G. Wang - School of Power and Energy, Northweatern Polytechnical University, Xi’an, Shanxi, ۷۱۰۱۲۹, China
W. Chu - School of Power and Energy, Northweatern Polytechnical University, Xi’an, Shanxi, ۷۱۰۱۲۹, China
H. Zhang - School of Power and Energy, Northweatern Polytechnical University, Xi’an, Shanxi, ۷۱۰۱۲۹, China
Z. Guo - School of Power and Energy, Northweatern Polytechnical University, Xi’an, Shanxi, ۷۱۰۱۲۹, China

In order to improve the performance of a high-load transonic axial compressor, this paper proposes a method of applying endwall synthetic jet to the casing for active flow control. Taking NASA Rotor۳۵ as the research object, the aerodynamic performance of the compressor is numerically calculated by applying three sets of synthetic jets with different excitation parameters at five different axial positions of ۰%Ca, ۲۵%Ca, ۵۰%Ca, ۷۵%Ca and ۹۶.۱۵%Ca. The results show that the three parameters of excitation position, jet peak velocity and jet frequency all have an effect on the performance of the compressor. The excitation position has the greatest influence on the flow margin of the compressor, and the best position is ۲۵%Ca. After the jet peak velocity is increased from ۱۰۰m/s to ۱۵۰m/s, the flow margin, total pressure ratio and efficiency of the compressor are not greatly improved, which shows that the impact of the jet peak velocity is not as good as the excitation position. After continuing to increase the excitation frequency of the synthetic jet from ۶۰۰Hz to ۱۲۰۰Hz, although the flow margin of the compressor is slightly reduced, the total pressure ratio and efficiency are further improved. This shows that there may be a threshold for the jet frequency, and only when the jet frequency is greater than the threshold can the overall aerodynamic performance of the compressor be improved.

Transoninc axial compressor, Aerodynamic performance improve, Endwall active flow control, Synthetic jet, Numerical simulation