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:
Mar. 26, 2019

Filed:

Oct. 03, 2014
Applicants:

Safran Aircraft Engines, Paris, FR;

Safran, Paris, FR;

Inventors:

Michael Podgorski, Paris, FR;

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

Son Le Hong, Thomery, FR;

Dominique Marie Christian Coupe, Le Haillan, FR;

Ludovic Edmond Camille Molliex, Brunoy, FR;

Jonathan Goering, York, ME (US);

Assignees:

SAFRAN AIRCRAFT ENGINES, Paris, FR;

SAFRAN, Paris, FR;

Attorney:
Primary Examiner:
Assistant Examiner:
Int. Cl.
CPC ...
F01D 9/02 (2006.01); B29C 53/02 (2006.01); B29C 53/04 (2006.01); B29C 70/54 (2006.01); F01D 25/00 (2006.01); D03D 3/02 (2006.01); C04B 35/80 (2006.01); F01D 9/04 (2006.01); B29C 70/24 (2006.01); B29C 70/48 (2006.01); B29B 11/16 (2006.01); B29C 69/00 (2006.01); B29L 31/08 (2006.01);
U.S. Cl.
CPC ...
F01D 9/02 (2013.01); B29B 11/16 (2013.01); B29C 53/02 (2013.01); B29C 53/04 (2013.01); B29C 69/001 (2013.01); B29C 70/24 (2013.01); B29C 70/48 (2013.01); B29C 70/545 (2013.01); B29C 70/546 (2013.01); C04B 35/80 (2013.01); D03D 3/02 (2013.01); F01D 9/041 (2013.01); F01D 25/005 (2013.01); B29K 2713/00 (2013.01); B29L 2031/08 (2013.01); C04B 2235/3217 (2013.01); C04B 2235/3244 (2013.01); C04B 2235/3418 (2013.01); C04B 2235/3463 (2013.01); C04B 2235/3826 (2013.01); C04B 2235/3873 (2013.01); C04B 2235/5216 (2013.01); F05D 2220/30 (2013.01); F05D 2220/32 (2013.01); F05D 2230/10 (2013.01); F05D 2230/21 (2013.01); F05D 2230/50 (2013.01); F05D 2300/21 (2013.01); F05D 2300/2112 (2013.01); F05D 2300/6012 (2013.01); F05D 2300/6033 (2013.01); F05D 2300/6034 (2013.01); Y02T 50/672 (2013.01); Y02T 50/673 (2013.01);
Abstract

A fiber preform for a hollow turbine engine vane, the preform including a main fiber structure obtained by three-dimensional weaving and including at least one main part, wherein the main part extends from a first link strip, includes a first main longitudinal portion forming a pressure side wall of an airfoil, an U-turn bend portion forming a leading edge or a trailing edge of the airfoil, a second main longitudinal portion facing the first main longitudinal portion and forming a suction side wall of the airfoil, and terminating at a second link strip. The first and second link strips are secured to each other and form a link portion of the main fiber structure. The main longitudinal portions are spaced apart so as to form a gap between the main longitudinal portions forming a hollow in the airfoil.


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