US 11,982,195 B2
Separation nozzle for aeronautic turbomachine
Damien Daniel Sylvain Lourit, Moissy-Cramayel (FR); Adrien Jacques Philippe Fabre, Moissy-Cramayel (FR); and Pierre Jean-Baptiste Metge, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 17/604,170
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Apr. 14, 2020, PCT No. PCT/EP2020/060453
§ 371(c)(1), (2) Date Oct. 15, 2021,
PCT Pub. No. WO2020/212344, PCT Pub. Date Oct. 22, 2020.
Claims priority of application No. 1904065 (FR), filed on Apr. 16, 2019.
Prior Publication US 2022/0205366 A1, Jun. 30, 2022
Int. Cl. F01D 9/02 (2006.01); F01D 25/02 (2006.01)
CPC F01D 25/02 (2013.01) [F01D 9/02 (2013.01); F05D 2220/323 (2013.01); F05D 2230/31 (2013.01); F05D 2240/128 (2013.01)] 9 Claims
OG exemplary drawing
 
1. A splitter between a primary flow and a secondary flow of a dual flow turbomachine, wherein the splitter has a single-piece structure comprising an outer annular wall, an inner annular wall, a radial annular wall and an inner annular baffle, defining a first cavity between the outer annular wall and the inner annular baffle, and a second cavity between the inner annular wall, the radial annular wall and the inner annular baffle,
wherein the splitter has at least one air cell formed at least partially in the radial annular wall.