Simulation research of nanosecond pulsed plasma actuation flow control on high speed compressor cascade

In order to research the mechanism of nanosecond pulsed plasma aerodynamic actuation flow control on a high subsonic speed compressor cascade, a heat source model based on phenomenology is established to simulate the characteristics of nanosecond pulsed dielectric barrier discharge. The influence of nanosecond pulsed plasma aerodynamic actuation on a compressor cascade flow field is studied in detail from a microsecond time scale perspective, and a preliminary research on the nanosecond pulsed plasma aerodynamic actuation flow control is performed. The results are: the heat source model based on phenomenology is successful in modeling the aerodynamic performance of the shock wave produced by nanosecond pulsed plasma aerodynamic actuation; under the condition of high subsonic speed, the shock wave produced by the nanosecond pulsed plasma aerodynamic actuation still has a dramatic impact on the structure of the compressor cascade flow field, and the impact is influenced by the actuation feature and the characteristics of the flow field; although the inlet flow is high subsonic speed, the nanosecond pulsed plasma aerodynamic actuation is capable of decreasing the total pressure loss at the outlet plane of the compressor cascade passage, and changing the structure of the flow field.