Patents by Inventor Eric L. Werner

Eric L. Werner 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).

  • Method and apparatus for variable exhaust nozzle exit area
    Patent number: 10060389
    Abstract: A nozzle effective exit area control system is created with a convergent-divergent nozzle with a divergent portion of the nozzle having a wall at a predetermined angle of at least 12° from the freestream direction. Disturbance generators are located substantially symmetrically oppositely on the wall to induce flow separation from the wall with the predetermined wall angle inducing flow separation to extend upstream from each disturbance generator substantially to a throat of the nozzle pressurizing the wall and reducing the effective area of the jet flow at the nozzle exit.
    Type: Grant
    Filed: August 3, 2015
    Date of Patent: August 28, 2018
    Assignee: The Boeing Company
    Inventors: Chad M. Winkler, Andrew J. Dorgan, Eric L. Werner
  • Self-sealing apparatus that adjusts a throat area of a nozzle
    Patent number: 10030605
    Abstract: A flow control panel in an aircraft engine two-dimensional, convergent/divergent nozzle adjusts a throat area of the nozzle and is configured to be self-sealing, thereby requiring fewer parts and providing a more simplified construction of the throat area of the nozzle.
    Type: Grant
    Filed: July 10, 2015
    Date of Patent: July 24, 2018
    Assignee: The Boeing Company
    Inventor: Eric L. Werner
  • Method and apparatus for nozzle thrust vectoring
    Patent number: 9551296
    Abstract: A thrust vectoring system is created with a convergent-divergent nozzle having a total angle no greater than 150 degrees. A divergent portion of the nozzle has a wall at a predetermined angle of at least 12° from the freestream direction. A disturbance generator is located on the wall to induce flow separation from the wall with the predetermined wall angle sufficient for the induced flow separation to extend upstream from disturbance generator substantially to a throat of the nozzle pressurizing the wall and creating a net vector angle in jet flow through the nozzle.
    Type: Grant
    Filed: January 20, 2014
    Date of Patent: January 24, 2017
    Assignee: The Boeing Company
    Inventors: Chad M. Winkler, Andrew J. Dorgan, Eric L. Werner
  • METHOD AND APPARATUS FOR VARIABLE EXHAUST NOZZLE EXIT AREA
    Publication number: 20150354498
    Abstract: A nozzle effective exit area control system is created with a convergent—divergent nozzle with a divergent portion of the nozzle having a wall at a predetermined angle of at least 12° from the freestream direction. Disturbance generators are located substantially symmetrically oppositely on the wall to induce flow separation from the wall with the predetermined wall angle inducing flow separation to extend upstream from each disturbance generator substantially to a throat of the nozzle pressurizing the wall and reducing the effective area of the jet flow at the nozzle exit.
    Type: Application
    Filed: August 3, 2015
    Publication date: December 10, 2015
    Inventors: Chad M. Winkler, Andrew J. Dorgan, Eric L. Werner
  • SELF-SEALING APPARATUS THAT ADJUSTS A THROAT AREA OF A NOZZLE
    Publication number: 20150315999
    Abstract: A flow control panel in an aircraft engine two-dimensional, convergent/divergent nozzle adjusts a throat area of the nozzle and is configured to be self-sealing, thereby requiring fewer parts and providing a more simplified construction of the throat area of the nozzle.
    Type: Application
    Filed: July 10, 2015
    Publication date: November 5, 2015
    Applicant: The Boeing Company
    Inventor: Eric L. Werner
  • METHOD AND APPARATUS FOR NOZZLE THRUST VECTORING
    Publication number: 20140145001
    Abstract: A thrust vectoring system is created with a convergent-divergent nozzle having a total angle no greater than 150 degrees. A divergent portion of the nozzle has a wall at a predetermined angle of at least 12° from the freestream direction. A disturbance generator is located on the wall to induce flow separation from the wall with the predetermined wall angle sufficient for the induced flow separation to extend upstream from disturbance generator substantially to a throat of the nozzle pressurizing the wall and creating a net vector angle in jet flow through the nozzle.
    Type: Application
    Filed: January 20, 2014
    Publication date: May 29, 2014
    Applicant: The Boeing Company
    Inventors: Chad M. Winkler, Andrew J. Dorgan, Eric L. Werner
  • METHOD AND APPARATUS FOR VARIABLE EXHAUST NOZZLE EXIT AREA
    Publication number: 20120145808
    Abstract: A nozzle effective exit area control system is created with a convergent-divergent nozzle with a divergent portion of the nozzle having a wall at a predetermined angle of at least 12° from the freestream direction. Disturbance generators are located substantially symmetrically oppositely on the wall to induce flow separation from the wall with the predetermined wall angle inducing flow separation to extend upstream from each disturbance generator substantially to a throat of the nozzle pressurizing the wall and reducing the effective area of the jet flow at the nozzle exit.
    Type: Application
    Filed: December 14, 2010
    Publication date: June 14, 2012
    Applicant: THE BOEING COMPANY
    Inventors: Chad M. Winkler, Andrew J. Dorgan, Eric L. Werner