马赫数2.5～7.0的二元变几何进气道设计

Design of a two dimensional variable geometry inlet with Mach number 2.5～7.0

针对RBCC发动机Ma=2.5~7.0的宽范围工作要求,提出了一种部分顶板转动+唇口平移的二元进气道变几何方案,并通过数值仿真对其总体性能和调节方法进行了研究。结果表明:采用激波依次封口设计概念的变几何进气道在高低马赫数下的总体性能较优,尤其具有良好的流量捕获能力。转动部分顶板的变几何方案拓宽了进气道工作范围,向后平移唇口可以实现超额定工况的起动和Ma=2.3的自起动。变几何进气道的调节方法简单、工程应用可行。

A scheme of two-dimensional RBCC variable-geometry inlet with rotating partial top wall and translating cowl is proposed for the RBCC engine with a wide Mach number range from 2.5to 7.0. The general performance and adjusting method are studied by the numerical simulation. The results show that the general performance of variable-geometry inlet is better in the entire operating range while shock waves seal the cowl in turn in this design concept. Especially, it has nice flow capture ability. In addition, the operating range is broaden by rotating partial top wall, and the inlet is able to start under the over rated condition and at Ma=2.3 by the backward translating cowl. The adjusting method is simple and feasible in engineering application.