| 摘要 |
A bladed rotor (1) of a gas turbine for aeronautic engines is cooled by making an air mass flow through a plurality of passages (10), each one defined by a turbine disk (2) on one side and by a root (7) of a corresponding blade (5) coupled to this turbine disk (2) on the other, the incoming air of each passage (10) being subdivided into two or more airflows and each flow being directed towards the turbine disk (2) in a predefined direction (21 and 22). |
