介绍了某型离心压气机叶轮与五种径向扩压器匹配的试验研究。
This paper introduces an experimental study of a centrifugal compressor matching with five different types of radial diffusers.
压气机叶轮作为离心压气机的核心零件，是一类典型的复杂曲面零件。
Compressor impeller is a type of representative parts with sculptured surface, which is the most important part in the centrifugal compressor.
本文给出了一种以微型计算机为工具绘制离心压气机叶轮图形的方法。
This paper gives a method for drawing centrifugal compressor impeller by use of microcomputer.
用三维激光多普勒测速系统测量研究了一个离心压气机转子近端壁区三维紊流流场。
Three-dimensional turbulent flow of the endwall region inside a centrifugal compressor impeller was studied using a Laser Doppler Velocimetry.
本文介绍了GZ680增压器的离心压气机与轴流透平的气动热力学设计思想及特点。
The thermoaerodynamic design philosophy and features of the centrifugal compressor and the axial turbine of the turbocharger GZ680 are discussed.
采用离心压气机计算机辅助集成设计系统，设计了两个不同子午形面和叶片角的离心压气机叶轮。
Two centrifugal compressor impellers with different meridional shape and blade Angle were designed using computer-aided integrated design systems.
因此，有必要开展离心压气机叶轮五轴高精度数控加工技术的研究，以期进一步提高压气机的性能。
Therefore, in order to improve the performance of compressor, it is necessary to accomplish the high accuracy five-axis nc machining of centrifugal compressor impeller.
分析了离心压气机叶轮的几何结构特点、加工工艺，并在此基础上规划了叶轮的粗、精加工刀具轨迹。
Based on the geometry characteristic and processing technique of centrifugal compressor impeller, the tool path of rough and finish machining are scheduled.
通过对离心压气机与轮盘空腔耦合流场的计算分析，得到了轮盘空腔流动的基本流场结构和动力特性。
The basic flow field structure and aerodynamic features of the impeller backside cavity are presented for the coupled computations of a centrifugal compressor and its impeller backside cavity.
所建立的叶轮几何参数优化选择方法，可用于车用涡轮增压器离心压气机的几何参数优化和性能预测。
The method of impeller parameters optimization design can be used in the selection of geometric parameters and the performance prediction of vehicle turbochargers.
本文采用一多功能流体动力学计算软件，详细计算分析了NASA低速离心压气机叶轮内部的三维速度场。
Based on a multifunctional CFD software, the three-dimensional velocity field within the impeller of NASA low-speed centrifugal compressor is computed in detail in this paper.
结果表明，弯管畸变对离心压气机性能的恶化程度与弯管所在位置有关，距离叶轮进口较远的弯管影响较大。
The results show different performance deterioration between different bent pipes, the larger distance between bent pipe outlet and impeller inlet creates more decrease.
涡轮增压器离心压气机是一种高速旋转的机械，在运行过程中经常遭遇叶片损坏的事故，而叶片损坏原因各异。
Turbocharger compressor is a kind of rotary machine with high speed, leaf destruction accident which have different reasons is very common when it is running.
此外，通过试验证明：在离心压气机上采用双列叶栅扩压器，可以改善压气机性能，扩大压气机的稳定工作范围。
Furthermore, experiments show that the adoption of double-row cascade diffusers in centrifugal compressors will improve its performance and widen its stable operating range.
采用所研制软件，对两个离心压气机工作轮进行优化设计，优化工作轮达到在压比近似不变的前提下效率有效提高。
Two impellers are redesigned using the optimization system. In the whole mass flow ranges at design rotating speed, the efficiency is improved obviously and the pressure ratio keeps nearly unchanged.
失速和喘振现象一直是离心压气机研究领域的重点和难点，对于压气机失速或喘振时的非定常效应的研究具有重要意义。
Stall and surge phenomenon are the research hotpots of centrifugal compressor. The study of steady effect of stall and surge is typically important.
用任定准正交面方法对一个航空涡轮冷却器的离心压气机叶轮流场进行了三元计算，计算考虑了上下游边界条件的影响。
The three-dimensional flow field of a centrifugal impeller for aircraft cooling turbine is computed with quasi-orthogonal surface method including the influence of upstream and downstream conditions.
采用离心压气机计算机辅助设计系统，设计了一个离心压气机叶轮，对这一叶轮在不同叶尖间隙下内部流场进行了数值计算。
Tip leakage flow in a compressor which designed by use of Computer Aided design System was investigated by numerical method, for different tip leakage at design flow conditions.
本文应用“旋转分离”理论对离心压气机喘振的内在机理作了初步分析。同时，还阐述了增压柴油机在工作时引起喘振的外界条件。
Based upon the "rotating stall" theory, a preliminary analysis is made in this paper on the internal mechanism of turbocharger centrifugal compressors.
离心式压气机，压气机的一种。当进气到达叶轮中心时，被叶轮离心抛出进人扩散器。在扩散器中气体流速减慢，压力增加。
Centrifugal FLOW compressor, a type of compressor in which air is taken into the center of the impeller and is slung outward centrifugally into a diffuser where it is slowed and pressure is increased.
本文的目的是用数值计算方法来研究离心式压气机叶轮内的旋涡运动。
The objective of the present paper is to study the vortices motions in the impeller ofvaneless diffuser of centrifugal compressor by numerical computations.
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。
The full-scale three-dimensional flow centrifugal stage test conducted on an axial compressor test rignecessitates a test rig compatibility design.
给出一种可展曲面后掠叶片离心式压气机叶轮选型方法。
A geometry designing method for developable surfaces backward swept centrifugal compressor was given in this paper.
给出一种可展曲面后掠叶片离心式压气机叶轮选型方法。
A geometry designing method for developable surfaces backward swept centrifugal compressor was given in this paper.
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