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叶轮
相关语句
  impeller
    Modeling Method for Titanium Addition Impeller by UG13
    UG13环境下小型钛合金叶轮的造型方法
短句来源
    EXPERIMENT STUDY ON EFFECT OF TIP CLEARANCE ON CENTRIFUGAL IMPELLER
    间隙泄漏对半开式离心叶轮性能影响的实验研究与分析
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    Impeller Sculpts Display and Virtual Machining with OpenGL
    利用OpenGL显示叶轮造型及模拟加工
短句来源
    Program Design of Database Based on MFC DAO in Impeller Machining
    基于MFC DAO的叶轮加工数据库程序设计
短句来源
    Numerical Study of 3-D Flow in a Diagonal Fan Impeller
    有无叶顶间隙条件下斜流风机叶轮内部三维流动的数值研究
短句来源
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  impellers
    DESIGN AND EXPERIMENT OF CENTRIFUGAL COMPRESSOR 3-D IMPELLERS FOR HEAVY GASES
    重气体离心压缩机三元叶轮的设计及实验
短句来源
    Welding Repairof Aero-engine Impellers
    航空发动机叶轮的焊接修理
短句来源
    A SINGLE HOT-FILM ASPIRATING PROBE FOR MEASURING THE TOTAL TEMPERATURE AND PRESSURE AT THE OUTLET OF IMPELLERS
    叶轮出口总温总压测量用单热膜吸气探针的研究
短句来源
    CONFORMAL INTEGRATED DESIGN OF IMPELLERS
    整体叶轮的一体化保形设计研究
短句来源
    A Design of Cathode for NC Evolution Electrochemical Mchining of Integral Impellers
    整体叶轮数控展成电解加工阴极的设计
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  “叶轮”译为未确定词的双语例句
    AERODYNAMIC CALCULATION AND ANALYSIS OF AHORIZONTAL AXIS WIND TURBINE INYAW OR IN PITCH-UP
    水平轴风车叶轮侧偏或上仰时的气动力计算与分析
短句来源
    Numerical control milling for aeroengine integrated impeler of TC6 titanium alloy
    TC6钛合金整体叶轮数控铣削工艺
短句来源
    NATURAL VIBRATION ANALYSIS OF TURBOMACHINERY DISK WITH SMALL MISTUNED BLADES
    小失谐叶轮的固有振动分析
短句来源
    TURBULANCE MEASUREMENTS AND ANALYSIS IN A CENTRIFUGAL PUMP ON THE OFF-DESIGN CONDITION
    非设计工况下低比速泵叶轮内不稳定流动和湍流度试验
短句来源
    DESTABLIZING BLADE TIP FORCES AND INSTABILITY OF AN AXIAL COMPRESSOR ROTOR Part 1. Theoretical Analyses
    压气机叶轮偏心引起的自激力和稳定性的理论分析
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  impeller
First, the internal flow field of each impeller was calculated.
      
Second, the concurrent working point of each impeller was approximately estimated.
      
Finally, a calculation was performed considering the influence on each impeller.
      
Although both impellers had the same blade cross-section, one impeller had a two-dimensional blade, while the other had a leaned blade.
      
The average cavitation performance of each impeller was satisfactorily predicted by the numerical simulations.
      
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  impellers
Cavitation in semi-open centrifugal impellers for a miniature pump
      
Cavitation in miniature pumps was investigated experimentally for two semi-open centrifugal impellers.
      
Although both impellers had the same blade cross-section, one impeller had a two-dimensional blade, while the other had a leaned blade.
      
Three impellers (I, II, III) having same outer diameter, but different radius ratio and blade angles were employed for the investigation.
      
The total pressure developed by the impellers in each case is found to be maximum at a circumferential position of around 270°.
      
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Two different ways of solving three-dimensional transonic shocked flow fields in turbomachinery are compared and the mistakes which exist in [2] are analyzed. None of the three programs given by [2] can be used to compute the transonic shocked flow fields on the S1 stream surfaces. On this basis, the following preliminary concluding remarks were obtained: The theory of two kinds of relative stream surfaces S1 and S2 might not necessarily be a good method for solving three-dimensional transonic shocked flow...

Two different ways of solving three-dimensional transonic shocked flow fields in turbomachinery are compared and the mistakes which exist in [2] are analyzed. None of the three programs given by [2] can be used to compute the transonic shocked flow fields on the S1 stream surfaces. On this basis, the following preliminary concluding remarks were obtained: The theory of two kinds of relative stream surfaces S1 and S2 might not necessarily be a good method for solving three-dimensional transonic shocked flow fields in modern turboma- chinery. On the contrary, the methods to solve three-dimensional flow fields directly might have some merits for recommendation.

本文比较了求解叶轮机械中带激波的三维跨音流场的两种不同的途径,着重分析了 文献[2]中存在的错误并指出[2]中所给出的三个程序没有一个能用来计算 S1流面上的 带激波的跨音流场。在此基础上,得到如下初步结论:两族相对流面理论未必是求解当 代叶轮机械中带激波的三维跨音流场的好方法,相反,直接求解三维流动的方法是更为 可取的。

In order to extent the usage range of a cascade having excellent aerodynamic performance, it is beneficial to investigate the similarity between different flow fieldS. Von Karman gave transonic similarity law of two-dimensional isolated airfoils many years ago. However, the law of cascades is still different from that one of airfoils. This paper points out that, to guarantee similarity between two flow fields around cascades, it is necessary that five corresponding transonic similarity parameters must be kept...

In order to extent the usage range of a cascade having excellent aerodynamic performance, it is beneficial to investigate the similarity between different flow fieldS. Von Karman gave transonic similarity law of two-dimensional isolated airfoils many years ago. However, the law of cascades is still different from that one of airfoils. This paper points out that, to guarantee similarity between two flow fields around cascades, it is necessary that five corresponding transonic similarity parameters must be kept equal, respectively. Also some examples have been presented in this paper for demonstration. They indicate that the similarity law will help us to obtain rapidly many similar transonic flow fields around cascades at different operating conditions from a known flow field around a given cascade.

跨音叶栅绕流参数繁多,为了便于系统研究参数影响,也为了扩展某个气动性能良好的叶栅的使用范围,研究不同流场之间的相仿可能是有益的。多年前VonKarman曾给出了二维孤立翼型的跨音相仿律。然而,由于远前后方边界条件的不对称性,以及叶轮机械流场的周期性 所以叶栅的相仿律和孤立翼型的尚应有所不同。本文指出,为了维持两个叶栅流场的相仿,五个对应跨音相仿参数应分别相等。文中举例表明,相仿性有助于由一个巳知给定叶栅流场迅速得到很多在不同条件下运转的相仿跨音叶栅流场。

The present paper gives a new solution method of 2-D cascade flow, in which the free streamline boundary conditions can be satisfied. This is a cross-iterative calculation method between two correlating flow fields. The 2-D subsonic flow problem for calculating the upstream and downstream regions of the ordinary blade cascade, the splitter and the tandem blade cascades is discussed from an unified viewpoint. The computer program can be available for these three cases.For calculating the splitter and the tandem...

The present paper gives a new solution method of 2-D cascade flow, in which the free streamline boundary conditions can be satisfied. This is a cross-iterative calculation method between two correlating flow fields. The 2-D subsonic flow problem for calculating the upstream and downstream regions of the ordinary blade cascade, the splitter and the tandem blade cascades is discussed from an unified viewpoint. The computer program can be available for these three cases.For calculating the splitter and the tandem blade cascades a physical condition of minimum disturbance of the flow field is proposed, so that the flow division of the two blade channels formed by the splitter blade or the splitter stream surface can be calculated.Some results of numerical examples are presented and compared with the experimental data, the comparison has proved preliminarily the validity of both the presented method and the proposed physical condition for determining the flow division. Some useful thoughts are also given concerning the aerodynamic design of the splitter blade rotors.

本文提出一种满足自由流线边界条件二元叶栅的新解法——两个相关流场交叉迭代的计算方法,统一地论述了普通叶栅的上下游区、分流叶片叶栅和串列叶栅的二元亚音速流场计算问题,计算程序可以通用于这三种情况。 在分流叶片叶栅和串列叶栅的计算中提出了一种流场最小干扰的物理条件,从而可以计算出由分流叶片或分流面所形成的两个叶道之间的流量分配比。 介绍了数值计算结果,并与试验数据作了比较,这些计算与比较初步验证了本文方法,以及所建议的计算流量分配比物理条件的合理性,并对分流叶片叶轮的气动设计提出了一些有益的设想。

 
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