轴流压气机叶片与机匣处理一体化优化设计

范忠岗; 巴顿; 邱佳慧; 杨晨; 杜娟

doi:10.13224/j.cnki.jasp.20220069

轴流压气机叶片与机匣处理一体化优化设计

doi: 10.13224/j.cnki.jasp.20220069

范忠岗^{1, 2, 3, 4,},
巴顿^{1, 2, 3, 4},
邱佳慧^{1, 2, 3, 4},
杨晨^{1, 2, 3},
杜娟^{1, 2, 3, 4,*, ,}

1.
中国科学院工程热物理研究所先进燃气轮机实验室，北京 100190
2.
中国科学院先进能源动力重点实验室，北京 100190
3.
中国科学院轻型动力创新研究院，北京 100190
4.
中国科学院大学航空宇航学院，北京 100049

基金项目: 国家自然科学基金（51922098）；国家重大科技专项（2017-Ⅱ-0004-0017，J2019-Ⅱ-0020-0041）

详细信息

作者简介:
范忠岗（1998-），男，博士生，主要从事压气机流动稳定性研究

通讯作者:
杜娟（1983-），女，研究员，博士，主要从事压气机内部流动失稳机理、稳定性调控策略及实验测量方面研究。E-mail：dujuan@iet.cn

中图分类号: V231.3
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- 被引次数: 0
出版历程
- 收稿日期: 2022-02-14
- 网络出版日期: 2024-03-04

Integrated design optimization of blade and casing treatment in axial compressor

FAN Zhonggang^{1, 2, 3, 4
,},
BA Dun^{1, 2, 3, 4},
QIU Jiahui^{1, 2, 3, 4},
YANG Chen^{1, 2, 3},
DU Juan^{1, 2, 3, 4,*
, ,}

1.
Advanced Gas Turbine Laboratory，Institute of Engineering Thermophysics，Chinese Academy of Sciences，Beijing 100190，China
2.
Key Laboratory of Advanced Energy and Power，Chinese Academy of Sciences，Beijing 100190，China
3.
Innovation Academy for Light-duty Gas Turbine，Chinese Academy of Sciences，Beijing 100190，China
4.
School of Aeronautics and Astronautics，University of Chinese Academy of Sciences，Beijing 100049，China

摘要

摘要:
针对一台低速轴流压气机搭建了叶片与机匣处理一体化优化设计平台，基于自由变形技术关联设计参数与工程参数，实现多目标优化。综合考虑效率和裕度指标，在峰值效率不降的情况下获得了7.21%的裕度拓宽量。针对最优方案，分析了叶顶堵塞及损失分布，探讨了叶片与机匣处理一体化优化设计的扩稳机理。研究发现：叶片弯掠和机匣处理组合作用下，最大堵塞位置由24.7%叶顶轴向弦长后移至33.6%叶顶轴向弦长，最大损失位置由21.4%叶顶轴向弦长后移至30.6%叶顶轴向弦长，叶顶泄漏涡的抑制和低能堵塞区的消除是一体化优化设计扩稳的主要原因。
- 轴流压气机 /
- 自由变形技术 /
- 一体化优化设计 /
- 裕度拓宽 /
- 堵塞 /
- 熵产率
Abstract:
An integrated optimization design platform of blade and casing treatments in a low-speed axial compressor was constructed. A practical partitioning approach for free-form deformation (FFD) parameterization combined with engineering parameters was applied to achieve multi-objective optimization. Taking both efficiency and stall margin into consideration, the optimal design improved the stall margin by 7.21% with negligible peak efficiency variation. After analysis and calculation of blockage and loss distribution, the influence mechanism on stall margin and efficiency was further studied. Results showed that with the combined effected of deformed blade and casing treatment, the location of peak blockage moved downstream from 24.7% rotor tip chord to 33.6% rotor tip chord, and the location of peak efficiency moved downstream from 21.4% rotor tip chord to 30.6% rotor tip chord. The main reason for stall margin improvement was attributable to the suppression of tip leakage and the elimination of low energy blockage flow at tip region.
- axial compressor /
- free-form deformation /
- integrated optimization design /
- stall margin improvement /
- blockage /
- entropy generation rate

HTML

图 1 网格无惯性验证

Figure 1. Grid-dependency test

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图 2 计算域及边界条件

Figure 2. Computational domain and boundary conditions

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图 3 数值和实验气动性能对比

Figure 3. Comparison of numerical and experimental aerodynamic performance

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图 4 FFD控制体

Figure 4. FFD control volume

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图 5 优化流程示意图

Figure 5. Optimization process diagram

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图 6 优化数据库

Figure 6. Optimization database

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图 7 最优设计

Figure 7. Optimal design

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图 8 优化前后叶片形状对比

Figure 8. Comparison of blade shape before and after optimization

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图 9 优化前后进口攻角对比

Figure 9. Comparison of inlet incidence before and after optimization

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图 10 Pareto图

Figure 10. Pareto diagram

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图 11 回归分析与相关性分析

Figure 11. Regression analysis and correlation analysis

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图 12 优化前后压气机特性线对比

Figure 12. Comparison of compressor performance before and after optimization

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图 13 优化前后轴向速度对比

Figure 13. Comparison of axial velocity before and after optimization

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图 14 不同工况下堵塞因子轴向分布对比

Figure 14. Axial distribution comparison of blockage factor at different conditions

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图 15 优化前后堵塞因子轴向分布对比

Figure 15. Axial distribution comparison of blockage factor before and after optimization

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图 16 优化前后叶顶涡量分布对比

Figure 16. Comparison of vorticity magnitude before and after optimization

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图 17 优化前后叶顶载荷对比

Figure 17. Comparison of rotor tip blade loading before and after optimization

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图 18 优化前后损失轴向分布对比

Figure 18. Axial distribution comparison of loss before and after optimization

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图 19 优化前后压气机特性线对比

Figure 19. Comparison of compressor performance before and after optimization

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表 1 压气机单转子设计参数

Table 1. Design parameters of the compressor single rotor

参数	数值
设计转速/（r/min）	2400
设计流量/（kg/s）	2.9
马赫数	0.19
转子数	60
叶顶弦长/mm	36.3
叶顶间隙/mm	0.8
叶顶轴向弦长/mm	22.8
轮毂比	0.75

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表 2 设计参数的变化范围

Table 2. Range of design parameters

设计变量		控制点	范围
叶片控制体	叶片前缘弯（LE bend）	P_ijk （i=0～2; j=0; k=2）	（−0.1～0.25）C_ax
	叶片尾缘弯（TE bend）	P_ijk （i=0～2; j=2; k=2）	（−0.1～0.25）C_ax
	叶片前缘掠（LE sweep）	P_ijk （i=0～2; j=0; k=2）	（−0.1～0.25）C_ax
	叶片尾缘掠（TE sweep）	P_ijk （i=0～2; j=2; k=2）	（−0.1～0.25）C_ax
	叶片旋转（Rotation）	P_ijk （i=0～2; j=0～2; k=2; 除i=j=1）	−10°～10°
轴向缝控制体	轴向缝弯（Slot bend）	P_ijk （i =0～2; j=0～2; k=2）	（−0.15～0.15）C_ax
	轴向缝掠（Slot sweep）	P_ijk （i =0～2; j=0～2; k=2）	（−0.15～0.15）C_ax
	轴向缝扭（Slot twist）	P_ijk （i=0～2; j=1,2; k=0～2; 除i=j=1）	−60°～60°
	轴向缝高（Slot height）	P_ijk （i=0～2; j=0～2; k=2）	（−0.05～0.2）C_ax
周向槽	周向槽缩放（Groove scale）		（0.044～0.178）C_ax

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