Turbomachine aircraft propeller

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 ) ( 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 ( 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.

1 . 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 ) comprising an air vein ( 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 ( 14 ) comprising:
 a first cooling means, called first surface cooling means ( 145 ), on a first surface, called outer surface ( 141 ), arranged at the outer wall ( 6 ) of the propeller ( 1 ) nacelle ( 10 ),   a second cooling means, called second surface cooling means, on a second surface ( 146 ), called inner surface ( 142 ), arranged at a wall ( 23 ) of the air duct ( 20 ),   
       wherein the air duct ( 20 ) comprises an air inlet ( 21 ) arranged at the front of the propeller to create an additional air inlet. 
     
     
         2 . Aircraft propeller according to  claim 1 , wherein:
 the first surface cooling means ( 145 ) is sized so as to be sufficient to ensure the desired cooling when the aircraft is in flight, within preselected environmental and speed conditions,   the second surface cooling means ( 146 ) is sized so as to be sufficient to ensure the desired cooling when the aircraft is at low or zero speed, within preselected environmental conditions.   
     
     
         3 . Aircraft propeller according to any one of the preceding claims, wherein an air inlet ( 11 ) is located at a 1 st  stage of an air compressor of the turbomachine ( 8 ) and in that the associated air vein ( 13 ) emerges upstream of cooler ( 14 ). 
     
     
         4 . Aircraft propeller according to any one of  claims 1  to  2 , wherein an air inlet ( 11   b ) is located downstream from an air compressor of the turbomachine ( 8 ) and in that the associated air vein ( 13   b ) emerges downstream from the cooler ( 14 ). 
     
     
         5 . Aircraft propeller according to  claim 4 , wherein the air vein ( 13   b ) comprises, at the air duct ( 20 ), an ejector, which ejects pressurized air into said air duct ( 20 ). 
     
     
         6 . Aircraft propeller according to one of  claims 1  to  2 , comprising two air veins ( 13 ,  13   b ) and a valve ( 12 ,  12   b ) associated with each vein, an air vein ( 13 ) emerging upstream of the cooler ( 14 ) and an air vein ( 13   b ) emerging downstream from the cooler, the valves ( 12 , 12   b ) controlling the entry of pressurized air according to one vein or the other. 
     
     
         7 . Aircraft propeller according to any one of the preceding claims, wherein at least one of the first ( 145 ) and second ( 146 ) surface cooling means is a set of fins extending from the outer/inner surface, and oriented mostly parallel to the direction of the airflow. 
     
     
         8 . Aircraft propeller according to any one of the preceding claims, wherein the first and second surface cooling means ( 145 ,  146 ) are of similar architecture. 
     
     
         9 . Aircraft comprising a propeller according to any one of the preceding claims.