Development of the dynamic simulator for the hypersonic turbojet engine including unsteady phenomena

建立了高超声速预冷涡轮喷气发动机的动力学仿真系统，包括进气道起动现象的非定常模型和两相氢流的流动特性。风洞试验和数值模拟表明，进气道嗡嗡声的振幅和频率是由进气道的流入和流出平衡以及进气道后的风道容积决定的。研制了一种电容式空隙率测定仪，研究了氮气质量与传热速率的关系。动态仿真结果与发动机点火试验结果吻合。

We developed a dynamic simulator for the hypersonic precooled turbojet including the unsteady models of the inlet unstart phenomenon and flow properties of two-phase hydrogen flow. Wind tunnel tests and numerical simulation clarify that the amplitude and frequency of the inlet buzz are determined by the inflow and outflow balance of the inlet and the duct volume located after the inlet. A capacitance-type void fraction meter was newly developed and relationship between the quality and heat transfer rate of the nitrogen was researched. The dynamic simulation agrees with the engine firing test.