US 12,104,498 B2
Inlet cone for an aircraft turbomachine
Alban Francois Louis, Moissy-Cramayel (FR); Jean-Yves Picart, Moissy-Cramayel (FR); Morgan Balland, Moissy-Cramayel (FR); Florent Robert Andre Godin, Moissy-Cramayel (FR); and Baghdad Achbari, Moissy-Cramayel (FR)
Assigned to SAFRAN AIRCRAFT ENGINES, Paris (FR)
Appl. No. 18/551,624
Filed by SAFRAN AIRCRAFT ENGINES, Paris (FR)
PCT Filed Mar. 23, 2022, PCT No. PCT/FR2022/050536
§ 371(c)(1), (2) Date Sep. 21, 2023,
PCT Pub. No. WO2022/200733, PCT Pub. Date Sep. 29, 2022.
Claims priority of application No. 2103001 (FR), filed on Mar. 25, 2021.
Prior Publication US 2024/0167394 A1, May 23, 2024
Int. Cl. F01D 25/02 (2006.01); B64D 33/02 (2006.01)
CPC F01D 25/02 (2013.01) [B64D 33/02 (2013.01); B64D 2033/0233 (2013.01); F05D 2250/14 (2013.01); F05D 2250/232 (2013.01)] 14 Claims
OG exemplary drawing
 
1. An inlet cone for an aircraft turbomachine, this inlet cone being configured so as to be driven in rotation about an axis and comprising a body of conical or elliptical shape and on which ice is capable of forming, said body having at least one first portion made of a first material referred to as rigid material, and at least one second portion made of a second material which has a hardness less than that of said first material and which is referred to as flexible material,
wherein said first portion is monobloc and formed by a plurality of axial sections connected together by partitions extending in a longitudinal direction relative to the axis, said sections and said partitions defining between them housings, and in that said body comprises a plurality of second portions located in said housings, these second portions being configured to deform elastically in the radial direction with respect to the axis when the cone is driven in rotation.