Patents by Inventor Zachary Mott

Zachary Mott 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).

  • Gas turbine engine control based on characteristic of cooled air
    Patent number: 11578668
    Abstract: A gas turbine engine includes a compressor section, a combustor, and a turbine section. The turbine section includes a high pressure turbine comprising a plurality of turbine blades. The gas turbine engine includes a tap for tapping air that is compressed by the compressor, to be passed through a heat exchanger to cool the air, the cooled air to be passed to the plurality of turbine blades. A sensor is located downstream of a leading edge of the combustor, and is configured to measure a characteristic of the cooled air. A controller is configured to compare the measured characteristic to a threshold and control an operating condition of the gas turbine engine based on the comparison.
    Type: Grant
    Filed: May 30, 2017
    Date of Patent: February 14, 2023
    Assignee: Raytheon Technologies Corporation
    Inventors: Jonathan Ortiz, Taryn Narrow, John H. Mosley, Zachary Mott, Paul R. Hanrahan
  • GAS TURBINE ENGINE CONTROL BASED ON CHARACTERISTIC OF COOLED AIR
    Publication number: 20180347472
    Abstract: A gas turbine engine includes a compressor section, a combustor, and a turbine section. The turbine section includes a high pressure turbine comprising a plurality of turbine blades. The gas turbine engine includes a tap for tapping air that is compressed by the compressor, to be passed through a heat exchanger to cool the air, the cooled air to be passed to the plurality of turbine blades. A sensor is located downstream of a leading edge of the combustor, and is configured to measure a characteristic of the cooled air. A controller is configured to compare the measured characteristic to a threshold and control an operating condition of the gas turbine engine based on the comparison.
    Type: Application
    Filed: May 30, 2017
    Publication date: December 6, 2018
    Inventors: Jonathan Ortiz, Taryn Narrow, John H. Mosley, Zachary Mott, Paul R. Hanrahan
  • Inner stage turbine seal for gas turbine engine
    Patent number: 9879557
    Abstract: A turbine section of a gas turbine engine includes a seal that extends between a vane platform and a Blade Outer Air Seal.
    Type: Grant
    Filed: June 12, 2015
    Date of Patent: January 30, 2018
    Assignee: United Technologies Corporation
    Inventors: Theodore W Hall, Michael G McCaffrey, Zachary Mott
  • Disk lug cooling flow trenches
    Patent number: 9835032
    Abstract: A rotor disk is provided. The rotor disk may comprise a disk lug and a trench. The disk lug may be fixed to a distal surface of the rotor disk. The trench may be disposed on a surface of the disk lug. The trench may extend radially inwards from a distal surface of the disk lug. The trench may be configured to at least partially define a flow path by which cooling air may reach a distal surface of the disk lug in order to provide disk lug cooling.
    Type: Grant
    Filed: June 1, 2015
    Date of Patent: December 5, 2017
    Assignee: United Technologies Corporation
    Inventors: David Richard Griffin, Zachary Mott, Christopher Corcoran, Ross Wilson, Jason D Himes
  • Retaining rings for turbomachine disk and coverplate assemblies
    Patent number: 9732619
    Abstract: A retaining ring for a turbomachine disk and coverplate assembly includes a ring body defining a coverplate interface side and an opposed disk lip interface side. A flow feature is defined by the ring body on the coverplate interface side to allow airflow between the turbomachine disk coverplate and the ring body such that a pocket defined between the coverplate and the turbomachine disk is in fluid communication with a conditioning flow pathway through the retaining ring.
    Type: Grant
    Filed: March 31, 2015
    Date of Patent: August 15, 2017
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Ross Wilson, Dwayne K. Mecklenburg, Zachary Mott, David R. Griffin
  • APPARATUS AND METHOD FOR COOLING GAS TURBINE ENGINE COMPONENTS
    Publication number: 20170044908
    Abstract: A rotor assembly for a gas turbine engine includes a rotor disc having an axially extending rotor disc arm and a plurality of rotor blades extending radially outwardly from the rotor disc. A cover plate is located at an axial face of the rotor disc and at least partially retained at a rotor disc arm. The rotor disc and cover plate define a rotor cavity. A plurality of airflow openings extend into the cavity to allow a flow of air into the rotor cavity to thermally condition the rotor disc and the cover plate at the rotor cavity.
    Type: Application
    Filed: August 14, 2015
    Publication date: February 16, 2017
    Inventors: David Richard Griffin, Ross Wilson, Zachary Mott, Dwayne K. Mecklenburg, Michael Lastrina
  • DISK LUG COOLING FLOW TRENCHES
    Publication number: 20160348510
    Abstract: A rotor disk is provided. The rotor disk may comprise a disk lug and a trench. The disk lug may be fixed to a distal surface of the rotor disk. The trench may be disposed on a surface of the disk lug. The trench may extend radially inwards from a distal surface of the disk lug. The trench may be configured to at least partially define a flow path by which cooling air may reach a distal surface of the disk lug in order to provide disk lug cooling.
    Type: Application
    Filed: June 1, 2015
    Publication date: December 1, 2016
    Applicant: United Technologies Corporation
    Inventors: David Richard Griffin, Zachary Mott, Christopher Corcoran, Ross Wilson, Jason D. Himes
  • RETAINING RINGS FOR TURBOMACHINE DISK AND COVERPLATE ASSEMBLIES
    Publication number: 20160290141
    Abstract: A retaining ring for a turbomachine disk and coverplate assembly includes a ring body defining a coverplate interface side and an opposed disk lip interface side. A flow feature is defined by the ring body on the coverplate interface side to allow airflow between the turbomachine disk coverplate and the ring body such that a pocket defined between the coverplate and the turbomachine disk is in fluid communication with a conditioning flow pathway through the retaining ring.
    Type: Application
    Filed: March 31, 2015
    Publication date: October 6, 2016
    Inventors: Ross Wilson, Dwayne K. Mecklenburg, Zachary Mott, David R. Griffin
  • INNER STAGE TURBINE SEAL FOR GAS TURBINE ENGINE
    Publication number: 20160047258
    Abstract: A turbine section of a gas turbine engine includes a seal that extends between a vane platform and a Blade Outer Air Seal.
    Type: Application
    Filed: June 12, 2015
    Publication date: February 18, 2016
    Inventors: Theodore W. Hall, Michael G. McCaffrey, Zachary Mott