Gas turbine engine with compensation disks inside the rotor of the high pressure compressor and manufacturing method for these disks.

摘要

The invention makes it possible to keep the rotor of the high-pressure compressor of a turbojet engine very rigid during the operation of the latter. The inside of the rotor of the high-pressure compressor comprises compensation discs (13) inclined upstream and having no balancing weights. Centrifugal force applied to such a disc creates a loading on this disc including a radial component tending to compensate for the outward loadings which are due to the vanes, facing which vanes the compensation discs (13) are placed. The method for manufacturing such an outlet jet pipe is reduced, especially as regards the blank to be provided in order to obtain such a component. Application to all turbojet engines having compensation discs inside the rotor of their high-pressure compressor. <IMAGE>