Patents by Inventor Russell H. Thomas
Russell H. Thomas 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: 9669921Abstract: An active pylon noise control system for an aircraft includes a pylon structure connecting an engine system with an airframe surface of the aircraft and having at least one aperture to supply a gas or fluid therethrough, an intake portion attached to the pylon structure to intake a gas or fluid, a regulator connected with the intake portion via a plurality of pipes, to regulate a pressure of the gas or fluid, a plenum chamber formed within the pylon structure and connected with the regulator, and configured to receive the gas or fluid as regulated by the regulator, and a plurality of injectors in communication with the plenum chamber to actively inject the gas or fluid through the plurality of apertures of the pylon structure.Type: GrantFiled: May 4, 2015Date of Patent: June 6, 2017Assignee: THE UNITED STATES OF AMERICA AS REPRESENTED BY THE ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATIONInventors: Russell H. Thomas, Michael J. Czech, Alaa A. Elmiligui
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Patent number: 9623952Abstract: Acoustic liners for aircraft noise reduction include one or more chambers that are configured to provide a pressure-release surface such that the engine noise generation process is inhibited and/or absorb sound by converting the sound into heat energy. The size and shape of the chambers can be selected to inhibit the noise generation process and/or absorb sound at selected frequencies.Type: GrantFiled: March 12, 2012Date of Patent: April 18, 2017Assignee: THE UNITED STATES OF AMERICA AS REPRESENTED BY THE ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATIONInventors: Michael G. Jones, Russell H. Thomas, Douglas M. Nark, Brian M. Howerton, Michael J. Czech
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Publication number: 20150232170Abstract: An active pylon noise control system for an aircraft includes a pylon structure connecting an engine system with an airframe surface of the aircraft and having at least one aperture to supply a gas or fluid therethrough, an intake portion attached to the pylon structure to intake a gas or fluid, a regulator connected with the intake portion via a plurality of pipes, to regulate a pressure of the gas or fluid, a plenum chamber formed within the pylon structure and connected with the regulator, and configured to receive the gas or fluid as regulated by the regulator, and a plurality of injectors in communication with the plenum chamber to actively inject the gas or fluid through the plurality of apertures of the pylon structure.Type: ApplicationFiled: May 4, 2015Publication date: August 20, 2015Inventors: Russell H. Thomas, Michael J. Czech, Alaa A. Elmiligui
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Patent number: 9022311Abstract: An active pylon noise control system for an aircraft includes a pylon structure connecting an engine system with an airframe surface of the aircraft and having at least one aperture to supply a gas or fluid therethrough, an intake portion attached to the pylon structure to intake a gas or fluid, a regulator connected with the intake portion via a plurality of pipes, to regulate a pressure of the gas or fluid, a plenum chamber formed within the pylon structure and connected with the regulator, and configured to receive the gas or fluid as regulated by the regulator, and a plurality of injectors in communication with the plenum chamber to actively inject the gas or fluid through the plurality of apertures of the pylon structure.Type: GrantFiled: August 22, 2011Date of Patent: May 5, 2015Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space AdministrationInventors: Russell H. Thomas, Michael J Czech, Alaa A. Elmiligui
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Patent number: 8876043Abstract: The aircraft exhaust engine nozzle system includes a fan nozzle to receive a fan flow from a fan disposed adjacent to an engine disposed above an airframe surface of the aircraft, a core nozzle disposed within the fan nozzle and receiving an engine core flow, and a pylon structure connected to the core nozzle and structurally attached with the airframe surface to secure the engine to the aircraft.Type: GrantFiled: August 22, 2011Date of Patent: November 4, 2014Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space AdministrationInventors: Russell H. Thomas, Michael J. Czech, Ronen Elkoby
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Patent number: 8651429Abstract: An aircraft system includes a wing and a trailing edge device coupled to the wing. The trailing edge device is movable relative to the wing, and includes a leading edge and a trailing edge having a center flap portion and a plurality of outer edge portions integrally combined with the center flap portion such that the center flap portion is shorter in width than that of outer edge portions.Type: GrantFiled: August 22, 2011Date of Patent: February 18, 2014Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space AdministrationInventors: Michael J Czech, Russell H. Thomas
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Patent number: 8157207Abstract: Nozzle exit configurations and associated systems and methods are disclosed. An aircraft system in accordance with one embodiment includes a jet engine exhaust nozzle having an internal flow surface and an exit aperture, with the exit aperture having a perimeter that includes multiple projections extending in an aft direction. Aft portions of individual neighboring projections are spaced apart from each other by a gap, and a geometric feature of the multiple can change in a monotonic manner along at least a portion of the perimeter. Projections near a support pylon and/or associated heat shield can have particular configurations, including greater flow immersion than other projections.Type: GrantFiled: August 9, 2007Date of Patent: April 17, 2012Assignees: The Boeing Company, The United States of America as Represented by the Administrator of the National Aeronautics and Space AdministrationInventors: Vinod G. Mengle, Russell H. Thomas
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Publication number: 20120068011Abstract: An active pylon noise control system for an aircraft includes a pylon structure connecting an engine system with an airframe surface of the aircraft and having at least one aperture to supply a gas or fluid therethrough, an intake portion attached to the pylon structure to intake a gas or fluid, a regulator connected with the intake portion via a plurality of pipes, to regulate a pressure of the gas or fluid, a plenum chamber formed within the pylon structure and connected with the regulator, and configured to receive the gas or fluid as regulated by the regulator, and a plurality of injectors in communication with the plenum chamber to actively inject the gas or fluid through the plurality of apertures of the pylon structure.Type: ApplicationFiled: August 22, 2011Publication date: March 22, 2012Applicant: U.S.A. as represented by the Administrator of the National Aeronautics and Space AdministrationInventors: Russell H. Thomas, Michael J. Czech, Alaa A. Elmiliqui
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Publication number: 20120061525Abstract: An aircraft system includes a wing and a trailing edge device coupled to the wing. The trailing edge device is movable relative to the wing, and includes a leading edge and a trailing edge having a center flap portion and a plurality of outer edge portions integrally combined with the center flap portion such that the center flap portion is shorter in width than that of outer edge portions.Type: ApplicationFiled: August 22, 2011Publication date: March 15, 2012Applicant: U.S.A. as represented by the Administrator of the National Aeronautics and Space AdministrationInventors: Michael J. Czech, Russell H. Thomas
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Publication number: 20120061510Abstract: The aircraft exhaust engine nozzle system includes a fan nozzle to receive a fan flow from a fan disposed adjacent to an engine disposed above an airframe surface of the aircraft, a core nozzle disposed within the fan nozzle and receiving an engine core flow, and a pylon structure connected to the core nozzle and structurally attached with the airframe surface to secure the engine to the aircraft.Type: ApplicationFiled: August 22, 2011Publication date: March 15, 2012Applicant: U.S.A. as represented by the Administrator of the National Aeronautics and Space AdministrationInventors: Russell H. Thomas, Michael J. Czech, Ronen Elkoby
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Patent number: 8015819Abstract: Disposed at or toward the trailing edge of one or more nozzles associated with a jet engine are injection ports which can selectively be made to discharge a water stream into a nozzle flow stream for the purpose of increasing turbulence in somewhat of a similar fashion as mechanically disposed chevrons have done in the known art. Unlike mechanically disposed chevrons of the known art, the fluid flow may be secured thereby increasing the engine efficiency. Various flow patterns, water pressures, orifice designs or other factors can be made operative to provide desired performance characteristics.Type: GrantFiled: September 29, 2006Date of Patent: September 13, 2011Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space AdministrationInventors: Russell H. Thomas, Kevin W. Kinzie
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Publication number: 20080272228Abstract: Nozzle exit configurations and associated systems and methods are disclosed. An aircraft system in accordance with one embodiment includes a jet engine exhaust nozzle having an internal flow surface and an exit aperture, with the exit aperture having a perimeter that includes multiple projections extending in an aft direction. Aft portions of individual neighboring projections are spaced apart from each other by a gap, and a geometric feature of the multiple can change in a monotonic manner along at least a portion of the perimeter. Projections near a support pylon and/or associated heat shield can have particular configurations, including greater flow immersion than other projections.Type: ApplicationFiled: August 9, 2007Publication date: November 6, 2008Applicant: The Boeing CompanyInventors: Vinod G. Mengle, Russell H. Thomas
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Publication number: 20080078159Abstract: Disposed at or toward the trailing edge of one or more nozzles associated with a jet engine are injection ports which can selectively be made to discharge a water stream into a nozzle flow stream for the purpose of increasing turbulence in somewhat of a similar fashion as mechanically disposed chevrons have done in the known art. Unlike mechanically disposed chevrons of the known art, the fluid flow may be secured thereby increasing the engine efficiency. Various flow patterns, water pressures, orifice designs or other factors can be made operative to provide desired performance characteristics.Type: ApplicationFiled: September 29, 2006Publication date: April 3, 2008Applicants: Space AdministrationInventors: Russell H. Thomas, Kevin W. Kinzie
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Patent number: 5662136Abstract: Reduction or cancellation of acoustic noise is achieved by providing an amplified, oppositely phased version of the noise by means of an acousto-fluidic amplifier. The amplified acoustic output noise is delivered through an impedance matching horn in destructively interfering relation with the original noise. Depending on the acoustic noise source and its spatial distribution, the acousto-fluidic amplifier may be a single stage amplifier or multiple stages connected in parallel and/or cascade, with output horns spatially distributed to have the maximum cancellation effect. Sensed noise, prior to fluidic amplification, may be processed in a manner to effect feedback or feedforward control of the amplified acoustic output signals.Type: GrantFiled: September 11, 1995Date of Patent: September 2, 1997Assignees: Defense Research Technologies, Inc., Virginia Tech Intellectual Properties, Inc.Inventors: Tadeusz M. Drzewiecki, John B. Niemczuk, Christopher R. Fuller, Russell H. Thomas, Ricardo A. Burdisso
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Patent number: 5515444Abstract: An active noise control system using a compact sound source is effective to reduce aircraft engine duct noise. The fan noise from a turbofan engine is controlled using an adaptive filtered-x LMS algorithm. Single multi channel control systems are used to control the fan blade passage frequency (BPF) tone and the BPF tone and the first harmonic of the BPF tone for a plane wave excitation. A multi channel control system is used to control any spinning mode. The multi channel control system to control both fan tones and a high pressure compressor BPF tone simultaneously. In order to make active control of turbofan inlet noise a viable technology, a compact sound source is employed to generate the control field. This control field sound source consists of an array of identical thin, cylindrically curved panels with an inner radius of curvature corresponding to that of the engine inlet.Type: GrantFiled: October 7, 1994Date of Patent: May 7, 1996Assignees: Virginia Polytechnic Institute and State University, Virginia Tech Intellectual Properties, The Center for Innovative TechnologyInventors: Ricardo Burdisso, Chris R. Fuller, Walter F. O'Brien, Russell H. Thomas, Mary E. Dungan
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Patent number: 5355417Abstract: An active noise control system using a compact sound source is effective to reduce aircraft engine duct noise. The fan noise from a turbofan engine is controlled using an adaptive filtered-x LMS algorithm. Single multi channel control systems are used to control the fan blade passage frequency (BPF) tone and the BPF tone and the first harmonic of the BPF tone for a plane wave excitation. A multi channel control system is used to control any spinning mode. The multi channel control system to control both fan tones and a high pressure compressor BPF tone simultaneously. In order to make active control of turbofan inlet noise a viable technology, a compact sound source is employed to generate the control field. This control field sound source consists of an array of identical thin, cylindrically curved panels with an inner radius of curvature corresponding to that of the engine inlet.Type: GrantFiled: October 21, 1992Date of Patent: October 11, 1994Assignees: The Center for Innovative Technology, Virginia Polytechnic Institute & State University, Virginia Tech Intellectual Properties, Inc.Inventors: Ricardo Burdisso, Chris R. Fuller, Walter F. O'Brien, Russell H. Thomas, Mary E. Dungan