Sealing system of a turbo engine

The invention relates to a sealing system for compressor modules of a turbomachine, in particular a gas turbine, namely for sealing a gap between a rotating component (10), in particular a rotor-side blade and a stationary component (12), in particular a stator-side housing, wherein the fixed component ( 12) a run-in coating (13) and the rotating component (10) is associated with one (in the abradable lining 12) incoming armor (11). According to the invention a) the rotating component (10) made of a relatively soft material, namely of a titanium-based alloy or an aluminum-based alloy or a magnesium-based alloy; b) (the rotating member 10) associated with the armor (11) made of a relatively hard material, namely of a nickel-based alloy or iron-based alloy, and c) produced the fixed component (12) associated with the run-in coating (13) of an erosion resistant material, the having a lower hardness than the relatively hard material of the armor.