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。
Numerical simulations were carried out to investigate interaction between a single stage compressor and pylons.
采用数值模拟方法，对单级低速轴流压气机与发动机吊架之间的干涉进行了计算分析。
The result indicates that the method of adding zero-stage compressor discussed in this paper is basically successful.
结果表明，本文采取的加零级方法是成功的。
Adopting the BITZER two stage compressor , the units power is from 5HP -30HP , and can be widely used in quick freezing equipment .
采用比泽尔双级压缩机，功率从5HP -30HP ，广泛应用于速冻设备中。
Last, a 9-stage compressor rotor was taken as an example, the effects of different types of seal on the rotor stability were compared.
最后以一台九级合成气压缩机转子为例，比较不同密封对转子稳定性的影响。
H. E. A. T. intercoolers and aftercoolers are specialized heat exchangers that are used in multi-stage compressor systems to cool the pressurized air or gas.
我们公司生产的中间冷却器&后冷却器均为特制的热交换器，主要应用于多节压缩系统中，冷却增压空气或煤气。
Numerical calculations were performed on a two-stage transonic fan and a five-stage compressor. The two-stage fan flow predictions show a good agreement with experimental data.
对某双级跨音速风扇及五级压气机流场进行了计算，双级风扇各状态的计算结果与实验数据吻合较好。
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。
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。
The present article describes the pilot stand of a full scale ten-stage subsonic axial-flow compressor and presents the test results of the rotating stall and surge obtained therefrom.
本文介绍了一个全尺寸十级亚音速轴流压气机试验台，并给出了该实物压气机旋转失速和喘振的试验结果。
The hub treatment with a circumferential groove was tested on the stator hub and compared with the casing treatment over the rotor tip for a single stage axial flow compressor.
在单级轴流压气机上，用周向槽式处理机匣在静子内径处进行轮毂处理，与转子尖部机匣处理作类比。
Experimental tests have been carried out to investigate the influence of inlet distortion on compressor stability margin in a low speed single stage research compressor.
在低速大尺寸单级压气机实验器上，实验研究了动态进气畸变对压气机稳定边界的影响。
The full-scale three-dimensional flow centrifugal stage test conducted on an axial compressor test rignecessitates a test rig compatibility design.
在轴流压气机试验台上进行全尺寸三元流离心级的试验，需进行适台设计。
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。
Numerical research of the three dimensional viscous flow field in diffuser with small flow rate stage of centrifugal compressor is carried out.
对一离心压缩机小流量级扩压器内部的三维粘性流场进行了数值研究。
A stage by stage mathematical model of the compressor in a turbojet engine is developed based on the control volume theory.
根据控制体理论，建立了涡喷发动机中压气机的逐级数学模型。
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。
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。
The internal flow field of a single-stage axial compressor is analyzed using a fast full 3-D viscous flow calculating method.
采用一种快速求解三维粘性流场的计算方法求解轴流压气机的内部流场及全工况特性。
The accuracy and realability of the numerical software used to simulate the flow field of subsonic compressor is verified by the experiment data of a certain low speed two stage repeated compressor.
采用低速重复级压气机实验数据，验证了本文所采用的数值方法模拟亚声速压气机流场的精度和可靠性。
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NASA37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。
The effect of bleeding on the performance of a two-stage axial-flow compressor was performed with the help of numerical method.
采用数值模拟的方法，研究了引气对某双级轴流压气机气动性能的影响。
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。
A first order lagging equation is used to acount for dynamic effects. This model can simulate the compressor response to inlet temperature transients and find the critical stage.
该模型可以模拟进口温度（或压力）瞬变下压气机的逐级响应，寻找首先失速的关键级。
Experiment results indicate that the mechanical and aerodynamical performances on the new two-stage axial-flow compressor have met the design requirements.
运转试验及性能考核表明，双级轴流压气机实验台在机械性能和气动性能两个方面均达到了预定的设计要求。
After using oil injection instead of water, analysis is also given to the actual situations of after-cooler of charge gas compressor and inter-stage tank.
分析了由注油改为注水后，裂解气压缩机后冷器和段间罐的情况。
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。
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。
The multi-stage axial compressor performance was measured using a streamline curvature method based on two-dimension(axisymmetric) mathematical model.
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 6th stage blade in aero-engine compressor is taken as an example, the temperature effect on the blade vibration frequency blade is investigated.
以某型航空发动机压气机第六级叶片为例，研究了温度对叶片振动频率的影响。
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