Patents by Inventor Konstantin M. Khritov

Konstantin M. Khritov 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).

  • Systems and methods for passively directing aircraft engine nozzle flows
    Patent number: 8166768
    Abstract: Systems and methods for passively directing aircraft engine nozzle flow are disclosed. One system includes an aircraft nozzle attachable to an aircraft turbofan engine, with the nozzle including a first flow path wall bounding a first flow path and being positioned to receive engine exhaust products, and a second flow path wall bounding a second flow path and being positioned to receive engine bypass air. The first flow path wall is positioned between the first and second flow paths, and the second flow path wall is positioned between the second flow path and an ambient air flow path. Multiple flow passages can be positioned in at least one of the first and second flow path walls to passively direct gas from a corresponding flow path within the flow path wall through the flow path wall to a corresponding flow path external to the flow path wall.
    Type: Grant
    Filed: December 7, 2010
    Date of Patent: May 1, 2012
    Assignee: The Boeing Company
    Inventors: Stanley F. Birch, Alexander N. Secundov, Dmitriy A. Lyubimov, Konstantin M. Khritov, Vladimir P. Maslov, Aleksey K. Mironov
  • SYSTEMS AND METHODS FOR PASSIVELY DIRECTING AIRCRAFT ENGINE NOZZLE FLOWS
    Publication number: 20110072781
    Abstract: Systems and methods for passively directing aircraft engine nozzle flow are disclosed. One system includes an aircraft nozzle attachable to an aircraft turbofan engine, with the nozzle including a first flow path wall bounding a first flow path and being positioned to receive engine exhaust products, and a second flow path wall bounding a second flow path and being positioned to receive engine bypass air. The first flow path wall is positioned between the first and second flow paths, and the second flow path wall is positioned between the second flow path and an ambient air flow path. Multiple flow passages can be positioned in at least one of the first and second flow path walls to passively direct gas from a corresponding flow path within the flow path wall through the flow path wall to a corresponding flow path external to the flow path wall.
    Type: Application
    Filed: December 7, 2010
    Publication date: March 31, 2011
    Applicant: The Boeing Company
    Inventors: Stanley F. Birch, Alexander N. Secundov, Dmitriy A. Lyubimov, Konstantin M. Khritov, Vladimir P. Maslov, Aleksey K. Mironov
  • Systems and methods for passively directing aircraft engine nozzle flows
    Patent number: 7870722
    Abstract: Systems and methods for passively directing aircraft engine nozzle flow are disclosed. One system includes an aircraft nozzle attachable to an aircraft turbofan engine, with the nozzle including a first flow path wall bounding a first flow path and being positioned to receive engine exhaust products, and a second flow path wall bounding a second flow path and being positioned to receive engine bypass air. The first flow path wall is positioned between the first and second flow paths, and the second flow path wall is positioned between the second flow path and an ambient air flow path. Multiple flow passages can be positioned in at least one of the first and second flow path walls to passively direct gas from a corresponding flow path within the flow path wall through the flow path wall to a corresponding flow path external to the flow path wall.
    Type: Grant
    Filed: December 6, 2006
    Date of Patent: January 18, 2011
    Assignee: The Boeing Company
    Inventors: Stanley F. Birch, Alexander N. Secundov, Dmitriy A. Lyubimov, Konstantin M. Khritov, Vladimir P. Maslov, Aleksey K. Mironov
  • Systems and methods for passively directing aircraft engine nozzle flows
    Publication number: 20080134665
    Abstract: Systems and methods for passively directing aircraft engine nozzle flow are disclosed. One system includes an aircraft nozzle attachable to an aircraft turbofan engine, with the nozzle including a first flow path wall bounding a first flow path and being positioned to receive engine exhaust products, and a second flow path wall bounding a second flow path and being positioned to receive engine bypass air. The first flow path wall is positioned between the first and second flow paths, and the second flow path wall is positioned between the second flow path and an ambient air flow path. Multiple flow passages can be positioned in at least one of the first and second flow path walls to passively direct gas from a corresponding flow path within the flow path wall through the flow path wall to a corresponding flow path external to the flow path wall.
    Type: Application
    Filed: December 6, 2006
    Publication date: June 12, 2008
    Inventors: Stanley F. Birch, Alexander N. Secundov, Dmitriy A. Lyubimov, Konstantin M. Khritov, Vladimir P. Maslov, Aleksey K. Mironov