Abstract
Unsteady behaviors are important issues in flow control of turbomachinery. Pulsed excitation or suction is widely investigated in compressor cascades. This paper presents a discussion on the unsteady flow control realized by dual sweeping jet actuator (SJA) located on the blade suction surface. The unsteady numerical simulations were utilized to study the effect of applying dual SJAs on controlling the corner separation. With the numerical results, the following conclusions could be drawn with current compressor cascade. A maximum total pressure loss coefficient reduction of 6.8% was obtained. The analysis of the flow field pointed out that the regulation mechanisms of the corner separation were different with each SJA. The SJA ahead achieved an interruption of the suction side boundary layer development and the rear SJA enhanced the interaction and entrainment between the excitation stream and the secondary flows. Meanwhile, the different unsteadiness structures of the flow field frequency spectrum compared with single SJA cases were identified. The first peak frequency corresponded to the difference of the two SJAs and the rest frequencies could be regulated to a base frequency and its harmonic frequencies.
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