Gas i.e. cooling air, guiding device for use in gas turbine of aircraft engine, has two guiding elements provided at two adjacent rotor disks and dimensioned such that pre-determined gap is formed between guiding elements

摘要

The device has two guiding elements (7) provided at opposite positions of two adjacent rotor disks (1), where the guiding elements are dimensioned such that a pre-determined gap (5) is formed between the guiding elements. The gap extends in a radial direction of the device. The guiding elements are provided at a distance to each other at the respective rotor disks. The guiding elements exhibit different lengths and different cross sections. The guiding elements exhibit identical geometry.