Design method for bionic turbine blade of aero-engine

The invention discloses an aero-engine bionic turbine blade design method which comprises the following steps: firstly, selecting a reference blade, and determining pressure surface data, suction surface data and mean camber line data of the reference blade at different spanwise position sections; interpolation is carried out between adjacent spanwise sections, so that pressure surface, suction surface and mean camber line data of more spanwise position sections are obtained; leading edge sawteeth and trailing edge sawteeth of all sections and transformed mean camber line point coordinates are generated; generating pressure surface and suction surface data according to the changed mean camber line point coordinates; and merging the pressure surface and suction surface data of each spanwise position to obtain geometric data of the whole bionic blade. According to the bionic turbine blade generated through the method, the noise reduction effect of about 6dB can be achieved, and meanwhile due to the fact that th