Patents by Inventor Derrick Simons
Derrick Simons 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: 9297315Abstract: Embodiments of the invention can provide systems and methods for determining a target exhaust temperature for gas turbines. In one embodiment of the disclosure, there is disclosed a method for determining a target exhaust temperature for a gas turbine. The method can include determining a target exhaust temperature based at least in part on a compressor pressure condition; determining a temperature adjustment to the target exhaust temperature based at least in part on steam humidity; and changing the target exhaust temperature based at least in part on the temperature adjustment.Type: GrantFiled: September 28, 2012Date of Patent: March 29, 2016Assignee: General Electric CompanyInventors: Derrick Simons, Douglas Dean, Carey Romoser, Kevin Wilkes, Predrag Popovic, Abhijit Kulkarni
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Patent number: 9140189Abstract: Embodiments can provide systems and methods for detecting fuel leaks in gas turbine engines. According to one embodiment, there is disclosed a method for detecting a fuel leak in a gas turbine engine. The method may include adjusting a control valve to correspond with a desired fuel flow. The method may also include determining an actual fuel flow based at least in part on an upstream pressure in a fuel manifold and one or more gas turbine engine parameters. The method may also include comparing the desired fuel flow with the actual fuel flow. Moreover, the method may include determining a difference between the desired fuel flow and the actual fuel flow, wherein the difference indicates a fuel leak.Type: GrantFiled: April 11, 2012Date of Patent: September 22, 2015Assignee: General Electric CompanyInventors: Bryan Wesley Romig, Derrick Simons, Douglas Dean
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Publication number: 20140090353Abstract: Embodiments of the invention can provide systems and methods for determining a target exhaust temperature for gas turbines. In one embodiment of the disclosure, there is disclosed a method for determining a target exhaust temperature for a gas turbine. The method can include determining a target exhaust temperature based at least in part on a compressor pressure condition; determining a temperature adjustment to the target exhaust temperature based at least in part on steam humidity; and changing the target exhaust temperature based at least in part on the temperature adjustment.Type: ApplicationFiled: September 28, 2012Publication date: April 3, 2014Applicant: General Electric CompanyInventors: Derrick Simons, Douglas Dean, Carey Romoser, Kevin Wilkes, Predrag Popovic, Abhijit Kulkarni
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Publication number: 20130269364Abstract: Embodiments can provide systems and methods for detecting fuel leaks in gas turbine engines. According to one embodiment, there is disclosed a method for detecting a fuel leak in a gas turbine engine. The method may include adjusting a control valve to correspond with a desired fuel flow. The method may also include determining an actual fuel flow based at least in part on an upstream pressure in a fuel manifold and one or more gas turbine engine parameters. The method may also include comparing the desired fuel flow with the actual fuel flow. Moreover, the method may include determining a difference between the desired fuel flow and the actual fuel flow, wherein the difference indicates a fuel leak.Type: ApplicationFiled: April 11, 2012Publication date: October 17, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Bryan Wesley Romig, Derrick Simons, Douglas Dean
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Patent number: 8371101Abstract: A combustor may include an interior flow path therethrough, a number of fuel nozzles in communication with the interior flow path, and an inlet guide vane system positioned about the interior flow path to create a swirled flow therein. The inlet guide vane system may include a number of windows positioned circumferentially around the fuel nozzles. The inlet guide vane system may also include a number of inlet guide vanes positioned circumferentially around the fuel nozzles and adjacent to the windows to create a swirled flow within the interior flow path.Type: GrantFiled: September 15, 2009Date of Patent: February 12, 2013Assignee: General Electric CompanyInventors: Baifang Zuo, Derrick Simons, William York, Willy S. Ziminsky
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Publication number: 20110061389Abstract: The present application thus provides a combustor. The combustor may include an interior flow path therethrough, a number of nozzles in communication with the interior flow path, and an inlet guide vane system positioned about the interior flow path to create a swirled flow therein.Type: ApplicationFiled: September 15, 2009Publication date: March 17, 2011Applicant: General Electric CompanyInventors: Baifang Zuo, Derrick Simons, William York, Willy S. Ziminsky
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Patent number: 7854121Abstract: Disclosed herein is a fuel nozzle. The fuel nozzle includes a first fuel introduction location, a second fuel introduction location, and fuel passages. The first fuel introduction location is located radially about the fuel nozzle and is connected with a fuel passage. The second fuel introduction location is located at an end of the fuel nozzle and is connected with another fuel passage such that the fuel passage connected to the first fuel introduction location is separate from the fuel passage connected to the second fuel introduction location.Type: GrantFiled: December 12, 2005Date of Patent: December 21, 2010Assignee: General Electric CompanyInventors: Daniel D. Vandale, Derrick Simons, Alberto Jose Negroni, Carey Romoser
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Patent number: 7320213Abstract: A system for ranking combustion chambers in a gas turbine in order of chamber combustion temperature including: at least one fuel nozzle supplying fuel to the combustion chambers at a predetermined fuel rate abnormally near a lean blow out (LBO) condition of the chambers; at least one dynamic pressure sensor in each chamber sensing combustion dynamic pressures in said combustion chambers and generating dynamic pressure signals representative of the dynamic pressure in each of said combustion chambers, wherein the dynamic pressure signals provide information regarding the dynamic pressure at a plurality of frequencies; a signal band pass filter segmenting the signals into a plurality of predefined frequency bands comprising a lean blow out (LBO) precursor frequency band, a cold tone frequency band and a hot tone frequency band; a processor determining a value for each chamber representative of amplitudes of the signals in each of LBO precursor frequency band, the cold tone frequency band and the hot tone frequType: GrantFiled: April 30, 2007Date of Patent: January 22, 2008Assignee: General Electric CompanyInventors: Minesh Ashok Shah, Ajai Singh, Willy Steve Ziminsky, Derrick Simons
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Publication number: 20070199328Abstract: A system for ranking combustion chambers in a gas turbine in order of chamber combustion temperature including: at least one fuel nozzle supplying fuel to the combustion chambers at a predetermined fuel rate abnormally near a lean blow out (LBO) condition of the chambers; at least one dynamic pressure sensor in each chamber sensing combustion dynamic pressures in said combustion chambers and generating dynamic pressure signals representative of the dynamic pressure in each of said combustion chambers, wherein the dynamic pressure signals provide information regarding the dynamic pressure at a plurality of frequencies; a signal band pass filter segmenting the signals into a plurality of predefined frequency bands comprising a lean blow out (LBO) precursor frequency band, a cold tone frequency band and a hot tone frequency band; a processor determining a value for each chamber representative of amplitudes of the signals in each of LBO precursor frequency band, the cold tone frequency band and the hot tone frequType: ApplicationFiled: April 30, 2007Publication date: August 30, 2007Applicant: GENERAL ELECTRIC COMPANYInventors: Minesh SHAH, Ajai SINGH, Willy ZIMINSKY, Derrick SIMONS
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Publication number: 20070157620Abstract: A method for determining a target exhaust temperature for a gas turbine including: determining a target exhaust temperature based on a compressor pressure condition; determining a temperature adjustment to the target exhaust temperature based on at least one parameter of a group of parameters consisting of specific humidity, compressor inlet pressure loss and turbine exhaust back pressure; and adjusting the target exhaust temperature by applying the temperature adjustment.Type: ApplicationFiled: March 16, 2007Publication date: July 12, 2007Applicant: GENERAL ELECTRIC COMPANYInventors: Timothy Healy, Derrick Simons
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Publication number: 20070130955Abstract: Disclosed herein is a fuel nozzle. The fuel nozzle includes a first fuel introduction location, a second fuel introduction location, and fuel passages. The first fuel introduction location is located radially about the fuel nozzle and is connected with a fuel passage. The second fuel introduction location is located at an end of the fuel nozzle and is connected with another fuel passage such that the fuel passage connected to the first fuel introduction location is separate from the fuel passage connected to the second fuel introduction location.Type: ApplicationFiled: December 12, 2005Publication date: June 14, 2007Inventors: Daniel Vandale, Derrick Simons, Alberto Negroni, Carey Romoser
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Patent number: 7210297Abstract: A method for identifying combustion characteristics of a plurality combustion chambers in a gas turbine, the method including: supplying fuel to the combustion chambers at a predetermined fuel rate; sensing combustion dynamic pressure in said plurality of combustion chambers and generating dynamic pressure signals representative of the dynamic pressure in each of said combustion chambers, wherein the dynamic pressure signals provide information regarding the dynamic pressure at a plurality of frequencies; segmenting the signals into a plurality of predefined frequency bands; determining a characteristic value for each of the segmented signals, and identifying an order of combustion chambers based on the characteristic value.Type: GrantFiled: November 4, 2004Date of Patent: May 1, 2007Assignee: General Electric CompanyInventors: Minesh Ashok Shah, Ajai Singh, Willy Steve Ziminsky, Derrick Simons
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Publication number: 20060288706Abstract: A method for combustion in a combustor in a gas turbine including: fueling the center fuel nozzle with a fuel-rich mixture of gaseous fuel and air and fueling the outer fuel nozzles with a fuel-lean mixture of fuel and air; igniting the fuel-rich mixture injected by the center fuel nozzle while the fuel-lean mixture injected by the outer combustors is insufficient to sustain ignition; stabilizing a flame on the center fuel nozzle using the bluff body and while the outer fuel nozzles inject the fuel-lean mixture; staging fuel to the outer nozzles by increasing a fuel ratio of the fuel-lean mixture, and after the outer nozzles sustain ignition, reducing fuel applied to the center nozzle.Type: ApplicationFiled: August 31, 2006Publication date: December 28, 2006Applicant: General Electric CompanyInventors: Willy Ziminsky, Derrick Simons, Arthur Fossum
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Publication number: 20060168967Abstract: A double wall venturi chamber having a converging section, a diverging section and a cylindrical section wherein said chamber defines a venturi zone in which compressed air, fuel and combustion products flow downstream through converging section, diverging section and cylindrical section, and has a cooling gas passage between the walls of the venturi chamber, a least one cooling gas inlet in an outlet wall of the venturi chamber, and at least one cooling gas outlet in an inner wall of the venturi chamber, wherein said cooling gas outlet is in at least one of the diverging and the cylindrical section, and the outlet is downstream of the at least one cooling gas inlet and upstream of an axial end of the chamber.Type: ApplicationFiled: January 31, 2005Publication date: August 3, 2006Applicant: General Electric CompanyInventors: Derrick Simons, Thomas Amond, Ajay Gupta
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Publication number: 20060090471Abstract: A method for identifying combustion characteristics of a plurality combustion chambers in a gas turbine, the method including: supplying fuel to the combustion chambers at a predetermined fuel rate; sensing combustion dynamic pressure in said plurality of combustion chambers and generating dynamic pressure signals representative of the dynamic pressure in each of said combustion chambers, wherein the dynamic pressure signals provide information regarding the dynamic pressure at a plurality of frequencies; segmenting the signals into a plurality of predefined frequency bands; determining a characteristic value for each of the segmented signals, and identifying an order of combustion chambers based on the characteristic value.Type: ApplicationFiled: November 4, 2004Publication date: May 4, 2006Applicant: General Electric CompanyInventors: Minesh Shah, Ajai Singh, Willy Ziminsky, Derrick Simons
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Publication number: 20050223713Abstract: A single stage combustor for a gas turbine having an annular array of outer fuel nozzles arranged about a center axis of the combustor; a center fuel nozzle aligned with the center axis, wherein the center fuel nozzle is substantially smaller than each of the outer fuel nozzles, wherein the combustor includes a pre-mix operating mode in which the center nozzle receives a fuel rich air-fuel mixture.Type: ApplicationFiled: April 12, 2004Publication date: October 13, 2005Applicant: General Electric CompanyInventors: Willy Ziminsky, Derrick Simons, Arthur Fossum
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Publication number: 20050204741Abstract: A transition piece body, having an inlet end for receiving combustion products from a turbine combustor and an outlet end for flowing the gaseous products into a first stage nozzle, has dilution holes in zones respectively adjacent the transition piece body inlet and outlet ends. The volume of dilution air flowing into the gas stream is substantially equal at the inlet and outlet ends of the transition piece. The locations and sizes of the openings are given in the respective X, Y, Z coordinates and hole diameters in Table I. The X and Y coordinates lie in the circular plane of the transition body at its inlet end and the Z coordinates extend in the direction of gas flow from the origin.Type: ApplicationFiled: March 17, 2004Publication date: September 22, 2005Applicant: General Electric CompanyInventors: Derrick Simons, Aja Gupta, Carey Romoser
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Publication number: 20050114010Abstract: A method for determining a target exhaust temperature for a gas turbine including: determining a target exhaust temperature based on a compressor pressure condition; determining a temperature adjustment to the target exhaust temperature based on at least one parameter of a group of parameters consisting of specific humidity, compressor inlet pressure loss and turbine exhaust back pressure; and adjusting the target exhaust temperature by applying the temperature adjustment.Type: ApplicationFiled: November 20, 2003Publication date: May 26, 2005Applicant: General Electric CompanyInventors: Timothy Healy, Derrick Simons