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:
Aug. 16, 2022

Filed:

Sep. 11, 2018
Applicant:

The Boeing Company, Chicago, IL (US);

Inventor:

Arvin Shmilovich, Huntington Beach, CA (US);

Assignee:

The Boeing Company, Chicago, IL (US);

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
B64C 21/04 (2006.01); F04D 29/28 (2006.01); F04D 29/44 (2006.01); F04D 29/40 (2006.01); F04D 25/04 (2006.01); F01D 1/32 (2006.01); F01D 25/24 (2006.01); F04D 17/16 (2006.01); F15D 1/12 (2006.01);
U.S. Cl.
CPC ...
B64C 21/04 (2013.01); F01D 1/32 (2013.01); F01D 25/24 (2013.01); F04D 17/16 (2013.01); F04D 25/045 (2013.01); F04D 29/281 (2013.01); F04D 29/403 (2013.01); F04D 29/442 (2013.01); B64C 2230/04 (2013.01); F15D 1/12 (2013.01);
Abstract

A fluidic actuator is configured to be mounted to an airfoil surface. The actuator includes a rotor supported within a housing. The rotor contains at least one generally radially extending nozzle that converges from an entry at an interior circumference of the rotor to an exit at an exterior circumference thereof, the converging shape of the nozzle assuring high velocity airflow at the nozzle exit. In one form, each nozzle also includes a curved path by which high-pressure air is enabled to induce spinning of the rotor. The fluidic actuator further includes a diffuser through which high-pressure air from the nozzles is cyclically ejected from those of the nozzles instantaneously exposed to the diffuser. In one form, the rotor spins at 300 revolutions per second and provides nozzle ejections effective to avoid boundary layer separation; i.e. to maintain an attached boundary layer flow over the airfoil.


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