Patents by Inventor Trajaen J. Troia

Trajaen J. Troia 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: 10006833
    Abstract: A method for optimizing size and position parameters of an array of vortex generator blades configured on an offset diffuser in an inlet of an aircraft engine. The method includes providing a computational fluid dynamic analysis of air flowing through the diffuser that identifies a height of a local boundary layer at a plurality of positions across the diffuser substantially parallel to the flow of air and a flow velocity vector at each of the plurality of positions at one half of a height of the local boundary layer. The method also includes determining an angle orientation of the blades using the boundary layer height and the flow vector, determining the length and height of the blades using the boundary layer height, and determining the number and spacing of the blades using the width of the diffuser.
    Type: Grant
    Filed: August 24, 2016
    Date of Patent: June 26, 2018
    Assignee: Northrop Grumman Systems Corporation
    Inventors: Nicholas V. Caldwell, Trajaen J. Troia, Richard Crouse
  • Patent number: 9758253
    Abstract: A swept gradient air boundary layer diverter for an aircraft. The aircraft includes a fuselage and an air inlet for an engine of the aircraft, where the air inlet includes a cowl at a leading edge of the inlet. The diverter includes a V-shaped ramp portion formed in the fuselage in an area proximate to and in front of the cowl where the ramp portion extends downward away from an outer surface of the fuselage towards an inside of the aircraft. The diverter also includes a V-shaped trough portion formed into the fuselage and being positioned adjacent to and integral with the ramp portion between the ramp portion and the air inlet. Air flowing over the fuselage towards the cowl is expanded and compressed by the ramp portion and the trough portion so as to create pressure gradients that generate vortices to redirect boundary layer airflow around the air inlet.
    Type: Grant
    Filed: June 25, 2015
    Date of Patent: September 12, 2017
    Assignee: Northrop Grumman Systems Corporation
    Inventors: Trajaen J. Troia, John F. Mangus
  • Patent number: 9752453
    Abstract: The present invention relates to a mechanical system that modulates airflow in an aircraft inlet diffuser that is used in conjunction with an aircraft engine that integrates both a center turbine engine and a high Mach engine such as a constant volume combustor (CVC) arrangement or ramjet arrangement with intakes formed co-centrically about the turbine. The modulation system uses an articulating cone. When in a retracted position the articulating cone allows the aircraft to operate in low speed mode as only the turbo jet receives airflow. At its widest expanse, the articulating cone completely covers the turbo jet circular intake face, precluding operation of the turbine engine.
    Type: Grant
    Filed: July 7, 2015
    Date of Patent: September 5, 2017
    Assignee: NORTHROP GRUMMAN SYSTEMS CORPORATION
    Inventors: George D. Rupp, Trajaen J. Troia
  • Publication number: 20160376018
    Abstract: A swept gradient air boundary layer diverter for an aircraft. The aircraft includes a fuselage and an air inlet for an engine of the aircraft, where the air inlet includes a cowl at a leading edge of the inlet. The diverter includes a V-shaped ramp portion formed in the fuselage in an area proximate to and in front of the cowl where the ramp portion extends downward away from an outer surface of the fuselage towards an inside of the aircraft. The diverter also includes a V-shaped trough portion formed into the fuselage and being positioned adjacent to and integral with the ramp portion between the ramp portion and the air inlet. Air flowing over the fuselage towards the cowl is expanded and compressed by the ramp portion and the trough portion so as to create pressure gradients that generate vortices to redirect boundary layer airflow around the air inlet.
    Type: Application
    Filed: June 25, 2015
    Publication date: December 29, 2016
    Inventors: TRAJAEN J. TROIA, JOHN F. MANGUS
  • Patent number: 9353684
    Abstract: The present invention relates to a system and method of LO airflow modulation for use with a DTSA engine. A DTSA engine is positioned within an aircraft fuselage and the second DTSA turbine fan includes it own dedicated decoupled air inlet duct that is formed co-centrically about the housing. An airflow modulator member is positioned in duct to form the duct wall when the modulator is in a closed position. The Modulator member is pivotally connected to the duct wall, and is movable by an actuator to a second open position that allows airflow to escape the third stream duct, and provide airflow to both the DTSA fan blades as well as engine bay for cooling. The method of the present invention provides airflow modulation to an aircraft employing a DTSA engine, said method including the receiving of airflow from a supersonic aircraft intake; sensing a number of parameters, including, but not limited to aircraft speed, temperature, engine load and/or altitude.
    Type: Grant
    Filed: December 11, 2009
    Date of Patent: May 31, 2016
    Assignee: Northrop Grumman Systems Corporation
    Inventors: George D. Rupp, Trajaen J. Troia
  • Publication number: 20150377060
    Abstract: The present invention relates to a mechanical system that modulates airflow in an aircraft inlet diffuser that is used in conjunction with an aircraft engine that integrates both a center turbine engine and a high Mach engine such as a constant volume combustor (CVC) arrangement or ramjet arrangement with intakes formed co-centrically about the turbine. The modulation system uses an articulating cone. When in a retracted position the articulating cone allows the aircraft to operate in low speed mode as only the turbo jet receives airflow. At its widest expanse, the articulating cone completely covers the turbo jet circular intake face, precluding operation of the turbine engine.
    Type: Application
    Filed: July 7, 2015
    Publication date: December 31, 2015
    Inventors: George D. Rupp, Trajaen J. Troia
  • Patent number: 9103280
    Abstract: The present invention relates to a mechanical system and method that modulates airflow in an aircraft inlet diffuser that is used in conjunction with an aircraft engine that integrates both a center turbine engine and a high Mach engine such as a constant volume combustor (CVC) arrangement or ramjet arrangement with intakes formed co-centrically about the turbine. The modulation system uses two articulating components, a movable air flow duct and an articulating cone. The air flow duct, in a first position, is in exclusive air flow communication with the circular intake face of the turbine in a first position to receive air from the intake diffuser. In this configuration the expandable cone is in a retracted position and does not redirect airflow and allows the aircraft to operates in low speed mode as only the turbo jet receives airflow. In a transition speed mode, the air flow duct is retracted to allow air flow to both the turbo jet and the CVC.
    Type: Grant
    Filed: February 28, 2013
    Date of Patent: August 11, 2015
    Assignee: Northrop Grumman Systems Corporation
    Inventors: George D. Rupp, Trajaen J. Troia
  • Patent number: 9009966
    Abstract: The construction of an internal/external single expansion ramp nozzle (nxSERN), and method of designing the same, is provided. Initial design parameters for primary stream construction are selected and additional parameters are determined by isentropic relations using the selected design parameters and Prandtl-Meyer function. The nozzle throat input and output angles are determined and used to define an initial portion of the nozzle primary stream lower expansion surface. The nozzle primary stream upper expansion surface and an aft portion of the primary stream lower expansion surface are defined using a method of characteristics. Initial and aft portions of the primary stream lower expansion surface are then connected by a straight line to define the primary stream nozzle.
    Type: Grant
    Filed: March 15, 2013
    Date of Patent: April 21, 2015
    Assignee: Northrop Gurmman Systems Corporation
    Inventors: Shane Bunnag, Gordon Hall, Kelly Strominger, John Tapee, Trajaen J. Troia
  • Patent number: 8429893
    Abstract: The present invention relates to a mechanical system and method that modulates airflow in an aircraft inlet diffuser that is used in conjunction with an aircraft engine that integrates both a center turbine engine and a high Mach engine such as a constant volume combustor (CVC) arrangement or ramjet arrangement with intakes formed co-centrically about the turbine. The modulation system uses two articulating components, a movable air flow duct and an articulating cone. The air flow duct, in a first position, is in exclusive air flow communication with the circular intake face of the turbine in a first position to receive air from the intake diffuser. In this configuration the expandable cone is in a retracted position and does not redirect airflow and allows the aircraft to operates in low speed mode as only the turbo jet receives airflow. In a transition speed mode, the air flow duct is retracted to allow air flow to both the turbo jet and the CVC.
    Type: Grant
    Filed: August 11, 2009
    Date of Patent: April 30, 2013
    Assignee: Northrop Grumman Corporation
    Inventors: George D Rupp, Trajaen J. Troia
  • Publication number: 20110138814
    Abstract: The present invention relates to a system and method of LO airflow modulation for use with a DTSA engine. A DTSA engine is positioned within an aircraft fuselage and the second DTSA turbine fan includes it own dedicated decoupled air inlet duct that is formed co-centrically about the housing. An airflow modulator member is positioned in duct to form the duct wall when the modulator is in a closed position. The Modulator member is pivotally connected to the duct wall, and is movable by an actuator to a second open position that allows airflow to escape the third stream duct, and provide airflow to both the DTSA fan blades as well as engine bay for cooling. The method of the present invention provides airflow modulation to an aircraft employing a DTSA engine, said method including the receiving of airflow from a supersonic aircraft intake; sensing a number of parameters, including, but not limited to aircraft speed, temperature, engine load and/or altitude.
    Type: Application
    Filed: December 11, 2009
    Publication date: June 16, 2011
    Inventors: George D. Rupp, Trajaen J. Troia
  • Publication number: 20110036067
    Abstract: The present invention relates to a mechanical system and method that modulates airflow in an aircraft inlet diffuser that is used in conjunction with an aircraft engine that integrates both a center turbine engine and a high Mach engine such as a constant volume combustor (CVC) arrangement or ramjet arrangement with intakes formed co-centrically about the turbine. The modulation system uses two articulating components, a movable air flow duct and an articulating cone. The air flow duct, in a first position, is in exclusive air flow communication with the circular intake face of the turbine in a first position to receive air from the intake diffuser. In this configuration the expandable cone is in a retracted position and does not redirect airflow and allows the aircraft to operates in low speed mode as only the turbo jet receives airflow. In a transition speed mode, the air flow duct is retracted to allow air flow to both the turbo jet and the CVC.
    Type: Application
    Filed: August 11, 2009
    Publication date: February 17, 2011
    Inventors: George D. Rupp, Trajaen J. Troia