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:
May. 02, 2023

Filed:

Nov. 15, 2018
Applicant:

Subaru Corporation, Tokyo, JP;

Inventors:

Hiroki Kato, Tokyo, JP;

Maki Kikuchi, Tokyo, JP;

Assignee:

SUBARU CORPORATION, Tokyo, JP;

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
F01D 11/10 (2006.01); B64C 23/00 (2006.01); F01D 11/20 (2006.01); F15D 1/00 (2006.01); B64C 11/00 (2006.01); B64C 27/82 (2006.01); B64C 29/00 (2006.01);
U.S. Cl.
CPC ...
F01D 11/10 (2013.01); B64C 23/005 (2013.01); F01D 11/20 (2013.01); F15D 1/0075 (2013.01); B64C 11/001 (2013.01); B64C 27/82 (2013.01); B64C 29/0025 (2013.01); B64C 2027/8254 (2013.01); B64C 2230/12 (2013.01); F05D 2220/328 (2013.01); F05D 2220/329 (2013.01); F05D 2270/172 (2013.01); Y02T 50/60 (2013.01);
Abstract

A rotor support device includes a plurality of first electrodes, a plurality of second electrodes, a dielectric material, and at least one alternating-current power supply. The dielectric material is disposed between the plurality of first electrodes and the plurality of second electrodes. The at least one AC power supply is configured to apply an alternating-current voltage across the plurality of first electrodes and the plurality of second electrodes and induce flows of gas by causing dielectric barrier discharge between the plurality of first electrodes and the plurality of second electrodes. At least one of the plurality of first electrodes or the plurality of second electrodes is disposed apart from each other in a static system that is stationary with respect to a rotor provided in an aircraft. The static system is adjacent to the rotor.


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