Patents by Inventor Shunshen Richard Wang

Shunshen Richard Wang 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).

  • Variable area fan nozzle with bypass flow
    Patent number: 9970387
    Abstract: The exit area of a nozzle assembly is varied by translating a ring assembly located at a rear of the engine nacelle. The ring may be axially translatable along the axis of the engine. As the ring translates, the trailing edge of the ring defines a variable nozzle exit area. Translation of the ring creates an upstream exit at a leading edge of the ring assembly. The upstream exit can be used to bleed or otherwise spill flow excess from the engine bypass duct. As the engine operates in various flight conditions, the ring can be translated to obtain lower fan pressure ratios and thereby increase the efficiency of the engine. Fairings partially enclose actuator components for reduced drag.
    Type: Grant
    Filed: August 7, 2008
    Date of Patent: May 15, 2018
    Assignees: ROHR, INC., GOODRICH ACTUATION SYSTEMTS LIMITED
    Inventors: Joel Hudson Frank, Norman John James, Shunshen Richard Wang, Bryant Lynoel McKleny, David A. Baer, Tony Jones, John H. Harvey, Peter W. Bacon, Mark Hubberstey, Brett J. Wharton, Neil C. Davies, Stephen Michael Roberts, Steven Andrew Wylie
  • Translating variable area fan nozzle with split beavertail fairings
    Patent number: 8505307
    Abstract: A nacelle assembly includes a first portion having an outer fairing and a trailing edge, and a translatable variable area fan nozzle. The fan nozzle includes two or more nozzle segments, each nozzle segment having first and second opposed ends and a leading edge. The nozzle segments are selectively movable between a stowed position and one or more deployed positions. In the deployed position, an upstream bypass flow exit is formed between the trailing edge and the leading edge. The nacelle assembly further includes a guide mechanism for guiding the nozzle segments between the stowed position and the deployed position. A split beavertail failing shields the guide mechanism against air flow when the nozzle segments are in the stowed position.
    Type: Grant
    Filed: April 6, 2009
    Date of Patent: August 13, 2013
    Assignee: Rohr, Inc.
    Inventor: Shunshen Richard Wang
  • VARIABLE AREA FAN NOZZLE WITH BYPASS FLOW
    Publication number: 20110296813
    Abstract: The exit area of a nozzle assembly is varied by translating a ring assembly located at a rear of the engine nacelle. The ring may be axially translatable along the axis of the engine. As the ring translates, the trailing edge of the ring defines a variable nozzle exit area. Translation of the ring creates an upstream exit at a leading edge of the ring assembly. The upstream exit can be used to bleed or otherwise spill flow excess from the engine bypass duct. As the engine operates in various flight conditions, the ring can be translated to obtain lower fan pressure ratios and thereby increase the efficiency of the engine. Fairings partially enclose actuator components for reduced drag.
    Type: Application
    Filed: August 7, 2008
    Publication date: December 8, 2011
    Applicant: Rohr, Inc.
    Inventors: Joel Hudson Frank, Norman John James, Shunshen Richard Wang, Bryant Lynoel Mckleny, David A. Baer, Stephen Michael Roberts, Steven Andrew Wylie, Tony Jones, John H. Harvey, Peter W. Bacon, Mark Hubberstey, Brett J. Wharton, Neil C. Davies
  • TRANSLATING VARIABLE AREA FAN NOZZLE WITH SPLIT BEAVERTAIL FAIRINGS
    Publication number: 20100064659
    Abstract: A nacelle assembly includes a first portion having an outer fairing and a trailing edge, and a translatable variable area fan nozzle. The fan nozzle includes two or more nozzle segments, each nozzle segment having first and second opposed ends and a leading edge. The nozzle segments are selectively movable between a stowed position and one or more deployed positions. In the deployed position, an upstream bypass flow exit is formed between the trailing edge and the leading edge. The nacelle assembly further includes a guide mechanism for guiding the nozzle segments between the stowed position and the deployed position. A split beavertail failing shields the guide mechanism against air flow when the nozzle segments are in the stowed position.
    Type: Application
    Filed: April 6, 2009
    Publication date: March 18, 2010
    Applicant: Rohr, Inc.
    Inventor: Shunshen Richard Wang