the characteristics of static pressure changing at stage exits of a multi-stage axial flow compressor relative to the design points at several typical operating modes are investigated.
对多级轴流式压气机在几个典型工况下各级静压相对于设计点静压的变化特性进行了研究。
based on the harika arithmetic used to caculate muti-stage axial compressor performance, a method to predict the rotating stall stage in multi-stage axial flow compressor is developed.
a stage - by - stage simulation method is introduced for analysis of inlet total pressure distortion effect on the multistage axial flow compressor characteristics.
介绍了1种分析进口总压畸变对多级轴流压气机特性影响的逐级模拟方法。
finally, the total loss distribution along the blade span of the axial flow compressor is estimated according to an improved end wall loss model and a shock loss model.
再应用改进了的端壁损失和激波损失模型,最终算出轴流压气机设计点损失沿叶高的分布规律。
firstly, the stalling pressure rise capability of axial flow compressor stages is predicted, and the stage in which stall occurs first could be located theoretically and be verified experimentally.
首先,预测多级轴流压气机各级的级极限负荷,依此确定旋转失速发生时率先失速的级并得到实验证实;
a new three-dimensional aerodynamic stability model for an axial flow compressor to study the effects of radial disturbance on the rotating stall is presented.
给出了考虑压气机径向扰动对失速影响的轴流压气机三维气动稳定性模型。
in this paper, virtual prototype technology of turbo-machinery, multistage axial flow compressor numerical simulation, and integrated design of turbo-machinery and engine have been introduced.
介绍了叶轮机虚拟样机技术、多级轴流压气机数值仿真和叶轮机与发动机一体化设计。
this article investigates the nonlinear dynamic characteristics and stability of an axial flow compressor with tip clearance and ball bearings.