Patents Examined by Louis Casaregola
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Patent number: 8141336Abstract: A combined cycle power plant includes a gas turbine having a first compressor, a second compressor downstream of the first compressor, and a regenerative heat exchanger between the first and second compressors. A steam generator is downstream of the gas turbine and receives exhaust from the gas turbine. A closed loop cooling system through the regenerative heat exchanger and the steam generator transfers heat from the regenerative heat exchanger to the steam generator. A method for operating a combined cycle power plant includes compressing a working fluid in a compressor and cooling the compressed working fluid with a regenerative heat exchanger so as to create a cooled compressed working fluid. The method further includes transferring heat from the regenerative heat exchanger to a steam generator.Type: GrantFiled: September 8, 2010Date of Patent: March 27, 2012Assignee: General Electric CompanyInventors: Joseph John, Jegadeesan Maruthamuthu, Sudhahar Rajan, Venugopala Durwasula Raju
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Patent number: 8141334Abstract: A combustor for a combustion turbine engine that includes: a chamber defined by an outer wall and forming a channel between windows defined through the outer wall toward a forward end of the chamber and at least one fuel injector positioned toward an aft end of the chamber; and a multilayer screen filter comprising at least two layers of screen over at least a portion of the windows and at least one layer of screen over the remaining portion of the windows. The windows include a forward end and a forward portion, and an aft end and an aft portion. The multilayer screen filter is positioned over the windows such that, in operation, a supply of compressed air entering the chamber through the windows passes through at least one layer of screen. The multilayer screen filter is configured such that the aft portion of the windows include at least two layers of screen, and the forward portion of the windows includes one less layer of screen than the aft portion of the windows.Type: GrantFiled: August 2, 2010Date of Patent: March 27, 2012Assignee: General Electric CompanyInventors: Thomas Edward Johnson, Baifang Zuo, Christian Xavier Stevenson
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Patent number: 8141339Abstract: There is provided an injector assembly having two or more oxidizer manifolds and/or two or more fuel manifolds for delivery of liquid propellants to a combustion chamber such that combustion instability is reduced or eliminated during throttling. Delivery of the oxidizer to the oxidizer manifolds is controlled by an oxidizer valve, which may comprise an integral valve. The oxidizer passes from the oxidizer manifolds into the oxidizer element and then into the combustion chamber. The multiple oxidizer manifolds allow the oxidizer to be provided through selective openings of the oxidizer element thus reducing the change in pressure drop across the oxidizer element to thereby reduce or eliminate combustion instability and other problems. Additionally, the injector assembly may also include a lift-off seal or a filler fluid source to fill any temporarily unused oxidizer manifolds with an oxidizer or filler fluid.Type: GrantFiled: November 6, 2009Date of Patent: March 27, 2012Assignee: Pratt & Whitney Rocketdyne, Inc.Inventors: James J. Fang, Steven C. Fisher, Robert J. Jensen
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Patent number: 8141369Abstract: The invention relates to a method of regulation of the temperature of a hot gas of a gas turbine, particularly of a stationary gas turbine used for generating electricity, which comprises injecting a liquid into an airflow, which can be drawn into a compressor and with the aid of which a fuel inside a combustion chamber, which is situated downstream, combusts while producing the hot gas that is subsequently expanded when flowing through the turbine part located downstream. A temperature measuring device is provided that measures the temperature of the airflow before the compressor, whereby the temperature of the hot gas is regulated by the quantity of fuel. The aim of the invention is to provide a regulation with which, during wet compression operation, the serviceable life of the components subjected to the action of hot gas is lengthened.Type: GrantFiled: February 26, 2009Date of Patent: March 27, 2012Assignee: Siemens AktiengesellschaftInventors: Joachim-Rene Nuding, Christoph Pels Leusden, Marco Tappen
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Patent number: 8141337Abstract: A bypass turbine engine includes a precooler having an annular cross-sectional shape about the axis of a pod and arranged inside the rear part of an inner shroud in contact with a cold fluid exiting a fan duct.Type: GrantFiled: January 18, 2007Date of Patent: March 27, 2012Assignee: Airbus Operations SASInventors: Alain Porte, Damien Prat
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Patent number: 8136342Abstract: 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: GrantFiled: November 19, 2010Date of Patent: March 20, 2012Assignee: United Technologies CorporationInventors: Fabio R. Bertolotti, David S. Liscinsky, Vincent C. Nardone, Michael K. Sahm, Bernd R. Noack, Daniel R. Sabatino
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Patent number: 8136360Abstract: A fuel injector for a gas turbine combustor is disclosed which includes a feed arm having a flange for mounting the injector within the combustor and a fuel nozzle depending from the feed arm for injecting fuel into the combustor for combustion. An optical sensor array is operatively associated with the fuel nozzle for observing combustor flame characteristics. The optical sensor array includes a plurality of sapphire rods positioned to be close enough to the combustor flame to oxidize soot deposits thereon.Type: GrantFiled: February 2, 2009Date of Patent: March 20, 2012Assignee: Rosemount Aerospace Inc.Inventor: Douglas C. Myhre
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Patent number: 8132399Abstract: A rotary engine includes a rotor having one or more combustion chambers connected to an exhaust passageway extending radially outward from the combustion chamber to an exhaust port adjacent a peripheral edge of the rotor. The exhaust gas is expelled at an angle to thereby generate cause the rotor to rotate. The housing may include reflective surfaces that reflect shockwaves from the exhaust gas back towards vanes on the rotor to thereby capture additional energy from the exhaust gas. The housing may also include stators that capture additional energy from the exhaust gas and rotate the rotor. An intake port fluidly connected to the combustion chamber is aligned with an opening in the housing as the rotor rotates to thereby allow comprised air to flow into the combustion chamber. As the combustion chamber rotates, it is closed off by a closed portion of the housing, fuel is injected, and ignited, to thereby generate exhaust gases and generate power.Type: GrantFiled: March 15, 2011Date of Patent: March 13, 2012Inventor: Alex VanHolstyn
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Patent number: 8127525Abstract: A device for, in a gas turbine engine, braking a turbine including a rotor, having at least one disk with a rim driving a shaft and capable of rotating with respect to a stator, is disclosed. The device is for the event of the shaft breaking and includes a first braking member, secured to the rim and provided with at least one cutting element, and a second braking member secured to the stator downstream of the rim and including a ring-shaped element made of a material that can be cut by the cutting element. The two braking members coming into contact with one another through axial displacement of the rotor once the shaft has broken. The cutting element of the first braking member cuts the ring-shaped element of the second braking member.Type: GrantFiled: May 23, 2008Date of Patent: March 6, 2012Assignee: SNECMAInventors: Jacques Rene Bart, Didier Rene Andre Escure, Claude Marcel Mons, Stephane Rousselin
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Patent number: 8127549Abstract: A burner is provided that has high flame stability and reduces NOx emissions. In the burner, air holes of an air hole member have a central axis inclined relative to a burner central axis. The leading end portion of a first fuel nozzle is configured to be able to suppress turbulence of air-flow flowing on the outer circumference side of the first fuel nozzle. The tip of the first fuel nozzle is located on a fuel jetting-out directional downstream side of the inlet of the fuel hole. The tip of the second fuel nozzle is located on a fuel jetting-out directional downstream side of the air hole inlet.Type: GrantFiled: November 26, 2008Date of Patent: March 6, 2012Assignee: Hitachi, Ltd.Inventors: Keisuke Miura, Hiroshi Inoue, Kazuhito Koyama, Takeo Saito, Satoshi Dodo
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Patent number: 8127555Abstract: An electrical power generation system incorporates thermoelectric devices (TE Devices) for electrical power generation adjacent a flow path heat exchanger (HEX) adjacent to a vehicle flowpath structure such as a scramjet flow path to take advantage of the waste heat, high thermal gradients, and available, unused volume. A thermally conductive material communicates thermal energy from a vehicle external skin structure to the TE Device while a thermally conductive compliant material allows the TE Device to “float” with minimal mechanical stress.Type: GrantFiled: December 13, 2007Date of Patent: March 6, 2012Assignee: Pratt & Whitney Rocketdyne, Inc.Inventors: David C. Jarmon, Mark A. Sillence, Paul Attridge, Jean Yamanis
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Patent number: 8127527Abstract: A method and system for operating a gas turbine engine is provided. The system includes in serial flow arrangement, at least one compressor, a combustor, and at least one turbine. The method includes compressing atmospheric air in the gas turbine engine, channeling at least a portion of the compressed air from the turbine engine flowpath to an oxidizer supply system, and channeling an oxygen-depleted flow of the compressed air from the oxidizer supply system to the gas turbine engine flowpath.Type: GrantFiled: November 22, 2004Date of Patent: March 6, 2012Assignee: General Electric CompanyInventor: Rollin George Giffin
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Patent number: 8127550Abstract: A gas turbine combustor (10) comprises a base plate (12) from which protrude a plurality of lips (36) that surround respective apertures (16) into which are positioned downstream ends (19) of main swirler assemblies (18). The apertures (16) are arranged about a centrally positioned pilot cone (22) that comprises an inner cone (23) and an outer cone (25), defining a space (31) there between. A number of laterally directed apertures (60) are disposed along the outer cone (25) so as to direct a flow of fluid toward a near portion (38) of each lip (36), thereby perturbing pockets of high fuel-to-air mixtures between the outer cone (25) and the near region (38). The provision of such laterally directed apertures (60) reduces or eliminates flashback between the outer cone (25) and the near region (38) through such action.Type: GrantFiled: January 23, 2007Date of Patent: March 6, 2012Assignee: Siemens Energy, Inc.Inventors: Arthur J. Harris, Jr., Rajeev Ohri
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Patent number: 8127547Abstract: A gas turbine engine is provided with a first heat exchanger associated with a cooling air flow to deliver cooling air to a turbine section. A second heat exchanger is associated with a fuel supply line for delivering fuel into a combustion section. An intermediate fluid cools air at the first heat exchanger and heats fuel at the second heat exchanger.Type: GrantFiled: June 7, 2007Date of Patent: March 6, 2012Assignee: United Technologies CorporationInventors: James W. Norris, Andrew P. Berryann
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Patent number: 8127531Abstract: A variable area nozzle system for a turbofan gas turbine engine comprises a fan duct inner wall, a fan duct outer wall and a fan nozzle. The fan duct outer wall is disposed in radially-spaced relation to the fan duct inner wall. The fan nozzle defines at least a portion of the fan duct outer wall and has a nozzle aft edge defining a fan duct throat area relative to the fan duct inner wall. The fan nozzle is configured to move outwardly relative to the longitudinal axis during axial aft translation thereof in order to vary the fan duct throat area.Type: GrantFiled: November 11, 2008Date of Patent: March 6, 2012Assignee: The Boeing CompanyInventor: Dean L. Parham
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Patent number: 8127557Abstract: Control systems and a method for controlling a load point of a gas turbine engine are provided. A control system includes a controller that receives a temperature signal and a pressure signal associated with exhaust gases from the gas turbine engine. The controller is further configured to generate the fuel control signal. The controller is further configured to generate an actuator control signal such that flow restriction member is moved from the first operational position to the second operational position to restrict the flow path such that the exhaust gases have a temperature level within a desired turndown temperature range, the pressure level in the exhaust gases is less than a threshold pressure level, and the load point of the gas turbine engine is adjusted to toward a target load point.Type: GrantFiled: April 7, 2008Date of Patent: March 6, 2012Assignee: General Electric CompanyInventor: Constantin Dinu
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Patent number: 8127532Abstract: A variable area nozzle system for a gas turbine engine includes a fan duct inner wall, a fan duct outer wall disposed in radially spaced relation to the fan duct inner wall, and a fan nozzle. The fan nozzle defines at least a portion of the fan duct outer wall and includes a nozzle aft edge. The fan duct inner wall and the nozzle aft edge collectively define a fan duct nozzle throat area. The fan nozzle is configured to pivot about a pivot axis that may be oriented transversely relative to a longitudinal axis of the gas turbine engine. The fan nozzle may be pivoted from a stowed position to a deployed position in order to vary the fan duct nozzle throat area.Type: GrantFiled: November 26, 2008Date of Patent: March 6, 2012Assignee: The Boeing CompanyInventor: Mark E. Howe
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Patent number: 8122702Abstract: A transcowl for a gas turbine engine thrust reverser includes an arcuate outer wall; an arcuate inner wall; and an arcuate baffle positioned between the inner and outer walls at a forward end of the transcowl. The baffle has an arcuate cross-sectional shape which defines a forward-facing interior area. An arcuate forward seal is carried at a forward end of the inner wall. The forward seal includes a plurality of axially-extending, spaced-apart arcuate seal teeth which collectively define a labyrinth seal.Type: GrantFiled: October 11, 2007Date of Patent: February 28, 2012Assignee: General Electric CompanyInventors: Chi-Ling Michael Tsou, Carl Francis Holdren, William Andrew Bailey, Dean Thomas Lenahan
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Patent number: 8122699Abstract: An ecology valve (EV) fuel return system includes a housing assembly, an ecology valve, and a fuel routing assembly. The ecology valve includes an EV piston slidably disposed within the housing assembly for movement between a fuel storage position and a fuel return position, a fuel storage chamber defined by the EV piston and the housing assembly, and an EV control chamber defined by the EV piston and the housing assembly. The fuel routing assembly, which is fluidly coupled to the EV control chamber and to the fuel storage chamber, is configured to route fuel: (i) from the fuel storage chamber to a fuel supply system when a gas turbine engine (GTE) is in a start-up mode, and (ii) from the first fuel manifold and from the EV control chamber to the fuel storage chamber when the GTE is in a shut-down mode.Type: GrantFiled: December 3, 2008Date of Patent: February 28, 2012Assignee: Honeywell International Inc.Inventors: David Lawrence, Paul Futa, Larry Portolese
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Patent number: 8122703Abstract: A bi-propellant injector includes first and second injector elements and a spark exciter assembly. The first injector element has a conductive layer electrically connected to the spark exciter assembly and a nonconductive layer disposed on an exterior portion of the conductive layer. The second injector element comprises a conductive material and has an opening therethrough in fluid communication with a combustion chamber. An end of the first injector element is positioned at or near the opening in the second injector element. The spark exciter assembly can generate an electrical arc between the conductive layer of the first injector element and the second injector element.Type: GrantFiled: April 28, 2006Date of Patent: February 28, 2012Assignee: United Technologies CorporationInventor: Steven C. Fisher