| 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 ) ( 13 b ) 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. |