Combined plasma flow control device and method for regulating inlet shock wave/boundary layer interference flow separation

Abstract

The invention provides a combined plasma flow control circuit system. The system comprises an air inlet passage simplified model (3), a shock wave generator (4), a pulsed arc discharge plasma actuator(1), a pulsed surface dielectric barrier discharge plasma actuator (2), a cylindrical vertical through hole (5) and a pulsed power supply (6). The invention further provides a method for regulating and controlling air inlet passage shock wave / boundary layer interference flow separation through combined plasma actuation. By the aid of the combined plasma actuation control device, on the one hand,persistent disturbance of air inlet passage incident shock waves is realized through flow-direction array type high-frequency low-energy pulsed arc plasma shock wave actuation, so that the strength ofthe shock waves is weakened; and on the other hand, the spanwise vortex structure is induced through surface dielectric barrier discharge plasma shock wave actuation, boundary layer transition is promoted, and thus the capability of inhibiting flow separation is improved.

Description

technical field [0001] The invention relates to a plasma active flow control technology, in particular to a method for regulating the separation of inlet shock wave / boundary layer interference flow and a corresponding combined plasma actuator. Background technique [0002] Turbo-ram combined power is the core technology for the development of near-space high-speed aircraft. The new generation of turbo-ram combined power has a wide working speed range (0-4.5Ma), and the reciprocating switching between turbine and ram working modes brings great challenges to the aerodynamic design of wide speed range, low loss, and weak distortion inlet. The intake port is prone to complex three-dimensional shock wave / boundary layer interference problems under non-design conditions. The flow separation induced by the strong reverse pressure gradient of the shock wave will cause the total pressure loss and flow field distortion of the intake port. The total pressure The loss directly affects t...

AI Technical Summary

Problems solved by technology

The new generation of turbo-ram combined power has a wide range of working speeds (0-4.5Ma), and the reciprocating switching between turbine and stamping modes brings great challenges to the aerodynamic design of wide speed range, low loss, and weak distortion inlet

The intake port is prone to complex three-dimensional shock wave / boundary layer interference problems under non-design conditions. The flow separation induced by the strong reverse pressure gradient of the shock wave will cause the total pressure loss and flow field distortion of the intake port. The total pressure The loss directly affects the thrust of the engine, and the distortion of the flow field will propagate downstream, and in severe cases, it will cause local edge combustion in the combustion chamber

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