| 摘要 |
A blade (19) for a stator (11) of a variable-geometry turbine (1), particularly for aircraft engines; the blade has an airfoil profile (20) hinged to a structure (14, 15) of the stator to rotate about an axis (24), and having a pressure front wall (30) and a suction rear wall (29); the blade (19) also has two end walls (34, 35), which are located at opposite ends of the airfoil profile (20), cooperate in sliding manner with the structure (14, 15) of the stator (11), and are cooled, in use, by air flowing through a number of holes (68); the outlets (69) of the holes (68) are located close to the outer edges (70, 71) between the end walls (34, 35) and the front wall (30) to generate a tangential stream (F2) of cooling air by virtue of the pressure difference acting on the front and rear walls (30, 29). <IMAGE> |
