Therefore, in the research of turbomachinery aeroelastics, it is more and more important to predict blade flutter and to avoid blade flutter.
所以，预报颤振发生几率，避免叶片颤振的研究工作在叶轮机械气动弹性力学学科中占有越来越突出的地位。
The results show that the tip leakage flow vortex has a great effect on the blade aeroelastical stability and large tip leakage vorticity may restrain blade flutter.
计算结果表明，漏流涡对叶片气弹稳定性影响较大，大涡量的漏流涡能抑制叶片颤振发生。
Through the computation and analysis of unsteady aerodynamic forces loading on the cascades and aerodynamic work, the probability of blade flutter is predicted through the energy method.
通过对叶片表面非定常气动力及其所做非定常气动功的计算分析，采用能量法对叶片颤振与否进行预估判断。
An experimental technique and method for flutter research of helicopter blade model are proposed.
提出了直升机模型桨叶颤振试验技术及试验方法。
The numerical flutter analysis system was formed by the three-dimensional numerical simulation of the vibrating cascade flow combined with the structural dynamics analysis of vibrating blade.
将振动叶栅三维流动数值模拟与振动叶片结构动力学分析相结合，建立了叶片颤振数值分析系统。
Some improvements in previous computation models of blade stall flutter in axial-flow compressors have been made on both aerodynamics and structural dynamics so as to make the models more practical.
本文对于现有的叶片失速颤振计算模型进行了一些改进，以期使其更接近于真实物理图画。
The methods of measurment which have been used in experiment is also presented and the stall flutter phenomena of blade are analyzed.
介绍了测试方法，并着重对叶片失速颤振现象进行了分析。
This paper also presents the experimental results of effects of the blade tip clearance and the airfoil shape on the stall flutter boundary.
此外还给出了两种叶尖间隙和两种叶型对失速颤振影响的实验结果。
The eigenvalue method is presented for determining the effects of blade mistuning and blade-disk on cascade flutter boundaries in incompressible flow.
本文用特征值法研完了叶片频率失调及盘片耦合对叶栅颤振边界的影响。
The eigenvalue method is presented for determining the effects of blade mistuning and blade-disk on cascade flutter boundaries in incompressible flow.
本文用特征值法研完了叶片频率失调及盘片耦合对叶栅颤振边界的影响。
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