Patent ID: 7658077

Claim:
A deicing system for an aircraft turbine engine inlet cone, comprising: an air bleed configured to supply pressurizing air from an airflow to at least one of bearing enclosure, and the air bleed configured to remove the pressurizing air from the airflow at one or more bleed points downstream of fan blades of the engine and upstream from a high-pressure compressor of the engine; the at least one bearing enclosure, each of the at least one bearing enclosure including at least one downstream sealing system configured to seal the bearing enclosure from a remainder of the turbine engine and to allow the pressurizing air to enter the bearing enclosure, at least one shaft rolling bearing system, and a lubricant configured to lubricate the at least one shaft roller bearing system; a circuit configured to supply the pressurizing air from the at least one bearing enclosure to an air diffusing means, the circuit including an oil removal system disposed within the at least one of the plurality of bearing enclosures, the oil removal system configured to allow the air bleed to exit from the bearing enclosure, the oil removal system configured to prevent the lubricant from exiting the bearing enclosure; and the air-diffusing means configured to supply the pressurizing air from the circuit to a deicing space, the deicing space configured to receive the pressurized air from the air-diffusing means near a location on an inner surface of the inlet cone disposed on a longitudinal axis of the turbine engine, the deicing space configured to allow the pressurized air to flow along the inner surface of the inlet cone and an outer surface of a secondary cone disposed downstream and enclosed by the inlet cone, and the deicing space configured to allow the pressurized air to flow out of the engine through a wall of the inlet cone at orifices disposed near a downstream end of the inlet cone to convectively heat an outside surface of the inlet cone.