Method and device for controlling laminar flow blade shock wave/boundary layer interference of supersonic compressor by using arc discharge plasma exciter

Abstract

The invention provides a device for regulating and controlling laminar flow blade type shock wave / boundary layer interference of a supersonic compressor by utilizing arc discharge plasma exciters. Thedevice comprises a grid plate (1-1), ceramic blades (1-2) and / or metal blades (1-3), the exciters (1-4) and a high-voltage pulse power supply (1-5). The invention also provides a method for regulating and controlling the laminar flow blade type shock wave / boundary layer interference of the supersonic compressor by utilizing the arc discharge plasma exciters. The method comprises the steps of blade shock wave system structure determination, designing of the layout mode of the plasma exciters, exciter / blade coupling arrangement, and control performance evaluation. The plasma flow control deviceand method have the advantages of being short in response time, wide in excitation frequency band, large in excitation intensity, free of moving parts, simple in structure and the like, and have veryobvious technical advantages in complex flow control inside the compressor.

Description

technical field [0001] The invention relates to plasma technology, in particular to a method and a device for controlling laminar flow blade shock wave / boundary layer interference of a supersonic compressor by using an arc discharge plasma exciter. Background technique [0002] As the power source of the aircraft, the aero engine is the heart of the aircraft, and it is also an important manifestation of the comprehensive strength of a country. The improvement of aero-engine performance requirements means that the aerodynamic performance of the compressor is increasingly demanding. In order to achieve faster flight speed and greater load capacity, aero-engines need greater thrust and thrust-to-weight ratio. Increasing the thrust-to-weight ratio is generally Start from two aspects of reducing the weight of the aero-engine and increasing the unit thrust. With the improvement of aero-engine performance requirements, due to the effect of high pressure ratio on increasing the thr...

AI Technical Summary

Problems solved by technology

In addition, shock wave / boundary layer interference often causes shock wave low-frequency oscillation (several thousand Hz or even lower), which can easily lead to mechanical oscillation, accelerate structure failure, and seriously endanger flight safety

[0005] Traditional active flow control technologies, such as blowing / breathing, often have the characteristics of complex mechanical structure, heavy driving device, limited excitation frequency band and response speed, which are not conducive to their application in aero-engines

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