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. 08, 2025

Filed:

Aug. 01, 2022
Applicant:

Rohr, Inc., Chula Vista, CA (US);

Inventors:

Julian Winkler, Glastonbury, CT (US);

Wentaur E. Chien, San Diego, CA (US);

Xiaolan Hu, San Diego, CA (US);

Assignee:

Rohr, Inc., Chula Vista, CA (US);

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
F02K 1/72 (2006.01); F02K 1/50 (2006.01); F02K 1/54 (2006.01); F02K 1/56 (2006.01); F02K 1/60 (2006.01); F02K 1/62 (2006.01); F02K 1/64 (2006.01); F02K 1/68 (2006.01); F02K 1/70 (2006.01);
U.S. Cl.
CPC ...
F02K 1/72 (2013.01); F02K 1/50 (2013.01); F02K 1/54 (2013.01); F02K 1/56 (2013.01); F02K 1/60 (2013.01); F02K 1/62 (2013.01); F02K 1/64 (2013.01); F02K 1/68 (2013.01); F02K 1/70 (2013.01); F05D 2220/323 (2013.01); F05D 2240/129 (2013.01);
Abstract

An apparatus is provided for an aircraft propulsion system. This apparatus includes a cascade structure including a thrust reverser cascade and a flow disruptor. The thrust reverser cascade extends longitudinally between a cascade forward end and a cascade aft end. The thrust reverser cascade extends laterally between a cascade first side and a cascade second side. The thrust reverser cascade extends radially between an inner face and an outer face. The thrust reverser cascade includes a plurality of vanes arranged in a longitudinally extending array along the inner face. The flow disruptor is arranged at the cascade inner face and forward of the vanes. The flow disruptor is configured to disrupt boundary layer air flowing towards the vanes.


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