Patent ID: 6913440

Claim:
A blade ( 19 ) for a stator ( 11 ) of a variable-geometry turbine ( 1 ), particularly for aircraft engines; said stator comprising a supporting structure ( 14 , 15 ); said blade comprising an airfoil profile ( 20 ) hinged to said supporting structure ( 14 , 15 ) to rotate about an axis ( 24 ) inside a conduit ( 18 ) and comprising a pressure front wall ( 30 ) and a suction rear wall ( 29 ); two end walls ( 34 , 35 ) located at opposite ends of said airfoil profile ( 20 ), with respect to a direction parallel to said axis ( 24 ), and cooperating in sliding manner with said supporting structure ( 14 , 15 ); and cooling means ( 74 ) for cooling said end walls ( 34 , 35 ); said cooling means ( 74 ) comprising a number of holes ( 68 ) for the passage of a cooling fluid from an inner cavity ( 39 ) of said blade ( 19 ) and guide means ( 44 , 45 ) for guiding a stream (F 1 ) of cooling fluid inside said blade ( 19 ) and tangentially to at least one of said end walls ( 34 , 35 ); characterized in that said holes ( 68 ) have respective outlets ( 69 ) close to an outer edge ( 70 , 71 ) joining at least one of said end walls ( 34 , 35 ) and said front wall ( 30 ).