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1·The information how to improve the stage design of centrifugal compressor stage is put forward.

对离心式压缩机级设计提供了改进信息。

2·A centrifugal compressor stage is designed with 1d method. The 3d flow field of the stage is simulated utilizing CFD software.

用一元的方法对一离心压缩机的级进行了设计，并用CFD软件对设计结果作了三维流场数值模拟。

3·The IGV-impeller gap barely influences the compressor stage performance, but small gap leads to large pressure pulsation inside the flow field.

叶排间距大小对级性能影响几乎可以忽略，但间距减小会造成流场内压力波动增大；

4·This paper presents a numerical study on the performances of a compressor stage under different circumferential positions of the rear blades of tandem stator.

本文采用数值模拟研究串列叶栅后排静叶周向位置对压气机级性能的影响。

5·The analysis shows that differences of mass flow and pressure rise between the two splitter-splitted passages have significant influence on unsteady flow in the compressor stage.

小叶片将大叶片通道分成的两个通道具有不同的流量和负荷，通道之间的负荷分配对于流动的非定常性会产生较大影响；

6·The overall performance for NASA 37 low-aspect ratio compressor stage at 70% design rotating speed was obtained and the internal flow fields at typical operating conditions were emphatically analyzed.

计算得到了NASA 37号低展弦比、跨音速轴流压气机级70％设计转速下的全工况性能曲线，并重点分析了其中一些典型工况下的内部流场。

7·The aircraft engines are the primary source of compressed air in flight. The air is bled from the 7th or 10th stage of the engine High Pressure (HP) compressor.

飞行中，发动机是主要的气源。空气由发动机高压压气机第7级或第10级引出。

8·Structural reliability analysis of an aeroengine 2nd-stage compressor disk is presented.

对某型发动机压气机第2级轮盘进行了结构可靠性分析。

9·Another application of stage-by-stage model is to investigate the post-stall behavior in the compression system which consists of one compressor and one combustion chamber.

逐级模型的另一种用途是用来研究压缩系统的过失速行为，本文研究了由压气机和主燃烧室组成的压缩系统。

10·The stall surging characteristic and its prevention measure are analysed with focus on low-pressure axial fan, high-pressure axial fan and mutiple-stage axial compressor.

针对低、高压轴流送风机及多级轴流压缩机在低流量区域的失速喘振特性及其预防措施进行了分析。