In this thesis

the blade number of wake effect disturbance coupling was changed in order to vary the exciting frequency of wake effect.In this way

the influence of exciting frequency on compressor steady state performance was studied.Through 12 wake effect disturbance coupling experiments

the stall margin was improved significantly at the wake effect frequencies of 2 000 Hz and 4 000 Hz

and the relative increase of surge margin reached 19.5% and 15.2% respectively.However

the exciting frequency of 1 000 Hz worsens compressor performance.The characteristic frequency of flow separation in rotors wake is about 2 000 Hz.That is

the optimal performance is achieved when the exciting frequency is exactly the characteristic frequency or its multiples.The performance is the worst when the exciting frequency is half of the characteristic frequency.Furthermore

the principle of wake effect

and the relation between stimulation frequency and the improvement of compressor performance was studied in a primary stage.This offers a new idea and method to the application of the conversion of two flow types in axis-flow compressor

especially to the matching in the design of multistage axis-flow compressor.