US 11,885,268 B2
Assembly for a turbine engine
Philippe Gérard Edmond Joly, Moissy-Cramayel (FR); Jean-Marc Claude Perrollaz, Moissy-Cramayel (FR); and Laurent Jablonski, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 17/758,731
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Jan. 6, 2021, PCT No. PCT/FR2021/050010
§ 371(c)(1), (2) Date Jul. 13, 2022,
PCT Pub. No. WO2021/144519, PCT Pub. Date Jul. 22, 2021.
Claims priority of application No. 2000259 (FR), filed on Jan. 13, 2020.
Prior Publication US 2023/0038378 A1, Feb. 9, 2023
Int. Cl. F01D 15/12 (2006.01); F02C 7/36 (2006.01)
CPC F02C 7/36 (2013.01) 9 Claims
OG exemplary drawing
 
1. An assembly for a turbine engine extending along an axis, including a stator, a low-pressure compressor shaft, a low-pressure compressor including a rotor comprising a drum coupled in rotation to the shaft of the low-pressure compressor, a fan including a disc coupled in rotation to the shaft of the low-pressure compressor, wherein the drum comprises a radially internal portion coupled in rotation to the shaft of the low-pressure compressor and a radially external portion fixed to the radially internal portion via removable fixing means, first axial retention means being configured to axially and removably retain the fan disc with respect to the shaft of the low-pressure compressor, second axial retention means configured to axially and removably remove the radially internal portion of the drum with respect to the shaft of the low-pressure compressor, wherein the first axial retention means include a first stop configured to prevent a displacement of the fan disc with respect to the shaft of the low-pressure compressor in a first direction and a first nut configured to form a second removable stop designed to prevent the displacement of the fan disc with respect to the shaft of the low-pressure compressor, in a second direction, opposite the first direction.