VANE FOR A COMPRESSOR OR A TURBINE OF AN AIRCRAFT ENGINE, AIRCRAFT ENGINE COMPRISING SUCH A VANE, AND METHOD FOR COATING A VANE OF AN AIRCRAFT ENGINE

摘要

The invention relates to an aircraft engine comprising a compressor and at least one turbine. The compressor and the turbine are each provided with vanes (1), each of which has a blade (10) that forms a suction side and a pressure side. At least one first (10) of said blades (10) is coated with a protective layer (16) in order to reduce erosion or wear. The protective layer (16) is applied to at least one side of the blade (10) in such a way that at least two areas (18, 20) are formed that adjoin each other at a boundary line (22). A first area (18) is provided with the protective layer (16) in such a way that the protective layer (16) has a substantially constant first thickness in said first area (18). A second area (20) is free from the protective layer (16) or is provided therewith in such a way that said protective layer (16) has a substantially constant second thickness in said second area (20), the second thickness differing from the first thickness. Said boundary line (22) has at least two points, of which the connecting line differs from the course of the boundary line between said two points.