The patent badge is an abbreviated version of the USPTO patent document. The patent badge does contain a link to the full patent document.
The patent badge is an abbreviated version of the USPTO patent document. The patent badge covers the following: Patent number, Date patent was issued, Date patent was filed, Title of the patent, Applicant, Inventor, Assignee, Attorney firm, Primary examiner, Assistant examiner, CPCs, and Abstract. The patent badge does contain a link to the full patent document (in Adobe Acrobat format, aka pdf). To download or print any patent click here.
Patent No.:
Date of Patent:
May. 15, 2018
Filed:
Aug. 07, 2008
Joel Hudson Frank, San Diego, CA (US);
Norman John James, San Diego, CA (US);
Shunshen Richard Wang, Chula Vista, CA (US);
Bryant Lynoel Mckleny, San Diego, CA (US);
David A. Baer, San Diego, CA (US);
Tony Jones, Northfield, GB;
John H. Harvey, Wolverhampton, GB;
Peter W. Bacon, Wolverhampton, GB;
Mark Hubberstey, Wolverhampton, GB;
Brett J. Wharton, Wednesbury, GB;
Neil C. Davies, Much Wenlock, GB;
Stephen Michael Roberts, Boulder, CO (US);
Steven Andrew Wylie, San Diego, CA (US);
Joel Hudson Frank, San Diego, CA (US);
Norman John James, San Diego, CA (US);
Shunshen Richard Wang, Chula Vista, CA (US);
Bryant Lynoel McKleny, San Diego, CA (US);
David A. Baer, San Diego, CA (US);
Tony Jones, Northfield, GB;
John H. Harvey, Wolverhampton, GB;
Peter W. Bacon, Wolverhampton, GB;
Mark Hubberstey, Wolverhampton, GB;
Brett J. Wharton, Wednesbury, GB;
Neil C. Davies, Much Wenlock, GB;
Stephen Michael Roberts, Boulder, CO (US);
Steven Andrew Wylie, San Diego, CA (US);
ROHR, INC., Chula Vista, CA (US);
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.