Patents by Inventor Lawrence Butler
Lawrence Butler 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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Publication number: 20090193786Abstract: A continuous detonation system, including: a rotatable member including a forward end, an aft end, a circumferential wall and a longitudinal centerline axis extending therethrough; an outer circumferential wall, wherein the rotatable member is positioned therein so that the circumferential wall of the rotatable member is spaced radially inwardly from the outer circumferential wall; at least one helical channel formed by a plurality of helical sidewalls extending between the circumferential wall of the rotatable member and the outer circumferential wall, each helical channel being open at the forward end and the aft end of the rotatable member so as to provide flow communication therethrough; an air supply for providing air to each helical channel; and, a fuel supply for providing fuel to each helical channel. In this way, a mixture of the fuel and air is continuously detonated within each helical channel in a manner such that combustion gases exit therefrom with an increased pressure and temperature.Type: ApplicationFiled: February 1, 2008Publication date: August 6, 2009Applicant: General Electric CompanyInventors: Kurt David Murrow, Lawrence Butler
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Patent number: 7328570Abstract: A gas turbine engine having a longitudinal centerline axis therethrough, including: a fan section at a forward end of the gas turbine engine including at least a first fan blade row connected to a first drive shaft; a booster compressor positioned downstream of the fan section, the booster compressor including a first compressor blade row and a second compressor blade row connected to a second drive shaft and interdigitated with the first compressor blade row; and, a pulse detonation system for powering the first and second drive shafts. The pulse detonation system powers only the second drive shaft during a first designated condition of the gas turbine engine and both the first drive shaft and the second drive shaft during a second designated condition of the gas turbine engine. The first and second drive shafts are powered independently of each other by the pulse detonation system.Type: GrantFiled: September 1, 2004Date of Patent: February 12, 2008Assignee: General Electric CompanyInventors: Kattalaicheri Srinivasan Venkataramani, Lawrence Butler, James Paul Davidson
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Patent number: 7195446Abstract: A method for assembling a gas turbine engine that includes providing a low-pressure turbine inner rotor configured to rotate in a first direction, providing a low-pressure turbine outer rotor configured to rotate in a second direction that is opposite the first rotational direction, and coupling at least one foil bearing to at least one of the inner and outer rotors to facilitate improving clearance control between a first rotating component and at least one of a second rotating component and a non-rotating component.Type: GrantFiled: October 29, 2004Date of Patent: March 27, 2007Assignee: General Electric CompanyInventors: Jorge Francisco Seda, Thomas Ory Moniz, Lawrence Butler
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Publication number: 20060265279Abstract: A reporting system is described which provides current information on the progress of advertising campaigns, consumer feedback on the brands or products being advertised, or details on sample and premium distribution. Individuals perform campaign activities on behalf of an advertiser, such as by driving vehicles that have been custom fitted to display advertisement information on their exterior about the brands or products, or by otherwise interacting with targets of the campaign. The on-line reporting system provides means for the individual drivers to upload reports about the individuals' advertising activities into a computer system in a timely fashion, such as on a daily basis. The reporting system also provides means for the advertiser to review the reports received from the individual drivers and evaluate the effectiveness of the campaigns.Type: ApplicationFiled: May 20, 2005Publication date: November 23, 2006Inventors: Andrew Livingston, Lawrence Butler
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Patent number: 7124573Abstract: A pulse detonation system for a gas turbine engine having a longitudinal centerline axis extending therethrough. The pulse detonation system includes a rotatable cylindrical member having a forward surface, an aft surface, and an outer circumferential surface, where at least one stage of circumferentially spaced detonation passages are disposed therethrough.Type: GrantFiled: March 18, 2004Date of Patent: October 24, 2006Assignee: General Electric CompanyInventors: Kattalaicheri Srinivasan Venkataramani, Lawrence Butler, Ching-Pang Lee
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Publication number: 20060207261Abstract: A pulse detonation system for a gas turbine engine having a longitudinal centerline axis extending therethrough. The pulse detonation system includes a rotatable cylindrical member having a forward surface, an aft surface, and an outer circumferential surface, where at least one stage of circumferentially spaced detonation passages are disposed therethrough.Type: ApplicationFiled: March 18, 2004Publication date: September 21, 2006Inventors: Kattalaicheri Venkataramani, Lawrence Butler, Ching-Pang Lee
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Publication number: 20060093466Abstract: A method for assembling a gas turbine engine that includes providing a low-pressure turbine inner rotor configured to rotate in a first direction, providing a low-pressure turbine outer rotor configured to rotate in a second direction that is opposite the first rotational direction, and coupling at least one foil bearing to at least one of the inner and outer rotors to facilitate improving clearance control between a first rotating component and at least one of a second rotating component and a non-rotating component.Type: ApplicationFiled: October 29, 2004Publication date: May 4, 2006Inventors: Jorge Seda, Thomas Moniz, Lawrence Butler
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Publication number: 20060042228Abstract: A gas turbine engine having a longitudinal centerline axis therethrough, including: a fan section at a forward end of the gas turbine engine including at least a first fan blade row connected to a first drive shaft; a booster compressor positioned downstream of the fan section, the booster compressor including a first compressor blade row and a second compressor blade row connected to a second drive shaft and interdigitated with the first compressor blade row; and, a pulse detonation system for powering the first and second drive shafts. The pulse detonation system powers only the second drive shaft during a first designated condition of the gas turbine engine and both the first drive shaft and the second drive shaft during a second designated condition of the gas turbine engine. The first and second drive shafts are powered independently of each other by the pulse detonation system.Type: ApplicationFiled: September 1, 2004Publication date: March 2, 2006Inventors: Kattalaicheri Venkataramani, Lawrence Butler, James Davidson
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Patent number: 6990797Abstract: A method facilitates assembling a turbine engine to facilitate preventing ice accumulation on the turbine engine during engine operation. The method comprises coupling at least one heat pipe to the engine such that a first end of the at least one heat pipe is coupled in thermal communication with a heat source, and coupling a second end of the at least one heat pipe in thermal communication with an outer surface of an engine component that is upstream from the heat source.Type: GrantFiled: September 5, 2003Date of Patent: January 31, 2006Assignee: General Electric CompanyInventors: Kattalaicheri Srinivasan Venkataramani, Lawrence Butler, Ching-Pang Lee
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Patent number: 6981361Abstract: A method facilitates generating thrust from a gas turbine engine using a pulse detonation system. The method includes introducing fuel and air to the engine, mixing fuel and air in a pulse detonation system deflagration chamber positioned radially outward from an engine exhaust centerbody, and detonating the fuel and air mixture within the pulse detonation system to facilitate increasing the temperature and pressure within the engine and to generate engine thrust.Type: GrantFiled: July 13, 2004Date of Patent: January 3, 2006Assignee: General Electric CompanyInventors: John Michael Koshoffer, Kevin R. Drake, Lawrence Butler
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Patent number: 6931858Abstract: A pulse detonation system for a gas turbine engine having a longitudinal centerline axis extending therethrough includes a rotatable cylindrical member having a forward surface, an aft surface, and an outer circumferential surface, where a plurality of spaced detonation passages are disposed therethrough. Each detonation passage includes at least a portion having a longitudinal axis extending therethrough oriented at a circumferential angle to the longitudinal centerline axis. The pulse detonation system further includes a shaft rotatably connected to the cylindrical member and a stator configured in spaced arrangement with the forward surface of the cylindrical member and a portion of the shaft. The stator has at least one group of ports formed therein alignable with the detonation passages as the cylindrical member rotates.Type: GrantFiled: April 24, 2003Date of Patent: August 23, 2005Assignee: General Electric CompanyInventors: Kattalaicheri Srinivasan Venkataramani, Lawrence Butler, Ching-Pang Lee, Harvey Michael Maclin
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Patent number: 6928804Abstract: A pulse detonation system for a gas turbine engine having a longitudinal centerline axis extending therethrough, the pulse detonation system includes an air inlet duct in flow communication with a source of compressed air, the air inlet duct including at least one port formed therein for permitting compressed air to flow therethrough, a fuel injector mounted to the air inlet duct in circumferentially spaced relation to each port, and a device mounted to the air inlet duct in circumferentially spaced relation to each fuel injector for initiating a detonation wave. A rotatable ring member is also positioned in coaxial relation around a portion of the air inlet duct, with the ring member including at least one stage of detonation disposed therein. Accordingly, a detonation wave is produced in each detonation stage and combustion gases following each detonation wave create a torque which causes the ring member to rotate.Type: GrantFiled: March 6, 2003Date of Patent: August 16, 2005Assignee: General Electric CompanyInventors: Kattalaicheri Srinivasan Venkataramani, Lawrence Butler, William Andrew Bailey
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Patent number: 6904750Abstract: A pulse detonation system for a gas turbine engine having a longitudinal centerline axis extending therethrough includes a rotatable cylindrical member having a forward surface, an aft surface, and an outer circumferential surface, where at least one stage of spaced detonation passages are disposed therethrough. The pulse detonation system further includes a shaft rotatably connected to the cylindrical member and a stator configured in spaced arrangement with the forward surface of the cylindrical member and a portion of the shaft. The stator has at least one group of ports formed therein alignable with the detonation passages as the cylindrical member rotates. In this way, detonation cycles are performed in the detonation passages so that combustion gases exit the cylindrical manner in a substantially tangential direction with respect to the outer circumferential surface to create a torque which causes the cylindrical member to rotate.Type: GrantFiled: April 18, 2003Date of Patent: June 14, 2005Assignee: General Electric CompanyInventors: Kattalaicheri Srinivasan Venkataramani, Lawrence Butler, Ching Pang Lee, Harvey Michael Maclin
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Patent number: 6889505Abstract: A pulse detonation system for a gas turbine engine having a longitudinal centerline axis extending therethrough includes a rotatable cylindrical member having a forward surface, an aft surface, and an outer circumferential surface, where at least one stage of circumferentially spaced detonation chambers is disposed therein. The pulse detonation system further includes a shaft rotatably connected to the cylindrical member and a stator configured in spaced arrangement around the forward surface, the aft surface, and the outer circumferential surface of the cylindrical member and a portion of the shaft. The stator has at least one group of ports formed therein which sequentially align with the detonation chambers as the cylindrical member rotates. In this way, detonation cycles are performed in the detonation chambers of each detonation stage so that reaction forces induced by the detonation cycles create a torque which causes the cylindrical member to rotate.Type: GrantFiled: April 2, 2003Date of Patent: May 10, 2005Assignee: General Electric CompanyInventors: Lawrence Butler, Kattalaicheri Srinivasan Venkataramani, Kurt David Murrow, Ivett Alejandra Leyva
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Patent number: 6868665Abstract: A method facilitates generating thrust from a gas turbine engine using a pulse detonation system. The method includes introducing fuel and air to the engine, mixing fuel and air in a pulse detonation system deflagration chamber positioned radially outward from an engine exhaust centerbody, and detonating the fuel and air mixture within the pulse detonation system to facilitate increasing the temperature and pressure within the engine and to generate engine thrust.Type: GrantFiled: December 21, 2001Date of Patent: March 22, 2005Assignee: General Electric CompanyInventors: John Michael Koshoffer, Kevin R. Drake, Lawrence Butler
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Publication number: 20050050877Abstract: A method facilitates assembling a turbine engine to facilitate preventing ice accumulation on the turbine engine during engine operation. The method comprises coupling at least one heat pipe to the engine such that a first end of the at least one heat pipe is coupled in thermal communication with a heat source, and coupling a second end of the at least one heat pipe in thermal communication with an outer surface of an engine component that is upstream from the heat source.Type: ApplicationFiled: September 5, 2003Publication date: March 10, 2005Inventors: Kattalaicheri Venkataramani, Lawrence Butler, Ching-Pang Lee
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Publication number: 20050028531Abstract: A pulse detonation system for a gas turbine engine having a longitudinal centerline axis extending therethrough includes a rotatable cylindrical member having a forward surface, an aft surface, and an outer circumferential surface, where a plurality of spaced detonation passages are disposed therethrough. Each detonation passage includes at least a portion having a longitudinal axis extending therethrough oriented at a circumferential angle to the longitudinal centerline axis. The pulse detonation system further includes a shaft rotatably connected to the cylindrical member and a stator configured in spaced arrangement with the forward surface of the cylindrical member and a portion of the shaft. The stator has at least one group of ports formed therein alignable with the detonation passages as the cylindrical member rotates.Type: ApplicationFiled: April 24, 2003Publication date: February 10, 2005Inventors: Kattalaicheri Venkataramani, Lawrence Butler, Ching-Pang Lee, Harvey Maclin
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Publication number: 20040244359Abstract: A method facilitates generating thrust from a gas turbine engine using a pulse detonation system. The method includes introducing fuel and air to the engine, mixing fuel and air in a pulse detonation system deflagration chamber positioned radially outward from an engine exhaust centerbody, and detonating the fuel and air mixture within the pulse detonation system to facilitate increasing the temperature and pressure within the engine and to generate engine thrust.Type: ApplicationFiled: July 13, 2004Publication date: December 9, 2004Inventors: John Michael Koshoffer, Kevin R. Drake, Lawrence Butler
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Publication number: 20040206089Abstract: A pulse detonation system for a gas turbine engine having a longitudinal centerline axis extending therethrough includes a rotatable cylindrical member having a forward surface, an aft surface, and an outer circumferential surface, where at least one stage of spaced detonation passages are disposed therethrough. The pulse detonation system further includes a shaft rotatably connected to the cylindrical member and a stator configured in spaced arrangement with the forward surface of the cylindrical member and a portion of the shaft. The stator has at least one group of ports formed therein alignable with the detonation passages as the cylindrical member rotates. In this way, detonation cycles are performed in the detonation passages so that combustion gases exit the cylindrical manner in a substantially tangential direction with respect to the outer circumferential surface to create a torque which causes the cylindrical member to rotate.Type: ApplicationFiled: April 18, 2003Publication date: October 21, 2004Inventors: Kattalaicheri Srinivasan Venkataramani, Lawrence Butler, Ching Pang Lee, Harvey Michael Maclin
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Patent number: D1052600Type: GrantFiled: November 8, 2022Date of Patent: November 26, 2024Assignee: Embecta Corp.Inventors: Joshua Daniel Coyle, Danielle Victoria Butler, Ryan Francis Bedell, Brett Lawrence Martin, David Downey, Linda Charlite-Ruiz