Patents by Inventor Daniel David Snook
Daniel David Snook 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: 9127598Abstract: Ambient air is compressed into a compressed ambient gas flow with a main air compressor. The compressed ambient gas flow having a compressed ambient gas flow rate is delivered to a turbine combustor and mixed with a fuel stream having a fuel stream flow rate and a portion of a recirculated low oxygen content gas flow to form a combustible mixture. The combustible mixture is burned and forms the recirculated low oxygen content gas flow that drives a turbine. A portion of the recirculated low oxygen content gas flow is recirculated from the turbine to the turbine compressor using a recirculation loop. The compressed ambient gas flow rate and the fuel stream flow rate are adjusted to achieve substantially stoichiometric combustion. An excess portion, if any, of the compressed ambient gas flow is vented. A portion of the recirculated low oxygen content gas flow is extracted using an extraction conduit.Type: GrantFiled: August 25, 2011Date of Patent: September 8, 2015Assignee: General Electric CompanyInventors: Daniel David Snook, Lisa Anne Wichmann, Samuel David Draper, Noémie Dion Ouellet
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Patent number: 9115595Abstract: A system adapted for clearance control for a gas turbine including an outer turbine casing, an inner turbine casing and a plenum defined between the inner and outer turbine casings is disclosed. The clearance control system may include an impingement box disposed within the plenum. The impingement box may define a plurality of impingement holes. In addition, the clearance control system may include a first conduit in flow communication with the interior of the impingement box and a second conduit in flow communication with the plenum at a location exterior to the impingement box.Type: GrantFiled: April 9, 2012Date of Patent: August 25, 2015Assignee: General Electric CompanyInventor: Daniel David Snook
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Patent number: 8690530Abstract: A system for supporting a nozzle assembly includes a first member connected to a stationary component and a second member extending from the first member radially through at least a portion of the nozzle assembly. A distal end of the second member is radially displaced from the first member and configured to contact the nozzle assembly. A method for supporting a nozzle assembly includes connecting a first member to a stationary component and extending a second member from the first member radially through at least a portion of the nozzle assembly. The method further includes contacting a distal end of the second member to the nozzle assembly, wherein the distal end is radially displaced from the first member.Type: GrantFiled: June 27, 2011Date of Patent: April 8, 2014Assignee: General Electric CompanyInventors: Daniel David Snook, Leissner Ferdinand Poth, III
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Publication number: 20130266418Abstract: A system adapted for clearance control for a gas turbine including an outer turbine casing, an inner turbine casing and a plenum defined between the inner and outer turbine casings is disclosed. The clearance control system may include an impingement box disposed within the plenum. The impingement box may define a plurality of impingement holes. In addition, the clearance control system may include a first conduit in flow communication with the interior of the impingement box and a second conduit in flow communication with the plenum at a location exterior to the impingement box.Type: ApplicationFiled: April 9, 2012Publication date: October 10, 2013Applicant: GENERAL ELECTRIC COMPANYInventor: Daniel David Snook
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Publication number: 20130160456Abstract: A system for controlling oxygen emissions from a gas turbine includes a combustor, a plenum downstream from the combustor, and a turbine downstream from the plenum that produces an exhaust. A compressor downstream from the turbine receives the exhaust and produces a compressed exhaust. A compressed exhaust plenum downstream from the compressor provides fluid communication to the combustor and the plenum. A method for controlling oxygen emissions from a gas turbine includes flowing an exhaust from a turbine and increasing the pressure of the exhaust to produce a compressed exhaust. The method further includes flowing a first portion of the compressed exhaust to an inlet of a combustor and flowing a second portion of the compressed exhaust to a plenum between the turbine and the combustor.Type: ApplicationFiled: December 22, 2011Publication date: June 27, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Daniel David Snook, John Charles Intile
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Patent number: 8453462Abstract: At least one main air compressor makes a compressed ambient gas flow. The compressed ambient gas flow is delivered to a turbine combustor at a pressure that is greater than or substantially equal to an output pressure delivered to the turbine combustor from a turbine compressor as at least a first portion of a recirculated gas flow. A fuel stream is delivered to the turbine combustor, and a combustible mixture is formed and burned, forming the recirculated gas flow. A turbine power is produced that is substantially equal to at least a power required to rotate the turbine compressor. At least a portion of the recirculated gas flow is recirculated through a recirculation loop. An excess portion of the recirculated gas flow is vented or a portion of the recirculated gas flow bypasses the turbine combustor or both.Type: GrantFiled: August 25, 2011Date of Patent: June 4, 2013Assignee: General Electric CompanyInventors: Lisa Anne Wichmann, Daniel David Snook, Samuel David Draper, Noémie Dion Ouellet, Scott Allen Rittenhouse
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Patent number: 8347600Abstract: At least one main air compressor makes a compressed ambient gas flow. The compressed ambient gas flow is delivered to both master and slave turbine combustors at a pressure that is greater than or substantially equal to an output pressure delivered to each turbine combustor from each turbine compressor as at least a first portion of a recirculated gas flow. A fuel stream is delivered to each turbine combustor, and combustible mixtures are formed and burned, forming the recirculated gas flows. A master and slave turbine power are produced, and each is substantially equal to at least a power required to rotate each turbine compressor. At least a portion of the recirculated gas flow is recirculated through recirculation loops. At least a second portion of the recirculated gas flow bypasses the combustors or an excess portion of each recirculated gas flow is vented or both.Type: GrantFiled: August 25, 2011Date of Patent: January 8, 2013Assignee: General Electric CompanyInventors: Lisa Anne Wichmann, Daniel David Snook, Noémie Dion Ouellet, Scott Allen Rittenhouse
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Publication number: 20120328413Abstract: A system for supporting a nozzle assembly includes a first member connected to a stationary component and a second member extending from the first member radially through at least a portion of the nozzle assembly. A distal end of the second member is radially displaced from the first member and configured to contact the nozzle assembly. A method for supporting a nozzle assembly includes connecting a first member to a stationary component and extending a second member from the first member radially through at least a portion of the nozzle assembly. The method further includes contacting a distal end of the second member to the nozzle assembly, wherein the distal end is radially displaced from the first member.Type: ApplicationFiled: June 27, 2011Publication date: December 27, 2012Applicant: GENERAL ELECTRIC COMPANYInventors: Daniel David Snook, Leissner Ferdinand Poth, III
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Patent number: 8266913Abstract: A power plant arrangement and method of operation are provided. The power plant arrangement comprises at lease one main air compressor and one or more gas turbine assemblies. Each assembly comprises a turbine combustor for mixing a portion of a compressed ambient gas flow with a portion of a recirculated low oxygen content gas flow and a fuel stream, and burning the combustible mixture to form the recirculated low oxygen content flow. The assembly further comprises a turbine compressor, fluidly connected to the turbine combustor, and connected to a turbine shaft that is arranged to be driven by rotation of a turbine. The assembly also comprises a recirculation loop for recirculating at least a portion of the recirculated low oxygen content gas flow from the turbine to the turbine compressor.Type: GrantFiled: August 25, 2011Date of Patent: September 18, 2012Assignee: General Electric CompanyInventors: Daniel David Snook, Lisa Anne Wichmann, Samuel David Draper, Noémie Dion Ouellet
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Patent number: 8266883Abstract: Ambient air is compressed into a compressed ambient gas flow and delivered to a turbine combustor. At least one of an exhaust port, a bypass conduit, or an extraction conduit is opened to vent the power plant. A turbine shaft is rotated at an ignition speed and a fuel stream is delivered to the turbine combustor for mixing with the compressed ambient gas flow to form a combustible mixture. The combustible mixture is burned and forms a recirculated gas flow that drives the turbine. The recirculated gas flow is recirculated using the recirculation loop. The turbine is operated at a target operating speed and then reaches substantially stoichiometric combustion. At least a portion of the recirculated gas flow is extracted using an extraction conduit that is fluidly connected to the turbine compressor.Type: GrantFiled: August 25, 2011Date of Patent: September 18, 2012Assignee: General Electric CompanyInventors: Noémie Dion Ouellet, Daniel David Snook, Lisa Anne Wichmann, Samuel David Draper, Scott Allen Rittenhouse
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Publication number: 20120214605Abstract: The present application and the resultant patent provide a gas turbine engine generator system. The gas turbine engine generator system may include a turbine, a generator, and a shaft. The turbine drives the generator via the shaft. A torsional damping coupling may be positioned about the shaft so as to limit the transmission of torque to the turbine during a generator based fault event.Type: ApplicationFiled: February 21, 2011Publication date: August 23, 2012Applicant: GENERAL ELECTRIC COMPANYInventors: Daniel David Snook, Klaus Werner Sommerlatte
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Publication number: 20120180493Abstract: A combined cycle power plant includes a first compressor that produces a compressed working fluid and a turbine downstream of the first compressor. The turbine includes stationary components and rotating components and produces an exhaust. A heat exchanger downstream of the turbine receives the exhaust from the turbine, and a second compressor downstream of the heat exchanger and upstream of the turbine receives the exhaust from the heat exchanger and provides a flow of exhaust to the turbine. A method for reducing oxygen emissions from a gas turbine includes flowing an exhaust from a turbine to a heat exchanger and removing heat from the exhaust. The method further includes increasing the pressure of the exhaust to produce a pressurized exhaust and flowing the pressurized exhaust back to the turbine to remove heat from the turbine.Type: ApplicationFiled: January 13, 2011Publication date: July 19, 2012Applicant: GENERAL ELECTRIC COMPANYInventors: Daniel David Snook, Andrew Mitchell Rodwell
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Publication number: 20120023966Abstract: Ambient air is compressed into a compressed ambient gas flow and delivered to a turbine combustor. At least one of an exhaust port, a bypass conduit, or an extraction conduit is opened to vent the power plant. A turbine shaft is rotated at an ignition speed and a fuel stream is delivered to the turbine combustor for mixing with the compressed ambient gas flow to form a combustible mixture. The combustible mixture is burned and forms a recirculated gas flow that drives the turbine. The recirculated gas flow is recirculated using the recirculation loop. The turbine is operated at a target operating speed and then reaches substantially stoichiometric combustion. At least a portion of the recirculated gas flow is extracted using an extraction conduit that is fluidly connected to the turbine compressor.Type: ApplicationFiled: August 25, 2011Publication date: February 2, 2012Applicant: General Electric CompanyInventors: Noémie Dion Ouellet, Daniel David Snook, Lisa Anne Wichmann, Samuel David Draper, Scott Allen Rittenhouse
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Publication number: 20120023959Abstract: A power plant arrangement and method of operation are provided. The power plant arrangement comprises at lease one main air compressor and one or more gas turbine assemblies. Each assembly comprises a turbine combustor for mixing a portion of a compressed ambient gas flow with a portion of a recirculated low oxygen content gas flow and a fuel stream, and burning the combustible mixture to form the recirculated low oxygen content flow. The assembly further comprises a turbine compressor, fluidly connected to the turbine combustor, and connected to a turbine shaft that is arranged to be driven by rotation of a turbine. The assembly also comprises a recirculation loop for recirculating at least a portion of the recirculated low oxygen content gas flow from the turbine to the turbine compressor.Type: ApplicationFiled: August 25, 2011Publication date: February 2, 2012Applicant: GENERAL ELECTRIC COMPANYInventors: Daniel David Snook, Lisa Anne Wichmann, Samuel David Draper, Noémie Dion Ouellet
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Publication number: 20120023963Abstract: At least one main air compressor makes a compressed ambient gas flow. The compressed ambient gas flow is delivered to both master and slave turbine combustors at a pressure that is greater than or substantially equal to an output pressure delivered to each turbine combustor from each turbine compressor as at least a first portion of a recirculated gas flow. A fuel stream is delivered to each turbine combustor, and combustible mixtures are formed and burned, forming the recirculated gas flows. A master and slave turbine power are produced, and each is substantially equal to at least a power required to rotate each turbine compressor. At least a portion of the recirculated gas flow is recirculated through recirculation loops. At least a second portion of the recirculated gas flow bypasses the combustors or an excess portion of each recirculated gas flow is vented or both.Type: ApplicationFiled: August 25, 2011Publication date: February 2, 2012Applicant: General Electric CompanyInventors: Lisa Anne Wichmann, Daniel David Snook, Noémie Dion Ouellet, Scott Allen Rittenhouse
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Publication number: 20120023962Abstract: At least one main air compressor makes a compressed ambient gas flow. The compressed ambient gas flow is delivered to a turbine combustor at a pressure that is greater than or substantially equal to an output pressure delivered to the turbine combustor from a turbine compressor as at least a first portion of a recirculated gas flow. A fuel stream is delivered to the turbine combustor, and a combustible mixture is formed and burned, forming the recirculated gas flow. A turbine power is produced that is substantially equal to at least a power required to rotate the turbine compressor. At least a portion of the recirculated gas flow is recirculated through a recirculation loop. An excess portion of the recirculated gas flow is vented or a portion of the recirculated gas flow bypasses the turbine combustor or both.Type: ApplicationFiled: August 25, 2011Publication date: February 2, 2012Applicant: General Electric CompanyInventors: Lisa Anne Wichmann, Daniel David Snook, Samuel David Draper, Noémie Dion Ouellet, Scott Allen Rittenhouse
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Publication number: 20120023958Abstract: Ambient air is compressed into a compressed ambient gas flow with a main air compressor. The compressed ambient gas flow having a compressed ambient gas flow rate is delivered to a turbine combustor and mixed with a fuel stream having a fuel stream flow rate and a portion of a recirculated low oxygen content gas flow to form a combustible mixture. The combustible mixture is burned and forms the recirculated low oxygen content gas flow that drives a turbine. A portion of the recirculated low oxygen content gas flow is recirculated from the turbine to the turbine compressor using a recirculation loop. The compressed ambient gas flow rate and the fuel stream flow rate are adjusted to achieve substantially stoichiometric combustion. An excess portion, if any, of the compressed ambient gas flow is vented. A portion of the recirculated low oxygen content gas flow is extracted using an extraction conduit.Type: ApplicationFiled: August 25, 2011Publication date: February 2, 2012Applicant: General Electric CompanyInventors: Daniel David Snook, Lisa Anne Wichmann, Samuel David Draper, Noémie Dion Ouellet
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Patent number: 8096757Abstract: A gas turbine engine nozzle is described. The gas turbine engine nozzle includes at least one nozzle vane having a first end and a second end. The first end is coupled to an inner sidewall and the second end is coupled to an outer sidewall. The gas turbine engine nozzle also includes at least one stress relief pocket defined within at least one of the inner sidewall and the outer sidewall proximate to the at least one nozzle vane. The at least one stress relief pocket is configured to reduce stress on the proximate nozzle vane.Type: GrantFiled: January 2, 2009Date of Patent: January 17, 2012Assignee: General Electric CompanyInventors: Daniel David Snook, Edward Durell Benjamin
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Patent number: 8057169Abstract: An article of manufacture includes an object having an airfoil core shape. The airfoil core shape has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in TABLE 1 where X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances are joined smoothly with one another to form a complete airfoil core shape.Type: GrantFiled: June 13, 2008Date of Patent: November 15, 2011Assignee: General Electric CompanyInventors: Edward Durell Benjamin, Jr., David John Humanchuk, Daniel David Snook
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Publication number: 20110189008Abstract: A retaining ring for a turbine nozzle of a gas turbine is disclosed. The retaining ring includes a main body and a pair of circumferential retaining lands projecting inward radially from the main body. The pair of circumferential retaining lands may be configured to be attached to a nozzle. Additionally, each retaining land of the pair of circumferential retaining lands may be segmented along its circumferential length.Type: ApplicationFiled: January 29, 2010Publication date: August 4, 2011Applicant: GENERAL ELECTRIC COMPANYInventors: THOMAS J. BRUNT, DANIEL DAVID SNOOK