A Study on the Relation between Stall Flutter and Rotating Stall

失速颤振与旋转失速关系的研究

• 批准号: 05650178
• 负责人: TAKATA Hiroyuki
• 金额: $ 1.41万
• 依托单位: Tokai University
• 依托单位国家: 日本
• 项目类别: Grant-in-Aid for General Scientific Research (C)
• 财政年份: 1993
• 资助国家: 日本
• 起止时间: 1993 至 1994
• 项目状态: 已结题
• 来源: https://kaken.nii.ac.jp/en/grant/KAKENHI-PROJECT-05650178/
• 关键词: Stall flutter; Rotating Stall; Cascade of Blades; Unsteady Flow; Axial compressor; 非定常内部流

The aim of this study is to understand the relation between the stall flutter and the rotating stall by means of numerical simulations.In the first year of the study, the numerical method for the analysis of rotating stall in rigid cascades was extended so that it can treat the cases where the cascade blades oscillate with small amplitudes. A typical cascade of NACA-65CA (30) 10 compressor blades was selected as a calculation objective, and its unsteady aerodynamic characteristics were analyzed when each blade was oscillating rotationally around the center of each camber line with various oscillation parameters. Rotating stall occurred in these cascades as well if the inlet flow angle was large, and further, when the phase velocity of blade oscillation coincided with the propagation velocity of the rotating stall, the both phenomena synchronized and the blade oscillation was excited strongly, i.e., the stall flutter occurred.In the second year, a series of numerical simulation was carried out for the same cascade with increasing the inlet flow angle step by step around the stalling inlet flow angle, in order to see the relation between the occurrence of stall flutter and the appearance of rotating stall. When the inlet flow angle is comparatively low, neither the stall flutter nor the rotating stall occurred. When the inlet flow angle was increased slightly, it became possible for the rotating stall to appear depending on oscillation conditions of the blades. In this situation, although the synchronization of the both phenomena as mentioned before was not seen, the excitation of the blade oscillation by a "broader sense of stall flutter" became possible. When the inlet flow angle was increased further beyond, it was found the situation was continued to that described in the first years' result.

本研究的目的是通过数值模拟来了解失速颤振和旋转失速之间的关系，在研究的第一年，对刚性叶栅旋转失速分析的数值方法进行了扩展，使其能够处理叶栅叶片以小振幅振荡的情况。以NACA-65 CA（30）10型压气机叶片为算例，分析了叶片在不同振荡参数下绕中弧线中心旋转振荡时的非定常气动特性。如果入口气流角较大，这些叶栅也会发生旋转失速，并且当叶片振荡的相速度与旋转失速的传播速度重合时，两者同步，强烈激发叶片振荡，即，第二年对同一叶栅在失速进口角附近逐步增大进口角进行了一系列的数值模拟，以了解失速颤振的发生与旋转失速的出现之间的关系。当来流角较小时，既不会发生失速颤振，也不会发生旋转失速。当入口气流角稍微增加时，根据叶片的振荡条件，可能会出现旋转失速。在这种情况下，虽然没有看到前面提到的两种现象的同步，但通过“更广泛意义上的失速颤振”激发叶片振荡成为可能。当进口气流角进一步增加时，发现情况继续到第一年的结果中所描述的情况。