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:
Jan. 15, 2019

Filed:

Apr. 28, 2014
Applicants:

Safran, Paris, FR;

Safran Aircraft Engines, Paris, FR;

Inventors:

Thierry Chauvin, Ermenonville, FR;

Franck Bernard Leon Varin, Moissy-Cramayel, FR;

Assignees:

SAFRAN, Paris, FR;

SAFRAN AIRCRAFT ENGINES, Paris, FR;

Attorney:
Primary Examiner:
Assistant Examiner:
Int. Cl.
CPC ...
B29C 65/00 (2006.01); B32B 37/00 (2006.01); C08J 5/00 (2006.01); B31F 5/00 (2006.01); B65H 29/00 (2006.01); B29C 65/08 (2006.01); B30B 5/02 (2006.01); B30B 5/04 (2006.01); B30B 15/34 (2006.01); B21K 25/00 (2006.01); B23P 15/04 (2006.01); B21D 53/78 (2006.01); B21K 3/04 (2006.01); B23P 15/02 (2006.01); F01D 5/28 (2006.01); B29C 65/78 (2006.01); F04D 29/02 (2006.01); F04D 29/32 (2006.01); F01D 25/28 (2006.01); F01D 5/14 (2006.01); B29C 65/48 (2006.01); B23Q 3/06 (2006.01); B29L 31/08 (2006.01); B29K 101/00 (2006.01); B29K 105/00 (2006.01); B29C 65/18 (2006.01);
U.S. Cl.
CPC ...
F01D 5/282 (2013.01); B29C 65/7847 (2013.01); B29C 66/81411 (2013.01); F01D 5/147 (2013.01); F01D 5/288 (2013.01); F01D 25/285 (2013.01); F04D 29/023 (2013.01); F04D 29/324 (2013.01); B23Q 3/063 (2013.01); B29C 65/18 (2013.01); B29C 65/48 (2013.01); B29C 65/7841 (2013.01); B29C 66/12441 (2013.01); B29C 66/12449 (2013.01); B29C 66/12461 (2013.01); B29C 66/12464 (2013.01); B29C 66/12469 (2013.01); B29C 66/301 (2013.01); B29C 66/53 (2013.01); B29C 66/721 (2013.01); B29C 66/7212 (2013.01); B29C 66/72141 (2013.01); B29C 66/742 (2013.01); B29C 66/81423 (2013.01); B29K 2101/00 (2013.01); B29K 2105/0097 (2013.01); B29L 2031/08 (2013.01); B29L 2031/082 (2013.01); F05D 2220/323 (2013.01); F05D 2230/23 (2013.01); F05D 2230/30 (2013.01); F05D 2230/60 (2013.01); F05D 2230/644 (2013.01); F05D 2240/303 (2013.01); F05D 2300/133 (2013.01); F05D 2300/603 (2013.01);
Abstract

A tooling for fastening metal reinforcement on the leading edge of a turbine engine blade, the tooling including a blade support for receiving a blade while leaving surfaces of the leading edge of the blade disengaged; and a leading edge reinforcement support on which the blade support is designed to be mounted, and including two lateral wedges between which the metal reinforcement for the leading edge of the blade is positioned, the wedges being suitable for being capable of moving towards each other and apart from each other and each of them being provided with a suction grid for gripping the metal reinforcement, the leading edge reinforcement support further including heater elements for polymerizing an adhesive film applied on the leading edge surfaces of the blade.


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