基于脉冲射流阵列的边界层吸入式S形进气道旋流全局调控机理与方法

The inlet system of the next generation of wide-body jet and stealthy UCAV abandons the traditional boundary layer diverter and inhales massive forebody boundary layer flows, leading to apparent swirling flow and serious inlet/engine matching problem. Aiming at providing a new way for the high performance of boundary layer ingesting inlets at wide operating envelope, this project brings forward a new flow control method which combines the plasma-jet type vortex generator array and the global regulation concept based on the rule of equivalent vortex signal. At first, this project will reveal the vortices coupling mechanism of multi-jets from holes and slots in the subsonic boundary layer. The design method of the plasma-jet type vortex generator array can thus be established. Then, according to the concept of global regulation, the plasma jet array will be used to suppress the inherent swirling flows and separated flows of S-shaped duct with rectangular cross sections and S-shaped inlet with variable cross sections globally and actively. The interaction mechanism between the jet-induced vortex and the duct-induce vortex with different size scale will be revealed. The effect of the design parameters and installation parameters of the plasma jet array on the swirling index, distortion index and total pressure recovery of the inlet will also be obtained. Finally, the control effect will be confirmed by a specially designed wind tunnel test.

下一代宽体客机、隐身无人作战飞机等的S形进气道均未采用传统边界层隔道，故吸入了较厚的机体边界层，导致了显著的管内旋流流动和严重的进气道/发动机匹配问题。本项目提出了将火花放电型激励器阵列与基于“当量涡”准则的全局流动控制策略相结合的流动控制方法，有望为实现边界层吸入式S形进气道的宽域高效工作提供新途径。首先，拟揭示亚声速边界层中多斜孔、多斜缝瞬态射流的耦合作用机理，建立基于等离子体射流的涡流发生器阵列设计方法。进一步，依据基于“当量涡”准则的全局流动控制策略，设计激励器阵列依次对矩形截面S形弯管、变截面超短S形进气道内的整体旋流、分离流进行全局主动调控，并揭示两类不同尺度旋涡(激励器诱导涡、弯管诱导涡)之间的作用机理，掌握激励器阵列安装参数、工作参数对进气道出口旋流指数、畸变指数、总压恢复系数的改善规律，建立全局的、通用的S形进气道主动流动控制方法，最终完成实验检验。

下一代宽体客机、隐身无人作战飞机等的新型S形进气道均未采用传统边界层隔道，故吸入了较厚的机体边界层，导致了显著的管内旋流流动和严重的进气道/发动机匹配问题。本项目提出了基于火花放电型激励器阵列的内流控制方法，有望为为边界层吸入式S形进气道的性能提升提供新途径。采用仿真和试验相结合的研究方法，本项目揭示了亚声速边界层中多斜孔、多斜缝瞬态射流的耦合作用机理，建立了基于等离子体射流的涡流发生器阵列设计方法，掌握了激励器阵列安装参数、工作参数对进气道出口性能参数的影响规律，并针对边界层吸入条件下变截面S形进气道开展了风洞试验验证。项目支撑获得了国防技术发明一等奖1项，发表学术论文9篇，获授权发明专利1项