论文部分内容阅读
基于带相位延迟的周期边界条件,建立了某跨声速转子的双通道高效气动阻尼计算模型.数值计算了该转子的气动性能、颤振边界和叶片模态,和实验数据吻合较好.通过传统的多通道能量法以及双通道方法计算了叶片在一弯模态,不同叶片间相位角条件下的气动阻尼,获得了基本一致的计算结果,而双通道方法相比于传统的多通道能量法计算效率提升约7.7倍,内存需求约为后者的0.45倍.不同叶片振幅对气动阻尼结果的影响研究表明,对于较小的叶片振幅,流动非线性对气动阻尼计算结果仍然有显著的影响.不同工况的计算结果表明:叶片间相位角对转子叶片的气动阻尼有显著的影响,对于该转子最小的气动阻尼均在叶片间相位角为-42.4°时得到;同时,在近颤振状态,不同叶片间相位角对应的气动阻尼均小于近设计状态.
Based on the periodic boundary conditions with phase delay, a two-channel high-efficiency aerodynamic damping model of a transonic rotor is established. The aerodynamic performance, flutter boundary and blade mode of the rotor are numerically calculated, which is in good agreement with the experimental data. The multi-channel energy method and the dual-channel method are used to calculate the aerodynamic damping of the blade under the condition of one-turn mode and different interphase angles. The results are basically the same. Compared with the traditional multi-channel energy method The calculation efficiency is about 7.7 times higher than that of the latter, and the memory requirement is about 0.45 times of the latter.The research on the effect of different blade amplitude on the aerodynamic damping results shows that the flow nonlinearity still has a significant effect on the aerodynamic damping calculation for the smaller blade amplitude. The calculation results of different working conditions show that the phase angle between blades has a significant influence on the aerodynamic damping of the rotor blades, and the minimum aerodynamic damping of the rotor is obtained when the interphase angle is -42.4 °. In the meantime, , The aerodynamic damping corresponding to the phase angle between different blades is less than the near design state.