相邻激励器合成射流流场数值模拟及机理研究  

Numerical simulation and mechanism study of the interaction of adjacent synthetic jet actuators

作　　者：罗振兵[1] 夏智勋[1] 胡建新[1] 王志吉[1] 赵建民[1] 缪万波[1] 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073

出　　处：《空气动力学学报》2004年第1期52-59,共8页Acta Aerodynamica Sinica

基　　金：国家自然科学基金资助项目(批准号:50176055);国家自然科学基金重大研究计划资助项目(批准号:90205016).

摘　　要：建立了将合成射流激励器腔体、出口喉道、外部流场作为单连域计算处理的吹/吸型边界模型。在此基础上,对不同相位差、不同振幅、不同频率的相邻激励器相互作用形成的合成射流流场进行了数值分析。计算结果表明:相邻激励器工作时的相位差、振幅不同、驱动频率不同对其形成的合成射流流场有很大影响,合成射流不再对称分布,流动将发生偏转。其机理是由于两激励器吸入和排出流体流动不同(不同相、不同幅值、不同频率),使得两列旋涡对不对称,因此在两列旋涡对之间存在涡量强度不同和压强梯度,从而引起旋涡对向低压侧和强涡量区偏转。Modeling a blowing/suction type boundary for synthetic jet actuator, it considers the actuator cavity, exit nozzle and exterior flow field as a single computational region. Then the adjacent synthetic flow field is numerical simulated and mechanism studied in different cases (phase, amplitude and frequency). It shows that the adjacent synthetic jet flow field is affected by the phase-difference, amplitude and frequency of two actuators, and the synthetic jet is asymmetric and turning when they are working differently. The main reasons result with the asymmetry and the interaction between the two adjacent synthetic jets, leading to the formation of 'low pressure closed circumfluence region', which is also called entrainment field, and the synthetic jet turns to the region where the pressure is lower and the vorticity magnitude is higher.

关 键 词：合成射流激励器 数值模拟 推力向量控制 计算模型 工作相位差 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程] V23