US 12,071,865 B2
Air flow straightening stage for a turbomachine
Christophe Marcel Lucien Perdrigeon, Moissy-Cramayel (FR); Cédric Zaccardi, Moissy-Cramayel (FR); and William Henri Joseph Riera, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 18/249,838
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Oct. 20, 2021, PCT No. PCT/FR2021/051841
§ 371(c)(1), (2) Date Apr. 20, 2023,
PCT Pub. No. WO2022/084634, PCT Pub. Date Apr. 28, 2022.
Claims priority of application No. 2010764 (FR), filed on Oct. 20, 2020.
Prior Publication US 2023/0383665 A1, Nov. 30, 2023
Int. Cl. F01D 9/04 (2006.01); F01D 25/24 (2006.01)
CPC F01D 9/042 (2013.01) [F01D 25/24 (2013.01); F05D 2250/71 (2013.01); F05D 2260/30 (2013.01)] 14 Claims
OG exemplary drawing
 
1. A bypass turbine engine with a longitudinal axis, the turbine engine comprising:
an upstream fan wheel; and
a downstream assembly for straightening an airflow from a secondary annular flow path delimited radially inwardly by a radially inner annular wall element and delimited radially outwardly by a radially outer annular wall element,
wherein the downstream assembly includes a radially inner shroud disposed radially inwardly of the radially inner annular wall element, a radially outer shroud disposed radially outwardly of the radially outer annular wall element, and vanes extending between the radially inner and outer shrouds and being fastened at a first end portion to the radially inner shroud and at a second end portion to the radially outer shroud, the first end portions being disposed in-between the radially inner annular wall element and the radially inner shroud and the second end portions being disposed in-between the radially outer annular wall element and the radially outer shroud, and
wherein the vanes comprising an aerodynamically useful portion extending between said first and second end portions and defining an intrados face and an extrados face, wherein for each vane, in a plane perpendicular to the longitudinal axis, each aerodynamically useful portion is curved in the circumferential direction with a C-like shape.