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:
Mar. 02, 2021
Filed:
Apr. 25, 2018
Applicant:
Rolls-royce North American Technologies Inc., Indianapolis, IN (US);
Inventor:
Patrick Bailey, Lebanon, IN (US);
Assignee:
Rolls-Royce North American Technologies Inc., Indianapolis, IN (US);
Attorney:
Primary Examiner:
Assistant Examiner:
Int. Cl.
CPC ...
F01D 7/00 (2006.01); F04D 29/36 (2006.01); F02K 3/06 (2006.01); F04D 29/32 (2006.01); B64C 11/32 (2006.01);
U.S. Cl.
CPC ...
F01D 7/00 (2013.01); B64C 11/32 (2013.01); F02K 3/06 (2013.01); F04D 29/323 (2013.01); F04D 29/325 (2013.01); F04D 29/362 (2013.01); F05D 2220/36 (2013.01); F05D 2260/532 (2013.01); F05D 2260/56 (2013.01); F05D 2260/74 (2013.01); F05D 2260/77 (2013.01); F05D 2260/79 (2013.01); F05D 2270/021 (2013.01);
Abstract
A gas turbine engine includes a fan having a plurality of fan blades configured to rotate about a central axis of the gas turbine engine. Each fan blade is configured to pivot about a pivot axis that extends radially away from the central axis to vary a pitch of the fan blade. The fan further includes a counterforce system configured to resist forces that urge the fan blades away from their pitch positions during operation of the gas turbine engine.