Patents by Inventor Matthew Patrick Boespflug
Matthew Patrick Boespflug 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: 10823126Abstract: A flow control actuator includes at least one side wall, an upstream wall coupled to an upstream end of the side wall, a downstream cap coupled to a downstream end of the side wall, the downstream cap comprising at least one orifice disposed therein, at least one fuel injector disposed in at least one of the upstream wall, and the sidewall, the fuel injector dispersing fuel into the interior of the flow control actuator, and at least one oxidizer inlet disposed in at least one of the upstream wall and the sidewall, the at least one oxidizer inlet introducing an oxidizer into the interior of the flow control actuator. The flow control actuator includes at least one external fuel injector disposed adjacent to the side wall. The fuel from the fuel injector and oxidizer from the oxidizer inlet ignite in the interior of the flow control actuator.Type: GrantFiled: August 31, 2018Date of Patent: November 3, 2020Assignee: General Electric CompanyInventors: Nicholas William Rathay, Matthew Patrick Boespflug, Narendra Digamber Joshi
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Patent number: 10718323Abstract: A synthetic jet pump and a method of pumping fluid using such a synthetic jet pump are disclosed. The synthetic jet pump includes a plurality of first stacks disposed in a series arrangement relative to each other, and a plurality of first valves. A first stack of the plurality of first stacks includes a plurality of first connector pairs coupled to a first support structure and a plurality of first bimorph pairs. The first connector pairs and the first bimorph pairs are disposed in a parallel arrangement relative to each other respectively. A bimorph of one of the first bimorph pairs is coupled to a corresponding first connector pair. The plurality of first valves is disposed at an upstream end of the plurality of first stacks. A valve of the plurality of first valves is movably coupled to a corresponding connector of the plurality of the first connector pairs.Type: GrantFiled: May 26, 2017Date of Patent: July 21, 2020Assignee: NUOVO PIGNONE TECNOLOGIE SRLInventors: Grover Andrew Bennett, Jr., Matthew Patrick Boespflug, Tak Kwong Woo
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Publication number: 20200072174Abstract: A flow control actuator includes at least one side wall, an upstream wall coupled to an upstream end of the side wall, a downstream cap coupled to a downstream end of the side wall, the downstream cap comprising at least one orifice disposed therein, at least one fuel injector disposed in at least one of the upstream wall, and the sidewall, the fuel injector dispersing fuel into the interior of the flow control actuator, and at least one oxidizer inlet disposed in at least one of the upstream wall and the sidewall, the at least one oxidizer inlet introducing an oxidizer into the interior of the flow control actuator. The flow control actuator includes at least one external fuel injector disposed adjacent to the side wall. The fuel from the fuel injector and oxidizer from the oxidizer inlet ignite in the interior of the flow control actuator.Type: ApplicationFiled: August 31, 2018Publication date: March 5, 2020Applicant: General Electric CompanyInventors: Nicholas William Rathay, Matthew Patrick Boespflug, Narendra Digamber Joshi
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Patent number: 10393103Abstract: A compressor includes a plurality of synthetic jet assemblies. Each synthetic jet assembly of the plurality of synthetic jet assemblies is in fluid communication with at least one other synthetic jet assembly of the plurality of synthetic jet assemblies. Each synthetic jet assembly of the plurality of synthetic jet assemblies includes a first side plate and a second side plate. The first side plate includes a first bimorph piezoelectric structure. The second side plate includes a second bimorph piezoelectric structure. The first side plate and the second side plate define a first fluid cavity extending between the first side plate and the second side plate.Type: GrantFiled: October 10, 2016Date of Patent: August 27, 2019Assignee: General Electric CompanyInventors: Grover Andrew Bennett, Jr., Matthew Patrick Boespflug, Seyed Gholamali Saddoughi
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Patent number: 10240579Abstract: A virtual aerodynamic component for a wind turbine including at least one rotor blade connected to a hub. The at least one rotor blade defines an inner portion and a profiled outer portion. The virtual aerodynamic component includes one or more air-blowing units configured to provide a flow of air substantially opposed to an incoming wind. The flow of air defines the virtual aerodynamic component in front of the inner portion of the at least one rotor blade and provides for redirection of the incoming wind toward the profiled outer portion of the at least one rotor blade in an operational state and allows the incoming wind to flow toward the inner portion of the at least one rotor blade in a non-operational state. Further described is a wind turbine including the above-described virtual aerodynamic component and method for aerodynamic performance enhancement of an existing wind turbine.Type: GrantFiled: January 27, 2016Date of Patent: March 26, 2019Assignee: General Electric CompanyInventors: Seyed Gholamali Saddoughi, Matthew Patrick Boespflug, Michael Solomon Idelchik, Grover Andrew Bennett
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Publication number: 20180340529Abstract: A synthetic jet pump and a method of pumping fluid using such a synthetic jet pump are disclosed. The synthetic jet pump includes a plurality of first stacks disposed in a series arrangement relative to each other, and a plurality of first valves. A first stack of the plurality of first stacks includes a plurality of first connector pairs coupled to a first support structure and a plurality of first bimorph pairs. The first connector pairs and the first bimorph pairs are disposed in a parallel arrangement relative to each other respectively. A bimorph of one of the first bimorph pairs is coupled to a corresponding first connector pair. The plurality of first valves is disposed at an upstream end of the plurality of first stacks. A valve of the plurality of first valves is movably coupled to a corresponding connector of the plurality of the first connector pairs.Type: ApplicationFiled: May 26, 2017Publication date: November 29, 2018Inventors: Grover Andrew Bennett, JR., Matthew Patrick Boespflug, Tak Kwong Woo
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Patent number: 10132290Abstract: A deployable aerodynamic component configured to be mounted to a wind turbine. The wind turbine includes at least one rotor blade. The deployable aerodynamic component configured to be positioned in front of an inner portion of the at least one rotor blade, and is structurally configured to cover a substantial portion of the inner portion of the at least one rotor blade in a wind direction during deployment of the deployable aerodynamic component and to allow the passage therethrough of an incoming wind when non-deployed. Further described is a wind turbine including the above-described deployable aerodynamic component and method for aerodynamic performance enhancement of an existing wind turbine, wherein the method includes mounting the above-described deployable aerodynamic component to a wind turbine.Type: GrantFiled: October 20, 2015Date of Patent: November 20, 2018Assignee: GENERAL ELECTRIC COMPANYInventors: Dmitry Floryovych Opaits, Seyed Gholamali Saddoughi, Grover Andrew Bennett, Matthew Patrick Boespflug, Stephen Bertram Johnson, Peggy Lynn Baehmann, Fulton Jose Lopez, Daniel Jason Erno, Robert Michael Zirin, Anurag Gupta
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Publication number: 20180100494Abstract: A compressor includes a plurality of synthetic jet assemblies. Each synthetic jet assembly of the plurality of synthetic jet assemblies is in fluid communication with at least one other synthetic jet assembly of the plurality of synthetic jet assemblies. Each synthetic jet assembly of the plurality of synthetic jet assemblies includes a first side plate and a second side plate. The first side plate includes a first bimorph piezoelectric structure. The second side plate includes a second bimorph piezoelectric structure. The first side plate and the second side plate define a first fluid cavity extending between the first side plate and the second side plate.Type: ApplicationFiled: October 10, 2016Publication date: April 12, 2018Inventors: Grover Andrew Bennett, JR., Matthew Patrick Boespflug, Seyed Gholamali Saddoughi
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Publication number: 20170211545Abstract: A virtual aerodynamic component for a wind turbine including at least one rotor blade connected to a hub. The at least one rotor blade defines an inner portion and a profiled outer portion. The virtual aerodynamic component includes one or more air-blowing units configured to provide a flow of air substantially opposed to an incoming wind. The flow of air defines the virtual aerodynamic component in front of the inner portion of the at least one rotor blade and provides for redirection of the incoming wind toward the profiled outer portion of the at least one rotor blade in an operational state and allows the incoming wind to flow toward the inner portion of the at least one rotor blade in a non-operational state. Further described is a wind turbine including the above-described virtual aerodynamic component and method for aerodynamic performance enhancement of an existing wind turbine.Type: ApplicationFiled: January 27, 2016Publication date: July 27, 2017Inventors: Seyed Gholamali Saddoughi, Matthew Patrick Boespflug, Michael Solomon Idelchik, Grover Andrew Bennett
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Publication number: 20160040650Abstract: A deployable aerodynamic component configured to be mounted to a wind turbine. The wind turbine includes at least one rotor blade. The deployable aerodynamic component configured to be positioned in front of an inner portion of the at least one rotor blade, and is structurally configured to cover a substantial portion of the inner portion of the at least one rotor blade in a wind direction during deployment of the deployable aerodynamic component and to allow the passage therethrough of an incoming wind when non-deployed. Further described is a wind turbine including the above-described deployable aerodynamic component and method for aerodynamic performance enhancement of an existing wind turbine, wherein the method includes mounting the above-described deployable aerodynamic component to a wind turbine.Type: ApplicationFiled: October 20, 2015Publication date: February 11, 2016Inventors: Dmitry Floryovych Opaits, Seyed Gholamali Saddoughi, Grover Andrew Bennett, Matthew Patrick Boespflug, Stephen Bertram Johnson, Peggy Lynn Baehmann, Fulton Jose Lopez, Daniel Jason Erno, Robert Michael Zirin, Anurag Gupta
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Patent number: 9194363Abstract: A deployable aerodynamic component configured to be mounted to a wind turbine. The wind turbine includes at least one rotor blade. The deployable aerodynamic component configured to be positioned in front of an inner portion of the at least one rotor blade, and is structurally configured to cover a substantial portion of the inner portion of the at least one rotor blade in a wind direction during deployment of the deployable aerodynamic component and to allow the passage therethrough of an incoming wind when non-deployed. Further described is a wind turbine including the above-described deployable aerodynamic component and method for aerodynamic performance enhancement of an existing wind turbine, wherein the method includes mounting the above-described deployable aerodynamic component to a wind turbine.Type: GrantFiled: June 29, 2012Date of Patent: November 24, 2015Assignee: General Electric CompanyInventors: Dmytro Floriyovych Opaits, Seyed Gholamali Saddoughi, Grover Andrew Bennett, Jr., Matthew Patrick Boespflug, Stephen Bertram Johnson, Peggy Lynn Baehmann, Anurag Gupta
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Patent number: 9162754Abstract: A method for actively manipulating a primary fluid flow over a surface using an active flow control system including an active fluid flow device to provide lift enhancement and lift destruction. The method including the disposing of an active fluid flow device in the surface. The active fluid flow device is then operated to generate at least one of a steady blowing secondary fluid flow, a pulsed secondary fluid flow or an oscillating secondary fluid flow. While flowing the primary fluid over the surface to create a primary flow field, a secondary fluid flow is injected in an upstream direction and substantially opposed to the incoming primary fluid flow. The injecting of the secondary fluid flow in this manner provides for influencing of the primary flow field by manipulating a momentum of the secondary fluid flow to influence the incoming primary fluid flow and resultant lift.Type: GrantFiled: April 27, 2012Date of Patent: October 20, 2015Assignee: General Electric CompanyInventors: Matthew Patrick Boespflug, Seyed Gholamali Saddoughi, Grover Andrew Bennett, Jr., Dmytro Floriyovych Opaits
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Patent number: 8991189Abstract: A gas turbine engine augmentor includes at least one fluid based augmentor initiator defining a chamber in flow communication with a source of air and a source of fuel. The chamber includes a plurality of ejection openings in flow communication with an exhaust flowpath. The at least one fluid based augmentor initiator is devoid of any exhaust flowpath protrusions thereby minimizing any pressure drops and loss of thrust during dry work phase of operation. The source of fuel is operable for injecting fuel into the chamber such that at least a portion of the fuel flow is ignited at the plurality of ejection openings to produce a plurality of fuel-rich hot jets radially into the exhaust flowpath.Type: GrantFiled: October 28, 2010Date of Patent: March 31, 2015Assignee: General Electric CompanyInventors: Narendra Digamber Joshi, Adam Rasheed, Matthew Patrick Boespflug, Seyed Gholamali Saddoughi
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Patent number: 8671659Abstract: A system and a method of generating energy in a power plant using a turbine are provided. The system includes an air separation unit providing an oxygen output; a plasma generator that is capable of generating plasma; and a combustor configured to receive oxygen and to combust a fuel stream in the presence of the plasma, so as to maintain a stable flame, generating an exhaust gas. The system can further include a water condensation system, fluidly-coupled to the combustor, that is capable of producing a high-content carbon dioxide stream that is substantially free of oxygen. The method of generating energy in a power plant includes the steps of operating an air separation unit to separate oxygen from air, combusting a fuel stream in a combustor in the presence of oxygen, and generating an exhaust gas from the combustion. The exhaust gas can be used in a turbine to generate electricity. A plasma is generated inside the combustor, and a stable flame is maintained in the combustor.Type: GrantFiled: April 29, 2011Date of Patent: March 18, 2014Assignee: General Electric CompanyInventors: Ahmed Mostafa ELKady, Uyigue Omoma Idahosa, Matthew Patrick Boespflug, Grover Andrew Bennett, John Thomas Herbon, Hasan Karim, Geoffrey David Myers, Seyed Gholamali Saddoughi
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Publication number: 20140003940Abstract: A deployable aerodynamic component configured to be mounted to a wind turbine. The wind turbine includes at least one rotor blade. The deployable aerodynamic component configured to be positioned in front of an inner portion of the at least one rotor blade, and is structurally configured to cover a substantial portion of the inner portion of the at least one rotor blade in a wind direction during deployment of the deployable aerodynamic component and to allow the passage therethrough of an incoming wind when non-deployed. Further described is a wind turbine including the above-described deployable aerodynamic component and method for aerodynamic performance enhancement of an existing wind turbine, wherein the method includes mounting the above-described deployable aerodynamic component to a wind turbine.Type: ApplicationFiled: June 29, 2012Publication date: January 2, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Dmytro Floriyovych Opaits, Seyed Gholamali Saddoughi, Grover Andrew Bennett, JR., Matthew Patrick Boespflug, Stephen Bertram Johnson, Peggy Lynn Baehmann, Anurag Gupta
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Publication number: 20130284273Abstract: A method for actively manipulating a primary fluid flow over a surface using an active flow control system including an active fluid flow device to provide lift enhancement and lift destruction. The method including the disposing of an active fluid flow device in the surface. The active fluid flow device is then operated to generate at least one of a steady blowing secondary fluid flow, a pulsed secondary fluid flow or an oscillating secondary fluid flow. While flowing the primary fluid over the surface to create a primary flow field, a secondary fluid flow is injected in an upstream direction and substantially opposed to the incoming primary fluid flow. The injecting of the secondary fluid flow in this manner provides for influencing of the primary flow field by manipulating a momentum of the secondary fluid flow to influence the incoming primary fluid flow and resultant lift.Type: ApplicationFiled: April 27, 2012Publication date: October 31, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Matthew Patrick Boespflug, Seyed Gholamali Saddoughi, Grover Andrew Bennett, JR., Dmytro Floriyovych Opaits
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Publication number: 20130192243Abstract: A fuel nozzle assembly for use with a turbine engine includes at least one fuel conduit coupled to at least one fuel source. The fuel nozzle assembly also includes at least one swirler that includes at least one wall having a porous portion. The at least one wall is coupled to the at least one fuel conduit. The porous portion is formed from a material having a porosity that facilitates fuel flow therethrough. At least one fuel flow path is thereby defined through the porous portion of the at least one wall.Type: ApplicationFiled: January 31, 2012Publication date: August 1, 2013Inventors: Matthew Patrick Boespflug, Seyed Gholamali Saddoughi, Grover Andrew Bennett, JR., John Thomas Herbon
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Publication number: 20120272655Abstract: A system and a method of generating energy in a power plant using a turbine are provided. The system includes an air separation unit providing an oxygen output; a plasma generator that is capable of generating plasma; and a combustor configured to receive oxygen and to combust a fuel stream in the presence of the plasma, so as to maintain a stable flame, generating an exhaust gas. The system can further include a water condensation system, fluidly-coupled to the combustor, that is capable of producing a high-content carbon dioxide stream that is substantially free of oxygen. The method of generating energy in a power plant includes the steps of operating an air separation unit to separate oxygen from air, combusting a fuel stream in a combustor in the presence of oxygen, and generating an exhaust gas from the combustion. The exhaust gas can be used in a turbine to generate electricity. A plasma is generated inside the combustor, and a stable flame is maintained in the combustor.Type: ApplicationFiled: April 29, 2011Publication date: November 1, 2012Applicant: GENERAL ELECTRIC COMPANYInventors: Ahmed Mostafa ELKady, Uyigue Omoma Idahosa, Matthew Patrick Boespflug, Grover Andrew Bennett, John Thomas Herbon, Hasan Karim, Geoffrey David Myers, Seyed Gholamali Saddoughi
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Patent number: 8205433Abstract: Pulse detonation/deflagration apparatus for providing enhanced pressure wave operating frequency and/or magnitude, and methods of increasing the frequency or the magnitude of deflagration to detonation waves, are provided. A pulse detonation/deflagration apparatus can include a main/outer pulse detonation/deflagration actuator/engine (PDA/E) with multiple smaller internal combustion chambers or tubes positioned inside the cavity of the main/outer PDA/E with each performing the function of individual PDA/Es. The output pressure waves created by the internal PDA/Es can be utilized for propulsion or for controlling large scale flows, where needed.Type: GrantFiled: August 21, 2008Date of Patent: June 26, 2012Assignee: Lockheed Martin CorporationInventors: Matthew Patrick Boespflug, Dennis Steenburgh, Seyed Gholami Saddoughi, Grover Andrew Bennett
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Publication number: 20120144832Abstract: A gas turbine combustion system passive air-fuel mixing prechamber includes one or more fuel passages. Each fuel passage includes at least one downstream fuel injection orifice. One or more fluid conduits connect an upstream portion of at least one fuel passage with one or more air passages such that pressure drops across each fuel injection orifice substantially self-equalize in a passive manner with corresponding air passage pressure drops over a broad range of fuel lower heating value (LHV) from about 150 Btu/scf to about 900 Btu/scf of fuel passing through the fuel passage while mixing with air passing through one or more connected fluid conduits. The effective area of each fluid conduit relative to the corresponding fuel and air passages is dependent upon the desired fuel LHV operating range.Type: ApplicationFiled: December 10, 2010Publication date: June 14, 2012Applicant: GENERAL ELECTRIC COMPANYInventors: John Thomas Herbon, Matthew Patrick Boespflug, Grover Andrew Bennett, Fengfeng Tao, Giridhar Jothiprasad