S弯进气道出口旋流对轴流压气机性能的影响

王加乐; 程邦勤; 费晓文; 尉洋; 冯路宁

doi:10.13700/j.bh.1001-5965.2020.0190

S弯进气道出口旋流对轴流压气机性能的影响

doi: 10.13700/j.bh.1001-5965.2020.0190

空军工程大学航空工程学院, 西安 710038

详细信息

通讯作者:
程邦勤. E-mail: 1695438620@qq.com

中图分类号: V231.3
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出版历程
- 收稿日期: 2020-05-15
- 录用日期: 2020-07-10
- 网络出版日期: 2021-07-20

Effects of swirl at outlet of S-shaped inlet on axial flow compressor performance

Aeronautics Engineering College, Air Force Engineering University, Xi'an 710038, China

More Information

Corresponding author: CHENG Bangqin. E-mail: 1695438620@qq.com

摘要

摘要:
为探究S弯进气道出口旋流对轴流压气机性能的影响，优化设计了旋流畸变网以模拟旋流，利用数值模拟的方法探究了单级轴流压气机在S弯进气道出口旋流作用下的气动响应，获得均匀进气条件和旋流进气条件下的压气机特性线和流场分布。结果表明：优化后的旋流畸变网总体旋流角误差降低了。S弯进气道出口旋流对增压能力影响不大，但会导致压气机效率下降，稳定工作范围减小。在100%和80%换算转速，压气机的压比最大降幅分别为0.12%和0.28%，在峰值效率点附近的效率最大降幅为3.2%和14.4%。S弯进气道出口旋流中的反向旋流区增大了转子叶片进气攻角，导致气流叶背分离、叶片通道堵塞，最终导致压气机失稳。
- S弯进气道 /
- 旋流畸变 /
- 压气机 /
- 性能 /
- 稳定性
Abstract:
In order to estimate the effects of swirl at outlet of S-shaped inlet on the performance of axial flow compressor, a swirl distortion network was optimized and designed to simulate the swirl flow field. The aerodynamic response of the single-stage axial flow compressor under the effect of the swirl at the outlet of the S-shaped inlet was investigated by numerical simulation. The characteristic map and flow field distributions of the compressor under the condition of uniform intake and swirling intake were obtained. The results show that the overall swirl angle error of the optimized swirl distortion network is reduced. The swirl flow at the outlet of S-shaped inlet has little influence on the pressurization ability, but it will lead to the decrease of compressor efficiency and decrease of stability. At the corrected speed of 100% and 80%, the maximum reduction of pressure ratio is 0.12% and 0.28% respectively, and the maximum reduction of efficiency near the peak efficiency point is 3.2% and 14.4% respectively. The reverse swirl zone in the swirl at the outlet of the S-shaped inlet increases the inlet attack angle of the rotor blade, resulting in the separation of airflow at the suction side and the blockage of the blade passage, which eventually leads to the instability of the compressor.
- S-shaped inlet /
- swirl distortion /
- compressor /
- performance /
- stability

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图 1 目标旋流场^[16]

Figure 1. Target swirl flow field^[16]

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图 2 旋流网

Figure 2. Swirl network

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图 3 压气机实验系统^[17]

Figure 3. Compressor experiment system ^[17]

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图 4 计算域

Figure 4. Computational domain

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图 5 50%叶高处网格

Figure 5. Mesh at 50% span of compressor

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图 6 不同网格计算的压气机特性对比

Figure 6. Comparison of compressor characteristics calculated by different grids

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图 7 全通道网格

Figure 7. Whole-passage mesh

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图 8 旋流网下游各截面旋流角云图

Figure 8. Swirl angle contour on each section downstream of swirl network

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图 9 压气机进口截面速度矢量场与旋流角云图

Figure 9. Velocity vector field and swirl angle contour of compressor inlet section

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图 10 测环示意图及测环上旋流角分布

Figure 10. Schematic of measuring ring and distribution of swirl angle on measuring ring

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图 11 S弯旋流对压气机性能的影响

Figure 11. Effect of S-shaped swirl on compressor performance

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图 12 S弯进气道各叶高处相对马赫数云图

Figure 12. Relative Mach number contour on each section with S-shaped inlet

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图 13 旋流发展趋势及叶顶区域流线

Figure 13. Development trend of swirl and streamlines of blade tip area

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图 14 失速点5%叶高截面相对马赫数云图

Figure 14. Relative Mach number contour on span 5% near stall point

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表 1 低速轴流压气机几何参数

Table 1. Geometric parameters of low-speed axial flow compressor

参数	转子	静子
叶片数目	45	60
弦长/mm	53.6	40
稠度	1.28	1.27
展弦比	1.87	2.5
叶顶间隙/mm	1.2	1.2

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表 2 低速轴流压气机设计点性能参数

Table 2. Designed point performance parameters of low-speed axial flow compressor

参数	数值
流量/(kg·s^-1)	6.5
转速/(r·min^-1)	3 000
压比	1.025

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表 3 不同网格类型的网格数量

Table 3. Number of grids for different grid types

网格类型	单通道网格数量/10⁴
粗网格	33.9
中网格	60.3
细网格	91.8

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