Patents Examined by Steven Sutherland
  • Cooled double walled article
    Patent number: 9010124
    Abstract: A gas turbine engine combustion chamber includes a first wall and a second wall. The second wall is arranged within and spaced from the first wall to define a cavity between the first wall and the second wall. The first wall has a plurality of impingement apertures extending there-through and the second wall has a plurality of effusion apertures extending there-through. The impingement apertures have a first diameter, a first pitch, and a first area. The effusion apertures have a second diameter, a second pitch, and a second area. The ratio of the first diameter to the second diameter is at least 3, the ratio of the first pitch to the second pitch is at least 4 and the ratio of the first area to the second area is at least 9. This arrangement increases the cooling performance of the effusion apertures in the second wall.
    Type: Grant
    Filed: March 15, 2012
    Date of Patent: April 21, 2015
    Assignee: ROLLS-ROYCE plc
    Inventors: Paul I. Chandler, Anthony Pidcock
  • Turbine engine and method for flowing air in a turbine engine
    Patent number: 9010082
    Abstract: According to one aspect of the invention, a gas turbine engine includes a combustor, a fuel nozzle placed in an end of the combustor, and a passage configured to receive an air flow from a compressor discharge casing, wherein the passage directs the air flow into a chamber downstream of the nozzle, wherein a chamber pressure is lower than a compressor discharge casing pressure. The gas turbine engine also includes a flow control device configured to control the air flow from the compressor discharge casing into the passage.
    Type: Grant
    Filed: January 3, 2012
    Date of Patent: April 21, 2015
    Assignee: General Electric Company
    Inventors: Lucas John Stoia, Patrick Benedict Melton, Predrag Peja Popovic
  • System and method for exhaust gas use in gas turbine engines
    Patent number: 9003761
    Abstract: In one embodiment, a system is provided that includes a first gas turbine engine. The first gas turbine engine has a first compressor configured to intake air and to produce a first compressed air and a first combustor configured to combust a first mixture to produce a first combustion gas. The first mixture has a first fuel, at least a first portion of the first compressed air, and a second combustion gas from a second gas turbine engine. The first gas turbine engine also includes a first turbine configured to extract work from the first combustion gas.
    Type: Grant
    Filed: May 28, 2010
    Date of Patent: April 14, 2015
    Assignee: General Electric Company
    Inventor: Samuel David Draper
  • Gas turbine engine oil buffering
    Patent number: 8997500
    Abstract: A turbine engine includes a shaft, a fan, at least one bearing mounted on the shaft and rotationally supporting the fan, a fan drive gear system coupled to drive the fan, a bearing compartment around the at least one bearing and a source of pressurized air in communication with a region outside of the bearing compartment.
    Type: Grant
    Filed: December 30, 2011
    Date of Patent: April 7, 2015
    Assignee: United Technologies Corporation
    Inventors: Jorn A. Glahn, Frederick M. Schwarz
  • Hybrid exhaust component
    Patent number: 8997496
    Abstract: An exhaust includes a wall that has a first composite material having a first coefficient of thermal expansion and a second composite material having a second coefficient of the thermal expansion that is less than the first coefficient of thermal expansion.
    Type: Grant
    Filed: June 29, 2011
    Date of Patent: April 7, 2015
    Assignee: United Technologies Corporation
    Inventors: Gerard D. Pelletier, Charles P. Logan, Bryan William McEnerney, Jeffrey D. Haynes
  • Gas turbine engine
    Patent number: 8984858
    Abstract: One embodiment of the present invention is a unique gas turbine engine. Another embodiment of the present invention is a unique gas turbine engine bearing system. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines and gas turbine engine bearing systems. 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 23, 2011
    Date of Patent: March 24, 2015
    Assignee: Rolls-Royce Corporation
    Inventor: Matthew Michael Miller
  • Fuel manifold heat shield for a gas turbine engine
    Patent number: 8978383
    Abstract: A fuel manifold assembly for a gas turbine engine is described and includes an annular manifold body and an annular heat shield assembly mounted to and surrounding the manifold body. The heat shield assembly has an inner surface facing the manifold body and spaced apart therefrom by an inner air gap, which substantially surrounds the manifold body, defined therebetween. The heat shield assembly has an outer surface facing away from the manifold body and spaced apart from the inner surface by an outer air gap substantially surrounding the inner air gap. At least the outer air gap is formed by a double wall configuration of the heat shield assembly.
    Type: Grant
    Filed: March 26, 2012
    Date of Patent: March 17, 2015
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Bhawan B. Patel, Oleg Morenko
  • Combustor shell air recirculation system in a gas turbine engine
    Patent number: 8973372
    Abstract: A shell air recirculation system for use in a gas turbine engine includes one or more outlet ports located at a bottom wall section of an engine casing wall and one or more inlet ports located at a top wall section of the engine casing wall. The system further includes a piping system that provides fluid communication between the outlet port(s) and the inlet port(s), a blower for extracting air from a combustor shell through the outlet port(s) and for conveying the extracted air to the inlet port(s), and a valve system for selectively allowing and preventing air from passing through the piping system. The system operates during less than full load operation of the engine to circulate air within the combustor shell but is not operational during full load operation of the engine.
    Type: Grant
    Filed: September 5, 2012
    Date of Patent: March 10, 2015
    Assignee: Siemens Aktiengesellschaft
    Inventors: Ching-Pang Lee, Evan C. Landrum, Jiping Zhang
  • Gas turbine engine with noise attenuating variable area fan nozzle
    Patent number: 8973364
    Abstract: A high-bypass gas turbine engine includes a variable area fan nozzle with an acoustic system having an acoustic impedance.
    Type: Grant
    Filed: June 26, 2008
    Date of Patent: March 10, 2015
    Assignee: United Technologies Corporation
    Inventors: Jonathan Gilson, Dennis Cicon, Oliver V. Atassi
  • Mixer assembly for a gas turbine engine
    Patent number: 8973368
    Abstract: A mixer assembly for a gas turbine engine is provided, including a main mixer with fuel injection holes located between at least one radial swirler and at least one axial swirler, wherein the fuel injected into the main mixer is atomized and dispersed by the air flowing through the radial swirler and the axial swirler.
    Type: Grant
    Filed: January 26, 2011
    Date of Patent: March 10, 2015
    Assignee: United Technologies Corporation
    Inventors: Zhongtao Dai, Jeffrey M. Cohen, Catalin G. Fotache, Lance L. Smith, Donald J. Hautman
  • Shielding for a gas turbine engine component
    Patent number: 8973375
    Abstract: One embodiment of the present application includes a hot section component of a gas turbine engine having a covering. The covering includes a protrusion and is attached to the hot section component though a flexible retainer. In one form the covering is made from ceramic matrix composite. The flexible retainer has a closed position and an open position. The retainer secures the protrusion to the hot section component when it engages part of the protrusion when in the closed position.
    Type: Grant
    Filed: December 9, 2009
    Date of Patent: March 10, 2015
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventor: Mark O'Leary
  • Heat recovery from a gasification system
    Patent number: 8959885
    Abstract: A heat recovery system for use with a gasification system is provided. One system includes a gasification system and an organic Rankine cycle system coupled to the gasification system. The organic Rankine cycle system is configured to receive heated fluid from the gasification system and to deliver cooled fluid to the gasification system. The organic Rankine cycle system is configured to produce power by converting heat energy in the heated fluid.
    Type: Grant
    Filed: August 22, 2011
    Date of Patent: February 24, 2015
    Assignee: General Electric Company
    Inventors: Ganesh Prasadh Kidambi, Atul Kumar Vij, Priyanandini Balasubramanian, Ronald Frederick Tyree
  • Aircraft engine fuel pump bearing flow and associated system and method
    Patent number: 8959920
    Abstract: An assembly or system is provided for selectively regulating journal bearing lubrication between at least first and second levels in an aircraft engine. A high pressure pump includes movable portions at least in part supported by a journal bearing. A selector valve is configured to selectively supply lubrication flow to the journal bearing. In addition, a relief valve is configured to receive a signal from the selector valve defining a pressure level at which the relief valve should relieve pressure.
    Type: Grant
    Filed: April 13, 2012
    Date of Patent: February 24, 2015
    Assignee: Eaton Corporation
    Inventor: Martin A. Clements
  • Self-calibration method for the electric jacks of a turbojet nacelle
    Patent number: 8955305
    Abstract: The invention relates to a method for the self-calibration of electric jacks (6a, 6b) capable of actuating a mobile member (2) of a turbojet nacelle (1) and connected to at least one position measuring member, characterized in that it comprises the steps of: moving the jack(s) into a retracted position corresponding to a first position of the mobile member, storing one or more position values fed back by the position measuring member for the jack(s) in said retracted position; moving the jack(s) into an extended position corresponding to a second position of the mobile member; storing one or mom position values fed back by the position measuring member for the jack(s) in said extended position.
    Type: Grant
    Filed: February 1, 2008
    Date of Patent: February 17, 2015
    Assignee: Aircelle
    Inventors: Thierry Marin Martinod, Hakim Maalioune
  • Method for synchronizing the actuators of a movable thrust reverser cowl
    Patent number: 8955306
    Abstract: The invention relates to a method for controlling a plurality of actuators (9a, 9b, 9c) for a movable thrust reverser cowl (1), characterized remarkable in that the position deviation between adjacent actuators is measured in real time, and in that the speed profile of the actuator or actuators in question is adjusted by a position deviation exceeding a predetermined threshold.
    Type: Grant
    Filed: April 27, 2009
    Date of Patent: February 17, 2015
    Assignee: Aircelle
    Inventors: Hakim Maalioune, David Pereira
  • Mounting assembly
    Patent number: 8943840
    Abstract: A mounting assembly 2 for mounting a gearbox 10 to a gas turbine engine, comprising a mount ring 4 and a spigot pin 8 having a flange 22 at one end. The spigot pin 8 extends radially outwardly through a bore 14 in the mount ring 4 for engagement with a gearbox 10 and the flange 22 locates against a radially inner surface of the mount ring 4. The bore 14 supports the spigot pin 8 and dissipates forces exerted on the spigot pin 8, for example forces generated during a fan blade-off event.
    Type: Grant
    Filed: May 23, 2011
    Date of Patent: February 3, 2015
    Assignee: Rolls-Royce PLC
    Inventor: Keith Williams
  • Variable cycle turbine engine
    Patent number: 8943796
    Abstract: A gas turbine engine comprises a high spool, a low spool and an intermediate spool. The high spool comprises a high pressure turbine coupled to a high pressure compressor. The intermediate spool comprises an intermediate pressure turbine coupled to a ducted fan. The low spool comprises a low pressure turbine coupled to an open-rotor propeller. A variable area turbine section positioned between the intermediate pressure turbine and the low pressure turbine variable turbine section is configured to vary an expansion ratio across the intermediate pressure turbine to control rotational speeds of the low spool and the intermediate spool.
    Type: Grant
    Filed: June 28, 2011
    Date of Patent: February 3, 2015
    Assignee: United Technologies Corporation
    Inventor: Michael G. McCaffrey
  • Fuel air heat exchanger
    Patent number: 8943827
    Abstract: A gas turbine engine with a fuel air heat exchanger located in the high pressure plenum. The heat exchanger includes at least one air conduit and at least one fuel conduit in heat exchange relationship with one another, with a fuel flow communication between a fuel source and fuel distribution members of the combustor being provided at least partly through the at least one fuel conduit, and the at least one air conduit defining a fluid flow communication between the high pressure plenum and an engine component to be cooled by the compressed air.
    Type: Grant
    Filed: May 31, 2011
    Date of Patent: February 3, 2015
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Lev Alexander Prociw, Eduardo Hawie
  • Control of axial thrust by guidance of the air drawn off from a centrifugal compressor
    Patent number: 8938975
    Abstract: An inner combustion chamber casing of a turbomachine, which is intended to be placed downstream of a centrifugal compressor, is provided. The casing has the shape of a disc, pierced by a central circle, and includes on its disc at least one guide vane of the drawn-off air. The guide vane extends longitudinally over the disc between the periphery of the disc and the central circle and spreads out axially from the disc so as to form with the downstream face of the centrifugal compressor a guide channel for the air which is drawn off upon exit from the said compressor. The guide vane has a curved shape orienting in a radial direction at the level of its most central end.
    Type: Grant
    Filed: June 7, 2011
    Date of Patent: January 27, 2015
    Assignee: SNECMA
    Inventors: Laurent Donatien Behaghel, Frederic Dallaine, Delphine Leroux, Benjamin Philippe Pierre Pegouet
  • Geared turbofan gas turbine engine architecture
    Patent number: 8935913
    Abstract: A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. A speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the fan section may rotate at a speed different than the turbine section so as to increase the overall propulsive efficiency of the engine. In such engine architectures, a shaft driven by one of the turbine sections provides an input to the epicyclical gear assembly that drives the fan section at a speed different than the turbine section such that both the turbine section and the fan section can rotate at closer to optimal speeds providing increased performance attributes and performance by desirable combinations of the disclosed features of the various components of the described and disclosed gas turbine engine.
    Type: Grant
    Filed: October 5, 2012
    Date of Patent: January 20, 2015
    Assignee: United Technologies Corporation
    Inventors: Daniel Bernard Kupratis, Frederick M. Schwarz