Due to the design requirements of higher efficiency and pressure ratio, and the characteristics of transonic velocity and bending-torsional profile, the problem of wake disturbance has become increasingly prominent on aeroengine blade. Traditional aerodynamic design makes it difficult to achieve the ideal control of blade wakes. While non-uniform serrations in the wing trailing edge indicate that they have better adaptability to blade wakes in nature. In this research, the serration feature is applied at the trailing edge of compressor blade, and then the effects of different serrated structures are explored on wake disturbance and aerodynamic performance. According to the characteristics of flow field and wake distribution in each blade span, a matching mechanism is established between wake velocities and serrated parameters. Finally, design criterion of the non-uniform serrations is successfully developed. The results show that the designed non-uniform serrations can enhance the mixing of mainstream and blade wakes, effectively reduce the wake loss and improve aerodynamic performance, resulting in an increase in compressor efficiency to 90.42% and an expansion of the stable operating range by 12.25%. This research not only has an important theoretical significance for wake control, but also has a great engineering significance for aeroelastic design of the high-performance blade-disk system.
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