跨声速压气机转子三维流动损失源量化评估方法

伊卫林; 李翔

doi:10.13224/j.cnki.jasp.20250189

跨声速压气机转子三维流动损失源量化评估方法

doi: 10.13224/j.cnki.jasp.20250189

伊卫林,
李翔

北京理工大学机械与车辆学院，北京 100081

基金项目: 国家自然科学基金面上项目（52176035）

详细信息

作者简介:
伊卫林（1978-），男，副教授，博士，主要从事航发/燃机气动热力学。E-mail：yiweilin@bit.edu.cn

中图分类号: V231.3
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出版历程
- 收稿日期: 2025-02-20
- 网络出版日期: 2025-11-27

Quantitative evaluation method of three-dimensional flow loss sources in transonic compressor rotor

YI Weilin,
LI Xiang

School of Mechanical and Engineering，Beijing Institute of Technology，Beijing 100081，China

摘要

摘要:
跨声速压气机内流动呈现强三维性，其损失来源多且复杂。分解损失成因并量化评估其致损程度具有重要意义。基于跨声速压气机三维流场分析明确了流动高损失的主要来源，发展了以涡识别方法为主、基于流动特征参数的高损失区域划分方法，进一步利用熵产率积分实现了损失量化评估。以NASA Stage 35为对象的分析结果表明：叶表边界层损失、端壁边界层损失、叶尖泄漏损失和尾迹损失是跨声速压气机转子流动损失的主要来源。近失速工况和峰值效率工况相比，叶表边界层损失、尾迹损失占比有所减小，叶尖泄漏损失和端壁损失占比显著增加，分别达到了21%和20%。转子进口叶尖相对马赫数接近1.5所产生的激波本身并未造成明显的损失，但激波与边界层相互作用所引发的额外流动损失需重点关注。
- 跨声速压气机 /
- 涡识别方法 /
- 熵产率 /
- 损失量化 /
- 流场分析
Abstract:
The flow within a transonic compressor exhibits strong three-dimensional characteristics, with diverse and complex sources of loss. Decomposing these losses and quantitatively evaluating their contributions is of great significance. Based on analysis of transonic compressor three-dimensional flow field, the main sources of high losses in transonic compressors were identified. A loss-separation method was developed by combining vortex-identification techniques with flow-feature parameters to partition the high-loss regions. Furthermore, entropy production rate integration was employed to achieve quantitative loss evaluation. Analysis of the NASA Stage 35 compressor indicated that blade boundary layer loss, endwall loss, tip leakage vortex loss, and wake loss were major sources of flow losses in the transonic compressor rotor. Compared with the peak-efficiency condition, the proportions of boundary layer loss and wake loss decreased under near-stall conditions, while the contributions of tip leakage vortex loss and endwall loss increased significantly, reaching 21% and 20%, respectively. Although the shock wave caused by a relative tip Mach number close to 1.5 at the rotor inlet did not result in significant loss by itself, the additional flow loss caused by the interaction between the shock wave and the boundary layer required special attention.
- transonic compressor /
- vortex recognition method /
- entropy production rate /
- loss quantification /
- flow field analysis

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图 1 NASA Stage 35级几何

Figure 1. Geometry of NASA Stage 35

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图 2 不同数量网格下Stage 35计算性能对比

Figure 2. Performance comparison of Stage 35 with different grid numbers

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图 3 不同网格数量下PE、NS工况级出口参数对比

Figure 3. Comparison of the stage exit parameters at PE&NS condition with different grid numbers

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图 4 湍流模型对预测Stage 35性能的影响

Figure 4. Effect of turbulence model on predicting Stage 35 performance

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图 5 湍流模型对预测PE和NS工况级出口参数的影响

Figure 5. Effect of turbulence model on predicting the parameters at the stage exit under the PE&NS condition

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图 6 熵产率分布云图

Figure 6. Distributions of entropy production rate

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图 7 PE和NS工况下转子出口截面相对马赫数云图

Figure 7. Relative Mach number at rotor exit under the PE&NS condition

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图 8 PE和NS工况下叶尖及角区三维流线、轮毂及吸力面流线、马赫数（Ma=1.3）等值面

Figure 8. Three-dimensional streamlines at tip and hub-corner section, streamlines on the hub and suction surface, and iso-surface of Mach number （Ma=1.3） under the PE&NS condition

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图 9 熵产率、湍流涡耗散率和归一化螺旋度云图

Figure 9. Entropy production rate，turbulence eddy dissipation and normalized helicity contours

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图 10 叶表边界层损失域

Figure 10. Blade boundary layer area

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图 11 马赫数、静压和密度云图

Figure 11. Mach number, static pressure and density contours

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图 12 ε方法识别的激波结构

Figure 12. Shock waves identified by the ε method

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图 13 $ \theta $方法识别的激波结构

Figure 13. Shock waves identified by the $ \theta $ method

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图 14 采用H_n绝对值着色的Q准则等值面

Figure 14. Iso-surfaces of positive Q-criterion coloured by the absolute value of H_n

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图 15 附面层分离损失域

Figure 15. Boundary layer separation area

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图 16 叶尖泄漏损失域

Figure 16. Leakage vortex area

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图 17 端壁损失域

Figure 17. Endwall area

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图 18 尾迹损失域

Figure 18. Wake area

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图 19 不同类型损失区域划分

Figure 19. Different types of loss areas

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图 20 不同类型损失分解

Figure 20. Breakdown of different types of loss

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表 1 NASA Stage 35级设计参数

Table 1. Design parameters of NASA Stage 35

设计参数	数值
质量流量/（kg/s）	20.188
总压比	1.82
设计转速/（r/min）	17188.7
流量系数	0.451
负荷系数	0.262
叶片数	36/46
转子叶尖马赫数	1.49
转子叶顶间隙/mm	0.408

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表 2 轮缘与轮毂的端壁损失变化

Table 2. Tip and hub endwall loss

工况	轮缘端壁损失/ （W/K）	轮毂端壁损失/ （W/K）
PE	9.35764	11.5101
NS	17.1671	12.8133

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