An aircraft support pylon designed to attach a turbomachine housed in a nacelle to an aircraft fuselage is disclosed. The pylon includes a cooler, located substantially in the vicinity of a leading edge of the pylon, and able to be heated by a hot fluid, the hot fluid intended to be cooled by heat e
An aircraft support pylon designed to attach a turbomachine housed in a nacelle to an aircraft fuselage is disclosed. The pylon includes a cooler, located substantially in the vicinity of a leading edge of the pylon, and able to be heated by a hot fluid, the hot fluid intended to be cooled by heat exchange with cold air outside the cooler. The pylon also includes at least one air evacuation duct, at the exit from the cooler and extending longitudinally in an internal volume of the pylon to a trailing edge of the pylon.
대표청구항▼
1. 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 exc
1. 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; andan 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. 2. The support pylon according to claim 1, wherein: the first surface cooling means is sized so as to be sufficient to ensure cooling of the liquid fluid when the aircraft is in steady flight, within preselected environmental and speed conditions, andthe air channeling means is sized so as to be sufficient to ensure cooling of the liquid fluid when the aircraft is the low speed phase, within preselected environmental conditions. 3. The support pylon according to claim 1, wherein the air channeling means is a surface cooling means. 4. The support pylon according claim 1, wherein the longitudinal panel on which the first surface cooling means is placed is an upper surface of the pylon. 5. The support pylon according to claim 1, further comprising an air outlet emerging at the outside of the pylon, at the trailing edge, and on which the at least one air evacuation duct is connected. 6. The support pylon according to claim 1, further comprising an additional surface cooling means placed on an outer wall opposite the outer wall of the longitudinal panel on which the first surface cooling means is placed. 7. An aircraft comprising a support pylon according to claim 1. 8. The support pylon according to claim 1, further comprising a liquid fluid flow regulator valve which directs flow of the liquid fluid towards the first surface cooling means or towards the air channeling means, wherein the electronic control unit controls the liquid fluid flow regulator valve. 9. The support pylon according to claim 1, further comprising an air inlet duct which directs outside air towards the air channeling means, the air inlet duct being located upstream of the air channeling means. 10. The support pylon according to claim 9, wherein the air inlet duct includes an opening/closing valve which opens and closes the air inlet duct, the opening/closing valve is provided at an outer wall of an upper surface of the pylon. 11. The support pylon according to claim 1, wherein the first surface cooling means comprises a set of fins oriented substantially parallel to flow lines of an air stream circulating over the outer wall of the pylon when the aircraft is in flight.
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이 특허에 인용된 특허 (8)
Gliebe Philip R. (Cincinnati OH) Majjigi Rudramuni K. (Cincinnati OH), Aircraft pylon.
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