Patents by Inventor Mohamad Hanif Vhora

Mohamad Hanif Vhora 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).

  • Temperature inversion detection and mitigation strategies to avoid compressor surge
    Patent number: 11448088
    Abstract: A system and method for controlling compressor inlet guide vanes of a gas turbine engine in an aircraft includes supplying, to a compressor inlet guide vane control algorithm, an inlet temperature value that is at least representative of sensed engine inlet total temperature. One or more gas turbine engine parameters are sensed with one or more sensors during operation of the gas turbine engine. The one or more gas turbine engine parameters are processed in the engine control unit to determine an inlet temperature modifier value that is an estimate of a difference between the sensed engine inlet total temperature and actual engine inlet total temperature. The inlet temperature modifier value is added to the inlet temperature value to derive a modified engine inlet total temperature. The modified engine inlet total temperature is used in the compressor inlet guide vane control algorithm, which controls the compressor inlet guide vanes.
    Type: Grant
    Filed: April 7, 2020
    Date of Patent: September 20, 2022
    Assignee: HONEYWELL INTERNATIONAL INC.
    Inventors: Ronnie Haugland, Gregory J. Chapman, Mohamad Hanif Vhora, Jeffrey J. Aitchison
  • TEMPERATURE INVERSION DETECTION AND MITIGATION STRATEGIES TO AVOID COMPRESSOR SURGE
    Publication number: 20210254496
    Abstract: A system and method for controlling compressor inlet guide vanes of a gas turbine engine in an aircraft includes supplying, to a compressor inlet guide vane control algorithm, an inlet temperature value that is at least representative of sensed engine inlet total temperature. One or more gas turbine engine parameters are sensed with one or more sensors during operation of the gas turbine engine. The one or more gas turbine engine parameters are processed in the engine control unit to determine an inlet temperature modifier value that is an estimate of a difference between the sensed engine inlet total temperature and actual engine inlet total temperature. The inlet temperature modifier value is added to the inlet temperature value to derive a modified engine inlet total temperature. The modified engine inlet total temperature is used in the compressor inlet guide vane control algorithm, which controls the compressor inlet guide vanes.
    Type: Application
    Filed: April 7, 2020
    Publication date: August 19, 2021
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Ronnie Haugland, Gregory J. Chapman, Mohamad Hanif Vhora, Jeffrey J. Aitchison
  • Valve control logic for gas turbine recuperator
    Patent number: 6463730
    Abstract: Control logic and a method for controlling turbine speed. In an embodiment, the inventive control logic controls turbine speed of turbine generators operating in a stand-alone mode and/or a grid mode.
    Type: Grant
    Filed: July 12, 2000
    Date of Patent: October 15, 2002
    Assignee: Honeywell Power Systems Inc.
    Inventors: Timothy J. Keller, Daniel Burns, Mohamad Hanif Vhora, Patrick O'Brien, Coung Van Nguyen