Patents by Inventor Warren James Mick
Warren James Mick has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 7461509Abstract: A method for determining a lean blow out condition for a combustor. In an exemplary embodiment, the method includes determining acoustical frequency data for the combustor, determining a combustor flame temperature based on the acoustical frequency data, determining an existing fuel/air ratio in the combustor based on the combustor flame temperature, and comparing the existing fuel/ratio to a lean blow out fuel/air ratio. A lean blow out condition for the combustor is indicated when the existing fuel/air ratio is about equal to the lean blow out fuel/air ratio.Type: GrantFiled: May 6, 2005Date of Patent: December 9, 2008Assignee: General Electric CompanyInventors: Warren James Mick, George Edward Williams, Fei Han, Eamon Patrick Gleeson, Shiva Srinivasan, Scott Alan Kopcho, Ilan Leibu
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Patent number: 7457688Abstract: A method for transient fuel control for fuel delivery circuits for a plurality of connected gas turbines, the method includes: detecting a transient grid event based on an indication of at least one of a rapid change in a fuel command to the gas turbine or an acceleration of the turbine shaft; upon detection of the transient grid event, commanding a gas turbine controller to transfer the gas turbine to at least one intermediate load; adjusting a fuel split to maintain combustor stability during the transient grid event, and using a predetermined island load demand signal to apportion an island load demand among the connected gas turbine generators.Type: GrantFiled: September 19, 2006Date of Patent: November 25, 2008Assignee: General Electric CompanyInventors: Scott William Szepek, John Michael Undrill, Michael Joseph Alexander, Warren James Mick
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Patent number: 7441411Abstract: A method for determining when a combustor is experiencing hardware damage includes sensing acoustic vibrations of a plurality of combustor cans, determining a center frequency for each acoustic tone of the sensed acoustic vibrations within a predetermined frequency range, and indicating an alarm when a center frequency of one or more of the combustor cans changes in a different manner compared to a representative center frequency of the plurality of combustor cans.Type: GrantFiled: September 16, 2005Date of Patent: October 28, 2008Assignee: General Electric CompanyInventors: Eamon Patrick Gleeson, Warren James Mick, George Edward Williams, Fei Han, Shivakumar Srinivasan, Scott Alan Kopcho, Ilan Leibu
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Publication number: 20080071427Abstract: A method for transient fuel control for fuel delivery circuits for a plurality of connected gas turbines, the method includes: detecting a transient grid event based on an indication of at least one of a rapid change in a fuel command to the gas turbine or an acceleration of the turbine shaft; upon detection of the transient grid event, commanding a gas turbine controller to transfer the gas turbine to at least one intermediate load; adjusting a fuel split to maintain combustor stability during the transient grid event, and using a predetermined island load demand signal to apportion an island load demand among the connected gas turbine generators.Type: ApplicationFiled: September 19, 2006Publication date: March 20, 2008Applicant: General Electric CompanyInventors: Scott William Szepek, John Michael Undrill, Michael Joseph Alexander, Warren James Mick
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Patent number: 7104070Abstract: In a gas turbine having a compressor, a combustor and a turbine, a gaseous fuel supply coupled to provide gaseous fuel to the combustor, a liquid fuel supply coupled to provide liquid fuel to the combustor via nozzle assembly. The nozzle assembly includes a plurality of passageways for flowing a fluid into the combustor, one of the passageways being an atomizing air passageway conduit interconnecting the atomizing air passageway to one of the plurality of passageways to enable fluid flow therebetween, while not allowing the flow of fluid back into the atomizing air passageway. High pressure air from the atomizing air passageway is diverted into one of the plurality of passageways via the conduit to protect the nozzle from ingestion of hot combustor gases, thus eliminating a need for a dedicated air purge system for that one of the plurality of passageways.Type: GrantFiled: March 4, 2004Date of Patent: September 12, 2006Assignee: General Electric CompanyInventors: Robert J. Iasillo, Warren James Mick
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Patent number: 6979118Abstract: A method of determining the temperature inside a combustion liner without making a direct measurement of the actual temperature. The technique is based on a measurement of the frequency of one of the transverse acoustic modes occurring inside the combustion chamber. The frequency is determined from the transverse geometric dimensions of the combustion chamber and the speed of sound in the gas inside the combustion chamber. The speed of sound in the gas is known from thermodynamics to be a function of gas temperature and gas properties. Thus, from a measurement of the resonant frequency and knowing the combustor dimensions and gas properties, the temperature can be determined with accuracy.Type: GrantFiled: June 1, 2004Date of Patent: December 27, 2005Assignee: General Electric CompanyInventors: Warren James Mick, Eamon P. Gleeson, Willy Steve Ziminsky, Aparna Basker, Fei Han
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Patent number: 6609380Abstract: In a gas turbine having a compressor, a combustor and a turbine, a gaseous fuel supply coupled to provide gaseous fuel to the combustor, a liquid fuel supply coupled to provide liquid fuel to the combustor via nozzle assembly. The nozzle assembly includes a plurality of passageways for flowing a fluid into the combustor, one of the passageways being a fuel passageway conduit interconnect the fuel passageway to one of the plurality of passageways to enable fluid flow therebetween. High pressure air from one of the plurality of passageways is diverted into the fuel passageway via the conduit to protect nozzle from ingestion of hot combustor gases.Type: GrantFiled: December 28, 2001Date of Patent: August 26, 2003Assignee: General Electric CompanyInventors: Warren James Mick, Urmila Chennuru Reddy, Robert Joseph Iasillo
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Publication number: 20030121269Abstract: In a gas turbine having a compressor, a combustor and a turbine, a gaseous fuel supply coupled to provide gaseous fuel to the combustor, a liquid fuel supply coupled to provide liquid fuel to the combustor via nozzle assembly. The nozzle assembly includes a plurality of passageways for flowing a fluid into the combustor, one of the passageways being a fuel passageway conduit interconnect the fuel passageway to one of the plurality of passageways to enable fluid flow therebetween. High pressure air from one of the plurality of passageways is diverted into the fuel passageway via the conduit to protect nozzle from ingestion of hot combustor gases.Type: ApplicationFiled: December 28, 2001Publication date: July 3, 2003Inventors: Warren James Mick, Urmila Chennuru Reddy, Robert Joseph Iasillo
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Patent number: 6250063Abstract: Each combustor for a gas turbine includes a fuel supply line for supplying fuel to a plurality of nozzles in the combustor. A remotely controlled valve has a valve member movable between valve-open and valve-closed positions. In a valve-closed position, fuel is supplied to a first group of one or more nozzles of the combustor, while fuel is cut off to a second group of one or more nozzles of the combustor. In a valve-open position, fuel is supplied to all nozzles of the combustor. By positively and selectively actuating the valve, the fuel/air ratio of the nozzles supplied by the fuel is increased to enhance flame stability.Type: GrantFiled: August 19, 1999Date of Patent: June 26, 2001Assignee: General Electric Co.Inventors: Lewis Berkley Davis, Jr., David Justin Balevic, Ronald Joseph Beaudoin, Warren James Mick
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Patent number: 6089025Abstract: A combustor assembly comprises a plurality of circumferentially arranged fuel nozzles, which fuel nozzles have a first end coupled to a combustion chamber and a second end attached to an endcover. The plurality of fuel nozzles define a central region therebetween. A baffle is disposed within the central region. The baffle has an upstream base portion adjacent the endcover and a contoured downstream portion having a width that is smaller with respect to a width of the upstream base portion so as to transition a recirculating flow into a downstream flow to minimize flashback occurrences within the central region.Type: GrantFiled: August 24, 1998Date of Patent: July 18, 2000Assignee: General Electric CompanyInventors: Prabhat Kumar Tekriwal, Lewis Berkley Davis, Jr., Warren James Mick
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Patent number: 5713205Abstract: A liquid fuel injector nozzle for a gas turbine combustor delivers liquid fuel to the combustion chamber in discrete jets. The liquid fuel injector nozzle includes a fuel passage that terminates with a swirl pilot including a plurality of swirl slots for imparting swirl to the liquid fuel. The spin chamber disposed downstream of the swirl pilot is configured to deliver the liquid fuel to the discharge orifice in discrete jets. The discrete fuel streams are concentrated in a fashion to minimize atomization until the fuel adequately penetrates the premixer air stream, resulting in burning properties that lead to increased efficiency, lower emissions, greater flame stability and improved pattern factor when compared to hollow cone spray pattern injection techniques.Type: GrantFiled: August 6, 1996Date of Patent: February 3, 1998Assignee: General Electric Co.Inventors: Michael Bruce Sciocchetti, Warren James Mick, Mitchell Reuben Cohen, William Theodore Bechtel, II