某1.5级压气机设计工况下的激励源分析

Excitation Source Analysis of a 1.5 Stage Compressor Under Design Condition

压气机存在繁多的激励源而无法避开所有的共振点,这就需要详细分析并揭示非定常时空演化规律,为预测并抑制危险共振工况的振动提供依据。本文采用数值方法计算某跨音速轴流压气机设计工况下前1.5级的流场。通过对定常、非定常结果的分析,确定各激励源并总结激励源对叶片非定常气动力的作用规律。研究发现设计工况下首级动叶的非定常力主要来自上游进口导叶和下游静叶的转静干涉效应,其中导叶的影响占主导地位,下游静叶主要影响尾缘部分。压力波动较大的位置与时均静压较大的位置相对应。

There are many excitation sources in compressor, which can not avoid all the resonance points. Therefore, it is necessary to analyze and reveal the unsteady spatio-temporal evolution law in detail, so as to provide a basis for predicting and suppressing the vibration under dangerous resonance conditions. In this paper, a numerical method is used to calculate the flow field of a transonic axial compressor in the first 1.5 stages under the design condition. By analyzing the steady and unsteady results, the excitation sources are determined and the action law of the excitation sources on the unsteady aerodynamic force of the blades is summarized. It is found that the unsteady force of the first-stage rotor blade is mainly caused by the upstream inlet guide blade and the downstream stator blade, in which the influence of the guide blade is dominant, and the downstream stator blade mainly affects the trailing edge. The position with higher static pressure on rotor blade surface also has higher pressure fluctuation.