Research on vortex structure near tip clearance in a highly loaded compressor cascade based on oil flow pattern
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摘要:
对某高负荷扩压叶栅的叶顶间隙流动进行不同来流攻角和马赫数下的油流实验以及数值模拟，通过对油流图谱进行拓扑分析，同时辅以数值模拟结果，从近壁面和流场空间共同对叶顶区域的涡系结构及其随负荷变化的规律进行了研究。结果显示，高负荷压气机扩压叶栅叶顶区域存在6个关键的涡结构：叶尖泄漏涡、叶顶分离涡、叶尖二次涡、马蹄涡、通道涡和诱导涡；来流攻角的增加会导致叶片负荷增大以及负荷分布变化，引起最大压差位置提前，导致泄漏提前发生，对流场涡系结构影响较为明显；而来流马赫数的变化对涡系结构的影响较小。
Abstract:Through the oil flow experiments on the tip clearance flow of a highly loaded compressor cascade under different attack angles and Mach numbers, the oil flow patterns on the tip wall and suction surface of the blade were clearly captured, and the vortex structure of the blade tip was studied by topological analysis. The results showed that there existed six key vortices in the tip region of the compressor blade: tip leakage vortex, tip separation vortex, tip secondary vortex, horseshoe vortex and induced vortex; the increase of the attack angle of the incoming flow led to the increase of the blade load and the change of load distribution, the position of the maximum pressure difference was advanced, leading to the leakage in advance, yielding an obvious influence on the vortex structure of the flow field. On the contrary, the change of Mach number had little effect on the vortex structure.
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Key words:
- highly loaded compressor /
- tip clearance /
- oil flow pattern /
- tip leakage vortex /
- vortex interference
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图 5 不同网格数的叶栅总压损失系数
Figure 5. Total pressure loss coefficient of cascade with different number of grid
图 6 Ma1= 0.5, i=0°工况下叶顶端壁和叶片吸力面的原始油流图谱
Figure 6. Origin oil flow pattern of endwall and suction section at Ma1= 0.5, i=0°
图 7 Ma1= 0.5, i=0°工况下叶顶端壁和叶片吸力面带辅助线的油流图谱
Figure 7. Oil flow pattern with guideline of endwall and suction section at Ma1= 0.5, i=0°
图 8 Ma1= 0.5, i=0°工况下叶顶端壁和叶片吸力面极带辅助线的限流线图
Figure 8. Limiting streamline pattern with guideline of endwall and suction section at Ma1= 0.5, i=0°
图 9 Ma1=0.5, i=0°工况下的流场Q等值面图（Q=1.0×108 （蓝）和Q=1.0×1010（红））
Figure 9. Iso-surface of Q=1.0×108 （blue） and Q=1.0×1010 （red） at Ma1=0.5, i=0°
图 10 压气机扩压叶栅叶顶区域涡系结构图
Figure 10. Vortex structure of tip clearance region of compressor cascade
图 11 99.5%叶高截面速度云图
Figure 11. Contour of magnitude of velocity of 99.5% blade height section
图 12 Ma1= 0.5，i=−4°，4°，8°工况下叶顶端壁以及叶片吸力面带辅助线的油流图谱
Figure 12. Oil flow pattern with guideline of endwall and suction section at Ma1= 0.5，i=−4°，4°，8°
图 13 Ma1为 0.6和0.7，i=0°工况下叶顶端壁以及叶片吸力面带辅助线的油流图谱
Figure 13. Oil flow with guideline of endwall and suction section at Ma of 0.6 and 0.7，i=0°
表 1 NPU-01叶栅参数
Table 1. The parameter of the NPU-01 cascade
参数 数值 叶片弦长 C/mm 65 展弦比h/C 1.523 稠度C/t 1.73 安装角${\,\beta _{\text{s} } }$/（°） 21.27 弯角$\theta $/（°） 49.16 叶顶间隙高度$\delta $/mm 1 
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