Patents by Inventor Thomas Scarinci
Thomas Scarinci 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: 11125437Abstract: A method for staging premixers in a combustion system for a gas turbine having a compressor section and a turbine section. The method includes providing a plurality of burners each including premixers wherein compressed air from the compressor section is provided to the premixers. The method also includes providing a plurality of fuel circuits that deliver fuel to the premixers to provide premixed air and fuel used for combustion in the combustion system. In addition, the method includes associating premixers with each fuel circuit in accordance with a power of base two pattern. Further, the method includes activating or deactivating the premixers in stages by activating or deactivating an associated fuel circuit to deliver fuel or stop fuel delivery, respectively, to the premixers wherein a staging step size between consecutive stages is in accordance with a power of base two staging scheme.Type: GrantFiled: May 16, 2017Date of Patent: September 21, 2021Assignee: SIEMENS ENERGY GLOBAL GMBH & CO. KGInventors: Marc Furi, Matthew Engelhardt, Fabian Enrique Sanchez, Thomas Scarinci
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Publication number: 20200103115Abstract: A method for staging premixers in a combustion system for a gas turbine having a compressor section and a turbine section. The method includes providing a plurality of burners each including premixers wherein compressed air from the compressor section is provided to the premixers. The method also includes providing a plurality of fuel circuits that deliver fuel to the premixers to provide premixed air and fuel used for combustion in the combustion system. In addition, the method includes associating premixers with each fuel circuit in accordance with a power of base two pattern. Further, the method includes activating or deactivating the premixers in stages by activating or deactivating an associated fuel circuit to deliver fuel or stop fuel delivery, respectively, to the premixers wherein a staging step size between consecutive stages is in accordance with a power of base two staging scheme.Type: ApplicationFiled: May 16, 2017Publication date: April 2, 2020Inventors: Marc Furi, Matthew Engelhardt, Fabian Enrique Sanchez, Thomas Scarinci
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Patent number: 9534789Abstract: A gas turbine engine combustion system including a mixing duct that separates into at least two branch passages for the delivery of a fuel and working fluid to distinct locations within a combustion chamber. The residence time for the fuel and working fluid within each of the two branch passages is distinct.Type: GrantFiled: May 9, 2014Date of Patent: January 3, 2017Assignee: INDUSTRIAL TURBINE COMPANY (UK) LIMITEDInventor: Thomas Scarinci
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Patent number: 8881531Abstract: One embodiment is a gas turbine engine premix injector including a mixing duct, a plurality of air inlet slots leading to the duct, a plurality of gaseous fuel inlet apertures leading to the duct, a plurality of vanes positioned in the duct downstream from said air inlets, a plurality of liquid fuel inlet apertures leading to the duct, and a plurality of discharge windows positioned between the vanes.Type: GrantFiled: December 14, 2006Date of Patent: November 11, 2014Assignee: Rolls-Royce Power Engineering PlcInventors: Thomas Scarinci, Kenneth James Young
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Publication number: 20140283525Abstract: A gas turbine engine combustion system including a mixing duct that separates into at least two branch passages for the delivery of a fuel and working fluid to distinct locations within a combustion chamber. The residence time for the fuel and working fluid within each of the two branch passages is distinct.Type: ApplicationFiled: May 9, 2014Publication date: September 25, 2014Applicant: Rolls-Royce Canada, Ltd.Inventor: Thomas Scarinci
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Patent number: 7841181Abstract: One embodiment is a unique gas turbine engine combustion chamber including primary and secondary burning zones. Other embodiments include unique gas turbine engine apparatuses, systems, methods, and combinations.Type: GrantFiled: July 19, 2007Date of Patent: November 30, 2010Assignee: Rolls-Royce Power Engineering plcInventors: Thomas Scarinci, Anthony John Moran, Lynn Ivor Thomas Steward, Bryn Jones
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Patent number: 7722316Abstract: An acoustic viscous damper for a compressor including a porous liner located within the discharge duct, the porous liner having a plurality of holes for passage of a purge working fluid therethrough into the discharge duct.Type: GrantFiled: September 13, 2006Date of Patent: May 25, 2010Assignee: Rolls-Royce Power Engineering PLCInventors: Thomas Scarinci, Mohammed Jalal Uddin, Robert Meier
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Publication number: 20100034634Abstract: An acoustic viscous damper for a compressor including a porous liner located within the discharge duct, the porous liner having a plurality of holes for passage of a purge working fluid therethrough into the discharge duct.Type: ApplicationFiled: September 13, 2006Publication date: February 11, 2010Inventors: Thomas Scarinci, Mohammed Jalal Uddin, Robert Meier
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Publication number: 20080006033Abstract: One embodiment is a unique gas turbine engine combustion chamber including primary and secondary burning zones. Other embodiments include unique gas turbine engine apparatuses, systems, methods, and combinations.Type: ApplicationFiled: July 19, 2007Publication date: January 10, 2008Inventors: Thomas Scarinci, Anthony Moran, Lynn Ivor Steward, Bryn Jones
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Publication number: 20070151248Abstract: One embodiment is a gas turbine engine premix injector including a mixing duct, a plurality of air inlet slots leading to the duct, a plurality of gaseous fuel inlet apertures leading to the duct, a plurality of vanes positioned in the duct downstream from said air inlets, a plurality of liquid fuel inlet apertures leading to the duct, and a plurality of discharge windows positioned between the vanes.Type: ApplicationFiled: December 14, 2006Publication date: July 5, 2007Inventors: Thomas Scarinci, Kenneth Young
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Publication number: 20070089427Abstract: A gas turbine engine combustion system including a mixing duct that separates into at least two branch passages for the delivery of a fuel and working fluid to distinct locations within a combustion chamber. The residence time for the fuel and working fluid within each of the two branch passages is distinct.Type: ApplicationFiled: October 24, 2005Publication date: April 26, 2007Inventor: Thomas Scarinci
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Publication number: 20070089428Abstract: A combustion chamber device having a field static pressure gradient adapted to expel a flame kernel or hot spot from a fuel-air mixing duct. The swirling flow passing through an annular mixing duct is turned from a radial direction to an axial direction before entering the combustion chamber. An ignition source located within the fuel-air mixing duct can then be used to start the combustion process in the gas turbine.Type: ApplicationFiled: October 21, 2005Publication date: April 26, 2007Inventor: Thomas Scarinci
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Patent number: 6959550Abstract: A three-stage lean burn combustion chamber (28) comprises a primary combustion zone (36), a secondary combustion zone (40) and a tertiary combustion zone (44). Each of the combustion zones (36, 40, 44) is supplied with premixed fuel and air by respective fuel and air mixing ducts (54, 70, 92). The fuel and air mixing ducts (54, 70, 92) have a plurality of air injection slots (62, 64, 76, 98) spaced apart transversely to the direction of flow through the fuel and air mixing ducts (54, 70, 92). The air injection slots (62, 64, 76, 98) extend in the direction of flow through the fuel and air mixing ducts (54, 70, 92) to the reduce the magnitude of the fluctuations in the fuel to air ratio of the fuel and air mixture supplied into the at least one combustion zone (36, 40, 44). This reduces the generation of harmful vibrations in the combustion chamber (28).Type: GrantFiled: December 30, 2003Date of Patent: November 1, 2005Assignee: Rolls-Royce plcInventors: Christopher Freeman, Ivor J Day, Thomas Scarinci
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Publication number: 20040154301Abstract: A three-stage lean burn combustion chamber (28) comprises a primary combustion zone (36), a secondary combustion zone (40) and a tertiary combustion zone (44). Each of the combustion zones (36,40,44) is supplied with premixed fuel and air by respective fuel and air mixing ducts (54,70,92). The fuel and air mixing ducts (54,70,92) have a plurality of air injection slots (62,64,76,98) spaced apart transversely to the direction of flow through the fuel and air mixing ducts (54,70,92). The air injection slots (62,64,76,98) extend in the direction of flow through the fuel and air mixing ducts (54,70,92) to the reduce the magnitude of the fluctuations in the fuel to air ratio of the fuel and air mixture supplied into the at least one combustion zone (36,40,44). This reduces the generation of harmful vibrations in the combustion chamber (28).Type: ApplicationFiled: December 30, 2003Publication date: August 12, 2004Inventors: Christopher Freeman, Ivor J. Day, Thomas Scarinci
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Patent number: 6732527Abstract: A three-stage lean burn combustion chamber (28) comprises a primary combustion zone (36), a secondary combustion zone (40) and a tertiary combustion zone (44). Each of the combustion zones (36,40,44) is supplied with premixed fuel and air by respective fuel and air mixing ducts (54,70,92). The fuel and air mixing ducts (54,70,92) have a plurality of air injection slots (62,64,76,98) spaced apart transversely to the direction of flow through the fuel and air mixing ducts (54,70,92). The air injection slots (62,64,76,98) extend in the direction of flow through the fuel and air mixing ducts (54,70,92) to the reduce the magnitude of the fluctuations in the fuel to air ratio of the fuel and air mixture supplied into the at least one combustion zone (36,40,44). This reduces the generation of harmful vibrations in the combustion chamber (28).Type: GrantFiled: May 1, 2002Date of Patent: May 11, 2004Assignee: Rolls-Royce plcInventors: Christopher Freeman, Ivor J. Day, Thomas Scarinci
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Patent number: 6698206Abstract: A three-stage lean burn combustion chamber (28) comprises a primary combustion zone (36), a secondary combustion zone (40) and a tertiary combustion zone (44). Each of the combustion zones (36,40,44) is supplied with premixed fuel and air by respective fuel and air mixing ducts (54,70,92). The fuel and air mixing ducts (54,70,92) have a plurality of air injections apertures (62,64,76,98) spaced apart in the direction of flow through the fuel and air mixing ducts (54,70,92). The apertures (62,64,76,98) reduce the magnitude of the fluctuations in the fuel to air ratio of the fuel and air mixture supplied into the at least one combustion zone (36,40,44). This reduces the generation of harmful vibrations in the combustion chamber (28).Type: GrantFiled: December 27, 2002Date of Patent: March 2, 2004Assignee: Rolls-Royce plcInventors: Thomas Scarinci, Ivor J Day, Christopher Freeman
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Publication number: 20030145576Abstract: A three-stage lean burn combustion chamber (28) comprises a primary combustion zone (36), a secondary combustion zone (40) and a tertiary combustion zone (44). Each of the combustion zones (36,40,44) is supplied with premixed fuel and air by respective fuel and air mixing ducts (54,70,92). The fuel and air mixing ducts (54,70,92) have a plurality of air injections apertures (62,64,76,98) spaced apart in the direction of flow through the fuel and air mixing ducts (54,70,92). The apertures (62,64,76,98) reduce the magnitude of the fluctuations in the fuel to air ratio of the fuel and air mixture supplied into the at least one combustion zone (36,40,44). This reduces the generation of harmful vibrations in the combustion chamber (28).Type: ApplicationFiled: December 27, 2002Publication date: August 7, 2003Applicant: Rolls-Royce plcInventors: Thomas Scarinci, Ivor J. Day, Christopher Freeman
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Patent number: 6532742Abstract: A three-stage lean burn combustion chamber (28) comprises a primary combustion zone (36), a secondary combustion zone (40) and a tertiary combustion zone (44). Each of the combustion zones (36,40,44) is supplied with premixed fuel and air by respective fuel and air mixing ducts (54,70,92). The fuel and air mixing ducts (54,70,92) have a plurality of air injections apertures (62,64,76,98) spaced apart in the direction of flow through the fuel and air mixing ducts (54,70,92). The apertures (62,64,76,98) reduce the magnitude of the fluctuations in the fuel to air ratio of the fuel and air mixture supplied into the at least one combustion zone (36,40,44). This reduces the generation of harmful vibrations in the combustion chamber (28).Type: GrantFiled: February 27, 2001Date of Patent: March 18, 2003Assignee: Rolls-Royce plcInventors: Thomas Scarinci, Ivor J Day, Christopher Freeman
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Publication number: 20020172904Abstract: A three-stage lean burn combustion chamber (28) comprises a primary combustion zone (36), a secondary combustion zone (40) and a tertiary combustion zone (44). Each of the combustion zones (36,40,44) is supplied with premixed fuel and air by respective fuel and air mixing ducts (54,70,92). The fuel and air mixing ducts (54,70,92) have a plurality of air injection slots (62,64,76,98) spaced apart transversely to the direction of flow through the fuel and air mixing ducts (54,70,92). The air injection slots (62,64,76,98) extend in the direction of flow through the fuel and air mixing ducts (54,70,92) to the reduce the magnitude of the fluctuations in the fuel to air ratio of the fuel and air mixture supplied into the at least one combustion zone (36,40,44). This reduces the generation of harmful vibrations in the combustion chamber (28).Type: ApplicationFiled: May 1, 2002Publication date: November 21, 2002Inventors: Christopher Freeman, Ivor J. Day, Thomas Scarinci
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Publication number: 20010004515Abstract: A three-stage lean burn combustion chamber (28) comprises a primary combustion zone (36), a secondary combustion zone (40) and a tertiary combustion zone (44). Each of the combustion zones (36,40,44) is supplied with premixed fuel and air by respective fuel and air mixing ducts (54,70,92). The fuel and air mixing ducts (54,70,92) have a plurality of air injections apertures (62,64,76,98) spaced apart in the direction of flow through the fuel and air mixing ducts (54,70,92). The apertures (62,64,76,98) reduce the magnitude of the fluctuations in the fuel to air ratio of the fuel and air mixture supplied into the at least one combustion zone (36,40,44). This reduces the generation of harmful vibrations in the combustion chamber (28).Type: ApplicationFiled: December 12, 2000Publication date: June 21, 2001Inventors: Thomas Scarinci, Ivor J. Day, Christopher Freeman