Swirl characteristics of inward turning combined power inlet at low speed
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摘要:
通过仿真获得了内转式进气道在低来流马赫数工况下的旋流特性和进出口参数的影响规律。结果表明：低速状态时，进气道流量系数较大，受“V”形唇口形状的影响，唇口绕流显著，沿着宽度方向存在强速度梯度，在唇口内侧产生1对强反向旋转旋涡，并在弯曲内流道中逐渐脱离唇罩壁面。当来流马赫数较低或出口马赫数较高时（流量系数较大），唇口侧产生的旋涡尺度更大。出口AIP（aerodynamics interface plane）的旋流角呈“V”形反对称式分布，随着出口马赫数的增加，逐步发展为“W”形反对称式分布，大尺度旋流角极值区与管道中心附近小尺度旋流角极值区相融合，并使得气流畸变指数增加，旋流畸变指数增加了1倍左右，周向总压畸变指数增大了1个量级。
Abstract:The swirl characteristics of the inward turning inlet under low incoming Mach number and the influences of inlet and outlet parameters were obtained by simulation. The results showed that at low speed, the flow coefficient of the inlet was large. Affected by the shape of the “V” lip, the encircling flow around the lip was significant, and there was a strong velocity gradient along the width direction. A pair of strong counter-rotating vortices were generated inside the lip, and gradually separated from the lip wall in the curved inner flow channel. When the incoming Mach number was low or the outlet Mach number was large (the flow coefficient was large), the vortex scale generated on the lip side was larger. The swirl angle of the outlet AIP (aerodynamics interface plane) cross section showed a “V” anti-symmetric distribution. With the increase of the outlet Mach number, it gradually developed into a “W” anti-symmetric distribution. The large-scale swirl angle extreme area merged with the small-scale swirl angle extreme area near the center of the pipeline, which increased the airflow distortion index. The swirl distortion index increased by about 1 times, and the circumferential total pressure distortion index increased by an order of magnitude.
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Key words:
- combined engine /
- inward turning inlet /
- swirl phenomenon /
- vortex /
- airflow distortion
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图 4 仿真、实验方法在MaAIP=0.428时的表面压力分布
Figure 4. Surface pressure distribution of simulation and experimental methods at MaAIP=0.428
图 5 数值仿真、实验方法在MaAIP=0.428时AIP的总压恢复系数云图
Figure 5. Total pressure recovery coefficient contour of the AIP surface at MaAIP = 0.428 by numerical simulation and experimental method
图 7 唇罩内侧云图及线图细节显示
Figure 7. Details of the contour and line map on the inside of the cowl
图 8 三维旋涡结构/空间流线图及对称面图谱
Figure 8. Three-dimensional vortex structure/space streamline diagram and symmetry plane map
图 9 MaAIP=0.2，Ma∞=0.1，0.15，0.2，0.25工况下截面马赫数云图与流线图
Figure 9. Cross-section Mach number contour and streamline diagram at MaAIP=0.2，Ma∞=0.1，0.15，0.2，0.25
图 10 Ma∞=0.1，MaAIP=0.2，0.3，0.4，0.5工况下各截面马赫数云图与流线图
Figure 10. Cross-section Mach number contour and streamline diagram at Ma∞=0.1，MaAIP=0.2，0.3，0.4，0.5
图 11 Ma∞=0.1，MaAIP=0.2，0.3，0.4，0.5工况下Q-准则所作出的旋涡结构图
Figure 11. Vortex structure diagram made by Q-criterion at Ma∞=0.1，MaAIP=0.2，0.3，0.4，0.5
图 12 Ma∞=0.1，MaAIP=0.2，0.3，0.4，0.5工况下MaAIP 云图及流线图
Figure 12. Mach number contour and streamline diagram of the AIP surface at Ma∞=0.1，MaAIP=0.2，0.3，0.4，0.5
图 13 MaAIP=0.2，Ma∞=0.1，0.15，0.2，0.25工况下对称面总压恢复系数、马赫数云图与流线图
Figure 13. Total pressure recovery coefficient, Mach number contour and streamline diagram of symmetry plane at MaAIP=0.2，Ma∞=0.1，0.15，0.2，0.25
图 15 不同MaAIP下AIP截面的旋流角分布（Ma∞=0.2）
Figure 15. Swirl angle distribution of AIP cross section at different MaAIP （Ma∞=0.2）
表 1 仿真模拟边界条件设置
Table 1. Simulation boundary conditions setting
参数 数值 来流马赫数 0.7 进口静压/Pa 101 325 进口静温/K 300 出口压力/Pa 119 563.5 出口总温/K 348 
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