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在航空压气机设计阶段,对其稳定裕度进行快速、准确评估,防患于未然,具有迫切需求和重要意义。首先评述了现有的压气机流动稳定性理论预测方法,并重点就近期发展起来的叶轮机流动稳定性通用理论做了系统的介绍。随后,汇总了叶轮机流动稳定性通用理论在亚声速、跨声速轴流压气机以及亚声速离心压气机等不同机型上的应用,从现有算例来看,该理论有能力对不同类型的压气机失速起始点做出准确的预测。进一步,综述了基于叶轮机流动稳定性通用理论所开展的针对压缩性、叶尖间隙以及三维叶片造型等因素的参数化研究工作。研究结果表明,该理论在定性层面上能够捕捉到这些因素的影响,然而,这些预测结果定量上尚未得到实验的验证,需要进一步开展相应的实验研究。目前,叶轮机流动稳定性通用理论只在单级或单转子压气机上得到应用,对于多级压气机,还需要在定常流场的计算方法、大规模矩阵特征值求解等方面开展更加深入的研究。
In the stage of aviation compressor design, it is urgently required and of great significance to carry out a quick and accurate assessment of its stability margins. Firstly, the existing theory of predicting the flow stability of the compressor is reviewed, and a general introduction to the recent general theory of the flow stability of the turbine is given. Subsequently, the application of the general theory of flow stability of turbomachine on different models of subsonic, transonic axial compressors and subsonic centrifugal compressors is summarized. From the existing examples, this theory has the ability to analyze different types Of the compressor stall starting point to make accurate predictions. Furthermore, the parametric research on compressibility, tip clearance and three-dimensional blade modeling based on the general theory of flow stability of impeller is reviewed. The results show that the theory can capture the influence of these factors qualitatively. However, these predictions have not yet been verified by experiments and need to be further studied. At present, the general theory of turbomachine flow stability is only applied to single-stage or single-rotor compressors. For multi-stage compressors, further research is needed on the calculation methods of steady flow field and the solution of large-scale matrix eigenvalues .