航空压气机流动稳定性预测研究进展

Research Progress in Prediction of Flow Instability of Aero-Compressor

关键词:  压气机  流动稳定性  压缩性  叶尖间隙  气动掠

Key words:  Compressor  Flow stability  Compressibility  Tip clearance  Aerodynamic sweep

摘要:

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。

Abstract:

In the design phase of aero-compressor，it is urgent and significant to assess its stability margin rapidly and accurately. In this paper，the existing theoretical prediction methods of flow stability of compressors are reviewed，among them the recently developed general theory is systematically introduced. The general theory has been used in various kinds of compressors including subsonic/transonic axial compressor and subsonic centrifugal compressor，which shows that the theory is able to make accurate prediction of the stall inception point. Furthermore，a series of parametric studies with respect to the flow compressibility，tip clearance and blade geometry have been carried out，the results of these studies show that the general theory can capture the effects of these factors on the flow stability qualitatively. However，the accuracy of these parametric studies has not yet been verified by experiments. The corresponding experimental studies need to be conducted in the future. At present，the general theory has only been applied on isolated-rotor or single stage compressor，for multi-stage compressor，it is necessary to further study the calculation of steady flow and eigenvalues of large-scale matrix.