Blade for a compressor or a turbine of an aircraft engine, an aircraft engine with such a blade, and methods for coating of a blade of an aircraft engine

The invention relates to an aircraft engine having a compressor and at least one turbine, said compressor and this turbine, respectively blades (1) which are each provided with a blade (10) are provided which forms a suction side and a pressure side, wherein at least a first ( 10 is coated) of these blades (10) for the reduction of erosion or wear with a protective layer (16) deposited on at least one side of the airfoil (10) such that at least two (at a boundary line 22) abutting areas (18, 20) are formed, of which a first region (18) is provided with the protective layer (16) such that the protective layer (16) in said first region (18) has a substantially constant first thickness, and of which a second region (20) free of the protective layer (16) or is provided with the protective layer (16) such that said protective layer (16) in this second area (20) in a having substantially constant, differing from the first thickness second thickness, wherein at least two points of the boundary line (22) exists, which deviates link from said boundary curve between these two points.