The physical characteristics of self-sustain shock oscillation and the key factors that affect the shock oscillation in turbine-based combined-cycle(TBCC) inlet were investigated through unsteady numerical simulation method in this paper. The terminal shock oscillation in the throat was caused by the separation bubble appeared in the lower wall of the turbojet flowpath. The angle of the splitter and the offset of the diffuser were the main factors which affect the characteristics of the shock oscillation. When the angle of the splitter increased from 0 deg to 12 deg, the frequency of terminal shock increased from 100Hz to 133Hz; while when it was greater than 18 deg the terminal shock oscillation phenomenon disappeared. Different offset of the turbojet diffuser affect the motion of terminal shock in the inlet. When the y-coordinate value of the control point (y m ) in the turbojet diffuser was smaller than 1.5, the shock oscillated in the inlet; when y m was greater than 2.0, the shock oscillation disappeared. The bleed in the diffuser was able to control the oscillation of the terminal shock.

中文翻译：

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基于涡轮的上下联合循环进气道末端激波振荡的数值模拟

通过非稳态数值模拟方法，研究了自持式激波振荡的物理特性以及影响涡轮联合循环进气道激波振荡的关键因素。涡轮喷气流路下壁中出现的分离气泡导致喉咙中的末端冲击振荡。分流器的角度和扩散器的偏移是影响冲击振动特性的主要因素。当分离器的角度从0度增加到12度时，终端冲击的频率从100Hz增加到133Hz；当大于18度时，终端冲击振荡现象消失。涡轮喷气扩散器的不同偏移量会影响进气口中终端冲击的运动。当涡轮喷气扩散器中控制点的y坐标值（ym）小于1.5时，冲击在入口处振荡；当ym大于2.0时，冲击振荡消失。扩散器中的排气能够控制终端电击的振荡。