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为研究纳秒脉冲等离子体气动激励在高亚声速来流条件下抑制压气机叶栅流动的分离机制,建立了基于唯象学的模拟纳秒脉冲介质阻挡等离子体气动激励特性的热源模型,在微秒量级时间尺度上分析研究了纳秒脉冲等离子体气动激励对叶栅通道流动结构的影响机制,并初步探究了纳秒脉冲等离子体气动激励的流动控制规律。研究结果表明:基于唯象学的热源模型能够较好地模拟纳秒脉冲等离子体气动激励诱导产生冲击波的气动特性;纳秒脉冲等离子体气动激励诱导产生的冲击波在高亚声速来流条件下能够对叶栅通道流动结构产生较大影响,其影响规律与激励特征和流场特性有关;高亚声速来流条件下,在叶栅通道中施加纳秒脉冲等离子体气动激励能够降低通道出口总压损失,改变流场结构。
In order to study the mechanism of suppression of compressor cascade flow induced by pneumatically excited nanosecond pulsed plasma at high subsonic flow, a thermodynamic model based on phenomenology for simulating pneumatics excitation of nanosecond-impulse dielectric barrier plasma was established. The mechanism of the aerodynamic excitation of nanosecond pulsed plasma on the cascade flow structure is analyzed and studied on the microsecond scale time scale. The flow control law of pneumatically actuated nanosecond pulsed plasma is preliminarily studied. The results show that the heat source model based on the phenomenology can simulate the aerodynamic characteristics of the shock wave induced by the aerodynamic excitation of the nanosecond pulsed plasma well. The shock wave induced by the aerodynamic excitation of the nanosecond pulsed plasma can, under high subsonic flow conditions, And the influence law is related to the excitation characteristics and the characteristics of the flow field. Under the condition of high subsonic flow, applying the nanosecond pulsed plasma aerodynamic excitation in the cascade channel can reduce the total pressure at the exit of the channel Loss, change the flow field structure.