US 11,851,157 B2
Aircraft turbine engine comprising variable-pitch propeller blades
Vincent Joudon, Moissy-Cramayal (FR); Clément Cottet, Moissy-Cramayal (FR); Vivien Mickaël Courtier, Moissy-Cramayal (FR); and Régis Eugène Henri Servant, Moissy-Cramayal (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 18/006,130
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Jul. 15, 2021, PCT No. PCT/FR2021/051310
§ 371(c)(1), (2) Date Jan. 19, 2023,
PCT Pub. No. WO2022/018353, PCT Pub. Date Jan. 27, 2022.
Claims priority of application No. 2007809 (FR), filed on Jul. 24, 2020; and application No. 2007812 (FR), filed on Jul. 24, 2020.
Prior Publication US 2023/0286643 A1, Sep. 14, 2023
Int. Cl. B64C 11/06 (2006.01); F04D 29/32 (2006.01)
CPC B64C 11/06 (2013.01) [F04D 29/323 (2013.01)] 15 Claims
OG exemplary drawing
 
1. A system for controlling the pitch setting of a propeller vane or an aircraft turbine engine, wherein it comprises:
a cup comprising an annular wall extending about an axis intended to be a pitch axis of the vane, said annular wall comprising a lower axial end closed by a bottom wall and an upper axial end that is open and configured to allow a root of the vane to be mounted inside the cup, the bottom wall being configured to cooperate in a form-fitting manner with a free end of said root so that the cup is secured in rotation to the root about said axis, and
an immobilisation ring extending about said axis and configured to be mounted about the root, this immobilisation ring being configured to be mounted within the cup and to cooperate with the root and the annular wall of the cup, respectively, in order to ensure the axial retention of the root within the cup.