US 11,719,253 B2
Blade provided with platforms possessing attachment portions
Thomas Alain De Gaillard, Massy (FR); Caroline Jacqueline Denise Berdou, Bures sur Yvette (FR); and Alexandre Bernard Marie Boisson, Moissy-Cramayel (FR)
Assigned to Safran Aircraft Engines, Paris (FR)
Filed by SNECMA, Paris (FR)
Filed on Apr. 28, 2016, as Appl. No. 15/141,360.
Claims priority of application No. 15 53850 (FR), filed on Apr. 29, 2015.
Prior Publication US 2017/0058912 A1, Mar. 2, 2017
Int. Cl. F01D 5/30 (2006.01); F04D 29/32 (2006.01); B29B 11/16 (2006.01); F01D 5/28 (2006.01); F01D 5/26 (2006.01); F02K 3/06 (2006.01); F04D 29/02 (2006.01); F04D 29/34 (2006.01); F04D 29/64 (2006.01); B29L 31/08 (2006.01)
CPC F04D 29/329 (2013.01) [B29B 11/16 (2013.01); F01D 5/26 (2013.01); F01D 5/282 (2013.01); F01D 5/3007 (2013.01); F02K 3/06 (2013.01); F04D 29/023 (2013.01); F04D 29/34 (2013.01); F04D 29/646 (2013.01); B29L 2031/08 (2013.01); F05D 2220/36 (2013.01); Y02T 50/60 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A blade for a turbine engine, the blade comprising:
a blade root;
an airfoil portion extending upwards from the blade root;
a platform made of composite material and extending transversely to the airfoil portion at a junction between the blade root and the airfoil portion, wherein the platform extends from the blade root along a first axis; and
an attachment portion provided on a lower surface of the platform at a distal end of the platform, configured to cooperate with a first hook of the turbine engine, wherein the attachment portion is at a furthest position of the platform on the first axis away from the blade root.