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TBCC(涡轮基组合循环)在过渡模态的工作,是这种新型高速动力系统的关键问题。本文针对基于内乘波概念的内并联式TBCC进气道进行了其过渡模态流场的研究。首先,应用本团队自主提出的内乘波式进气道设计概念,提出一种新型TBCC进气道设计方案。然后,验证了其在设计马赫数4.0下实现全流量捕获,在模态转换时,分流板的分流是有效的。针对其在过渡模态马赫数2.5的性能,通过基于数值模拟的设计参数分析,发现在内参考收缩比为3.11时进气道流通面积合适可实现自起动、且综合性能较优。研究还发现,分流板偏转角度范围越小,分流段流动越好、通流出口总压恢复系数也越高。
The TBCC (Turbine Base Combined Cycle) work in the transition mode is a key issue for this new high-speed power system. In this paper, the intercooled TBCC inlets based on the concept of internal multiplication waves are studied. First of all, applying the design concept of the internal multiplied wave inlet designed by our team, a new type of TBCC inlet design is proposed. Then, it is verified that it achieves full-flow capture at a design Mach 4.0, and the splitter shunt is effective during modal transitions. Aiming at the performance of the Mach number 2.5 at the transient modal, it was found through the analysis of the design parameters based on numerical simulation that when the internal reference shrinkage ratio is 3.11, the suitable area of the air inlet can be self-starting and the overall performance is superior. The study also found that the smaller the deflection angle of the manifold, the better the flow in the splitter section and the higher the total pressure recovery factor of the outlet.