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:
Jul. 06, 2021

Filed:

Dec. 07, 2017
Applicant:

Safran Aircraft Engines, Paris, FR;

Inventors:
Assignee:
Attorney:
Primary Examiner:
Assistant Examiner:
Int. Cl.
CPC ...
F01D 11/00 (2006.01); F01D 5/22 (2006.01); F01D 5/28 (2006.01); F04D 29/32 (2006.01); F04D 29/64 (2006.01); F04D 29/08 (2006.01); F04D 29/66 (2006.01); F01D 5/14 (2006.01);
U.S. Cl.
CPC ...
F01D 11/008 (2013.01); F01D 5/143 (2013.01); F01D 5/22 (2013.01); F01D 5/282 (2013.01); F01D 11/006 (2013.01); F04D 29/083 (2013.01); F04D 29/322 (2013.01); F04D 29/324 (2013.01); F04D 29/644 (2013.01); F04D 29/667 (2013.01); F01D 5/146 (2013.01); F01D 5/147 (2013.01); F05D 2220/36 (2013.01); F05D 2240/80 (2013.01); F05D 2250/11 (2013.01); F05D 2250/23 (2013.01); F05D 2260/30 (2013.01); F05D 2300/603 (2013.01); Y02T 50/60 (2013.01);
Abstract

The invention relates to an assembly of turbine engine () parts having a longitudinal axis (X), the assembly comprising at least two adjacent fan blades made of a 3D woven composite material, each blade () comprising a root (), a vane () extending from the root (), and an integrated platform () inserted between the root () and the vane (), the platform () extending on either side of the vane () and forming a pressure face platform portion (I) and a suction face platform portion (E), the pressure face and suction face platform portions of adjacent blades being connected by a fin () extending at least radially at the outer side of the pressure face and suction face platform portions (I,E), relative to the longitudinal axis (X), having a substantially triangular transverse cross section and extending axially and so as to upper overlap the longitudinal edges (A,B) of the pressure face and suction face platform portions (I,E) of the adjacent blades.


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