Abstract: 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.

Abstract: The invention relates to an aircraft support pylon (1), designed to attach a turbomachine housed in a nacelle (7) to an aircraft fuselage (8). The pylon comprises a cooler (21), located substantially in the vicinity of a leading edge (12) of the pylon, and able to be heated by a hot fluid, said hot fluid intended to be cooled by heat exchange with cold air outside said cooler. The pylon also comprises at least one air evacuation duct (22), at the exit from the cooler (21) and extending longitudinally in an internal volume of the pylon to a trailing edge (11) of the pylon.

Abstract: The invention relates to an aircraft propeller (1) comprising a turbomachine (8) housed in a nacelle (10) and a cooler (14) capable of being traversed by a hot fluid, which is to be cooled by thermal exchange with cold air external to the cooler. The propeller (1) comprises an air vein (13) (13b) capable of directing pressurized air towards an air duct (20) realized between an outer wall (6) and an inner wall (60) of the nacelle (10). The cooler (14) comprises a first cooling means, called first surface cooling means (145), on a first surface (141), arranged at the outer wall (6) of the propeller nacelle (10) and a second surface cooling means (146), on a second surface (142) arranged at a wall (23) of the air duct (20). The invention also concerns an aircraft equipped with such a propeller.

Abstract: The invention relates to an aircraft propeller (1) comprising a turbomachine (8) housed in a nacelle (10) and a cooler (45) capable of being traversed by a hot fluid, which is to be cooled by thermal exchange with cold air external to the cooler. The propeller (1) comprises an air stream (13) (13b) capable of directing pressurized air towards an air duct (20) realized between an outer wall (6) and an inner wall (60) of the nacelle (10). The cooler comprises volumetric cooling means (14) located in the air duct (20) and surface cooling means (15), unrelated to said volumetric cooling means, located at an outside wall (6, 101) of the aircraft.