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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.:

US 11536740 B1

PDFFull Text
Date of Patent:
Dec. 27, 2022

Filed:

Nov. 12, 2019

Pitch control assembly for an aircraft-bladed rotor

Applicant:

Pratt & Whitney Canada Corp., Longueuil, CA;

Inventor:

Dana Tomescu, Brampton, CA;

Assignee:

PRATT & WHITNEY CANADA CORP., Longueuil, CA;

Attorney:

Norton Rose Fulbright Canada LLP

Primary Examiner:

Woody A Lee, Jr

Assistant Examiner:

Jesse M Prager

Int. Cl.
CPC ...
G01P 3/488 (2006.01); B64C 11/30 (2006.01); B64D 27/10 (2006.01); F01D 7/00 (2006.01); F01D 17/20 (2006.01); F01D 21/00 (2006.01); F01D 17/06 (2006.01); G01D 5/14 (2006.01); F01D 17/02 (2006.01); F04D 29/36 (2006.01); B64C 27/473 (2006.01); B64C 27/57 (2006.01); F02C 9/22 (2006.01); F02D 29/02 (2006.01); G01D 5/12 (2006.01); G01D 5/20 (2006.01); G01P 3/487 (2006.01); F02C 7/32 (2006.01); B63H 3/00 (2006.01); B64C 11/06 (2006.01); F02D 41/28 (2006.01);
U.S. Cl.
CPC ...
G01P 3/488 (2013.01); B64C 11/301 (2013.01); B64C 27/473 (2013.01); B64C 27/57 (2013.01); B64D 27/10 (2013.01); F01D 7/00 (2013.01); F01D 17/02 (2013.01); F01D 17/06 (2013.01); F01D 17/20 (2013.01); F01D 21/003 (2013.01); F02C 9/22 (2013.01); F02D 29/02 (2013.01); F04D 29/362 (2013.01); G01D 5/125 (2013.01); G01D 5/145 (2013.01); G01D 5/2013 (2013.01); G01P 3/487 (2013.01); B63H 2003/006 (2013.01); B64C 11/06 (2013.01); B64C 2027/4733 (2013.01); F02C 7/32 (2013.01); F02D 2041/281 (2013.01); F02D 2041/288 (2013.01); F05B 2270/328 (2013.01); F05D 2220/323 (2013.01); F05D 2260/70 (2013.01); F05D 2270/02 (2013.01); F05D 2270/80 (2013.01); F05D 2270/821 (2013.01); F05D 2300/507 (2013.01);
Abstract

A feedback device for use in a gas turbine engine, and methods and systems for controlling a pitch for an aircraft-bladed rotor, are provided. The feedback device is composed of a circular disk and a plurality of position markers. The circular disk is coupled to rotate with a rotor of the gas turbine engine, to move along a longitudinal axis of the rotor, and has first and second opposing faces defining a root surface that extends between and circumscribes the first and second faces. The plurality of position markers extend radially from the root surface, are circumferentially spaced around the circular disk, and extending along the longitudinal axis from a first end portion to a second end portion. At least part of the first end portion and/or of the second end portion comprises a material having higher magnetic permeability than that of a remainder of the position markers.

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