支板尾流引起轴流压气机叶片失效的数值分析  

Numerical analysis on blade failure induced by strut wake in axial compressor

作　　者：罗楚威 陈江[1] 徐宁 王琦 LUO Chuwei;CHEN Jiang;XU Ning;WANG Qi(School of Energy and Power Engineering,Beihang University,Beijing 100191,China;The 703 Research Institute,China State Shipbuilding Corporation Limited,Harbin 150078,China)

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100191 [2]中国船舶集团有限公司第七〇三研究所,哈尔滨150078

出　　处：《航空动力学报》2022年第11期2617-2626,共10页Journal of Aerospace Power

基　　金：国家科技重大专项(J2019-Ⅱ-0005-0025)。

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。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 fluidstructure coupling methods were used to analyze the effects of strut on unsteady flow in 1.5 stages highpressure 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.

关 键 词：支板 非定常 轴流压气机 强迫响应 流固耦合 频谱 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]