| 摘要 |
The invention relates to a rotor blade (2) of an axial-flow engine, especially for a fan or a compressor high pressure stage of a gas turbine system. The inventive rotor blade has a configuration in the tip area (2b) for improving the supersonic behavior. According to the invention, the edge (4a) against which air flows has a forward-backward sweep. The tip area of the edge (4b) away from which air flows can be formed such that it is essentially similar to that of the edge against which air flows, whereby the tip area extends over the outer 15 % to 25 % of the blade height (h). |
