a fuel pump to sustain a combustion process, heating a flow of air with exhaust gas from the combustion process, and heating fuel from the fuel pump en route to the gas turbine engine with the flow of air based on a temperature of the fuel.
    Type: Grant
    Filed: March 6, 2012
    Date of Patent: December 29, 2015
    Assignee: Hamilton Sundstrand Corporation
    Inventor: Omar I. Osorio
  • Vortex cannon with enhanced ring vortex generation
    Patent number: 9217392
    Abstract: A vortex cannon based on pulse detonation engine comprises a combustion chamber, a fuel source, an oxidizer source, a purge gas source, a valve allowing delivery of fuel from the fuel source to the combustion chamber, a valve allowing deliver of either oxidizer or purge gas from the oxidizer and purge gas sources to the combustion chamber, an ignition source for the combustion chamber for initiating detonation of fuel and oxidizer, and a conical barrel outlet from the combustion chamber. The combustion chamber is configured for control over the detonation front. A control system provides for varying the rate and quantity of fuel and oxidizer injected to the combustion chamber for varying the frequency and strength of pulse generation. Ring vortices may be generated either in single pulses or at high rates of fire which maintain a consistent track.
    Type: Grant
    Filed: December 12, 2011
    Date of Patent: December 22, 2015
    Inventor: Curtis E. Graber
  • Rocket turbopump valves and associated systems and methods
    Patent number: 9217389
    Abstract: Rocket turbopump valves and associated system and methods. A valve in accordance with at least one embodiment includes a housing having a valve aperture, and first and second valve elements positioned in the housing and movable relative to the valve aperture between a closed position and an open position. Each valve element can be pivotably connected to the housing toward a first end and supported by the other valve element toward a second end. A drive mechanism is coupled to the first and second valve elements to pivot the valve elements toward and away from their open and closed positions.
    Type: Grant
    Filed: November 10, 2011
    Date of Patent: December 22, 2015
    Assignee: Blue Origin, LLC
    Inventors: Gerald A. Lee, Michael C. Krene
  • Fluid flow control device and method
    Patent number: 9217372
    Abstract: A fluid flow control system includes a fluid inlet, a central chamber, a first nozzle extending from a first side of the central chamber and comprising a first throat, a second nozzle extending from a second side of the central chamber opposite the first side and comprising a second throat, and a flow control shuttle. The flow control shuttle includes a first needle having a first tapered portion positioned within the first throat for controlling flow through the first nozzle and a second needle having a second tapered portion positioned within the second throat for controlling flow through the second nozzle.
    Type: Grant
    Filed: January 25, 2012
    Date of Patent: December 22, 2015
    Assignee: Hamilton Sundstrand Corporation
    Inventor: Bruce Paradise
  • Engine propulsion system
    Patent number: 9212626
    Abstract: An engine propulsion system is configured to utilize bursts of pressurized media in order to transmit mechanical energy. The engine propulsion system includes at least one cannon, wherein each cannon is configured to displace the pressurized media and further includes a casing configured to accommodate a rotational firing pin. The rotational firing pin is configured to transmit the mechanical energy.
    Type: Grant
    Filed: June 9, 2014
    Date of Patent: December 15, 2015
    Inventor: Derrick T. Miller, Jr.
  • Catalytically enhanced gas generator system for rocket applications
    Patent number: 9200596
    Abstract: A rocket engine system with a fuel conversion system in communication with a gas generator.
    Type: Grant
    Filed: December 13, 2011
    Date of Patent: December 1, 2015
    Assignee: AEROJET ROCKETDYNE, INC.
    Inventors: Robert B. Fowler, Claude R. Joyner