Patents Examined by L. J. Casaregola
  • Patent number: 7493770
    Abstract: A check valve is provided that includes a valve housing that has a side wall and a flow path therethrough, the side wall defining the flow path. The flow path includes an inlet, an outlet, and a centerline extending between the inlet and the outlet. At least one control member is positioned in the flow path and movable between a first position, wherein fluid flow through the valve housing is substantially prohibited and a second position wherein fluid flow is permitted. The side wall includes a stop configured to limit movement of the at least one control member at a pre-determined stop angle relative to the flow path centerline.
    Type: Grant
    Filed: August 9, 2004
    Date of Patent: February 24, 2009
    Assignee: General Electric Company
    Inventors: Eric Jon Christianson, Jerry Wayne Myers, John Mathew Hand, Kevin Todd Bowers
  • Patent number: 7430851
    Abstract: In a fuel injector assembly, for an internal combustion engine such as a gas turbine engine, a generally cylindrical air transfer sleeve is, in one embodiment, juxtaposed around a shroud, the sleeve having a peripheral inner recessed cavity, the outer end thereof encompassing a plurality of air inlets and the inner end thereof having a plurality of air openings connecting the cavity with tertiary air for a positive air wash, or in another embodiment, is located intermediate a fuel body and the shroud while having such inner radial dimensions so as to maintain first and second fuel/air venting gaps, with the transfer sleeve also having a peripheral outer recessed cavity wherein the inner end thereof encompasses the air inlets, with an outer end thereof being provided with a plurality of air openings, these openings connecting the recessed cavity with the first fuel/air gap downstream of a restrictor.
    Type: Grant
    Filed: September 6, 2005
    Date of Patent: October 7, 2008
    Assignee: Parker-Hannifin Corporation
    Inventor: Kiran Patwari
  • Patent number: 7421844
    Abstract: A method used for combustion of a fuel-oxidizer mixture in a combustion chamber of a turbogroup, in particular of a power plant wherein total oxidizer flow is divided into a main oxidizer flow and a secondary oxidizer flow. The main oxidizer flow is lean mixed with a main fuel flow in a premix burner, and the mixture is fully oxidized in the combustion chamber. The secondary oxidizer flow is divided into a pilot oxidizer flow and a heat-exchanging oxidizer flow. The pilot oxidizer flow is rich mixed with a pilot fuel flow, and the mixture is partially oxidized in a catalyst, with hydrogen being formed. Downstream of the catalyst, the partially oxidized pilot fuel-oxidizer mixture and the heat-exchanging oxidizer flow are together introduced into at least one zone which is suitable for stabilizing the combustion of the main fuel-oxidizer mixture.
    Type: Grant
    Filed: February 28, 2005
    Date of Patent: September 9, 2008
    Assignee: Alstom Technology Ltd
    Inventors: Timothy Griffin, Dieter Winkler
  • Patent number: 7415826
    Abstract: A combustor dome assembly for a gas turbine engine having a longitudinal centerline axis extending therethrough, including: an annular dome plate having an inner portion, an outer portion, a forward surface and a plurality of circumferentially spaced openings formed therein, wherein a radial section is defined between each adjacent opening; and, a mixer assembly located upstream of and in substantial alignment with each of the openings in the dome plate, with the mixer assembly including a forward portion and an aft portion. Each mixer assembly is retained in a manner so as to be movable in a radial and axial direction without obstructing the radial sections of the dome plate. A first pair of tabs are positioned on the forward surface of the dome plate adjacent each opening and a second pair of tabs are positioned on the aft portion of each mixer assembly, wherein the dome plate tabs interface with the mixer assembly tabs to prevent rotation of each mixer assembly.
    Type: Grant
    Filed: July 25, 2005
    Date of Patent: August 26, 2008
    Assignee: General Electric Company
    Inventors: Marie Ann McMasters, David Allen Kastrup
  • Patent number: 7415827
    Abstract: In an air mixing arrangement wherein a primary fluid is introduced through an opening in a wall to be mixed with a secondary fluid flowing along the wall surface, the opening is airfoil shaped with its leading edge being orientated at an attack angle with respect to the secondary fluid flow stream so as to thereby enhance the penetration and dispersion of the primary fluid stream into the secondary fluid stream. The airfoil shaped opening is selectively positioned such that its angle of attack provides the desired lift to optimize the mixing of the two streams for the particular application. In one embodiment, a collar is provided around the opening to prevent the secondary fluid from contacting the surface of the wall during certain conditions of operation. Multiple openings maybe used such as the combination of a larger airfoil shaped opening with a smaller airfoil shaped opened positioned downstream thereof, or a round shaped opening placed upstream of an airfoil shaped opening.
    Type: Grant
    Filed: May 18, 2005
    Date of Patent: August 26, 2008
    Assignee: United Technologies Corporation
    Inventors: Fabio P. Bertolotti, David S. Liscinsky, Daniel R. Sabatino
  • Patent number: 7406820
    Abstract: The present invention provides an adaptive combustion controller and method for a turbine engine. The adaptive combustion controller and method modulates the fuel flow to the turbine engine combustor to reduce combustion instabilities. In particular, the adaptive combustion controller includes a fuel flow phase controller and a fuel flow magnitude controller. The adaptive combustion controller receives sensor data from the turbine engine. In response to the sensor data the fuel flow phase controller adjusts the phase of the modulated fuel flow to reduce instabilities in the combustor. Likewise, in response to the sensor data the fuel flow magnitude controller adjusts the magnitude of the modulated fuel flow to further reduce the instabilities in the combustor. By modulating the fuel flow to the combustor, and adaptively adjusting the phase and magnitude of the modulated fuel flow, the adaptive combustion controller is able to effectively reduce combustion instabilities.
    Type: Grant
    Filed: March 25, 2005
    Date of Patent: August 5, 2008
    Assignee: Honeywell International Inc.
    Inventors: Ian L. Critchley, Bruce Anson, Matthew C. Caspermeyer, Mike W. Scott
  • Patent number: 7404294
    Abstract: Method and arrangement for providing and controlling a gas turbine (1) at least one turbine (11, 20, 20?), at least one compressor (2, 5) driven by the turbine and a combustion chamber (16) arranged between the compressor and the turbine in the airflow path. The gas turbine includes devices (8) for direct measurement of the air mass flow at a position upstream of the combustion chamber in the airflow path, with the aim of regulating the quantity of fuel that is delivered to the combustion chamber (16) on the basis of the measured air mass flow.
    Type: Grant
    Filed: December 5, 2005
    Date of Patent: July 29, 2008
    Assignee: Volvo Aero Corporation
    Inventor: Lars Sundin
  • Patent number: 7401461
    Abstract: A fuel system (10) for a gas turbine engine (18) having a shaft (30) and requiring fuel to be supplied at a first rate for engine start up, the fuel system (10) including: a main fuel pump (14) for providing fuel to the gas turbine engine (18), the main fuel pump (14) having an output varying with shaft speed, the output being at a windmilling rate when the engine (18) is windmilling, the windmilling rate being less than the first rate; and an auxiliary fuel pump (40) for providing fuel to the gas turbine engine (18) and having an auxiliary output rate greater than or equal to the difference between the first rate and the windmilling rate. A method of operating such a fuel system (10) is also disclosed.
    Type: Grant
    Filed: May 27, 2005
    Date of Patent: July 22, 2008
    Assignee: Honeywell International Inc.
    Inventors: Christopher D. Eick, Timothy D. Mahoney, David D. Jones, William Lorenz
  • Patent number: 7395655
    Abstract: Hydromechanical regulator for controlling the flow of fuel injected into a turbomachine by means of a fuel feed unit (10), comprising a tachometric balance (20) having a beam consisting of two arms (24, 26), which beam can move about a pivot pin (22) under the action of at least a first force F1 applied by a drive rod (18) of the fuel feed unit via a first elastic member (28), and a rod (36) associated with a drive piston (38) for applying, via a second elastic member (40), a force F4 opposing the first force F1 to the beam of the balance so as to cause the fuel feed unit to open further during the transition from a first engine acceleration law to a second engine acceleration law.
    Type: Grant
    Filed: August 4, 2005
    Date of Patent: July 8, 2008
    Assignee: Hispano Suiza
    Inventor: Sylvain Poitout
  • Patent number: 7389644
    Abstract: A combustion turbine power generation system 10 includes a combustion turbine assembly 11 including a main compressor 12 constructed and arranged to receive ambient inlet air, a main expansion turbine 14 operatively associated with the main compressor, a combustor 16 constructed and arranged to receive compressed air from the main compressor and to feed the main expansion turbine, and an electric generator 15 associated with the main expansion turbine for generating electric power. Pressure reducing structure 28 is constructed and arranged to reduce pressure of compressed air from a source of compressed air to atmospheric pressure and thus to reduce a temperature of the compressed air from the source of compressed air to a temperature below ambient temperature when exhausted from the pressure reducing structure.
    Type: Grant
    Filed: January 19, 2007
    Date of Patent: June 24, 2008
    Inventor: Michael Nakhamkin
  • Patent number: 7389635
    Abstract: An exhaust mixer assembly having a twisted mixer and an open centerbody is provided. The open centerbody is centrally disposed within the twisted mixer and helps to provide efficient cooling of exhaust air from gas turbine engines. A method for cooling exhaust air from a gas turbine engine using the exhaust mixer assembly of the invention is also provided.
    Type: Grant
    Filed: December 1, 2004
    Date of Patent: June 24, 2008
    Assignee: Honeywell International Inc.
    Inventors: Morris G. Anderson, David F. Ross
  • Patent number: 7386981
    Abstract: A fuel system includes a first fuel line carrying fuel at a first line pressure (P22), a second fuel line carrying fuel at a second line pressure (PFNC) greater than the first line pressure (P22), at least one pressure regulating section 102 having an input 101 connected to the second fuel line and at least one output (103), a first pressure regulator (120) connected to the input and a second pressure regulator (130) connected between the first pressure regulator (120) and the at least one output (103), and a controller (160) controlling the position of the first and second pressure regulators (120, 130) to produce at the output (103) one of a predetermined number of output pressures relative to the first line pressure (P22).
    Type: Grant
    Filed: January 11, 2005
    Date of Patent: June 17, 2008
    Assignee: Honeywell International Inc.
    Inventors: Edward J. Zielinski, Paul W. Futa, Jr.
  • Patent number: 7383685
    Abstract: A passive exhaust system is described that provides effective infrared signature suppression without affecting radar cross-section while maintaining stable function in crosswinds. A passive exhaust system may include an array of ducts with each duct having a primary and secondary nozzle. Central ducts draw in ambient cooling air to create a thick cooling film along exterior surfaces and cause plume dilution, stabilize the plume flow in a crosswind, and prevent heating of visible surfaces. Visible surfaces may incorporate radar absorbing materials and may be inclined at an angle or fabricated with a diffuse surface to prevent specular reflection. Visible surfaces may be constructed from or covered with low infrared emissivity materials. A variable passive flow controller ensures a sufficient velocity exhaust flow.
    Type: Grant
    Filed: June 8, 2007
    Date of Patent: June 10, 2008
    Assignee: Northrop Grumman Ship Systems, Inc.
    Inventor: James L. Means
  • Patent number: 7377116
    Abstract: A barrier structure (302) blocks exit of spring clip fragments (317) that may break off from a spring clip assembly disposed between a gas turbine engine combustor (300) and a transition piece component (360). The barrier structure (302) may additionally comprise an aspect (326) effective to restrict a spring clip's (310, 311) radially inward compression, thereby reducing or eliminating damage to the spring clip (310, 311) during shipping and handling. The barrier structure (302) additionally may comprise an aspect (330) to restrict access by a human hand to the free ends (318) of the spring clips (310, 311). This aspect (330) reduces or eliminates the undesired lifting of the compressor by grabbing the spring clips (310, 311) during combustor transport, installation or removal. Accordingly, barrier structure embodiments are provided that reduce stress on spring clips, and that prevent the exit of spring clips from a containment space partly formed by the barrier structure.
    Type: Grant
    Filed: April 28, 2005
    Date of Patent: May 27, 2008
    Assignee: Siemens Power Generation, Inc.
    Inventors: David Marchant Parker, Kristian I. Wetzl
  • Patent number: 7377111
    Abstract: Carbon dioxide recirculating apparatus (20, 120) is disclosed for use in an arrangement having combination means (115) and a path for the flow of a gas through the combustion means (115). The apparatus (20, 120) comprises extraction means (221) for extracting carbon dioxide from a first region of the path downstream of the combustion means (115). It further includes condensing means (26, 30) for condensing the extracted carbon dioxide, and feed means (36, 136) for feeding the condensed carbon dioxide to a second region of the path upstream of the combustion means.
    Type: Grant
    Filed: April 22, 2004
    Date of Patent: May 27, 2008
    Assignee: Rolls-Royce plc
    Inventor: Gerard D Agnew
  • Patent number: 7377112
    Abstract: A method and device of this invention includes a fuel deoxygenator and a heating device for removing dissolved oxygen from fuel and then heating that fuel to a temperature above the temperature that would otherwise produce undesirable insoluble materials from a hydrocarbon fuel. The temperature of the fuel and the amount of dissolved oxygen that is removed from the fuel are adjusted according to the combustion process and optimization of desired combustion characteristics.
    Type: Grant
    Filed: June 22, 2005
    Date of Patent: May 27, 2008
    Assignee: United Technologies Corporation
    Inventors: Louis Spadaccini, Catalin Fotache
  • Patent number: 7377098
    Abstract: Disclosed is a structural frame for a gas turbine engine comprising an integral fluid reservoir and air/fluid heat exchanger. A central hub includes a reservoir for storing a fluid and an outer rim circumscribes the hub. A heat exchanger is fluidly coupled to the reservoir and is in simultaneous communication with the fluid and an air stream.
    Type: Grant
    Filed: August 26, 2004
    Date of Patent: May 27, 2008
    Assignee: United Technologies Corporation
    Inventors: Herbert L. Walker, Stevan W. Akerley
  • Patent number: 7373780
    Abstract: An oil scavenge system includes a tangential scavenge scoop and a settling area adjacent thereto which separately communicate with a duct which feeds oil into an oil flow path and back to an oil sump. A shield is mounted over the settling area to at least partially shield the collecting liquid oil from interfacial shear. A multiple of apertures are located through the shield to permit oil flow through the shield and into the duct. The scavenge scoop forms a partition which separates the duct into a first portion and a second portion. The first portion processes upstream air/oil mixture that is captured by the tangential scoop while the second portion receives the oil collected in the settling area.
    Type: Grant
    Filed: October 25, 2005
    Date of Patent: May 20, 2008
    Assignee: United Technologies Corporation
    Inventors: Robert E. Peters, Dwayne Messerschmidt, J. Axel Glahn, Kenneth L. Allard, Hsianmin F. Jen, Larry W. Spires, Roger M. Barnsby
  • Patent number: 7373773
    Abstract: The invention provides a gas turbine installation, a cooling air supplying method, a method of modifying a gas turbine installation, which can reduce the amount of compressed air extracted for cooling of an exhaust plenum and which can increase energy efficiency. The gas turbine installation comprises an exhaust plenum comprising an exhaust casing connected to the downstream side of a turbine and made up of an outer casing and an inner casing, and an exhaust diffuser made up of an outer diffuser and an inner diffuser, which are disposed between the outer casing and the inner casing; a first cooling system for introducing, from the outer peripheral side of the outer diffuser, cooling air for cooling the exhaust plenum; and a second cooling system for introducing, from the inner peripheral side of the inner diffuser, cooling air for cooling the exhaust plenum.
    Type: Grant
    Filed: August 12, 2004
    Date of Patent: May 20, 2008
    Assignee: Hitachi, Ltd.
    Inventor: Masami Noda
  • Patent number: 7373771
    Abstract: The accessory gearbox (AGB) has at least one coolant passage between the AGB and the accessory for externally cooling the accessory without coolant flow inside the accessory.
    Type: Grant
    Filed: July 9, 2004
    Date of Patent: May 20, 2008
    Assignee: Pratt & Whitney Canada Corp.
    Inventor: David Brouillet