Patents by Inventor Victor M. Pinedo

Victor M. Pinedo 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: 10787277
    Abstract: A system for starting a gas turbine engine of an aircraft is provided. The system includes a pneumatic starter motor, a discrete starter valve switchable between an on-state and an off-state, and a controller operable to perform a starting sequence for the gas turbine engine. The starting sequence includes alternating on and off commands to an electromechanical device coupled to the discrete starter valve to achieve a partially open position of the discrete starter valve to control a flow from a starter air supply to the pneumatic starter motor to drive rotation of a starting spool of the gas turbine engine below an engine idle speed, where the controller modulates a duty cycle of the discrete starter valve via pulse width modulation.
    Type: Grant
    Filed: July 13, 2018
    Date of Patent: September 29, 2020
    Assignee: RAYTHEON TECHNOLOGIES CORPORATION
    Inventors: Matthew D. Teicholz, Jeffrey W. Sutliff, William H. Greene, Jr., Kenneth J. White, Matthew R. Feulner, John P. Virtue, Jr., Jorn A. Glahn, Philip D. Hoover, Victor M. Pinedo, Jason B. Solomonides
  • Patent number: 10625881
    Abstract: A system for controlling a start sequence of a gas turbine engine includes an electronic engine control system, a thermal model, memory, a model for determining a time period (tmotoring), and a controller. The thermal model synthesizes a heat state of the gas turbine engine. The memory records the current heat state at shutdown and a shutdown time of the gas turbine engine. The model for determining the time period is for motoring the gas turbine engine at a predetermined speed Ntarget that is less than a speed to start the gas turbine engine, where tmotoring is a function of the heat state recorded at engine shutdown and an elapsed time of an engine start request relative to a previous shutdown time. The controller modulates a starter valve to maintain the gas turbine engine within a predetermined speed range of NtargetMin to NtargetMax for homogenizing engine temperatures.
    Type: Grant
    Filed: May 22, 2018
    Date of Patent: April 21, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Matthew D. Teicholz, Jeffrey W. Sutliff, William H. Greene, Jr., Kenneth J. White, Matthew R. Feulner, John P. Virtue, Jr., Jorn A. Glahn, Philip D. Hoover, Victor M. Pinedo, Jason B. Solomonides
  • Publication number: 20190120140
    Abstract: A gas turbine engine includes a bearing compartment that has at least one seal, a bearing disposed in the bearing compartment, a deoiler fluidly connected with the bearing compartment, and a vacuum generator fluidly connected with the deoiler.
    Type: Application
    Filed: October 24, 2017
    Publication date: April 25, 2019
    Inventors: Jorn A. Glahn, Matthew J. Howlett, Myles R. Kelly, Victor M. Pinedo, Gregory E. Reinhardt, Bradley C. Schafer, Ethan K. Stearns
  • Publication number: 20180327117
    Abstract: A system for starting a gas turbine engine of an aircraft is provided. The system includes a pneumatic starter motor, a discrete starter valve switchable between an on-state and an off-state, and a controller operable to perform a starting sequence for the gas turbine engine. The starting sequence includes alternating on and off commands to an electromechanical device coupled to the discrete starter valve to achieve a partially open position of the discrete starter valve to control a flow from a starter air supply to the pneumatic starter motor to drive rotation of a starting spool of the gas turbine engine below an engine idle speed, where the controller modulates a duty cycle of the discrete starter valve via pulse width modulation.
    Type: Application
    Filed: July 13, 2018
    Publication date: November 15, 2018
    Inventors: Matthew D. Teicholz, Jeffrey W. Sutliff, William H. Greene, JR., Kenneth J. White, Matthew R. Feulner, John P. Virtue, JR., Jorn A. Glahn, Philip D. Hoover, Victor M. Pinedo, Jason B. Solomonides
  • Publication number: 20180265223
    Abstract: A system for controlling a start sequence of a gas turbine engine includes an electronic engine control system, a thermal model, memory, a model for determining a time period (fmotoring), and a controller. The thermal model synthesizes a heat state of the gas turbine engine. The memory records the current heat state at shutdown and a shutdown time of the gas turbine engine. The model for determining the time period is for motoring the gas turbine engine at a predetermined speed Ntarget that is less than a speed to start the gas turbine engine, where tmotoring is a function of the heat state recorded at engine shutdown and an elapsed time of an engine start request relative to a previous shutdown time. The controller modulates a starter valve to maintain the gas turbine engine within a predetermined speed range of NtargetMin to NtargetMax for homogenizing engine temperatures.
    Type: Application
    Filed: May 22, 2018
    Publication date: September 20, 2018
    Inventors: Matthew D. Teicholz, Jeffrey W. Sutliff, William H. Greene, JR., Kenneth J. White, Matthew R. Feulner, John P. Virtue, JR., Jorn A. Glahn, Philip D. Hoover, Victor M. Pinedo, Jason B. Solomonides
  • Patent number: 10040577
    Abstract: A system for starting a gas turbine engine of an aircraft is provided. The system includes a pneumatic starter motor, a discrete starter valve switchable between an on-state and an off-state, and a controller operable to perform a starting sequence for the gas turbine engine. The starting sequence includes alternating on and off commands to an electromechanical device coupled to the discrete starter valve to achieve a partially open position of the discrete starter valve to control a flow from a starter air supply to the pneumatic starter motor to drive rotation of a starting spool of the gas turbine engine below an engine idle speed.
    Type: Grant
    Filed: February 12, 2016
    Date of Patent: August 7, 2018
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Matthew D. Teicholz, Jeffrey W. Sutliff, William H. Greene, Jr., Kenneth J. White, Matthew R. Feulner, John P. Virtue, Jr., Jorn A. Glahn, Philip D. Hoover, Victor M. Pinedo, Jason B. Solomonides
  • Publication number: 20170233103
    Abstract: A system for starting a gas turbine engine of an aircraft is provided. The system includes a pneumatic starter motor, a discrete starter valve switchable between an on-state and an off-state, and a controller operable to perform a starting sequence for the gas turbine engine. The starting sequence includes alternating on and off commands to an electromechanical device coupled to the discrete starter valve to achieve a partially open position of the discrete starter valve to control a flow from a starter air supply to the pneumatic starter motor to drive rotation of a starting spool of the gas turbine engine below an engine idle speed.
    Type: Application
    Filed: February 12, 2016
    Publication date: August 17, 2017
    Inventors: Matthew D. Teicholz, Jeffrey W. Sutliff, William H. Greene, JR., Kenneth J. White, Matthew R. Feulner, John P. Virtue, JR., Jorn A. Glahn, Philip D. Hoover, Victor M. Pinedo, Jason B. Solomonides
  • Publication number: 20160169120
    Abstract: A fuel injection system for a gas turbine engine can be used to ensure successful transition in all conditions, while avoiding the possibility of steady state, or increasing power mode, operations with an insufficiently filled secondary fuel line. This may be accomplished by altering a pressure in a secondary fuel line. The present disclosure allows for the elimination of individual fuel injector valves, which may reduce the total complexity and number of parts of the fuel injection system.
    Type: Application
    Filed: November 3, 2015
    Publication date: June 16, 2016
    Inventors: Anthony Van, Dennis M. Moura, James B. Hoke, Thomas A. Bush, Timothy J. Gaudet, Victor M. Pinedo, David Kwoka, Matthew G. Van Eck