Numerical analysis on blade failure induced by strut wake in axial compressor
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摘要:
为探究某燃气轮机压气机过渡段支板后方导叶发生疲劳失效的原因，以带支板过渡段及高压压气机前1.5级为研究对象，利用非定常数值模拟及单向流固耦合方法，分析支板对压气机非定常流场的影响及导叶的强迫响应特征，并通过疲劳强度实验对分析结果进行了校核。结果表明：支板的存在使压气机设计点等熵效率下降3.6个百分点；支板尾缘交替脱落的涡使导叶进口攻角偏离设计值，造成气动性能下降，叶表压力脉动大幅增加；随着导叶与支板周向距离增大，支板对导叶的影响先增大后迅速减小；支板脱落涡引起的扰动频率比较分散，其低频分量引起的低阶共振是造成导叶疲劳失效的根本原因，其振动应力可达400 MPa；数值计算与实验结果吻合，证明了计算的可靠性。
Abstract:To explore the reasons for fatigue failure of inlet guide vane (IGV) downstream the strut in the transition section of a gas turbine compressor, unsteady numerical simulation and one-way fluid-structure coupling methods were used to analyze the effects of strut on unsteady flow in 1.5 stages high-pressure compressor and forced response characteristics of the IGV. Furthermore, the analysis results were checked by fatigue strength experiments. The results showed that the isentropic efficiency in the design point of compressor was reduced by 3.6 percent points compared with the model without strut. Vortex shedding alternately at the trailing edge of the strut caused the inlet attack angle of the IGV to deviate from the design value, resulting in a decrease in aerodynamic performance and a significant increase in the unsteady pressure pulsation on the IGV surface. With the increase of circumferential distance between IGV and strut, the influence of strut on IGV first increased and then decreased rapidly. The perturbation frequency resulted from the shedding vortex was relatively disperse, and the low-order resonance of IGV induced by the low frequency component was the fundamental reason of the fatigue failure of IGV; the maximum vibration stress can reach 400 MPa. The numerical simulation results were consistent with the experiment, proving the reliability of the simulation.
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Key words:
- strut /
- unsteady /
- axial compressor /
- forced response /
- fluid-structure coupling /
- spectrum
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图 8 不同时刻S0进口气流攻角展向分布
Figure 8. Distribution of attack angle along vane height in the S0 inlet at different moments
图 9 5%叶高S0进口气流攻角随时间变化
Figure 9. Time-varying curve of attack angle in the S0 inlet at 5% span
图 10 5%叶高S0表面静压脉动方均根轴向分布
Figure 10. Axial distribution of RMS of static pressure pulsation in S0 surface at 5% span
图 13 瞬态响应监测点应力收敛曲线
Figure 13. Stress convergence curve of transient response monitoring points
表 1 模态分析结果
Table 1. Results of mode analysis
阶次 固有频率/Hz 振型 1 554.0 一弯 2 1622.0 一扭 3 2581.7 二弯 4 3608.2 5 5920.0 6 6237.9 7 7571.5 8 8281.4 9 10684.0 10 11548.0 
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表 2 压气机进口参数
Table 2. Compressor inlet parameters
归一化叶高/% 总压/kPa 总温/K 10 531.65 454.575 30 551.65 446.150 50 556.75 446.775 70 560.00 451.675 90 559.05 458.500
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表 3 疲劳强度实验结果
Table 3. Results of fatigue strength test
叶片序号 频率/Hz 应力/MPa 寿命/106 实验时间/h 1 511.3 350 4.69 2.5 2 494.3 300 9.57 5.4 3 512.4 250 14.00 7.6
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