Fan rotor for a turbo machine such as a multiple flow turbojet engine driven by a reduction gear
A forward fan rotor is disclosed with a hub of axis of rotation (X) and a cone mounted on the hub of the fan. The cone comprises an air bleed orifice which opens into an air duct of which a forward end portion passes through the fan rotor, said forward end portion comprising mechanical air entrainment means. The air bleed orifice has an annular shape and in that the cone is divided by said orifice into a front vertex portion and a rear frustoconical portion. A turbomachine forward axial spool equipped with such a fan rotor is also disclosed.
1. A turbine engine fan rotor which is intended to be mounted so as to rotate about an axis of rotation (X), the rotor comprising:
a hub, and
a cone which is mounted upstream of the hub;
the cone comprising an air take-off opening which opens into an air channel, an upstream end portion of which comprises a ring of radial blades, wherein the air take-off opening has an annular shape which is coaxial to the axis of rotation (X) of the fan rotor, the cone being divided by the take-off opening into a front summit portion and a rear frustoconical portion.
2. The fan rotor according to claim 1 , wherein the summit portion is attached to the frustoconical portion of the cone by the ring of radial blades.
3. The fan rotor according to claim 1 , wherein the ring of blades is arranged in said cone.
4. The fan rotor according to claim 1 , wherein the air channel is centred on the axis of rotation (X) of the rotor.
5. An upstream axial body of the turbine engine comprising a turbine engine fan rotor which is produced according to claim 1 , and at least one portion of a compressor shaft, wherein the air channel extends in the upstream axial body beyond the fan rotor, the air channel comprising at least one oil-cooling wall which is intended to cool oil by exchanging heat through said wall with the air flow circulating in the air channel.
6. The upstream axial body according to claim 5 , wherein the cooling wall is located downstream of the ring of radial blades.
7. The upstream axial body according to claim 6 , wherein the rotational torque of the compressor shaft is transmitted to the rotor of the fan by a speed reduction gear which is placed in the upstream axial body, the speed reduction gear being lubricated by oil which is cooled through contact with said cooling wall.
8. A turbine engine comprising the upstream axial body according to claim 5 , and at least one hollow central shaft, wherein the air channel opens downstream into the hollow central shaft, the air flow circulating in the air channel being discharged downstream into said hollow central shaft.