Sealing arrangement for use in e.g. gas turbine of aircraft engine, has rotor sealing element for sealing of gap between chambers and arranged at rotor, where peripheral surface of sealing element is partially formed in helical shape

摘要

The arrangement (1) has a rotor (11) i.e. shaft, rotatable relative to the stator, where a gap (13) between two chambers (R1, R2) is formed between the rotor and the stator. A rotor sealing element (2) for sealing the gap is arranged at the rotor, where a peripheral surface of the sealing element is partially formed in helical shape. The peripheral surface comprises an increase from one of the chambers to the other chamber. The chamber is formed as a storage chamber, and the sealing element is in contact with fluid i.e. oil, in any one of the chambers. An independent claim is also included for a method for sealing two chambers against each other.