叶尖间隙及转速增大对对转压气机非定常流场的影响研究

刘波; 李敏; 张瑞辰; 茅晓晨

doi:10.13224/j.cnki.jasp.20240045

叶尖间隙及转速增大对对转压气机非定常流场的影响研究

doi: 10.13224/j.cnki.jasp.20240045

刘波^{1, 2,},
李敏^{1, 2},
张瑞辰³,
茅晓晨^{1, 2}

1.
西北工业大学动力与能源学院，西安 710072
2.
西北工业大学翼型、叶栅空气动力学国家级重点实验室，西安 710072
3.
中国航空工业集团有限公司成都飞机设计研究所，成都 610091

基金项目: 国家自然科学基金（52106057）；翼型、叶栅空气动力学国家级重点实验室基金（D5150210006，D5050220008）

详细信息

作者简介:
刘波（1960-），男，教授、博士生导师，博士，主要从事叶轮机械气动热力学研究。E-mail：liubo704@nwpu.edu.cn

中图分类号: V231.3
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出版历程
- 收稿日期: 2024-01-20
- 网络出版日期: 2025-06-04

Research on effects of increased tip clearance and rotational speed on unsteady flow behaviors in a counter-rotating axial flow compressor

LIU Bo^{1, 2
,},
LI Min^{1, 2},
ZHANG Ruichen³,
MAO Xiaochen^{1, 2}

1.
School of Power and Energy，Northwestern Polytechnical University，Xi’an 710072，China
2.
The National Key Laboratory of Aerodynamic Design and Research，Northwestern Polytechnical University，Xi’an 710072，China
3.
Chengdu Aircraft Design and Research Institute，Aviation Industry Corporation of China，Limited，Chengdu 610091，China

摘要

摘要:
以两级轴流对转压气机（CRAC）为对象，研究了叶尖间隙（TCS）耦合转速变化引起的流场非定常特性。在数值模拟结果的基础上，采用本征正交分解（POD）方法获取POD模态分布规律，进一步分析了近失速工况下叶尖间隙流场的流动特性。数值和FFT结果表明：随着叶尖间隙的增大，叶尖泄漏流（TLF）增强，叶尖泄漏涡（TLV）破碎加剧，引起的非定常波动范围增大，波动强度减弱；后排转子（R2）叶尖泄漏流波动频率提高；R2叶尖泄漏流溢出通道前缘并与相邻叶片前缘发生干涉是导致其前缘非定常性突增的原因。POD分析验证了上述的结论，并揭示了叶表静压波动区域产生的原因，还发现叶尖间隙增大导致前排转子（R1）的三维流场主导模态结构减小，R1高阶模态结构沿径向向叶根方向迁移。随着转速增大，上游转子对下游转子的干涉也随之增大。
- 对转压气机 /
- 叶尖间隙 /
- 转速 /
- 叶尖泄漏流 /
- 非定常流动 /
- POD方法
Abstract:
A two-stage counter-rotating axial-flow compressor (CRAC) was studied and the unsteady flow characteristics induced by the coupling of blade tip clearance size (TCS) and rotational speed changes were investigated. Based on numerical simulation results, the proper orthogonal decomposition (POD) method was employed to extract the POD modal distribution patterns. Further analysis on the flow characteristics of the blade TCS under near-stall conditions was conducted. Numerical and FFT results showed that as the blade TCS increased, the leakage flow and the fragmentation of blade tip leakage vortex (TLV) intensified, leading to an enlargement of the range of unsteady fluctuations and a reduction in fluctuation intensity. The frequency of blade tip leakage flow (TLF) fluctuations in the rear rotor (R2) increased. The interference between the blade TLF overflowing channel of R2 and the leading edge of adjacent blades was attributed to the sudden increase in unsteadiness at the leading edge. The POD analysis confirmed the above conclusions and revealed the reasons for the static pressure fluctuation region on the blade surface. It was also found that an increase in blade TCS resulted in a decrease in the dominant modal structure of the three-dimensional flow field in the front rotor (R1), and the higher-order modal structure of R1 migrated radially towards the blade root. As the rotational speed increased, the interference between the upstream and downstream rotors also increased.
- counter-rotating axial-flow compressor /
- tip clearance /
- rotational speed /
- tip leakage flow /
- unsteady flow /
- POD method

HTML

图 1 两级对转压气机

Figure 1. Two-stage counter-rotating axial flow compressor

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图 2 网格示意图

Figure 2. Schematic diagram of grids

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图 3 不同叶尖间隙及转速下总性能对比

Figure 3. Overall performance comparison between different TCS and rotational speeds

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图 4 不同叶尖间隙不同转速下99%叶高时均流场熵云图

Figure 4. Time averaged flow field entropy cloud map of 99% blade span at different TCS and rotational speeds

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图 5 不同叶尖间隙不同转速下R1叶尖三维流线图

Figure 5. Distribution of blade tip leakage flow in the R1 at different TCS and rotational speeds

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图 6 不同叶尖间隙不同转速下R2叶尖三维流线图

Figure 6. Distribution of blade tip leakage flow in the R2 at different TCS and rotational speeds

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图 7 不同叶尖间隙不同转速下R1涡系图

Figure 7. Vortex structure of R1 at different TCS and rotational speeds

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图 8 不同叶尖间隙不同转速下R2涡系图

Figure 8. Vortex structure of R2 at different TCS and rotational speeds

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图 9 不同叶尖间隙不同转速下99%叶高处S_u云图

Figure 9. Contours of S_u at 99% blade span at different TCS and rotational speeds

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图 10 不同叶尖间隙不同转速下R1压力面和吸压力面S_u云图

Figure 10. Contours of S_u on PS and SS of R1 at different TCS and rotational speeds

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图 11 不同叶尖间隙不同转速下R2压力面和吸力面S_u云图

Figure 11. Contours of S_u on PS and SS of R2 at different TCS and rotational speeds

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图 12 不同叶尖间隙不同转速下R2吸力面极限流线图

Figure 12. Limit streamline diagram on SS of R2 at different TCS and rotational speeds

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图 13 静压监测点位置图

Figure 13. Diagram of static pressure monitoring locations

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图 14 不同叶尖间隙不同转速下R1叶尖静压监测数据经FFT后频谱

Figure 14. FFT results for monitoring points of R1 located near the blade tip at different TCS and rotational speeds

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图 15 不同叶尖间隙不同转速下R2叶尖静压监测数据经FFT后频谱

Figure 15. FFT results for monitoring points of R2 located near the blade tip at different TCS and rotational speeds

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图 16 不同叶尖间隙不同转速下的模态能量占比

Figure 16. Energy ratio distribution of the modes at different TCS and rotational speeds

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图 17 不同叶尖间隙不同转速下R1通道静压场的前4阶POD模态云图

Figure 17. The first four POD modes contours of R1 static pressure field at different TCS and rotational speeds

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图 18 不同叶尖间隙不同转速下R2通道静压场的前4阶POD模态云图

Figure 18. The first four POD modes contours of R2 static pressure field at different TCS and rotational speeds

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表 1 对转压气机主要设计参数

Table 1. Main design parameters of the CRAC

设计参数数值

R1 R2

转速/（r/min） 8000 −8000

叶片数 19 20

叶尖间隙/mm 0.5 0.5

叶尖速度/（m/s） 167.6 167.6

轮毂比 0.485 0.641

下载: 导出CSV

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