Study of flow field characteristics of an over-under TBCC exhaust system during mode transition process
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摘要: 为了研究并联式TBCC（Turbine Based Combined Cycle）排气系统在模态转换过程中出口流场的变化特性及其气动性能的变化规律，采用动网格等技术完成了某并联式TBCC组合排气系统在整个模态转换过程中的非定常数值模拟。同时，对该排气系统模态转换过程中若干工况时的冷流进行了风洞试验，并将试验与数值仿真结果进行比较。研究结果表明：模态转换过程中，并联式TBCC排气系统出口流场的波系结构十分复杂，分流板出口激波对排气系统的气动性能产生了一定影响；TBCC排气系统的推力系数始终保持在0.9以上，但其产生的升力变化较大；风洞试验获得的壁面压力分布及流场纹影与数值模拟结果吻合较好，从而证明了本文数值模拟方法的可行性。Abstract: To study the flow characteristics and aerodynamic performance of an over-under TBCC exhaust system during the mode transition process, the unsteady numerical simulation of the mode transition process is completed by using dynamic grid method. Moreover, a series of cold flow wind tunnel tests of the TBCC exhaust system are carried out under several working conditions during the mode transition process, and the results are compared with the numerical simulation results. The results show that the wave structure of the TBCC exhaust flow field is extremely complex during the mode transition process, and the shock generated at the trailing edge of the splitter plate has some effects on the aerodynamic performance of the exhaust system. The axial thrust coefficient keeps above 0.9, yet the lift varies greatly during the process. The static pressure distribution on the walls and schlieren images obtained by wind tunnel experiments are consistent well with the numerical simulation results, which proves the accuracy of the numerical simulation results in this paper.
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Key words:
- over-under TBCC /
- exhaust system /
- mode transition /
- wind tunnel test /
- aerodynamics performance
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图 1 并联式TBCC排气系统风洞试验模型
Figure 1. Wind tunnel test model of the over-under TBCC exhaust system
图 2 并联式TBCC排气系统实验模型剖面图
Figure 2. Profile of wind tunnel model of the over-under TBCC exhaust system
图 3 并联式TBCC排气系统混合网格示意图
Figure 3. Hybrid grid schematic of over-under TBCC exhaust system
图 4 模态转换过程中TBCC排气系统气流参数与喉道面积的变化规律
Figure 4. Variation of airflow parameters and throat area during mode transition process
图 5 模态转换t=0.01~5.00s内TBCC排气系统出口流场的马赫数等值线图
Figure 5. Mach number contour of TBCC exhaust system in 0.01~5.00s during mode transition process
图 6 模态转换t=0.01~5.00s内TBCC排气系统出口流场的纹影图
Figure 6. Schlieren images of TBCC exhaust system in t=0.01~5.00s during mode transition process
图 7 t=0.01s时TBCC排气系统出口流场纹影与数值计算结果的比较
Figure 7. Comparison of schlieren and numerical results of TBCC exhaust system at t=0.01s
图 8 t=0.01s时涡轮流道上膨胀面沿程静压分布
Figure 8. Static pressure distribution along ramp in turbine channel at t=0.01s
图 9 模态转换t=5.00~12.00s内排气系统出口流场的马赫数等值线图
Figure 9. Mach number contour of TBCC exhaust system in t=5.00~12.00s during mode transition process
图 11 t=9.50s冲压流道上壁面沿程压力分布
Figure 11. Static pressure distribution along the upwall of ramp channel at t=9.50s
图 10 t=10.00s时TBCC排气系统出口流场的波系结构
Figure 10. Wave structure of TBCC exhaust system at t=10.00s
图 12 涡轮流道上膨胀面沿程压力分布随时间的变化
Figure 12. Variation of static pressure distribution along ramp in turbine channel with time
图 13 t=24.00s时TBCC排气系统出口流场
Figure 13. Exit flow field of TBCC exhaust system at t=24.00s
图 14 模态转换过程TBCC排气系统轴向推力系数的变化曲线
Figure 14. Curves of axial thrust coefficient of TBCC exhaust system during mode transition process
图 15 模态转换过程TBCC排气系统升力的变化曲线
Figure 15. Curves of the lift of TBCC exhaust system during mode transition process
表 1 并联式TBCC排气系统试验工况点
Table 1. Experimental points of over-under TBCC exhaust system
t/s Turbojet NPR Ramjet NPR 0 50.66 0 2 50.66 21.00 4 50.66 57.47 8 52.36 55.03 10 52.97 51.57 24 18.06 51.56 25 12.39 51.56 
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表 2 TBCC组合推进系统模态转换过程时间序列
Table 2. Time series of mode transition process for TBCC system
模态转换时间 模态转换阶段 0~5.0s 冲压发动机通道(冷通流)打开 5.0~12.0s 涡轮发动机关闭加力 12.0~20.0s 涡轮发动机降转 20.0~25.0s 涡轮发动机通道(风车)关闭
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