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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 11413828 B1

PDFFull Text
Date of Patent:
Aug. 16, 2022

Filed:

May. 21, 2018

Aircraft blade and methods of forming and repairing an aircraft blade

Applicant:

Ratier-figeac Sas, Figeac, FR;

Inventors:

Kévin Le Meur, Figeac, FR;

Patrice Brion, Lunan, FR;

Ludovic Prunet, Themines, FR;

Fabien Ramirez, Tauriac, FR;

Assignee:

RATIER-FIGEAC SAS, Figeac, FR;

Attorney:

Cantor Colburn LLP

Primary Examiner:

Daniel McNally

Int. Cl.
CPC ...
B29C 65/00 (2006.01); B64F 5/10 (2017.01); B64F 5/40 (2017.01); B64C 11/26 (2006.01); B29C 73/04 (2006.01); B29C 65/02 (2006.01); B29C 65/48 (2006.01); F01D 5/28 (2006.01); F01D 5/00 (2006.01); F01D 5/14 (2006.01); B29D 99/00 (2010.01); B29L 31/08 (2006.01); B29C 65/16 (2006.01); B29C 65/08 (2006.01); B29C 65/06 (2006.01); B64C 27/473 (2006.01);
U.S. Cl.
CPC ...
B29C 66/73116 (2013.01); B29C 65/02 (2013.01); B29C 65/4815 (2013.01); B29C 66/112 (2013.01); B29C 66/114 (2013.01); B29C 66/1142 (2013.01); B29C 66/543 (2013.01); B29C 66/721 (2013.01); B29C 66/73115 (2013.01); B29C 66/73921 (2013.01); B29C 73/04 (2013.01); B29D 99/0028 (2013.01); B64C 11/26 (2013.01); B64F 5/10 (2017.01); B64F 5/40 (2017.01); F01D 5/005 (2013.01); F01D 5/147 (2013.01); F01D 5/282 (2013.01); B29C 65/06 (2013.01); B29C 65/08 (2013.01); B29C 65/16 (2013.01); B29C 66/71 (2013.01); B29C 66/7212 (2013.01); B29L 2031/08 (2013.01); B29L 2031/082 (2013.01); B64C 2027/4736 (2013.01); F05D 2230/60 (2013.01); F05D 2230/80 (2013.01); F05D 2300/603 (2013.01);
Abstract

A method of making an aircraft blade is provided. The method comprises the steps of: assembling two or more fibre-reinforced thermoplastic composite parts into a blade assembly; and welding the fibre-reinforced thermoplastic composite parts together utilising an additional thermoplastic located at least at locations where the parts will abut when assembled. The additional thermoplastic has a melting or softening temperature lower than a melting temperature of each of the fibre-reinforced thermoplastic composite parts being assembled. The step of welding comprises heating the blade assembly to a temperature above the melting/softening temperature of the additional thermoplastic and below the melting temperature of each of the fibre-reinforced thermoplastic composite parts so as to melt/soften the additional thermoplastic and thereby weld the fibre-reinforced thermoplastic composite parts together to form the aircraft blade.

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