Ignition Or Fuel Injection After Starting Patents (Class 60/776)
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Publication number: 20140260296Abstract: A slinger combustor has an annular combustor shell defining a combustion chamber having a radially inner fuel inlet for receiving a spray of fuel centrifuged by a fuel slinger. The combustion chamber has a fuel atomization zone extending radially outwardly from the fuel inlet and merging into a radially outwardly flaring expansion zone leading to a combustion zone. A plurality of nozzle air inlets are defined in the fuel atomization zone of the combustor shell. The nozzle air inlets have a nozzle axis intersecting the stream of fuel and a tangential component in a direction of rotation of the fuel slinger. A plurality of dilution holes are defined in the combustor shell and have a dilution axis intersecting the combustion zone. The dilution axis of at least some of the dilution holes has a tangential component opposite to the direction of rotation of the fuel slinger.Type: ApplicationFiled: March 12, 2013Publication date: September 18, 2014Applicant: PRATT & WHITNEY CANADA CORP.Inventor: PRATT & WHITNEY CANADA CORP.
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Publication number: 20140260304Abstract: A method including providing a wet algae material having been subjected to a refinement process without a water separation phase; supplying the wet algae material including a water fraction and an algae-grown biofuel to a turbine engine; and operating the turbine engine with the wet algae material where a retained portion of the water fraction is retained in the wet biofuel during a manufacturing process not including a dehydration step and includes an amount sufficient to reduce generation of a quantity of nitrogen oxides, and where the turbine engine can further include a combustor capable of combusting the wet biofuel.Type: ApplicationFiled: December 27, 2013Publication date: September 18, 2014Applicant: ROLLS-ROYCE CORPORATIONInventors: William G. CUMMINGS, III, Enrico LO GATTO
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Publication number: 20140260299Abstract: Embodiments of the present disclosure are directed to systems and methods for premixing fuel and air prior to combustion within a combustion chamber. The system includes a plurality of fuel injectors and a plurality of mixing tubes, wherein each mixing tube has a first portion for receiving one of the plurality of fuel injectors and a second portion having a mixing chamber that is configured to mix fuel and air. The length of the mixing chamber varies among the plurality of mixing tubes to allow for different mixing times.Type: ApplicationFiled: March 12, 2013Publication date: September 18, 2014Applicant: GENERAL ELECTRIC COMPANYInventor: GENERAL ELECTRIC COMPANY
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Publication number: 20140260298Abstract: A combustor comprises an annular combustor chamber formed between the inner and outer liners. Fuel nozzles each have an end in fluid communication with the annular combustor chamber to inject fuel in the annular combustor chamber, the fuel nozzles oriented to inject fuel in a fuel flow direction having an axial component relative to the central axis of the annular combustor chamber. A plurality of nozzle air holes are defined through the inner liner and the outer liner adjacent to and downstream of the fuel nozzles. The nozzle air holes are configured for high pressure air to be injected from an exterior of the liners through the nozzle air holes generally radially into the annular combustor chamber. A central axis of the nozzle air holes has a tangential component relative to the central axis of the annular combustor chamber.Type: ApplicationFiled: March 12, 2013Publication date: September 18, 2014Applicant: PRATT & WHITNEY CANADA CORP.Inventors: Lev Alexander Prociw, Parham Zabeti, Tin Cheung John Hu
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Publication number: 20140260301Abstract: A fuel system for a gas turbine engine includes an engine fuel manifold, a hydraulic actuator, and a drain piston assembly. The hydraulic actuator actuates in response to a change in pressures within the hydraulic actuator. The drain piston assembly is fluidically connected to both the hydraulic actuator and the engine fuel manifold. The drain piston assembly receives fuel from the engine fuel manifold and sends fuel to the hydraulic actuator during engine shut down.Type: ApplicationFiled: March 14, 2013Publication date: September 18, 2014Applicant: HAMILTON SUNDSTRAND CORPORATIONInventors: Todd Haugsjaahabink, Charles E. Reuter
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Publication number: 20140260297Abstract: A combustor comprises an annular combustor chamber formed between the inner and outer liners, the annular combustor chamber having a central axis. Fuel nozzles are in fluid communication with the annular combustor chamber to inject fuel in the annular combustor chamber. The fuel nozzles are oriented to inject fuel in a fuel flow direction having an axial component relative to the central axis of the annular combustor chamber. Nozzle air inlets are in fluid communication with the annular combustor chamber to inject nozzle air generally radially in the annular combustor chamber. A plurality of dilution air holes are defined through the inner and outer liner downstream of the nozzle air inlets, the dilution holes configured for high pressure air to be injected from an exterior of the liners through the dilution air holes generally radially into the combustor chamber, a central axis of the dilution air holes having a tangential component relative to the central axis of the annular combustor chamber.Type: ApplicationFiled: March 12, 2013Publication date: September 18, 2014Applicant: PRATT & WHITNEY CANADA CORP.Inventors: Lev Alexander Prociw, Parham Zabeti
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Publication number: 20140260302Abstract: The present application and the resultant patent provide a diffusion combustor fuel nozzle for a gas turbine engine. The fuel nozzle may include one or more gas fuel passages for one or more flows of gas fuel, a swirler surrounding the one or more gas fuel passages and positioned about a downstream face of the fuel nozzle, a number of swirler gas fuel ports defined in the swirler, and a number of downstream face gas fuel ports defined in the downstream face of the fuel nozzle. The swirler may include a number of swirl vanes and a number of air chambers defined between adjacent swirl vanes. The present application and the resultant patent further provide a method of operating a diffusion combustor fuel nozzle of a gas turbine engine.Type: ApplicationFiled: March 14, 2013Publication date: September 18, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Arvind Venugopal Menon, Gilbert Otto Kraemer, Predrag Popovic, Abinash Baruah
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Publication number: 20140260300Abstract: A system includes a multi-tube fuel nozzle of a turbine combustor. The multi-tube fuel nozzle includes a support structure defining an interior volume configured to receive an air flow; a plurality of mixing tubes disposed within the interior volume, wherein each of the plurality of mixing tubes comprises a respective fuel injector; and an outer annular wall configured to direct an air flow from an annulus between a liner and a flow sleeve of the turbine combustor at least partially radially inward into the interior volume through an air inlet and toward the plurality of mixing tubes, wherein the outer annular wall at least partially defines an air flow passage extending from the annulus to the interior volume.Type: ApplicationFiled: March 12, 2013Publication date: September 18, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Ronald James Chila, Gregory Allen Boardman, James Harold Westmoreland
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Publication number: 20140260305Abstract: A combustion chamber may include a first surface and a second surface interconnected by a wall forming a chamber having a central axis. The first surface may define an exhaust opening and the second surface defining a pilot opening, wherein the exhaust opening and the pilot opening align along the central axis. A plurality of inlet ports may be configured to deliver air to the chamber. A plurality of fuel ports may be arranged on an inside of the second surface to deliver fuel to the chamber. The air flow from the inlet ports and fuel from the fuel ports may oppose each other to create a vortex of product proximal to the second surface.Type: ApplicationFiled: December 30, 2013Publication date: September 18, 2014Applicant: Rolls-Royce Canada, Ltd.Inventors: Joseph L. Hobbs, Jennifer A.M. Sidey, Robert L. Gordon, Epaminondas Mastorakos, Gilles Bourque
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Publication number: 20140260303Abstract: A method for use in a gas turbine engine. The method includes the steps of: configuring a downstream injection system within the interior flowpath that includes two injection stages, a first stage and a second stage, wherein the first stage and the second stage are each axially spaced from the other; and circumferentially positioning the injectors of the first stage and the second stage based on: a) a characteristic of an anticipated combustion flow occurring just upstream of the first stage during a mode of operation; and b) the characteristic of an anticipated combustion flow just downstream of the second stage given an anticipated effect of the air and fuel injection from the first stage and the second stage.Type: ApplicationFiled: March 15, 2013Publication date: September 18, 2014Inventors: Lewis Berkley Davis, JR., Krishna Kumar Venkataraman, Kaitlin Marie Graham
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Publication number: 20140250908Abstract: Systems and methods for controlling the composition of a combustion exhaust gas are provided.Type: ApplicationFiled: July 1, 2011Publication date: September 11, 2014Applicants: ExxonMobil Upsteam Research Company, Georgia Tech Research CorporationInventors: Richard Huntington, Chad C. Rasmussen, Franklin F. Mittricker, Tim Lieuwen, Sulabh K. Dhanuka, Himansh Gupta, Moses K. Minta, Loren K. Starcher
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Publication number: 20140250907Abstract: A fuel injector for a gas turbine engine may include a flow path for a fuel-air mixture extending longitudinally through the fuel injector, and a fuel gallery extending circumferentially around the flow path. The fuel gallery may be adapted to inject a liquid fuel into the flow path. The fuel injector may also include an annular casing positioned circumferentially around the fuel gallery to define an insulating chamber around the gallery. The fuel injector may also include an annular cover extending around the fuel injector to define a metering chamber. The fuel injector may further include one or more purge holes fluidly coupling the metering chamber to the insulating chamber, and one or more metering holes fluidly coupling the metering chamber to a volume exterior to the fuel injector.Type: ApplicationFiled: March 7, 2013Publication date: September 11, 2014Applicant: Solar Turbines IncorporatedInventors: Christopher Zdzislaw TWARDOCHLEB, James Gregory Roesch
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Publication number: 20140245744Abstract: Systems, devices, and methods for controlling a fuel supply for a turbine or other engine using direct and/or indirect indications of power output and optionally one or more secondary control parameters.Type: ApplicationFiled: August 15, 2013Publication date: September 4, 2014Applicant: Pratt & Whitney Canada Corp.Inventors: Brant Duke, Jim R. Jarvo, Benoit Lachance, Harris Shafique
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Publication number: 20140245745Abstract: A method for purging fuel from a fuel system of a gas turbine engine on shutdown of the engine comprises, in one aspect, terminating a fuel supply to the fuel system and using the residual compressed air to create a reversed pressure differential in the fuel system relative to a forward pressure differential of the fuel system used to maintain fuel supply for engine operation, and under the reversed pressure differential substantially purging the fuel remaining in the system therefrom to a fuel source.Type: ApplicationFiled: May 15, 2014Publication date: September 4, 2014Applicant: PRATT & WHITNEY CANADA CORP.Inventor: Kevin Allan DOOLEY
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Publication number: 20140238036Abstract: A fuel nozzle includes an inner wall defining a central passage extending in an axial direction of the fuel nozzle, a hub wall surrounding the inner wall and defining a first annular passage, an outer wall surrounding the hub wall and defining a second annular passage, and a shroud surrounding the outer wall and defining a third annular passage. A swirler may receive air and direct the air into the first annular passage. The swirler includes at least one swirl vane extending from the shroud to the hub wall that has an air passage extending between the shroud and the hub wall. The air passage is coupled to the first annular passage and has a first width adjacent the shroud and a second width adjacent the hub wall. The second width is larger than the first width defining a diverging outlet into the first annular passage.Type: ApplicationFiled: February 25, 2013Publication date: August 28, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Jong Ho Uhm, Bryan Wesley Romig, Yon Han Chong
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Publication number: 20140238037Abstract: One embodiment of the present disclosure is a unique method for operating a gas turbine engine during flight operation of the gas turbine engine in an aircraft. Another embodiment of the present disclosure is a unique gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for gas turbine engines. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.Type: ApplicationFiled: December 20, 2013Publication date: August 28, 2014Applicant: Rolls-Royce CorporationInventor: William G. Cummings, III
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Patent number: 8813504Abstract: A protocol for assembling a fuel shut off pin valve assembly for a gas turbine engine. The protocol outlines a specific sequence of events in order to ensure failsafe incorporation of a fuel shut off valve assembly within the low pressure turbine area and specifically within the engine casing of the gas turbine.Type: GrantFiled: September 30, 2010Date of Patent: August 26, 2014Assignee: Pratt & Whitney Canada Corp.Inventors: Guy Lefebvre, Claude Giardetti
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Publication number: 20140230447Abstract: A fuel nozzle for a gas turbomachine includes an outer nozzle body including an inner surface defining a mixing zone, and an inner nozzle body arranged within the outer nozzle body. The inner nozzle body includes a fluid passage. At least one flow affector extends from the inner nozzle body to the outer nozzle body. The at least one flow affector includes an inner surface that defines an interior chamber having an inlet fluidly connected to the fluid passage and at least two openings fluidically linking the interior chamber and the mixing zone. One or more flow tuning elements are arranged at the interior chamber upstream of the at least two openings. The one or more flow affectors are configured and disposed to condition a fluid passing into the interior chamber to affect a substantially iso-kinetic distribution of the fluid within the interior chamber.Type: ApplicationFiled: February 20, 2013Publication date: August 21, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Heena Vinodkumar Panchasara, Gilbert Otto Kraemer
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Publication number: 20140230449Abstract: A valve control device is provided in a gas turbine having a combustor for generating combustion gas, a turbine driven by the combustion gas generated by the combustor, a flow rate regulating valve for regulating the flow rate of the fuel to be supplied to the combustor, and a pressure regulating valve disposed upstream of the flow rate regulating valve, for regulating the fuel pressure. The valve control device controls the opening degree of the valve. The valve control device includes a load decrease detection part which detects a load decrease of the gas turbine, and a pressure control part which controls the opening degree of the valve in accordance with the output of the gas turbine. The valve control device suppresses instability of the gas turbine output even when the load rapidly decreases.Type: ApplicationFiled: November 22, 2012Publication date: August 21, 2014Applicant: Mitsubishi Hitachi Power Systems, Ltd.Inventors: Akihiko Saito, Takashi Sonoda, Takafumi Uda, Fuminori Fujii
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Publication number: 20140230448Abstract: A method for preventing flashback in a burner having swirl generator with a central fuel distributor element and an outer wall enclosing the central fuel distributor element and bounding an axial flow channel for combustion air is provided. A separating wall encloses the central fuel distributor element radially within the outer wall, wherein the axial flow channel is divided into a radially inner channel segment and a radially outer segment by the separating wall. A tangential flow component in the radially outer channel segment is provided to the combustion air flowing through the axial flow channel, wherein, during combustion, the combustion air passes the radially inner channel segment without a tangential flow component.Type: ApplicationFiled: April 28, 2014Publication date: August 21, 2014Applicant: SIEMENS AKTIENGESELLSCHAFTInventor: Michael Huth
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Patent number: 8801429Abstract: A burner arrangement is disclosed with a conical swirler in the form of a double cone which is arranged concentric to a burner axis and which encloses a swirl chamber, and with a central fuel lance which lies in the burner axis and projects from the cone point of the swirler into the swirl chamber, wherein a first stage is provided for injecting premix fuel, in which the premix fuel is injected radially outwards into the swirl chamber through injection openings which are arranged on the fuel lance, and wherein a second stage is provided for injecting premix fuel, in which the premix fuel is injected into an air flow, which is guided in the double cone, through injection openings in the double cone. With such a burner arrangement, the gas pressure which is required in the first stage is reduced by the entire premix fuel being injected into the swirl chamber in the first stage through two oppositely-disposed injection openings with increased opening diameter.Type: GrantFiled: September 29, 2008Date of Patent: August 12, 2014Assignee: Alstom Technology LtdInventors: Adnan Eroglu, Rudolf Lachner, Martin Zajadatz, James Robertson
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Patent number: 8800296Abstract: An object is to reduce a fluctuation in the gas-turbine output in a nozzle switching period. In the nozzle switching period during which a first nozzle group that has been used is switched to a second nozzle group that is going to be used, the amounts of fuel supplied through the first nozzle group and the second nozzle group are adjusted by using at least one adjustment parameter registered in advance, the adjustment parameter registered in advance is updated according to the operating condition of the gas turbine, and the updated adjustment parameter is registered as an adjustment parameter to be used next.Type: GrantFiled: December 11, 2008Date of Patent: August 12, 2014Assignee: Mitsubishi Heavy Industries, Ltd.Inventors: Makoto Kishi, Akihiko Saito, Takashi Sonoda, Shinsuke Nakamura, Sosuke Nakamura
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Publication number: 20140216050Abstract: The present application provides a combustor for use with a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles, a fuel manifold system in communication with the micro-mixer fuel nozzles to deliver a flow of fuel thereto, and a linear actuator to maneuver the micro-mixer fuel nozzles and the fuel manifold system.Type: ApplicationFiled: February 6, 2013Publication date: August 7, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Johnie Franklin McConnaughhay, Christopher Paul Keener, Thomas Edward Johnson, Heath Michael Ostebee
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Publication number: 20140216051Abstract: The present application provides a combustor for use with flow of fuel and a flow of air in a gas turbine engine. The combustor may include a number of micro-mixer fuel nozzles positioned within a liner and an air bypass system position about the liner. The air bypass system variably allows a bypass portion of the flow of air to bypass the micro-mixer fuel nozzles.Type: ApplicationFiled: February 6, 2013Publication date: August 7, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Thomas Edward Johnson, Willy Steve Ziminsky, Heath Michael Ostebee, Christopher Paul Keener
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Publication number: 20140216052Abstract: A method and device for igniting a turbomachine combustion chamber including alternately: an intake phase of a fluid into a chamber through an intake port, during which a piston compresses an elastic mechanism under pressure of the fluid such that the elastic mechanism applies onto a piezoelectric element a force sufficient for the piezoelectric element to induce between the electrodes an electric voltage enabling an electric arc to be generated, until the piston reaches a predetermined position for closing a valve for sealing the intake port; and an exhaust phase of the fluid, during which the elastic mechanism pushes back the piston to induce a fluid ejection out of the chamber through an exhaust port, and the valve is open.Type: ApplicationFiled: August 22, 2012Publication date: August 7, 2014Applicant: SNECMAInventors: Etienne Juchauld, Jean-Pierre Badinier, Jean Pierre Roberdeau, Marc Serrau
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Publication number: 20140216048Abstract: The present application provides a variable volume combustor for use with a gas turbine engine. The variable volume combustor may include a liner, a number of micro-mixer fuel nozzles positioned within the liner, and a linear actuator so as to maneuver the micro-mixer fuel nozzles axially along the liner.Type: ApplicationFiled: February 6, 2013Publication date: August 7, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Heath Michael Ostebee, Willy Steve Ziminsky, Thomas Edward Johnson, Christopher Paul Keener
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Publication number: 20140216049Abstract: The present application provides a combustor for use with a gas turbine engine. The combustor may include a number of fuel nozzles, a pre-nozzle fuel injection system supporting the fuel nozzles, and a linear actuator to maneuver the fuel nozzles and the pre-nozzle fuel injection system.Type: ApplicationFiled: February 6, 2013Publication date: August 7, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Christopher Paul Keener, Thomas Edward Johnson, Johnie Franklin McConnaughhay, Heath Michael Ostebee
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Patent number: 8794008Abstract: In a method for the low-CO emissions part load operation of a gas turbine with sequential combustion, the air ratio (?) of the operative burners (9) of the second combustor (15) is kept below a maximum air ratio (?max) at part load In order to reduce the maximum air ratio (?), a series of modifications in the operating concept of the gas turbine are carried out individually or in combination. One modification is an opening of the row of variable compressor inlet guide vanes (14) before engaging the second combustor (15). For engaging the second combustor, the row of variable compressor inlet guide vanes (14) is quickly closed and fuel is introduced in a synchronized manner into the burner (9) of the second combustor (15). A further modification is the deactivating of individual burners (9) at part load.Type: GrantFiled: April 3, 2013Date of Patent: August 5, 2014Assignee: Alstom Technology LtdInventors: Adnan Eroglu, Klaus Knapp, Peter Flohr, Hans Peter Knoepfel, Weiqun Geng
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Patent number: 8783042Abstract: A method for operating a firing plant with at least one combustion chamber and at least one burner, especially a gas turbine, includes an operating characteristic for operating the combustion chamber close to the lean extinction limit defined as a burner group staging ratio (BGVRich). Pressure pulsations (PulsActual) measured in the combustion chamber are processed by a filter device (2) and converted into corresponding signals (PulsActual,Filter(t)). An exceeding/falling short of at least one pulsation limiting value (PulsLimit) is monitored by a monitoring device (3) and adapts a pulsation reference value (PulsRef) in dependence upon the monitoring. The processed pressure pulsations (PulsActual,Filter(t)) are then compared with the adapted pulsation reference value (PulsRef,adapt), and, from this, a correction value ?BGV is determined, by which the burner group staging ratio (BGVRich) is corrected, and as a result operation of the firing plant close to the lean extinction limit is realized.Type: GrantFiled: September 12, 2012Date of Patent: July 22, 2014Assignee: Alstom Technology LtdInventors: Mauricio Garay, Gianfranco Guidati, Stanka Kokanovic, Stephan Torchalla
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Publication number: 20140196465Abstract: An apparatus and method for lean/rich combustion in a gas turbine engine (10), which includes a combustor (12), a transition (14) and a combustor extender (16) that is positioned between the combustor (12) and the transition (14) to connect the combustor (12) to the transition (14). Openings (18) are formed along an outer surface (20) of the combustor extender (16). The gas turbine (10) also includes a fuel manifold (28) to extend along the outer surface (20) of the combustor extender (16), with fuel nozzles (30) to align with the respective openings (18). A method (200) for axial stage combustion in the gas turbine engine (10) is also presented.Type: ApplicationFiled: January 11, 2013Publication date: July 17, 2014Inventors: Walter R. Laster, Peter Szedlacsek
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Publication number: 20140196466Abstract: Methods and systems for operating a gas turbine engine including a fuel delivery system and a plurality of combustor assemblies are provided. The fuel delivery system comprises a primary fuel circuit configured to continuously supply fuel to each of the plurality of combustor assemblies during a first mode of operation and a second mode of operation. At least one secondary fuel circuit of the fuel delivery system is configured to supply fuel to each of the plurality of combustor assemblies during the second mode of operation. The secondary fuel circuit includes at least one isolation valve coupled in flow communication with each of the plurality of combustor assemblies. The at least one isolation valve facilitates preventing fluid flow upstream into the secondary fuel circuit during the first mode of operation. The fuel delivery system, using the isolation valve, replaces a purging system in the gas turbine engine.Type: ApplicationFiled: January 15, 2013Publication date: July 17, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Fabien Thibault Codron, John Edward Pritchard, Stanley Kevin Widener
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Publication number: 20140196467Abstract: A mixture of air and fuel is received into a reaction chamber of a gas turbine system. The fuel is oxidized in the reaction chamber, and a maximum temperature of the mixture in the reaction chamber is controlled to be substantially at or below an inlet temperature of a turbine of the gas turbine system. The oxidation of the fuel is initiated by raising the temperature of the mixture to or above an auto-ignition temperature of the fuel. In some cases, the reaction chamber may be provided without a fuel oxidation catalyst material.Type: ApplicationFiled: March 17, 2014Publication date: July 17, 2014Applicant: ENER-CORE POWER, INC.Inventor: Edan PRABHU
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Publication number: 20140190174Abstract: A micromixer assembly for a turbine system includes a plurality of pipes each having an inlet for receiving an airflow from an annulus defined by an inwardly disposed liner and an outwardly disposed sleeve, each of the plurality of pipes also including an outlet for dispersing an air-fuel mixture into a combustor chamber. Also included is a first portion of each of the plurality of pipes. Further included is a second portion of each of the plurality of pipes, the second portion comprising the inlet for receiving the airflow. Yet further included is at least one fuel receiving path in communication with at least one of the first portion and the second portion.Type: ApplicationFiled: January 7, 2013Publication date: July 10, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Patrick Benedict Melton, Gregory Allen Boardman
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Publication number: 20140190178Abstract: A combustion method and combustor for use in a jet engine, the jet engine having a compressor portion and a turbine portion. The combustor includes an outer tube having a central axis that extends longitudinally intermediate the compressor portion and turbine portion and is positioned to receive air discharged by the compressor portion. An inner tube is positioned within the outer tube that includes an associated outer surface spaced from the inner surface of the outer tube thereby defining a combustion chamber. The outer tube and inner tube include fluid directing structure for communicating at least some of the air discharged by the compressor portion to the combustion chamber. The fluid directing structure directs air into the combustion chamber in a direction offset from the central axis, thereby causing rotation or swirling of the air about the central axis.Type: ApplicationFiled: August 10, 2012Publication date: July 10, 2014Applicant: BECKETT GAS, INC.Inventor: Michael J. O'Donnell
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Publication number: 20140190175Abstract: A combustor liner with an input end and an output end includes an annular inner wall and an annular outer wall. At least one of the inner wall and outer wall is three-dimensionally contoured. The inner wall and the outer wall form a combustion chamber with the contours creating alternating expanding and constricting regions inside the chamber causing combustion gases to flow in the circumferential and axial directions.Type: ApplicationFiled: March 10, 2014Publication date: July 10, 2014Applicant: United Technologies CorporationInventors: Joel H. Wagner, Paul M. Lutjen
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Publication number: 20140190176Abstract: A fuel control method for a gas turbine with a combustor being formed of at least two groups of a pluralities of main nozzles for supplying fuel, and that supplies fuel from the main nozzles of all groups upon ignition of the combustor (S1), and supplies fuel from three main nozzles of a group A during subsequent acceleration of the gas turbine (S3). Because fuel is injected from a small number of the main nozzles during acceleration, the fuel flow rate per one main nozzle is increased, thereby increasing the fuel-air ratio (fuel flow rate/air flow rate) in a combustion region and improving the combustion characteristics. Accordingly, the generation of carbon monoxide and unburned hydrocarbon is reduced, whereby no bypass valve is required and manufacturing costs are reduced.Type: ApplicationFiled: March 10, 2014Publication date: July 10, 2014Applicant: MITSUBISHI HEAVY INDUSTRIES, LTD.Inventors: Sosuke NAKAMURA, Satoshi TANIMURA, Shinji AKAMATSU, Shinsuke NAKAMURA, Takashi SONODA, Akihiko SAITO, Makoto KISHI
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Publication number: 20140190177Abstract: A method for running up a stationary gas turbine is provided. The turbine has a combustion chamber, the burners of which have a pilot burner and a main burner and by which various types of fuel are introduced into the combustion chamber for burning. The method, carried out while a rotor of the gas turbine is accelerating from a standstill to a nominal speed, includes feeding fuel of a first type of fuel to the pilot burners and feeding fuel of the first type of fuel to the main burners. In order to provide a method in which a comparatively low supply pressure is required in the fuel supply system and in which combustion vibrations that put the machine at risk are avoided during the running-up process, it is proposed that fuel of a second type of fuel is fed to the burner before the nominal speed is reached.Type: ApplicationFiled: July 25, 2012Publication date: July 10, 2014Applicant: SIEMENS AKTIENGESELLSCHAFTInventors: Eberhard Deuker, Berthold Kostlin, Jurgen Meisl, Dennis Nehlsen, Kai-Uwe Schildmacher
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Patent number: 8763401Abstract: There is provided an integrated fuel nozzle and ignition assembly for a gas turbine engine comprising a body having a fuel nozzle portion and an igniter portion. The fuel nozzle portion defines a fuel passage extending therethrough between a fuel inlet and a fuel outlet for directing a fuel flow into a combustion chamber. The igniter portion projects laterally from the fuel nozzle portion on a side thereof and comprises an igniter receiving cavity positioned adjacently and laterally on a side of the fuel passage. The assembly further comprises an igniter secured in the igniter receiving cavity for igniting the fuel flow discharged by the fuel passage.Type: GrantFiled: May 30, 2011Date of Patent: July 1, 2014Assignee: Pratt & Whitney Canada Corp.Inventors: Bhawan B. Patel, Enzo Macchia, Oleg Morenko, George Guglielmin
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Patent number: 8763405Abstract: A rotary injector (95, 222) comprising one or more radially-extending arms (93) provides for injecting fuel (12, 12.1, 12.4) into a combustion chamber (16). The combustion chamber (16) receives air (14) from locations upstream and down-stream of the rotary injector (95, 222), and the arms (93) of the rotary injector (95, 222) are adapted so that a pressure (P2) in the combustion chamber (16) upstream of the rotary injector (95, 222) is less than a pressure (P0) in a plenum (212) supplying air (14) to the combustion chamber (16) upstream of the rotary injector (95, 222).Type: GrantFiled: April 9, 2009Date of Patent: July 1, 2014Assignee: Williams International Co., L.L.C.Inventors: John Sordyl, Jamey J. Condevaux
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Publication number: 20140174096Abstract: An arrangement for injection of an emulsion of a first fluid and a second fluid into a flame of a burner has a central gas duct, an outer gas channel disposed coaxially with the gas duct, and a fluid channel disposed coaxially between the gas duct and the outer gas channel The central gas duct and the fluid channel are separated by a first frustoconical wall. The fluid channel and the outer gas channel are separated by a second frustoconical wall. The arrangement is mounted concentrically surrounding a heat source which provides through the gas duct hot gases being directed into the flame of the burner. Further, the arrangement includes a mixing device for forming an emulsion of the first fluid and the second fluid, for supplying the emulsion into the fluid channel and for injecting the emulsion from the fluid channel into the flame.Type: ApplicationFiled: September 20, 2011Publication date: June 26, 2014Inventor: Vladimir Dusan Milosavljevic
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Publication number: 20140165583Abstract: In one aspect, the present disclosure is directed to a method for controlling a position of a bleed valve of a gas turbine engine. The onset of an off-load transient may be determined. Values representative of the turbine rotor inlet temperature and the exhaust outlet temperature may be determined. Also, the amount of time elapsed since the onset of the off-load transient may be determined. Three provisional bleed valve command positions may be determined based on value representative of the turbine rotor inlet temperature, the value representative of the exhaust outlet temperature, and the amount of time elapsed, respectively. The provisional bleed valve command position associated with the lowest relative value may be selected. Then, the bleed valve position may be adjusted to match the selected bleed valve command position.Type: ApplicationFiled: December 14, 2012Publication date: June 19, 2014Applicant: SOLAR TURBINES INCORPORATEDInventor: Fabrizio Oliverio
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Publication number: 20140165584Abstract: A system for converting liquid fuel into gaseous fuel is provided. The system may have a supply of liquid fuel. The system may also have a combustor, and one or more pumps in fluid communication with the supply. The one or more pumps may be configured to pump liquid fuel from the supply into the combustor. The system may also have a compressor in fluid communication with an inlet of the combustor, and a turbine in fluid communication with an outlet of the combustor. The turbine may be connected to drive the compressor and the one or more pumps. The system may also have a heat exchanger in fluid communication with an outlet of the turbine and an outlet of the one or more pumps.Type: ApplicationFiled: December 14, 2012Publication date: June 19, 2014Inventor: Aaron Foege
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Publication number: 20140165585Abstract: In accordance with one aspect of the disclosure, a swirler is disclosed. The swirler may include an outer shroud and inner shroud. The inner shroud may be positioned radially inside the outer shroud. At least one of the outer shroud and inner shroud may have a major diameter which is larger than a minor diameter such that the shrouds define an oblong shape. The swirler may further include a plurality of vanes which may be positioned between the inner and outer shrouds.Type: ApplicationFiled: December 17, 2012Publication date: June 19, 2014Applicant: United Technologies CorporationInventor: Steven W. Burd
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Publication number: 20140157787Abstract: A gas turbine system includes a fuel nozzle. The fuel nozzle includes a first fluid conduit defining an oxidant passage, a second fluid conduit defining a first fuel passage, and a third fluid conduit surrounding the second fluid conduit and defining a second fuel passage. A first orifice is disposed on the second fluid conduit and is configured to fluidly couple the first fuel passage to the oxidant passage. A second orifice is disposed on the third fluid conduit and is configured to fluidly couple the second fuel passage to the oxidant passage. A first diameter of the first orifice is less than a second diameter of the second orifice.Type: ApplicationFiled: December 6, 2012Publication date: June 12, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Mahesh Bathina, Madanmohan Manoharan, Stephen Robert Thomas
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Publication number: 20140157788Abstract: A gas turbine system includes a fuel nozzle. The fuel nozzle has a first wall extending along an axis and defines a first fluid passage. A second wall surrounds the first wall and defines a second fluid passage. A third wall surrounds the second wall and defines a third fluid passage. The first and second fluid passages are configured to collectively direct a flow of air and fuel into a combustion region to produce a flame. The third fluid passage is configured to direct a diluent into the combustion region to adjust a combustion parameter of the flame.Type: ApplicationFiled: December 6, 2012Publication date: June 12, 2014Applicant: GENERAL ELECTRIC COMPANYInventor: Mahesh Bathina
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Publication number: 20140150445Abstract: A system is provided with a turbine combustor having a first diffusion fuel nozzle, wherein the first diffusion fuel nozzle is configured to produce a diffusion flame. The system includes a turbine driven by combustion products from the diffusion flame in the turbine combustor. The system also includes an exhaust gas compressor, wherein the exhaust gas compressor is configured to compress and route an exhaust gas from the turbine to the turbine combustor along an exhaust recirculation path.Type: ApplicationFiled: October 30, 2013Publication date: June 5, 2014Applicants: ExxonMobil Upstream Research Company, General Electric CompanyInventors: Richard A. Huntington, Sulabh K. Dhanuka, Ilya Aleksandrovich Slobodyanskiy
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Publication number: 20140150444Abstract: In some implementations, a system may include a compressor, a heat exchanger and an ITM. The compressor is configured to receive an air stream and compress the air stream to generate a pressurized stream. The heat exchanger is configured to receive the pressured stream and indirectly heat the pressurized stream using heat from an oxygen stream from an Ion Transport Membrane (ITM). The ITM is configured to receive the heated pressurized stream and generate an oxygen stream and the non-permeate stream, wherein the non-permeate stream is passed to a gas turbine burner and the oxygen stream is passed to the heat exchanger.Type: ApplicationFiled: May 31, 2013Publication date: June 5, 2014Applicant: GTLPETROL, LLCInventor: Rodney J. Allam
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Publication number: 20140144153Abstract: A system and method control a gas turbine subject to fuel composition variation. The method includes operating a first effector to control the gas turbine based on fuel composition. The method also includes operating a second effector to maintain operation of the first effector within a first boundary limit, the second effector operation being initiated when the operating the first effector reaches a second boundary limit within the first boundary limit.Type: ApplicationFiled: November 27, 2012Publication date: May 29, 2014Applicant: GENERAL ELECTRIC COMPANYInventor: Timothy Andrew Healy
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Publication number: 20140144152Abstract: A premixer includes an air tube formed in a burner tube defining a longitudinal axis, and a coaxially disposed fuel tube with a turbulence enhancing chevron outlet. The fuel tube may include an exterior tube and an interior tube with the interior tube, the exterior tube or both having chevron outlets. The chevron outlets may be tapered and notched.Type: ApplicationFiled: November 26, 2012Publication date: May 29, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Jong Ho Uhm, Thomas Edward Johnson, Baifang Zuo, Christian Xavier Stevenson
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Patent number: 8733108Abstract: The present application provides for a combustor for use with a gas turbine engine. The combustor may include a cap member and a number of fuel nozzles extending through the cap member. One or more of the fuel nozzles may be provided in a non-flush position with respect to the cap member.Type: GrantFiled: July 9, 2010Date of Patent: May 27, 2014Assignee: General Electric CompanyInventors: Kwanwoo Kim, Thomas Edward Johnson, Jong Ho Uhm, Gilbert Otto Kraemer