Research on effect of inlet bend on aerodynamic excitation force in centrifugal compressor based on nonlinear harmonic method
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摘要:
基于非线性谐波法研究了进气弯管对离心压气机气动激振力的影响，通过数值模拟分析了弯管诱导的流动畸变与蜗壳几何非均匀性的耦合作用。结果表明，当弯管安装角度与蜗壳0截面一致时，弯管进气显著强化了叶片表面1阶脉动压力（最大压力增幅达77%），但对2阶激振力表现出抑制效应（压力幅值降低27%），且高压力幅值激振区域集中于主叶片及分流叶片前缘叶顶附近。质量流量工况分析显示，小质量流量工况下弯管使1阶脉动压力幅值最高增加78%，而大质量流量工况下跨声速流动导致激振力高压力幅值区向叶片下游移动，且弯管对吸力面叶顶前缘的扰动显著增强（增幅为800%）。机理分析表明，弯管与蜗壳的协同效应通过周向压力畸变和扰动相位干涉影响激振力，而马赫数变化（亚声速/跨声速）决定了扰动传播路径及耦合强度。此外，弯管安装角度对激振力的阶次特性具有显著影响，叶片入口区域对安装角度变化最为敏感，随着流动向下游发展，蜗壳势流效应逐渐削弱了弯管的影响。
Abstract:The impact of inlet bends on the aerodynamic excitation forces in a centrifugal compressor was investigated using the nonlinear harmonic method. Numerical simulations were conducted to analyze the coupling effects between flow distortions induced by the bend and the geometric non-uniformity of the volute. The results showed that when the installation angle of the bend aligned with the 0-section of the volute, the bend inlet significantly amplified the first-order fluctuating pressure on the blade surface (with a maximum increase of 77%) but suppressed the second-order excitation force (amplitude reduction of 27%). High-amplitude excitation regions were concentrated near the leading edge of the main and splitter blades at the tip. Flow condition analysis revealed that under low-flow conditions, the bend increased the first-order fluctuating pressure amplitude by up to 78%, while under high-flow conditions, transonic flow shifted the high-amplitude excitation region toward the downstream part of the blade. Additionally, the bend's disturbance to the suction side near the leading edge of the blade tip was significantly enhanced (an increase of 800%). Mechanism analysis indicated that the synergistic effect of the bend and volute influenced the excitation forces through circumferential pressure distortion and disturbance phase interference, while the Mach number variation (subsonic/transonic) determined the disturbance propagation path and coupling intensity. Furthermore, the installation angle of the bend had a significant impact on the order characteristics of excitation forces. The blade inlet region was most sensitive to changes in the installation angle, and as the flow developed downstream, the potential flow effect of the volute gradually diminished the influence of the bend.
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Key words:
- nonlinear harmonic method /
- centrifugal compressor /
- inlet bend /
- distortion /
- excitation force
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图 3 压气机特性线（直管vs.弯管）
Figure 3. Compressor performance curves（straight pipe vs. bend pipe）
图 4 进气管出口及无叶扩压器入口时均静压分布对比
Figure 4. Comparison of time-averaged static pressure distribution at the intake pipe outlet and vaneless diffuser inlet
图 5 不同时刻进气管出口静压分布
Figure 5. Temporal variation of static pressure distribution at the intake pipe outlet
图 6 叶片监测点静压随时间的变化
Figure 6. Static pressure fluctuations at the blade monitoring points
图 7 叶片监测点脉动压力幅值频谱
Figure 7. Amplitude spectrum of static pressure at the blade monitoring points
图 12 设计工况点脉动压力子午坐标分布
Figure 12. Harmonic pressure distribution along meridional coordinate at design point
图 13 小流量工况脉动压力子午坐标分布
Figure 13. Harmonic pressure distribution along meridional coordinate at low flow regime
图 14 大流量工况脉动压力子午坐标分布
Figure 14. Harmonic pressure distribution along meridional coordinate at high flow regime
图 15 95%B2B截面马赫数云图及主叶片压力面1阶脉动压力分布
Figure 15. Mach number contours at 95% B2B span with 1st harmonic pressure distribution on pressure side of the main blade
图 16 95%B2B截面马赫数云图及主叶片吸力面1阶脉动压力分布
Figure 16. Mach number contours at 95% B2B span with 1st harmonic pressure distribution on suction side of the main blade
图 17 弯管安装角vs.前4阶脉动压力最大值
Figure 17. Installation angle of bent pipe vs. maximum values of the first four harmonic pressures
图 18 弯管安装角vs.主叶片监测点前4阶脉动压力
Figure 18. Installation angle of bent pipe vs. the first four harmonic pressures at the monitoring points of the main blade
表 1 不同阶次谐波计算值与实测值对比
Table 1. Harmonic independence verification
谐波阶次 压比 压比偏差% 效率% 效率偏差% 内存/MB 实测 2.755 79.52 2 2.801 1.67 80.29 0.97 3716 3 2.797 1.52 80.1 0.73 4789 4 2.794 1.42 79.97 0.57 5861 5 2.794 1.42 79.93 0.52 6934 6 2.794 1.42 79.92 0.50 8006 
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