Patents by Inventor Gary L. Lidstone
Gary L. Lidstone 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: 7775460Abstract: A fluid flow system for use with a gas turbine engine includes an exhaust nozzle, a primary air supply valve, a distribution manifold connected to the primary fluid supply valve and in fluid communication therewith, and a plurality of fluid injector assemblies positioned at the exhaust nozzle and connected in fluid communication with the distribution manifold. Each fluid injector assembly includes a first tube, a secondary air valve positioned at least partially within the first tube and in fluid communication with the distribution manifold, a fuel valve positioned at least partially within the first tube and located downstream of the air valve, an igniter extending into the first tube downstream of the fuel valve, and an outlet in fluid communication with the first tube and connected in fluid communication with the exhaust nozzle. The outlet has a different geometry than the first tube.Type: GrantFiled: October 24, 2006Date of Patent: August 17, 2010Assignee: United Technologies CorporationInventors: Gerald R. Berg, Nathan L. Messersmith, Gary L. Lidstone, John Hinkey
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Patent number: 7500348Abstract: A pulse combustion device has a number of combustors with upstream bodies and downstream nozzles. Coupling conduits provide communication between the combustors. For each given combustor this includes a first communication between a first location upstream of the nozzle thereof and a first location along the nozzle of another. There is second communication between a second location upstream of the nozzle and a second communication between a second location upstream of the nozzle of a second other combustor and a second nozzle location along the nozzle of the given combustor.Type: GrantFiled: March 24, 2005Date of Patent: March 10, 2009Assignee: United Technologies CorporationInventors: Kirk R. Lupkes, Gary L. Lidstone
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Patent number: 7448200Abstract: A pulse combustion device has a number of combustors with upstream bodies and downstream nozzles. Coupling conduits provide communication between the combustors. For each given combustor this includes a first communication between a first location upstream of the nozzle thereof and a first location along the nozzle of another. There is second communication between a second location upstream of the nozzle and a second communication between a second location upstream of the nozzle of a second other combustor and a second nozzle location along the nozzle of the given combustor.Type: GrantFiled: March 24, 2005Date of Patent: November 11, 2008Assignee: United Technologies CorporationInventors: Kirk R. Lupkes, Gary L. Lidstone, Mark W. Parish
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Publication number: 20080092543Abstract: A fluid flow system for use with a gas turbine engine includes an exhaust nozzle, a primary air supply valve, a distribution manifold connected to the primary fluid supply valve and in fluid communication therewith, and a plurality of fluid injector assemblies positioned at the exhaust nozzle and connected in fluid communication with the distribution manifold. Each fluid injector assembly includes a first tube, a secondary air valve positioned at least partially within the first tube and in fluid communication with the distribution manifold, a fuel valve positioned at least partially within the first tube and located downstream of the air valve, an igniter extending into the first tube downstream of the fuel valve, and an outlet in fluid communication with the first tube and connected in fluid communication with the exhaust nozzle. The outlet has a different geometry than the first tube.Type: ApplicationFiled: October 24, 2006Publication date: April 24, 2008Applicant: United Technologies CorporationInventors: Gerald R. Berg, Nathan L. Messersmith, Gary L. Lidstone, John Hinkey
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Patent number: 6003301Abstract: A nozzle for a detonative combustion engine, the engine having multiple combustor tubes, comprises a common plenum communicating with the combustor tubes. The common plenum combines separate exhaust streams from the combustor tubes into a compound subsonic exhaust stream. A compound flow throat communicates with the common plenum. The compound flow throat converts the compound subsonic exhaust stream into a compound sonic exhaust stream. The common plenum and compound flow throat cooperate to maintain a predetermined upstream combustor pressure regardless of down stream pressure exiting the expansion section. Optionally, an interface section is inserted between the plenum and the engine such that it communicates with the common plenum section and with outlets of the combustor tubes. The interface section is compartmentalized into flow passages with each flow passage having a cross-sectional area that increases from that of a particular nozzle intake port connected to a conductor tube exit.Type: GrantFiled: March 27, 1997Date of Patent: December 21, 1999Assignee: Adroit Systems, Inc.Inventors: Thomas E. Bratkovich, Kevin E. Williams, Thomas R. A. Bussing, Gary L. Lidstone, John B. Hinkey
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Patent number: 5941065Abstract: An ejector nozzle (10) including an first cowling (12), a second cowling (14), and opposed upright sidewalls (16) that together form an internal nozzle exhaust path is provided. A reconfigurable plug assembly (18) having separable first and second diverters (20), (22) is located in the exhaust path to direct engine exhaust (24) in either dual paths formed around diverter outer surfaces (76), or dual paths formed between the diverter inner surfaces (74) and centerbody exterior surfaces. When the diverters direct exhaust airflow between themselves, first and second ejectors (26), (28) formed in the first and second cowlings (12), (14), respectively, are available to entrain ambient air (30) into the exhaust stream (24). The preferred ejectors include translatable aft flaps (32), (34). Mixing devices, such as a lobed mixer (90) are incorporated into the diverters (20), (22) to improve engine noise suppression.Type: GrantFiled: November 4, 1996Date of Patent: August 24, 1999Assignee: The Boeing CompanyInventors: Gary L. Lidstone, Larry T. Clark, Imre A. Szupkay, David L. Sandquist
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Patent number: 5884843Abstract: A moderately high bypass ratio turbofan engine nozzle (36) is provided including an outer structure (46) and one or more ejectors (38). The ejectors (38) include inner and outer doors (82), (80) for closing off an ejector passage (76) extending through the outer structure (46). The ejectors (38) are sized to entrain exterior air (40) at aspiration ratios of generally less than 60%. The exterior air (40) is mixed with engine exhaust (42), resulting in a lower combined airflow velocity which in turn reduces jet exhaust noise. Mixing components formed as turning vanes (108) are located in the ejector passage (76) for encouraging further mixing of the airflows (40), (42). In preferred embodiments, the nozzle (36) further includes a translatable centerbody (52), an aft flap assembly (112), and a control system (122) for controlling the movements of the nozzle components.Type: GrantFiled: November 4, 1996Date of Patent: March 23, 1999Assignee: The Boeing CompanyInventors: Gary L. Lidstone, Larry T. Clark, Imre A. Szupkay, David L. Sandquist
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Patent number: 5779150Abstract: An aircraft ejector nozzle includes a plug assembly (26) located between upper and lower cowlings (18, 20) and upright sidewalls (22). The plug assembly (26) includes separable upper and lower diverters (28, 30). Each diverter includes multiple subsections pivotably attached end-to-end. In one embodiment, first, second, and third subsections (90, 92, 94) are provided. Stationary ejectors (40, 42) located in the cowlings (18, 20) input ambient airflow (44) into an exhaust stream (32). Preferably the ejectors (40, 42) include mixing components (46). Upper and lower aft flaps (48, 50) further tailor the exhaust path shape. An actuation assembly (52) moves the diverters (28, 30) and aft flaps (48, 50) between their various positions. One actuation assembly embodiment includes a number of rotatable disks (118, 120, 132, 134, 142) for guiding the upper and lower diverters (28, 30) and the aft flaps (48, 50).Type: GrantFiled: October 1, 1996Date of Patent: July 14, 1998Assignee: The Boeing CompanyInventors: Gary L. Lidstone, David L. Sandquist, Larry T. Clark, Imre A. Szupkay
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Patent number: 5222359Abstract: A supersonic jet engine for improved noise abatement and thrust augmentation. There is an intake section, an engine, a mixing section, an exhaust section, and a secondary air passageway. Ambient air is directed into the engine and into the secondary air passageway. Exhaust from the engine and the secondary air are directed into primary and secondary segments to mix in a stream direction as supersonic flow. Selectively controllable primary bypass passageways are provided at the primary passageway segments and are operated to bypass the primary flow through the primary segments at times when greater primary flow area is required.Type: GrantFiled: June 28, 1991Date of Patent: June 29, 1993Assignee: The Boeing CompanyInventors: Garry W. Klees, Gary L. Lidstone, Mark L. Sloan