Numerical simulation of effect of circumferential non-uniform tip clearance on rotating instability in a rotor
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摘要:
为了研究非均匀叶尖间隙压气机中的旋转不稳定流动现象，以Rotor 67为研究对象，采用全环非定常数值计算方法，对3种偏心度转子在不同的工况下分别进行了详细的计算，获得了3种偏心度情况下的特性线，得到了3种偏心度情况下的流场结果。数值计算结果表明：当平均叶尖间隙一定时，偏心度对未失速部分的总压比特性线和效率曲线几乎没有影响，而对失速边界影响明显；同心和偏心转子叶尖区域的扰动具有统一的物理结构，其在机匣上表现为移动的低压团，在三维空间上是起始于叶片吸力面，终止于机匣上的三维径向涡，与叶尖间隙泄漏涡并无直接关系；偏心度只是改变了扰动的周向分布规律，并不改变扰动的物理本质。
Abstract:In order to study the flow phenomenon of rotating instability in compressors with non-uniform tip clearance, the Rotor 67 was taken as the research object, and the detailed flow field results and the characteristic lines of three kinds of eccentric rotor were calculated utilizing the three-dimensional full annulus unsteady computational fluid dynamics. The numerical calculation results showed that when the average tip clearance was constant, the eccentricity had little effect on the characteristic line of the non-stall part, but had a significant effect on the stall boundary. The disturbances in the tip region of concentric and eccentric rotors had a unified physical structure. These disturbances presented as moving low-pressure spots on the shroud, which were three-dimensional radial vortices starting from the suction surface of the blade and ending in the shroud, and had no direct relationship with the tip clearance leakage vortex. The eccentricity only changed the circumferential distribution pattern of the disturbances, and did not change the physical nature of the perturbation.
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图 1 同心压气机和偏心压气机的示意图
Figure 1. Schematic diagram of concentric compressor and eccentric compressor
图 6 最大效率点实验和计算的马赫数分布
Figure 6. Mach number distribution of the experimental and calculated value at the point of NPE
图 7 实验和计算的特性线对比（E=0）
Figure 7. Comparison of experimental and calculated characteristic line （E=0）
图 8 非定常方法计算的不同偏心度特性线（ε=1 mm）
Figure 8. Characteristic lines under different eccentricity obtained by unsteady method （ε=1 mm）
图 9 工况A情况监控点C1A4的压力信号频谱图（εave=1 mm、E=0）
Figure 9. Signal spectrum diagram at monitoring point C1A4 in case A （εave=1 mm, E=0）
图 10 工况A情况监控点C1Aj（j=1～10）扰动幅值的轴向分布（f=0.61fBPF）
Figure 10. Axial distribution of disturbance amplitude at monitoring points C1Aj （j=1—10） in case A （f=0.61fBPF）
图 12 工况A情况叶顶截面上的静压系数云图和速度矢量图（εave=1 mm、E=0）
Figure 12. Cps contour and Relative flow vectors at rotor tip plane during transient in case A （εave=1 mm, E=0）
图 13 工况A情况t=0～2τ/5时刻下的机匣壁面静压云图和被静压系数着色的Q准则三维涡系图（εave=1 mm、 E=0）
Figure 13. Cps contour at casing and Q-criterion with CPS visualization during t=0—2τ/5 in case A （εave=1 mm, E=0）
图 14 监控点CiA4（i=1～12）的频谱图
Figure 14. Signal spectrum diagram at monitoring point CiA4 （i=1—12）
图 15 近失速点扰动幅值在机匣上的分布
Figure 15. Distribution about the disturbance in shroud surface at the near stall working point
图 16 近失速点转子进口L1截面上的流量系数分布
Figure 16. Distribution of mass flow coefficient of inlet in plane L1 at the near stall working point
图 17 工况 B和工况 C情况监控点P1的压力信号
Figure 17. Pressure signal for P1 during one cycle in case B and case C
图 18 某瞬时叶顶截面上的静压系数云图和轴向速度云图
Figure 18. Instantaneous contour plot of Cps and Vz at rotor tip plane
图 19 工况 B情况机匣静压系数和被静压系数着色的Q准则三维涡系图（εave=1 mm、E=80%）
Figure 19. Cps contour at casing and Q-criterion with Cps visualization in case B （εave=1 mm, E=80%）
表 1 Rotor 67的主要设计参数
Table 1. Main design parameters of Rotor 67
参数 数值 叶片数 22 旋转速度/（r/min） 16043 叶尖间隙/mm 1.016 展弦比 1.56 叶尖马赫数 1.38 
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表 2 内部计算域单通道网格数分布
Table 2. Mesh statistic for single channel in the inner domain
网格 网格数/万 网格节点数 K J I 叶尖区域 A 47 177 65 41 13 B 68 189 77 49 13 C 80 193 81 53 17 D 119 201 97 61 21
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表 3 外部计算域网格数分布
Table 3. Mesh statistic in the outer domain
网格 网格数/万 网格节点数 K J I 叶尖区域 A 123 170 8 41×22 8 B 190 180 10 49×22 10 C 330 190 15 53×22 15 D 400 200 17 55×22 17
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