Loading patent…
AssigneeSafran Aircraft Engines
InventorsKevin Morgane Lemarchand, Nils Bordoni, Guillaume Kubiak
Estimating the term…
The invention relates to an aviation turbine engine fan module including a de-icing system (10) for de-icing an inlet cone (1) and comprising a sheath (30) placed inside an inside space defined upstream by the inlet cone, said sheath comprising a first duct (38) having at least one hot air admission orifice (42), said first duct being configured to convey hot air from a bearing enclosure (22) of the engine towards a wall of the inlet cone in order to heat it from the inside, the sheath further comprising a second duct (40) having at least one outlet situated downstream from the admission orifice of the first duct, said second duct being configured to discharge air from the first duct towards the downstream end of the engine. The invention also provides a method of de-icing a turbine engine inlet cone.
An aviation turbine engine fan module including an inlet cone, a lubrication bearing enclosure, and a de-icing system for de-icing the inlet cone, said de-icing system comprising a sheath placed within a space defined in the inlet cone, said sheath comprising a first duct having at least one hot air admission orifice, said first duct being configured to convey hot air from the lubrication bearing enclosure towards a wall of the inlet cone in order to heat the inlet cone from an inside of the inlet cone,
A de-icing method for de-icing an aviation turbine engine inlet cone, the de-icing method comprising using a first duct of a sheath placed within a space defined in the aviation turbine engine inlet cone, said first duct having at least one hot air admission orifice that conveys hot air taken from an inside of a bearing enclosure to a wall of the aviation turbine engine inlet cone of an engine in order to heat said aviation turbine engine inlet cone from an inside of the aviation turbine engine inlet cone, the de-icing method being characterized in that the de-icing method further comprises discharging the hot air from the first duct via a second duct of the sheath from the aviation turbine engine inlet cone towards a downstream end of the engine, the hot air being discharged from upstream to downstream by flowing inside at least one rotor shaft of the engine, the at least one rotor shaft of the engine being coupled to a fan drive shaft, wherein a sealing collar positioned on an outer surface of the sheath and bearing against the fan drive shaft, holds the sheath in leaktight manner within the fan drive shaft, the sealing collar extends radially outward from the outer surface of the sheath, and wherein the outer surface of the sheath extends substantially parallel to the fan drive shaft.
Dependencies are inferred from the claim text.