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).

  • Patent number: 9669921
    Abstract: 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: Grant
    Filed: May 4, 2015
    Date of Patent: June 6, 2017
    Assignee: THE UNITED STATES OF AMERICA AS REPRESENTED BY THE ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION
    Inventors: Russell H. Thomas, Michael J. Czech, Alaa A. Elmiligui
  • Patent number: 9623952
    Abstract: 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: Grant
    Filed: March 12, 2012
    Date of Patent: April 18, 2017
    Assignee: THE UNITED STATES OF AMERICA AS REPRESENTED BY THE ADMINISTRATOR OF THE NATIONAL AERONAUTICS AND SPACE ADMINISTRATION
    Inventors: Michael G. Jones, Russell H. Thomas, Douglas M. Nark, Brian M. Howerton, Michael J. Czech
  • Publication number: 20150232170
    Abstract: 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: Application
    Filed: May 4, 2015
    Publication date: August 20, 2015
    Inventors: Russell H. Thomas, Michael J. Czech, Alaa A. Elmiligui
  • Patent number: 9022311
    Abstract: 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: Grant
    Filed: August 22, 2011
    Date of Patent: May 5, 2015
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventors: Russell H. Thomas, Michael J Czech, Alaa A. Elmiligui
  • Patent number: 8876043
    Abstract: 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: Grant
    Filed: August 22, 2011
    Date of Patent: November 4, 2014
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventors: Russell H. Thomas, Michael J. Czech, Ronen Elkoby
  • Patent number: 8651429
    Abstract: 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: Grant
    Filed: August 22, 2011
    Date of Patent: February 18, 2014
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventors: Michael J Czech, Russell H. Thomas
  • Patent number: 8157207
    Abstract: 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: Grant
    Filed: August 9, 2007
    Date of Patent: April 17, 2012
    Assignees: The Boeing Company, The United States of America as Represented by the Administrator of the National Aeronautics and Space Administration
    Inventors: Vinod G. Mengle, Russell H. Thomas
  • Publication number: 20120068011
    Abstract: 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: Application
    Filed: August 22, 2011
    Publication date: March 22, 2012
    Applicant: U.S.A. as represented by the Administrator of the National Aeronautics and Space Administration
    Inventors: Russell H. Thomas, Michael J. Czech, Alaa A. Elmiliqui
  • Publication number: 20120061525
    Abstract: 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: Application
    Filed: August 22, 2011
    Publication date: March 15, 2012
    Applicant: U.S.A. as represented by the Administrator of the National Aeronautics and Space Administration
    Inventors: Michael J. Czech, Russell H. Thomas
  • Publication number: 20120061510
    Abstract: 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: Application
    Filed: August 22, 2011
    Publication date: March 15, 2012
    Applicant: U.S.A. as represented by the Administrator of the National Aeronautics and Space Administration
    Inventors: Russell H. Thomas, Michael J. Czech, Ronen Elkoby
  • Patent number: 8015819
    Abstract: 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: Grant
    Filed: September 29, 2006
    Date of Patent: September 13, 2011
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventors: Russell H. Thomas, Kevin W. Kinzie
  • Publication number: 20080272228
    Abstract: 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: Application
    Filed: August 9, 2007
    Publication date: November 6, 2008
    Applicant: The Boeing Company
    Inventors: Vinod G. Mengle, Russell H. Thomas
  • Publication number: 20080078159
    Abstract: 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: Application
    Filed: September 29, 2006
    Publication date: April 3, 2008
    Applicants: Space Administration
    Inventors: Russell H. Thomas, Kevin W. Kinzie
  • Patent number: 5662136
    Abstract: 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: Grant
    Filed: September 11, 1995
    Date of Patent: September 2, 1997
    Assignees: 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
  • Patent number: 5515444
    Abstract: 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: Grant
    Filed: October 7, 1994
    Date of Patent: May 7, 1996
    Assignees: Virginia Polytechnic Institute and State University, Virginia Tech Intellectual Properties, The Center for Innovative Technology
    Inventors: Ricardo Burdisso, Chris R. Fuller, Walter F. O'Brien, Russell H. Thomas, Mary E. Dungan
  • Patent number: 5355417
    Abstract: 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: Grant
    Filed: October 21, 1992
    Date of Patent: October 11, 1994
    Assignees: 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