Fan rotor for turbomachines such as multi-stream turbojet engines driven by reduction gears

摘要

The present invention has a cone (22) mounted on a hub (18) of a rotation axis (X) and a hub (18) of a fan (16), the cone (22) being a front end portion ( 32A) is provided with an air bleed opening (34) that opens into an air duct (32) passing through the fan rotor (27), said front end portion (32A) comprising a mechanical air intake means a front fan (16) The rotor, wherein the air bleed opening (34) has an annular shape, and the cone (22) is divided by the opening (34) into a front top portion (22A) and a rear frustoconical portion (22B). The present invention relates to a front fan (16) rotor. The invention also relates to a turbomachine forward axial spool comprising said fan (16) rotor.