US 12,030,616 B2
Composite blade for a turbine engine rotor
Vivien Mickael Courtier, Moissy-Cramayel (FR); and Anthony Binder, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 17/904,076
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Feb. 12, 2021, PCT No. PCT/FR2021/050258
§ 371(c)(1), (2) Date Aug. 11, 2022,
PCT Pub. No. WO2021/165604, PCT Pub. Date Aug. 26, 2021.
Claims priority of application No. 2001593 (FR), filed on Feb. 18, 2020.
Prior Publication US 2023/0081843 A1, Mar. 16, 2023
Int. Cl. B64C 11/26 (2006.01); B64C 27/473 (2006.01); F01D 5/28 (2006.01); F01D 5/30 (2006.01)
CPC B64C 11/26 (2013.01) [B64C 27/473 (2013.01); F01D 5/282 (2013.01); F01D 5/30 (2013.01); B64C 2027/4736 (2013.01); F05D 2220/323 (2013.01); F05D 2230/20 (2013.01); F05D 2240/30 (2013.01); F05D 2300/6034 (2013.01)] 18 Claims
OG exemplary drawing
 
1. A composite blade for a turbine engine rotor, the composite blade comprising a skin made of woven fibres forming the external profile of the composite blade and an attachment with cylindrical geometry in the direction of a span emerging from a root of the composite blade, the composite blade extends radially between a head and the root, wherein the attachment is intended to hold the composite blade on a hub of said turbine engine rotor,
wherein said composite blade further comprises a spar having a hollow tube structure made of braided carbon fibres, the hollow tube structure is fixed to the attachment and extending inside the skin over at least one portion of the span of the composite blade,
wherein the skin comprises a lower portion and an upper portion, the lower portion starting from the root at the level of which there is an unbinding of the skin, the lower portion surrounding the spar, and the upper portion comprising the head of the composite blade which is a monolithic portion of woven skin without the spar, and
wherein the head of the composite blade is distant from a tip of the spar.