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.

Date of Patent:
Apr. 20, 2021

Filed:

Jan. 05, 2018
Applicant:

Gulfstream Aerospace Corporation, Savannah, GA (US);

Inventors:

Michael Rybalko, Savannah, GA (US);

Timothy R. Conners, Tucson, AZ (US);

Thomas R. Wayman, Savannah, GA (US);

Assignee:
Attorney:
Primary Examiner:
Assistant Examiner:
Int. Cl.
CPC ...
B64D 29/00 (2006.01); B64D 27/00 (2006.01); B64D 33/02 (2006.01); F02K 7/10 (2006.01); F02K 3/02 (2006.01); B64C 30/00 (2006.01); B64D 27/02 (2006.01);
U.S. Cl.
CPC ...
B64D 29/00 (2013.01); B64D 27/00 (2013.01); B64D 33/02 (2013.01); F02K 3/025 (2013.01); F02K 7/10 (2013.01); B64C 30/00 (2013.01); B64D 27/02 (2013.01); B64D 2033/026 (2013.01); B64D 2033/0226 (2013.01); F05D 2210/33 (2013.01); F05D 2220/10 (2013.01); Y02T 50/60 (2013.01);
Abstract

An arrangement for use with a propulsion system for a supersonic aircraft includes a center body configured for coupling to an inlet and to support a boundary layer formed when the supersonic aircraft is flown at a predetermined altitude supersonic speed. The arrangement further includes a first vortex generator disposed on the center body. The first vortex generator extends a first height above the center body. The arrangement still further includes a second vortex generator disposed on the center body. The second vortex generator extends a second height above the center body, the second height being greater than the first height. The first height and the second height are greater than approximately seventy-five percent of a thickness of the boundary layer proximate a location of the first vortex generator and the second vortex generator, respectively, when the aircraft if flown at the predetermined altitude and the predetermined speed.


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