经优化后，透平高压级静叶的总压损失系数减少0.95%；多级压气机整机效率提高2.1%。
After optimization, the total pressure loss of the turbine vane was reduced by 0.95%, and the efficiency of the overall compressor was increased by 2.1%.
较详细地介绍了某多级压气机修改前后，利用叶型受感部测取各级转子出口总压、总温分布的试验方法和结果。
This paper details the experimental methods and results using the airfoil sensors to measure total pressure and total temperature distributions behind the rotors in a multistage axial-flow compressor.
本文采用改进的流线曲率法对跨声速多级轴流压气机非设计点进行了性能模拟。
An improved streamline curvature numerical method is modified and applied to better approximate the flow fields of multi-stage transonic axial compressors.
本文采用改进的流线曲率法+对跨声速多级轴流压气机非设计点进行了性能模拟。
An improved streamline curvature numerical method is modified and applied to better approximate the flow fields of multi-stage transonic axial compressors.
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。
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.
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。
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.
为了比较，在数字机上分别用这两种模型预算了一台多级轴流压气机的失速线。
For comparison the stall lines of a multi-stage axial flow com-pressor have been predicted with these two models respectively.
采用二维（轴对称）数学模型，应用流线曲率法求解多级轴流压气机特性。
The multi-stage axial compressor performance was measured using a streamline curvature method based on two-dimension(axisymmetric) mathematical model.
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。
A stage - by - stage simulation method is introduced for analysis of inlet total pressure distortion effect on the multistage axial flow compressor characteristics.
利用所设计的计算机程序，完成了对多级轴流压气机旋转失速起始边界的理论估算。
The prediction of the rotating stall onset boundary in the multistage axial flow compressors has been accomplished with the computer program designed by the authors.
利用所设计的计算机程序，完成了对多级轴流压气机旋转失速起始边界的理论估算。
The prediction of the rotating stall onset boundary in the multistage axial flow compressors has been accomplished with the computer program designed by the authors.
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