Then the deposition characteristic of different particle diameters in the blade cascade of the axial compressor was obtained.
在此基础上，研究了轴流压缩机叶栅内不同直径粒子在叶片压力面和吸力面的沉积规律；
Through spectrum analysis of the unsteady aerodynamic forces and moments of each blade cascade, the unsteady aerodynamic interferences between blades were discussed.
对各列叶栅的非定常气动力和气动力矩进行频谱分析，探讨叶列间的非定常气动干扰。
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。
A diffuser cascade of a centrifugal compressor was chosen to be designed with the proposed approach, with its two operating points specified, and its blade profile to be optimized.
以离心压缩机扩压器叶栅为例，在两个给定设计工况下采用所提出的方法求解其最佳叶片型线。
For the turbine stator cascade, the negative curving of blade can not improve the performance of the cascades as well, the total losses of straight cascade are the lowest.
叶栅中部和端部二次流均增强，总平均的二次流动能增大。对于该叶栅，叶片反弯曲亦不能提高叶栅流场的气动性能，直叶片叶栅总损失最小。
Compared with conventional blade, the passage vortex structure is more stable in cascade with aft-loaded blade which secondary loss is small.
与常规叶片相比，二次流损失较小的后部加载叮型所构成的叶栅内的通道涡在结构上较为稳定。
In this paper unsteady numerical simulation of planar diffuse cascade is performed in the model profiles that choosing from mid-span of the blade in a repeated compressor.
本文选取某重复级压气机平均半径处的型线，进行平面扩压叶栅非定常数值模拟。
It is important to study the mechanism between the cascade blade profile parameters and the thrust reverser effectiveness.
航空发动机叶栅反推器叶型参数与反推效率、流量系数之间的规律对于反推装置的设计具有重要意义。
The cascade aerodynamic performance is obviously improved in the region of middle blade, but the improvement of the cascade aerodynamic performance is not clear near the end wall region.
叶栅气动性能的改善主要在靠近叶展中部区域，而对角区核心区和端部区域的影响并不明显。
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。
Because of relative movement of blade rows, the pressure distributions on the blade and the flow field in the cascade vary periodically.
由于叶排间的相互运动，使叶片表面压力和叶栅通道内的流场呈周期性地变化；
Under high velocity flow conditions, cascade losses are mainly caused by radial drift of the boundary layer along the suction surface and by blade wakes.
在高速流动条件下，叶栅损失主要是吸力面边界层径向串流及其尾迹。
A new model is presented for calculating the end-wall boundary layer and its blade force defect inside the axial compressor cascade, based on theoretical analysis.
通过理论分析提出一种考虑叶片端部间隙影响的叶片力亏损模型，并对三种轴流压气机叶栅的端壁边界层及叶片力亏损进行了数值计算。
Results show that incidence affects evidently not only the pressure profile, but also the flows behavior close to the blade profile, especially in the rear part of the cascade passage.
结果表明：冲角不仅对叶片表面的压力分布，而且对叶片附近的流动状态，特别是在叶栅流道的后半部，有很大的影响。
This blade can be used to produce counter pressure gradient at cascade passage end, reduce secondary flow loss, increase the efficiency of IP casing consequently, and improve the heat rate of units.
本文讨论了透平叶栅中的二次流产生的机理，并深入探讨了一种减少二次流损失的有效方法---叶片斜置和复合斜置技术，分析研究它对叶栅气动性能和级特性的影响。
A new comparative test approach is provided for the thermal fatigue life experiments of turbine blade under thermal shock. The tested blades and reference blades were mounted in a common vane cascade.
针对涡轮叶片的热冲击疲劳寿命实验，提出了一种新的对比实验方案和措施：将实验叶片和参照叶片组合在同一组试验叶栅上，并且在试验过程中定期对调两种叶片的安装位置。
A new comparative test approach is provided for the thermal fatigue life experiments of turbine blade under thermal shock. The tested blades and reference blades were mounted in a common vane cascade.
针对涡轮叶片的热冲击疲劳寿命实验，提出了一种新的对比实验方案和措施：将实验叶片和参照叶片组合在同一组试验叶栅上，并且在试验过程中定期对调两种叶片的安装位置。
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