| 摘要 |
The invention relates to a cooling device for a jet engine having an axial compressor having a plurality of compressor stages, comprising a rotor having rotor blades, a stator having stator blades, and an annulus. In order to reduce the temperature of the components at the outlet of the high-pressure compressor using simple measures, and thus to increase the efficiency of a jet engine, a slot-shaped branch opening (1) for a cooling air flow (12) that is branched away from the main air flow (11) in a first cavity (3) upstream of the rotor (5) is provided upstream of the last compressor stage (9) of the axial compressor, wherein passage openings (2, 2') for conducting the branched cooling air flow (12) out of the first cavity (3) into a second cavity (4) downstream of the rotor (5) are provided in the rotor (5). |
