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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 11835543 B1

PDFFull Text
Date of Patent:
Dec. 05, 2023

Filed:

May. 19, 2022

Blade angle position feedback system with embedded markers

Applicant:

Pratt & Whitney Canada Corp., Longueuil, CA;

Inventors:

Dana Tomescu, Brampton, CA;

James Jarvo, Saint-Bruno, CA;

Assignee:

PRATT & WHITNEY CANADA CORP., Longueuil, CA;

Attorney:

NORTON ROSE FULBRIGHT CANADA LLP

Primary Examiner:

Gonzalo Laguarda

Int. Cl.
CPC ...
F03D 17/00 (2016.01); 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

There is provided a blade angle feedback system for an aircraft-bladed rotor rotatable about a longitudinal axis and having an adjustable blade pitch angle. A feedback device is coupled to rotate with the rotor and to move along the axis with adjustment of the blade pitch angle. The feedback device comprises a body having position marker(s) embedded therein, the body made of a first material having a first magnetic permeability and the position marker(s) comprising a second material having a second magnetic permeability greater than the first. Sensor(s) are positioned adjacent the feedback device and configured for producing, as the feedback device rotates about the axis, sensor signal(s) in response to detecting passage of the position marker(s). A control unit is communicatively coupled to the sensor(s) and configured to generate a feedback signal indicative of the blade pitch angle in response to the sensor signal(s) received from the sensor(s).

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