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为利用内收缩进气道在流量捕获、高性能压缩等方面的优势,积极探索基于内收缩式TBCC进气道设计技术是当前高速推进系统的前沿方向。本文基于自主提出的内乘波式进气道技术,研究了内乘波式TBCC进气道变几何技术。为保证变几何作动时进气道气流密封,同时减小密封板对进气道等熵波系的影响,采用对称面带二元过渡板的内乘波进气道作为TBCC基础型面。根据TBCC变几何方案,随马赫数变化进气道进行变几何作动,得到了变几何参数随来流马赫数变化的拟合公式,为各马赫数下变几何作动提供参考和依据.数值模拟结果表明:在工作马赫数2.0～4.0范围内,变几何进气道均能成功起动,流量系数在0.86以上,喉道总压恢复系数在0.77～0.93之间,气动性能良好。
In order to take advantage of the internal contraction of the inlet in the flow capture, high-performance compression, and actively explore the contraction based on the TBCC intake port design technology is the forward direction of the current high-speed propulsion system. Based on the self-propelled in-port wave inlet technology proposed in this paper, the in-passage wave-based TBCC inlet variable geometry technique is studied. In order to ensure the seal of the inlet air flow under variable geometry and to reduce the influence of the seal plate on the isentropic wave regime of the inlet airway, the internal wave inlet of the symmetric plane with binary transition plate is adopted as the TBCC basic profile. According to the variable geometry scheme of TBCC, the geometry of the inlet varies with Mach number, and the fitting formula of varying geometric parameters with the change of Mach number is obtained, which provides a reference and basis for the geometric changes of each Mach number. The simulation results show that the variable geometry inlet can start up successfully with the Mach number of 2.0 ~ 4.0, the flow coefficient is above 0.86 and the throat total pressure recovery coefficient is between 0.77 and 0.93, and the aerodynamic performance is good.