Abstract: The invention relates to a system for rotating a fan (2) of a turbojet engine (1) about a first rotation axis ?, including a reduction gear (3) made up of a planetary gearset placed at the centre of the fan (2), which includes: a central sun gear (31); an outer planet gear (33) attached to the fan (2); at least one satellite gear (32) arranged between the central sun gear (31) and the outer planet gear (33) in order to transmit a rotary movement between the central sun gear (31) and the outer planet gear (33); characterised in that the outer planet gear (33) includes an inner portion (33a) which meshes with the satellite gear (32), as well as an outer portion (33b) to which blades (21) of the fan (2) are directly attached.

Abstract: A turbine engine includes two rotary shafts and a lubrication unit. The lubrication unit has at least one pump which a casing inside of which a rotor is mounted and driven by one of the rotary shafts. The pump casing is rotated by the other rotary shaft such that the actuation of the pump depends on the difference between rotational speeds of the shafts. The shafts are a drive shaft and a fan shaft, respectively, wherein the fan shaft is driven by the drive shaft by means of a reduction gear which is lubricated by the lubrication unit. The reduction gear is annular and the pump passes axially therethrough.

Abstract: The invention relates to a system for rotating a fan (2) of a turbojet engine (1) about a first rotation axis ?, including a reduction gear (3) made up of a planetary gearset placed at the centre of the fan (2), which includes: a central sun gear (31); an outer planet gear (33) attached to the fan (2); at least one satellite gear (32) arranged between the central sun gear (31) and the outer planet gear (33) in order to transmit a rotary movement between the central sun gear (31) and the outer planet gear (33); characterised in that the outer planet gear (33) includes an inner portion (33a) which meshes with the satellite gear (32), as well as an outer portion (33b) to which blades (21) of the fan (2) are directly attached.

Abstract: A device for deicing a separator nose of an aviation turbine engine, and including a separator nose for positioning downstream from a fan of the engine to separate annular channels for passing a primary stream and a secondary stream coming from the engine, and a casing fastened to the separator nose so as to extend it downstream, the casing having an inner shroud defining the outside of the primary stream flow passage, and including at least one air duct incorporated in the inner shroud so as to be formed integrally therewith, the air duct opening out downstream to an air feed and opening out upstream into the inside of the separator nose.

Abstract: A turbine engine includes two rotary shafts and a lubrication unit. The lubrication unit has at least one pump which a casing inside of which a rotor is mounted and driven by one of the rotary shafts. The pump casing is rotated by the other rotary shaft such that the actuation of the pump depends on the difference between rotational speeds of the shafts. The shafts are a drive shaft and a fan shaft, respectively, wherein the fan shaft is driven by the drive shaft by means of a reduction gear which is lubricated by the lubrication unit. The reduction gear is annular and the pump passes axially therethrough.

Abstract: A device for deicing a separator nose of an aviation turbine engine, and including a separator nose for positioning downstream from a fan of the engine to separate annular channels for passing a primary stream and a secondary stream coming from the engine, and a casing fastened to the separator nose so as to extend it downstream, the casing having an inner shroud defining the outside of the primary stream flow passage, and including at least one air duct incorporated in the inner shroud so as to be formed integrally therewith, the air duct opening out downstream to an air feed and opening out upstream into the inside of the separator nose.