Cooled turbine blade

A turbine blade for a turbojet engine, comprising:

• an outer wall having an outer surface and defining a leading edge zone, an intrados face and an extrados face of said blade, at least one longitudinal internal cavity which, in use, is swept by cooling air, and a plurality of rows of holes located in said outer wall for the escape of cooling air from said internal cavity, at least one first row of said rows of holes being disposed in said leading edge zone of said blade wherein each hole of said at least one first row of holes communicates at one end with a first cavity of said at least one longitudinal internal cavity and is opened at its other end in the outer surface of said outer wall, and at least one second row of said rows of holes being provided in said leading edge zone, said at least one second row of holes being parallel to a center line of said leading edge zone such that each hole of said at least one second row communicates at one end with a respective one of said holes in said at least one first row at a position between the two ends of said respective first row hole and opens at its other end in said outer surface of said outer wall, such that the holes of said first and second rows of holes intersect each other in pairs and cooling air from said first longitudinal internal cavity flows through the holes of said at least one first row and cooling air from said holes of said at least one first row flows through the holes of said at least one second row.