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:
Feb. 09, 2021

Filed:

Jan. 23, 2015
Applicant:

United Technologies Corporation, Farmington, CT (US);

Inventors:

Wendell V. Twelves, Jr., Glastonbury, CT (US);

Tracy A. Propheter-Hinckley, Manchester, CT (US);

Pauline Cabrila, Bristol, CT (US);

Assignee:

Raytheon Technologies Corporation, Farmington, CT (US);

Attorney:
Primary Examiner:
Assistant Examiner:
Int. Cl.
CPC ...
F04D 29/66 (2006.01); F01D 5/16 (2006.01); B22F 5/04 (2006.01); B22F 7/06 (2006.01); B22F 3/105 (2006.01); F04D 29/32 (2006.01); F04D 29/38 (2006.01);
U.S. Cl.
CPC ...
F04D 29/668 (2013.01); B22F 3/1055 (2013.01); B22F 5/04 (2013.01); B22F 7/06 (2013.01); F01D 5/16 (2013.01); F04D 29/325 (2013.01); F04D 29/388 (2013.01); F05B 2220/302 (2013.01); F05B 2230/31 (2013.01); F05B 2230/60 (2013.01); F05D 2230/22 (2013.01); F05D 2230/30 (2013.01); F05D 2230/31 (2013.01); Y02P 10/25 (2015.11); Y02T 50/60 (2013.01);
Abstract

A blade is provided for a gas turbine engine. The blade includes an airfoil portion with at least one internal cavity and a damper located within the internal cavity. The damper includes a cantilever spring arm. A fan blade is provided for a gas turbine engine. The fan blade includes an airfoil portion with at least one internal cavity; and a damper located within the internal cavity. The damper includes a cantilever spring arm that terminates with a rub surface pad adjacent to a friction bridge between a concave pressure side and a convex suction side of the airfoil portion. A method is also provided for damping a blade of a gas turbine engine. The method includes deflecting a cantilever spring arm to contact a rub surface pad with a friction bridge between a concave pressure side and a convex suction side of an airfoil portion of the blade.


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