Patent ID: 8714477

Claim:
A support pylon for an aircraft, designed to attach a turbomachine housed in a nacelle to an aircraft fuselage comprising: a cooler, located substantially in a vicinity of a leading edge of the pylon, able to be heated by a hot liquid fluid, said hot liquid fluid intended to be cooled by heat exchange with cold air outside said cooler, the cooler including a first surface cooling means placed at an outer wall of a longitudinal panel of the pylon, and an air channeling means attached to the first surface cooling means at an inner wall of the longitudinal panel of the pylon and positioned in an internal volume of the pylon; at least one air evacuation duct, at an exit from the cooler and extending longitudinally in the internal volume of the pylon to a trailing edge of the pylon; a pressurized-air collection duct which collects pressurized-air from a compressor of the turbomachine emerging downstream from the air channeling means in the at least one air evacuation duct; a regulator valve placed on the collection duct; and an electronic control unit which controls the regulator valve, wherein, when the aircraft is in a low speed phase, the electronic control unit substantially sets the regulator valve to a maximum open position so as to eject pressurized-air in the at least one air evacuation duct to produce a suction of an airflow coming from the air channeling means to generate a flow of cooling air passing through the air channeling means, and when the aircraft is in steady flight, the electronic control unit sets the regulator valve in a closed position.