Patent ID: 8894288

Claim:
A system ( 7 ) for cooling a transmission ( 6 ) of a hover-capable aircraft ( 1 ), the system comprising: a stator ( 3 ); a heat exchanger ( 8 ) connectable thermally to said transmission ( 6 ); a fan ( 9 ) for creating a first current (P) of a first heat-carrying fluid from said heat exchanger ( 8 ) to the fan ( 9 ) itself, to remove heat from said heat exchanger ( 8 ); a rotary member ( 10 ), which rotates about an axis (A) to rotate an impeller ( 20 a ) of said fan ( 9 ) about said axis (A); and a bearing ( 16 ) supporting said rotary member ( 10 ) for rotation about said axis (A) and with respect to said stator ( 3 ); the system being characterized by comprising cooling means for cooling said bearing ( 16 ); said cooling means comprising conducting means ( 40 ; 42 , 41 , 30 , 29 ) for conducting a second current (Q) of a second heat-carrying fluid along a path from an outside environment ( 50 ), external to said bearing ( 16 ), to said bearing ( 16 ), so as to cool the bearing ( 16 ); said conducting means ( 40 ; 42 , 41 , 30 , 29 ) comprising: a first cavity ( 41 ) defined by said rotary member ( 10 ) and connectable fluidically to said outside environment ( 50 ); and a second cavity ( 29 ) into which said bearing ( 16 ) faces, and which, when said impeller ( 20 a ) is operated, is at a lower pressure than said outside environment ( 50 ) external to said bearing ( 16 ); said second cavity ( 29 ) being defined by said impeller ( 20 a ).