Influence of circumferential position of intake struts on rotor blade excitation and vibration
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摘要:
为探究进气支板与下游叶片相对周向位置对压气机动叶所受激励和振动的影响规律和机理，模拟了一个带进气支板的重型燃气轮机压气机前1.5级。通过对动叶片的流场和振动的分析发现：进气支板周向位置对总压比和总温比影响很小，但会明显改变动叶受到的激励和振动水平。当进气支板尾迹与导叶尾迹重合时，两种尾迹叠加加强，导致动叶的激励和振动整体增强。支板位置会明显改变支板尾迹和下游静叶势流对动叶的叠加影响，这对弦长中部非定常载荷和整体振动的影响较明显，对前尾缘附近影响很小。研究结果为支板的安装提供了参考和指导。
Abstract:In order to investigate the influence law and mechanism of the relative circumferential position of the intake struts and downstream blades on the excitation and vibration of the rotor blade, the first 1.5 stage of a heavy-duty gas turbine compressor with intake struts was numerically simulated. Through analysis of the flow field and vibration of the rotor blade, it was found that the circumferential position of the intake struts had little effect on the total pressure ratio and total temperature ratio, but it could obviously change the excitation and vibration level of the rotor blade. When intake strut wakes and guide vane wakes coincided, the two wakes were superimposed and strengthened, resulting in the overall enhancement of excitation and vibration on the rotor blade. The circumferential position of struts obviously changed the combined effect of strut wake and downstream static blade potential flow on rotor blades, which had obvious influence on the unsteady load and global vibration in the middle chord length, but had little influence on the unsteady load near the leading edge and trailing edge. The research results can provide a reference and guidance for the installation of struts.
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Key words:
- intake struts /
- excitation /
- vibration /
- rotor-stator interaction /
- compressor
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图 2 支板与IGV的相对位置（灰线表示同一周向位置）
Figure 2. Circumferential relative position of struts and IGVs （gray lines indicate the same circumferential position）
图 10 通过频域结果重构的叶尖位移瞬态响应（垂直于弦长方向）
Figure 10. Blade tip transient response reconstructed from frequency domain results （perpendicular to chord）
图 11 展向50%处的静熵（白线为激波）
Figure 11. Static entropy at 50% blade span （white line is shock wave）
图 12 IGV/R1交界面展向50%处总压时均值
Figure 12. Time-averaged total pressure at 50% blade span at IGV/R1 interface
图 13 R1动叶表面EO54静压幅值（白线为激波）
Figure 13. EO54 amplitude of static pressure on the surface of R1 rotor blade （white line is shock wave）
图 14 R1动叶展向50%处静压EO54分量
Figure 14. EO54 component of static pressure at 50% blade span of R1 rotor blade
图 17 R1动叶表面EO45静压幅值分布（白线为激波）
Figure 17. EO45 amplitude of static pressure on the surface of R1 rotor blade （white line is shock wave）
图 18 R1/S1交界面展向50%处静压时均值
Figure 18. Time-averaged static pressure at 50% blade span at R1/S1 interface
图 19 R1动叶展向50%处静压EO45分量
Figure 19. EO45 component of static pressure at 50% blade span of R1 rotor blade
表 1 R1动叶受力的主要频率与叶片数关系
Table 1. Relationship between main frequencies of R1 rotor blade force and number of blades
频率/Hz 激励阶次EO 频率倍数 Strut IGV S1 1350 9 1 2700 18 2 4050 27 3 6750 45 5 1 8100 54 6 1 
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表 2 R1轴向力主要频率分量
Table 2. Main frequency component of R1 axial force
频率/Hz 轴向力/N 轴向力
相对差值/%C# M# 1350 3.77 3.77 0.11 2700 2.81 2.81 −0.20 4050 2.55 2.43 −4.77 6750 2.79 1.13 −59.55 8100 3.40 2.36 −30.64
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表 3 R1动叶最大振幅
Table 3. Maximum amplitude of R1 rotor blade
频率/Hz 振幅/μm 相对差值/% C# M# 1350 3.02 3.10 2.65 2700 0.98 1.03 5.10 4050 0.78 0.80 2.56 6750 5.63 4.20 −25.40 8100 0.63 0.52 −17.46
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表 4 IGV/R1交界面处总压EO54分量
Table 4. EO54 component of total pressure at IGV/R1 interface
尾迹来源 总压谐波
分量/Pa总压幅值/
Pa相位角/
（°）进气支板+
进口导叶（C#）1079.9+566.88i 1219.6 27.70 进气支板+
进口导叶（M#）660.32+335.82i 740.81 26.96 单独进口导叶 865.93+447.35i 974.66 27.32 单独进气支板（C#） 213.95+119.53i 245.08 29.19 单独进气支板（M#） −205.60−111.54i 233.91 −151.52
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