Patents by Inventor Andre M. Hall

Andre M. Hall 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).

  • Variable area fan nozzle for gas turbine engine
    Patent number: 10808648
    Abstract: A nacelle assembly according to an exemplary aspect of the present disclosure includes, among other things, a core nacelle defined at least partially about a core engine, a fan nacelle mounted at least partially around the core nacelle to define a fan bypass flow path, and a variable area fan nozzle in communication with the fan bypass flow path. The variable area fan nozzle has a first fan nacelle section and a second fan nacelle section downstream of the first fan nacelle section. The first fan nacelle section and the second fan nacelle section are axially movable relative to one another to define an auxiliary port to vary a fan nozzle exit area and adjust fan bypass airflow. The auxiliary port is defined between the first fan nacelle section and the second fan nacelle section. The first fan nacelle section comprises a first acoustic system which provides an acoustic impedance configured to attenuate a noise characterized by a leading edge of the second fan nacelle section.
    Type: Grant
    Filed: August 29, 2014
    Date of Patent: October 20, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Jonathan Gilson, Andre M. Hall, Oliver V. Atassi, Ramons A. Reba
  • Gas turbine engine with variable area fan nozzle
    Patent number: 8997497
    Abstract: A bypass gas turbine engine includes a variable area fan nozzle with a second fan nacelle section axially movable relative to a first fan nacelle section to define an auxiliary port to vary a fan nozzle exit area and adjust fan bypass airflow. The second fan nacelle section includes a leading edge region that defines a concave external contour and the first fan nacelle section includes a trailing edge region that defines a convex internal contour.
    Type: Grant
    Filed: October 29, 2010
    Date of Patent: April 7, 2015
    Assignee: United Technologies Corporation
    Inventors: Andre M. Hall, Gregory A. Kohlenberg, Jonathan Gilson
  • CROSS REFERENCE TO RELATED APPLICATIONS
    Publication number: 20140366554
    Abstract: A nacelle assembly according to an exemplary aspect of the present disclosure includes, among other things, a core nacelle defined at least partially about a core engine, a fan nacelle mounted at least partially around the core nacelle to define a fan bypass flow path, and a variable area fan nozzle in communication with the fan bypass flow path. The variable area fan nozzle has a first fan nacelle section and a second fan nacelle section downstream of the first fan nacelle section. The first fan nacelle section and the second fan nacelle section are axially movable relative to one another to define an auxiliary port to vary a fan nozzle exit area and adjust fan bypass airflow. The auxiliary port is defined between the first fan nacelle section and the second fan nacelle section. The first fan nacelle section comprises a first acoustic system which provides an acoustic impedance configured to attenuate a noise characterized by a leading edge of the second fan nacelle section.
    Type: Application
    Filed: August 29, 2014
    Publication date: December 18, 2014
    Inventors: Jonathan Gilson, Andre M. Hall, Oliver V. Atassi, Ramons A. Reba
  • Variable area fan nozzle with acoustic system for a gas turbine engine
    Patent number: 8820088
    Abstract: A high-bypass gas turbine engine includes a variable area fan nozzle with an acoustic system having an acoustic impedance.
    Type: Grant
    Filed: July 27, 2010
    Date of Patent: September 2, 2014
    Assignee: United Technologies Corporation
    Inventors: Jonathan Gilson, Andre M. Hall, Oliver V. Atassi, Ramons A. Reba
  • Gas turbine engine with noise attenuating variable area fan nozzle
    Patent number: 8800261
    Abstract: A bypass gas turbine engine includes a variable area fan nozzle with a leading edge region that defines an increased airfoil leading edge radius.
    Type: Grant
    Filed: July 19, 2010
    Date of Patent: August 12, 2014
    Assignee: United Technologies Corporation
    Inventors: Andre M. Hall, Oliver V. Atassi, Jonathan Gilson
  • GAS TURBINE ENGINE WITH VARIABLE AREA FAN NOZZLE
    Publication number: 20120109593
    Abstract: A bypass gas turbine engine includes a variable area fan nozzle with a second fan nacelle section axially movable relative to a first fan nacelle section to define an auxiliary port to vary a fan nozzle exit area and adjust fan bypass airflow. The second fan nacelle section includes a leading edge region that defines a concave external contour and the first fan nacelle section includes a trailing edge region that defines a convex internal contour.
    Type: Application
    Filed: October 29, 2010
    Publication date: May 3, 2012
    Inventors: Andre M. Hall, Gregory A. Kohlenberg, Jonathan Gilson
  • Variable area fan nozzle for gas turbine engine
    Publication number: 20120023901
    Abstract: A high-bypass gas turbine engine includes a variable area fan nozzle with an acoustic system having an acoustic impedance.
    Type: Application
    Filed: July 27, 2010
    Publication date: February 2, 2012
    Inventors: Jonathan Gilson, Andre M. Hall, Oliver V. Atassi, Ramons A. Reba
  • GAS TURBINE ENGINE WITH NOISE ATTENUATING VARIABLE AREA FAN NOZZLE
    Publication number: 20120011825
    Abstract: A bypass gas turbine engine includes a variable area fan nozzle with a leading edge region that defines an increased airfoil leading edge radius.
    Type: Application
    Filed: July 19, 2010
    Publication date: January 19, 2012
    Inventors: Andre M. Hall, Oliver V. Atassi, Jonathan Gilson