A method of changing vibration frequency of a rotating blade of a turbo-machine, especially of a rotating compressor blade in an aircraft turbine engine.

摘要

1. The method of changing vibration frequency of a rotating blade of a turbo-machine is designed especially for rotating compressor blades in aircraft turbine engines. It is characterised in that the geometry of the blade tip is changed by removing mechanically a part of the material from the blade surface, while maintaining the minimum profile thickness of at least 0.5 mm. The blade materials is removed by making very flat bevels at the blade tip and along its edges, or at the blade tip and along the final section of the edge of attack and/or along the final section of the trailing edge.