Numerical simulation on combination of circumferential groove and tip clearance modification to control tip clearance flow field
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摘要:
设计了一种平行扩张式叶尖间隙来抑制转子叶尖间隙处的流动损失。对其进行数值模拟发现改型间隙可以有效地抑制转子吸力面处的尾流损失，使转子吸力面尾缘处由径向潜流与泄漏流掺混形成的机匣角区分离涡尺度减小。转子吸力面上激波作用位置向下游移动，边界层长度缩短，边界层分离程度减弱，研究表明改型间隙比设计间隙的峰值等熵效率提高0.374%，稳定裕度提高3.457%。为了提高改型间隙对涡流损失抑制的效果，在叶尖前缘加入周向单槽，研究表明组合方案降低了双泄漏流的风险，使主流与叶尖泄漏流交界面向通道内移动且熵值减小，延迟在小质量流量工况下由前缘溢出而导致的尖峰型失速的发生，且组合方案比设计间隙的稳定裕度提高4.105%，峰值等熵效率提高0.164%。
Abstract:A parallel dilation tip clearance was designed to inhibit the flow loss at rotor tip clearance. Through numerical simulation, it was found that the modified tip clearance can effectively suppress the wake loss at the trailing edge of the rotor and reduce the size of the corner separation vortex in the region of the casing formed by mixing the spanwise underflow and the leakage flow at the trailing edge of the suction surface. The position of shock waves action on the rotor suction surface moved downstream, which shortened the length of the boundary layer and weakened the separation degree of the boundary layer. The research showed that the peak efficiency of the modified tip clearance increased to 0.374% and the stability margin increased to 3.457% compared with the design tip clearance. To improve the effect of vortex loss suppression by the modified tip clearance, a circumferential single casing groove was added at the leading edge of the rotor tip. The results showed that the combination scheme can reduce the risk of double leakage flow, make the interface between the main stream and the tip leakage flow move into the channel and reduce the entropy, delay the occurrence of spike stall caused by leading edge spillage at low flow rate. Moreover, the stability margin and peak efficiency of the combination scheme increased by 4.105% and 0.164%, respectively, compared with the design tip clearance.
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Key words:
- vortex loss /
- wake loss /
- tip clearance modification /
- circumferential groove /
- positive helicity /
- span-wise underflow
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图 1 100%设计转速下不同湍流模型压气机特性线
Figure 1. Compressor characteristic for different turbulence models at 100% design speed
图 3 叶尖间隙与周向槽子午图（单位：mm）
Figure 3. Meridian view of tip clearance and circumferential groove （unit: mm）
图 4 不同网格数与实验值性能对比
Figure 4. Performance comparison of different grids and experiment values
图 5 模拟结果与实验值在设计点处对比
Figure 5. Comparison of simulation results and experiment data at designed point
图 6 不同转速下模拟结果与实验值性能对比
Figure 6. Performance comparison of calculation and experiment with different rotational speeds
图 7 不同转子间隙的形状和网格（单位：mm）
Figure 7. Rotor tip clearance with different shapes and grids （unit：mm）
图 8 不同叶尖间隙方案的压气机性能曲线
Figure 8. Compressor performance curves of different tip clearance schemes
图 9 不同叶尖间隙方案下SMI与PEI对比
Figure 9. Comparison of SMI and PEI for different tip clearance schemes
图 11 转子叶尖前缘三维泄漏流流线分布
Figure 11. Three-dimensional leakage flow streamlines near rotor blade leading edge
图 13 不同叶尖间隙下泄漏涡系三维结构（Q=9×107）
Figure 13. Three-dimensional structure of leakage vortex for different tip clearances （Q=9×107）
图 14 径向涡和相对马赫数在转子吸力面与叶尖尾缘出处分布
Figure 14. Radial vortex and relative Mach number distribution on trailing edge and suction surface of rotor blade
图 15 径向潜流在转子吸力面处沿叶高方向分布
Figure 15. Distribution of span-wise underflow along blade span on suction surface of rotor
图 16 组合方案与SW方案下压气机特性曲线
Figure 16. Compressor performance curves of coupling scheme and SW scheme
图 17 99.2%叶高处转子间隙的熵分布
Figure 17. Distribution of entropy on blade tip clearance at99.2% blade span
图 18 99.2%叶高处转子间隙的相对马赫数分布
Figure 18. Distribution of relative Mach number on blade tip clearance at 99.2% blade span
图 19 相对速度流线在叶尖间隙区域的分布
Figure 19. Relative velocity streamlines distribution at tip clearance area
图 20 叶尖间隙20%～70%弦长处泄漏流三维流线分布
Figure 20. Distribution of 3D leakage flow at 20% to 70% chord of tip clearance
图 21 子午面叶尖间隙处涡量与流线分布
Figure 21. Meridian view of vorticity and streamline distribution in tip clearance region
表 1 Stage 35设计参数
Table 1. Design parameter of Stage 35
设计参数 数值 总压比 1.820 绝热效率 0.828 流量/（kg/s） 20.188 转速/（r/min） 17188.7 
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