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:
Apr. 16, 2019

Filed:

Jul. 03, 2013
Applicant:

Safran Aircraft Engines, Paris, FR;

Inventors:

Thierry Godon, Sevran, FR;

Bruno Jacques Gerard Dambrine, Le Chatelet en Brie, FR;

Franck Bernard Leon Varin, Voulangis, FR;

Assignee:
Attorney:
Primary Examiner:
Int. Cl.
CPC ...
B29C 65/54 (2006.01); B23P 15/04 (2006.01); B29C 65/78 (2006.01); B29C 65/00 (2006.01); F01D 5/28 (2006.01); B29C 65/48 (2006.01); B29C 45/14 (2006.01); B29C 45/16 (2006.01); B29C 45/26 (2006.01); B32B 37/12 (2006.01); B32B 37/16 (2006.01); B32B 38/18 (2006.01); F04D 29/32 (2006.01); B29L 31/08 (2006.01); B29K 305/00 (2006.01); B29L 9/00 (2006.01); B32B 38/00 (2006.01);
U.S. Cl.
CPC ...
B29C 65/542 (2013.01); B23P 15/04 (2013.01); B29C 45/14008 (2013.01); B29C 45/14065 (2013.01); B29C 45/1657 (2013.01); B29C 45/1671 (2013.01); B29C 45/2602 (2013.01); B29C 65/483 (2013.01); B29C 65/7847 (2013.01); B29C 66/12461 (2013.01); B29C 66/301 (2013.01); B29C 66/532 (2013.01); B29C 66/721 (2013.01); B29C 66/72141 (2013.01); B29C 66/742 (2013.01); B29C 66/81423 (2013.01); B29C 66/8221 (2013.01); B29C 66/83241 (2013.01); B32B 37/1284 (2013.01); B32B 37/16 (2013.01); B32B 38/1858 (2013.01); F01D 5/282 (2013.01); F04D 29/324 (2013.01); B29C 65/4835 (2013.01); B29C 2045/14155 (2013.01); B29C 2045/1664 (2013.01); B29K 2305/00 (2013.01); B29L 2009/003 (2013.01); B29L 2031/08 (2013.01); B29L 2031/082 (2013.01); B32B 2038/0076 (2013.01); B32B 2305/08 (2013.01); B32B 2311/18 (2013.01); B32B 2603/00 (2013.01); F01D 5/288 (2013.01); F05D 2240/303 (2013.01); Y02T 50/672 (2013.01); Y02T 50/673 (2013.01);
Abstract

A method of fastening structural metal reinforcement on a portion of a gas turbine blade made of composite material and an injection mold for performing the method, the method including positioning the structural metal reinforcement in an injection mold, positioning the portion of the blade onto which the structural metal reinforcement is to be fastened in the injection mold, the portion of the blade and the structural metal reinforcement being positioned relative to each other in their final relative position while leaving between them a gap, injecting adhesive into the gap between the structural metal reinforcement and the portion of the blade onto which the structural metal reinforcement is to be fastened, and polymerizing the adhesive.


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