Element e.g. downstream wall, for use in blade of rotor of turbine stage of e.g. twin spool turbine engine of aircraft, has multiperforation part for passage of flow of cooling air to upstream face of downstream flange

摘要

The element i.e. downstream wall (42), has a multiperforation part (82) for passage of flow of impact cooling air (84) to an upstream face (68) of a downstream flange (60), where the element is projected radially toward inside from a foot of blades (34). The downstream flange is mounted in downstream of a disk (26) of a rotor (20) and the blades that are mounted on the disk, where the element defines a cavity (70) toward downstream by the upstream face of the downstream flange. The multiperforation part has holes having diameter in the order of 0.6 mm.