Patents by Inventor Mark Cunningham

Mark Cunningham 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).

  • Publication number: 20250116229
    Abstract: A system is provided for an aircraft. This aircraft system includes an aircraft engine, an inlet guard and an actuation system. The aircraft engine has a flowpath projecting into the aircraft engine from an airflow inlet. The inlet guard is arranged at the airflow inlet and extends across the flowpath. The inlet guard includes a first screen, a second screen and a plurality of perforations. The first screen is adjacent and overlaps the second screen. The perforations project through the inlet guard and are formed by the first screen and the second screen. The actuation system is configured to move the first screen along the second screen. The movement of the first screen along the second screen changes a geometry of each of the perforations.
    Type: Application
    Filed: October 5, 2023
    Publication date: April 10, 2025
    Inventors: Eray Akcayoz, Mark Cunningham, Roberto Marrano, Corentin Brette
  • Publication number: 20250115366
    Abstract: A system is provided for an aircraft. This aircraft system includes a gas turbine engine, a flowpath and an inlet guard. The gas turbine engine includes a compressor section. The flowpath projects longitudinally into the gas turbine engine from an airflow inlet and longitudinally through the compressor section. The inlet guard extends across the flowpath longitudinally upstream of the compressor section. The inlet guard extends circumferentially about an axis. The inlet guard includes a first screen and a second screen. The first screen includes a plurality of first perforations with a first perforation size. The second screen is circumferentially adjacent the first screen about the axis. The second screen includes a plurality of second perforations with a second perforation size that is different than the first perforation size.
    Type: Application
    Filed: October 5, 2023
    Publication date: April 10, 2025
    Inventors: Mark Cunningham, Eray Akcayoz, Roberto Marrano, Corentin Brette
  • Publication number: 20250116230
    Abstract: A system for an aircraft includes an aircraft engine having a central axis with a flowpath projecting into the aircraft engine from an airflow inlet. An inlet plenum at the airflow inlet extends between a front wall and a rear wall along the central axis. An inlet guard is arranged at the airflow inlet and extends across the flowpath. The inlet guard includes a first screen extending circumferentially about the central axis and axially from the front wall to the rear wall, and a second screen radially outward of the first screen and axially overlapping the first screen. An actuator is operable to move the first screen and the second screen relative to one another in one or more of a radial, axial and circumferential direction to shed ice from the inlet guard.
    Type: Application
    Filed: October 5, 2023
    Publication date: April 10, 2025
    Inventors: Roberto MARRANO, Mark CUNNINGHAM, Eray AKCAYOZ, Corentin BRETTE
  • Patent number: 12241412
    Abstract: A system for an aircraft includes an aircraft engine having a central axis with a flowpath projecting into the aircraft engine from an airflow inlet. An inlet plenum at the airflow inlet extends between a front wall and a rear wall along the central axis. An inlet guard is arranged at the airflow inlet and extends across the flowpath. The inlet guard includes a first screen extending circumferentially about the central axis. The first screen has a first screen axial width L1 extending from the front wall to the rear wall. The inlet guard further includes a second screen extending at least partially circumferentially about the central axis. The second screen is disposed radially outward of the first screen and axially overlaps the first screen. The second screen has a second screen axial width L2 less than the first screen axial width L1.
    Type: Grant
    Filed: October 5, 2023
    Date of Patent: March 4, 2025
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Roberto Marrano, Mark Cunningham, Eray Akcayoz, Corentin Brette
  • Publication number: 20250051029
    Abstract: A method of operation is provided during which rotation of a propulsor rotor of an aircraft is driven using mechanical power output from a powerplant. The powerplant includes a heat engine and an electric machine. The heat engine provides a first portion of the mechanical power. The electric machine provides a second portion of the mechanical power. An operational temperature of the heat engine is regulated by controlling the first portion of the mechanical power generated by the heat engine and the second portion of the mechanical power generated by the electric machine.
    Type: Application
    Filed: August 11, 2023
    Publication date: February 13, 2025
    Inventors: Trevor T. Ricci, Frank Paoletti, Mark Cunningham
  • Patent number: 12161716
    Abstract: An anti-IL-23 antibody, including isolated nucleic acids that encode at least one anti-IL-23 antibody, vectors, host cells, transgenic animals or plants, and methods of making and using thereof have applications in diagnostic and/or therapeutic compositions, methods and devices.
    Type: Grant
    Filed: November 9, 2021
    Date of Patent: December 10, 2024
    Assignee: Janssen Biotech, Inc.
    Inventors: Jacquelne Benson, Mark Cunningham, Cynthia Duchala, Jill Giles-Komar, Jinquan Luo, Michael Rycyzyn, Raymond Sweet
  • Patent number: 12163486
    Abstract: An exhaust mixer assembly for a gas turbine engine includes a core passage extending along a central engine axis for directing a core gas flow. An outer annular passage coaxially surrounds the core passage for directing a bypass gas flow. An exhaust mixer communicating with the core passage and outer annular passages has an upstream end, a downstream end and an annular wall extending therebetween. The annular wall defines a mixing plane at a trailing edge thereof at the downstream end at which the core and bypass gas flows are mixed. The annular wall has a radially inner surface and a radially outer surface. A plurality of protrusions are disposed on and extend laterally along and radially from at the radially inner surface and/or the radially outer surface. The plurality of protrusions are arranged one alongside another on the radially inner surface and/or the radially outer surface.
    Type: Grant
    Filed: January 10, 2023
    Date of Patent: December 10, 2024
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Metin Ilbay Yaras, Mark Cunningham, Raja Ramamurthy
  • Patent number: 12129293
    Abstract: A human anti-IL-23p19 antibody, including isolated nucleic acids that encode at least one anti-IL-23p19 antibody, vectors, host cells, and methods of making and using thereof have applications in diagnostic and/or therapeutic compositions, methods and devices.
    Type: Grant
    Filed: February 22, 2021
    Date of Patent: October 29, 2024
    Assignee: Janssen Biotech, Inc.
    Inventors: Jacqueline Benson, Jill Carton, Mark Cunningham, Yevgeniya Orlovsky, Robert Rauchenberger, Raymond Sweet
  • Publication number: 20240254942
    Abstract: An exhaust duct of an aircraft engine includes an annular inlet conduit having an inlet central axis, and at least two outlet conduits in flow communication with the inlet conduit. The at least two outlet conduits are located non-parallel to the inlet central axis. Each of the at least two outlet conduits include an outlet port defining a distal end of each of the two outlet conduits. At least one of the outlet ports is non-circular in cross-sectional shape.
    Type: Application
    Filed: March 1, 2024
    Publication date: August 1, 2024
    Inventors: Eray Akcayoz, Mark Cunningham
  • Publication number: 20240229740
    Abstract: An exhaust mixer assembly for a gas turbine engine includes a core passage extending along a central engine axis for directing a core gas flow. An outer annular passage coaxially surrounds the core passage for directing a bypass gas flow. An exhaust mixer communicating with the core passage and outer annular passages has an upstream end, a downstream end and an annular wall extending therebetween. The annular wall defines a mixing plane at a trailing edge thereof at the downstream end at which the core and bypass gas flows are mixed. The annular wall has a radially inner surface and a radially outer surface. A plurality of protrusions are disposed on and extend laterally along and radially from at the radially inner surface and/or the radially outer surface. The plurality of protrusions are arranged one alongside another on the radially inner surface and/or the radially outer surface.
    Type: Application
    Filed: January 10, 2023
    Publication date: July 11, 2024
    Inventors: Metin Ilbay YARAS, Mark CUNNINGHAM, Raja RAMAMURTHY
  • Publication number: 20240230089
    Abstract: An exhaust mixer assembly for a gas turbine engine includes a core passage extending along a central engine axis for directing a core gas flow. An outer annular passage coaxially surrounds the core passage for directing a bypass gas flow. An exhaust mixer communicating with the core passage and the outer annular passage has an upstream end, a downstream end and an annular wall extending therebetween. A plurality of protrusions extend axially from a downstream end of the annular wall to form a jagged trailing edge of the exhaust mixer. Each of the plurality of protrusions extend separately from the downstream end of the annular wall from the other of the plurality of protrusions. At least one of the plurality of protrusions is twisted about a protrusion axis extending through the at least one of the plurality of protrusions, the protrusion axis parallel to the central axis.
    Type: Application
    Filed: January 10, 2023
    Publication date: July 11, 2024
    Inventors: Metin Ilbay YARAS, Mark CUNNINGHAM, Raja RAMAMURTHY
  • Patent number: 12018615
    Abstract: An air intake for an aircraft propulsion system includes an air inlet duct, a core flow duct, a bypass flow duct, and a flow control device. The air inlet duct includes an intake inlet of the air intake. The core flow duct includes a core flow outlet. The core flow duct extends between and to the air inlet duct and the core flow outlet. The bypass flow duct includes a bypass flow outlet. The bypass flow duct extends between and to the air inlet duct and the bypass flow outlet. The bypass flow duct includes an interior surface forming and surrounding a bypass flow passage through the bypass flow duct. The flow control device is disposed on the interior surface. The flow control device is configured to variably control an area of a cross-sectional flow area of the bypass flow passage.
    Type: Grant
    Filed: October 31, 2022
    Date of Patent: June 25, 2024
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Eray Akcayoz, Mark Cunningham, Raja Ramamurthy, Roberto Marrano
  • Publication number: 20240199733
    Abstract: A human anti-IL-23p19 antibody, including isolated nucleic acids that encode at least one anti-IL-23p19 antibody, vectors, host cells, and methods of making and using thereof have applications in diagnostic and/or therapeutic compositions, methods and devices.
    Type: Application
    Filed: February 16, 2024
    Publication date: June 20, 2024
    Inventors: Jacqueline Benson, Jill Carton, Mark Cunningham, Yevgeniya Orlovsky, Robert Pauchenberger, Raymond Sweet
  • Patent number: 12000358
    Abstract: An engine nacelle assembly includes a nacelle that defines a flow path between an intake end and an exhaust end, and a nozzle that is disposed at the exhaust end of the nacelle about a central axis. The nozzle includes opposing thrust reverser openings and thrust reverser doors. A cross-sectional area transverse to the central axis proximate a forward side of each of the opposing thrust reverser openings is oval shaped with an offset radius within offset arc segments that are aligned with the opposing thrust reverser openings and a first radius outside of the offset arc segment. The first radius is less than the offset radius.
    Type: Grant
    Filed: February 14, 2023
    Date of Patent: June 4, 2024
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Mark Cunningham, Eray Akcayoz
  • Patent number: 11994064
    Abstract: An air intake for an aircraft propulsion system includes an air inlet duct and a flow control device. The air inlet duct includes an interior surface and an intake inlet. The interior surface extends from the intake inlet. The interior surface forms and surrounds an inlet flow passage through the air inlet duct. The intake inlet includes a top side, a bottom side, a first lateral side, and a second lateral side. Each of the first lateral side and the second lateral side extend between and to the top side and the bottom side. The flow control device is disposed inside the air inlet duct at the first lateral side. The flow control device is configured to form an asymmetrical shape of the intake inlet at the first lateral side relative to the second lateral side.
    Type: Grant
    Filed: October 31, 2022
    Date of Patent: May 28, 2024
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Mark Cunningham, Eray Akcayoz, Raja Ramamurthy, Roberto Marrano
  • Publication number: 20240141832
    Abstract: An air intake for an aircraft propulsion system includes an air inlet duct and a flow control device. The air inlet duct includes an interior surface and an intake inlet. The interior surface extends from the intake inlet. The interior surface forms and surrounds an inlet flow passage through the air inlet duct. The intake inlet includes a top side, a bottom side, a first lateral side, and a second lateral side. Each of the first lateral side and the second lateral side extend between and to the top side and the bottom side. The flow control device is disposed inside the air inlet duct at the first lateral side. The flow control device is configured to form an asymmetrical shape of the intake inlet at the first lateral side relative to the second lateral side.
    Type: Application
    Filed: October 31, 2022
    Publication date: May 2, 2024
    Inventors: Mark Cunningham, Eray Akcayoz, Raja Ramamurthy, Roberto Marrano
  • Publication number: 20240141833
    Abstract: An air intake for an aircraft propulsion system includes an air inlet duct, a core flow duct, a bypass flow duct, and a flow control device. The air inlet duct includes an intake inlet of the air intake. The core flow duct includes a core flow outlet. The core flow duct extends between and to the air inlet duct and the core flow outlet. The bypass flow duct includes a bypass flow outlet. The bypass flow duct extends between and to the air inlet duct and the bypass flow outlet. The bypass flow duct includes an interior surface forming and surrounding a bypass flow passage through the bypass flow duct. The flow control device is disposed on the interior surface. The flow control device is configured to variably control an area of a cross-sectional flow area of the bypass flow passage.
    Type: Application
    Filed: October 31, 2022
    Publication date: May 2, 2024
    Inventors: Eray Akcayoz, Mark Cunningham, Raja Ramamurthy, Roberto Marrano
  • Patent number: 11965460
    Abstract: An air intake for an aircraft propulsion system includes an air inlet duct, a core flow duct, a bypass flow duct, a splitter, and a flow control device. The air inlet duct includes an intake inlet and a gas path floor. The core flow duct includes a core flow outlet. The bypass flow duct includes a bypass flow outlet. The bypass flow duct includes the gas path floor. The splitter separates the core flow duct and the bypass flow duct. The flow control device is disposed on a portion of the gas path floor. The flow control device is configured to be selectively positioned to control an air flow path for air flowing through the air inlet duct, the core flow duct, and the bypass flow duct.
    Type: Grant
    Filed: October 31, 2022
    Date of Patent: April 23, 2024
    Assignee: Pratt & Whitney Canada Corp.
    Inventors: Raja Ramamurthy, Eray Akcayoz, Mark Cunningham, Roberto Marrano
  • Patent number: 11952962
    Abstract: An exhaust duct of an aircraft engine includes an annular inlet conduit having an inlet central axis, and at least two outlet conduits in flow communication with the inlet conduit. The at least two outlet conduits are located non-parallel to the inlet central axis. Each of the at least two outlet conduits include an outlet port defining a distal end of each of the two outlet conduits. At least one of the outlet ports is non-circular in cross-sectional shape.
    Type: Grant
    Filed: January 31, 2023
    Date of Patent: April 9, 2024
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Eray Akcayoz, Mark Cunningham
  • Patent number: 11939876
    Abstract: A system is provided for an aircraft. This aircraft system includes a gas turbine engine and a sensor system. The gas turbine engine includes an inlet and a compressor section. A flowpath projects radially inward into the gas turbine engine from the inlet and extends through the compressor section. The sensor system includes a plurality of static pressure sensors at least partially within the flowpath. The sensor system is configured to determine a total pressure characteristic within the flowpath using the plurality of static pressure sensors.
    Type: Grant
    Filed: July 29, 2022
    Date of Patent: March 26, 2024
    Assignee: PRATT & WHITNEY CANADA CORP.
    Inventors: Damien Le Pape, Mark Cunningham