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扩压器     
相关语句
  diffuser
    CALCULATION OF BOUNDARY LAYER FOR SUBSONIC DIFFUSER
    亚音速扩压器附面层计算
短句来源
    AN EXPERIMENTAL STUDY OF HIGH SUBSONIC TWO-DIMENSIONAL DIFFUSER DESIGNED BY dM/dx-CONST
    按dM/dm=常数设计的二元高亚音速扩压器的试验研究
短句来源
    NUMERICAL CALCULATION OF FLOW FIELD IN AFTERBURNER DIFFUSER OF TURBOFAN ENGINE
    涡扇发动机加力燃烧室扩压器流场的数值计算
短句来源
    MONITORING PARAMETERS OF SWIRLING FLOW IN S-SHAPED DIFFUSER
    S弯扩压器内旋流的监测参数
短句来源
    ANALYSIS OF COMBUSTION TEST RESULTS OF THREE COMBUSTORS WITH THE VORTEX CONTROLLED DIFFUSER
    三种带涡流控制扩压器的燃烧室燃烧试验结果分析
短句来源
更多       
  diffusers
    Dynamic Characteristics of the Flow Field at the Exit of Transonic Diffusers
    跨音扩压器出口流场的动态特征
短句来源
    AN ENGINEERING METHOD FOR DESIGNING LARGEAREA-RATIO SUPERSONIC DIFFUSERS
    大面积比超音速扩压器的工程设计方法
短句来源
    THE CALCULATION OF THE AXISYMMETRIC SUBSONIC VISCOUS FLOW FIELD OF ANNULAR DIFFUSERS WITH SWIRL AT THE INLETS
    进口具有预旋流动的亚音速轴对称环形扩压器粘性流场计算
短句来源
    The Predication of Subsonic Diffusers(2)
    亚音速扩压器计算(二)
短句来源
    Unsteady Flow in Transonic Diffusers
    跨音扩压器中的不稳定流
短句来源
更多       
  dump diffuser
    EXPERIMENTAL STUDY ON A COMBUSTOR WITH VORTEX-CONTROLLED DUMP DIFFUSER
    采用抽气控制旋涡式短突扩扩压器的燃烧室试验研究
短句来源
    Influence of Inlet Velocity Distribution on Dump Diffuser Performance
    进口速度分布对短突扩压器性能的影响
短句来源
    An Investigation of Matching between Dump Diffuser and Flame Tube
    短突扩扩压器与火焰筒匹配的实验研究
短句来源
    Numerical Investigation on Pressure Characteristics of Dump Diffuser
    短突扩扩压器压力特性的数值研究
短句来源
    In this paper, numerical analysis of three-dimensional two-phase reacting flow field in an annular combustor with the dump diffuser is developed in an arbitrary curvilinear coordinate system.
    本文在任意曲线坐标下对包括扩压器和火焰筒在内的环形燃烧室三维两相反应流进行了数值模拟,燃烧室性能是采用多维经验分析法估算所用的数学模型有k-ε紊流模型,EBU-Arrhenius紊流燃烧室模型,六通量热辐射模型以及颗粒群轨道模型。
短句来源
更多       
  a diffuser
    NUMERICAL MODELING OF TURBULENT TWO-PHASE FLOWS AND FUEL CONCENTRATION FIELD IN A DIFFUSER OF AFTERBURNER
    内外函混合加力燃烧室扩压器内液雾湍流两相流场和浓度场数值模拟
短句来源
    EFFECT OF CONDENSATION IN A DIFFUSER ON THE FLOW FIELD
    扩压器内的冷凝对流场的影响
短句来源
    NUMERICAL ANALYSIS ON TURBULENT FLOW IN A DIFFUSER BY TIME MARCHING METHOD
    扩压器内二维湍流流动的时间推进数值解
短句来源
    NUMERICAL ANALYSIS ON TURBULENT FLOW IN A DIFFUSER WITH ANY GEOMETRIC SHAPE BY TIME MARCHING METHOD
    任意边界扩压器内紊流流动的时间推进数值计算
短句来源
    For matching turbine work condition, designed a diffuser that transformed square to round, chose central line and shape changed method, defined diffuser expanding angle.
    给出了一种亚音速方转圆扩压器的设计方法,并对中心线形状、型面变化规律和扩张角等进行了选择和说明。
短句来源
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      diffuser
    Investigation into the influence of diffuser stagger angles on the flow field and performance of a centrifugal compressor
          
    The performance graphs of a centrifugal compressor under different diffuser stagger angles were measured, and the influence of different stagger angles of vanes on the stage performance as well as flow field was investigated numerically.
          
    The results show that the performance graph shifts when the diffuser stagger angle is altered; the influence of different stagger angles of vanes on the flow field inside the centrifugal compressor is great.
          
    Large scale vortices appear on the diffuser vane under larger incidence.
          
    An optimal diffuser stagger angle should exist at a specified flow rate to make the characteristic of the flow optimized.
          
    更多          
      diffusers
    Calculation of the initial segment and the stabilized flow segment in two-dimensional separation-free diffusers
          
    The results obtained enable conclusions to be made regarding the possibility of investigating diffusers in such types of tubes.
          
    Conditions of pulsed starting of supersonic diffusers of wind tunnels
          
    In the framework of an ideal gas and quasi-one-dimensional approach, a study is made of the unsteady processes associated with the starting of supersonic unregulated diffusers of pulsed wind tunnels.
          
    A class of self-similar thermal problems for flows in plane diffusers is formulated.
          
    更多          
      dump diffuser
    Numerical study of an annular gas turbine combustor with dump diffuser
          
    A general numerical method is presented for calculating steady three-dimensional and two-phase turbulent reactive flows with a nonstaggered body-fitted coordinate system in an annular gas turbine combustor with the dump diffuser.
          
      a diffuser
    In [1] the possibility of, in principle, determining the throat starting of a diffuser in an aerodynamic shock tube, and the time to establish flow in the diffuser channel, which was ~300 μsec, was measured.
          
    Effect of humidity on the flow characteristics of a two-phase medium in a diffuser
          
    The effect of the initial humidity of a two-phase flow on the aerodynamic characteristics of a diffuser is considered.
          
    Axisymmetric flow in the channel of such a diffuser is calculated in the presence of an oblique shock in front of the separation region formed at the corner of the central body.
          
    Using a diffuser of laser radiation is proposed as a way to reduce this effect.
          
    更多          


    To compute accurtely the energy losses in the flow passage is of great importance in predicting the stage performance of a centrifugal compressor. Based on some assumptions and according to the boundary layer theory, this paper offers a fomula for computing directly the stagnation pressure loss in the vaned diffuser. These assumptions are1. It is an incompressible steady turbulent flow.2. At the inlet of the diffuser, the flow direction coincides with the vane angle, i. e. , no shock loss occurs at the entry...

    To compute accurtely the energy losses in the flow passage is of great importance in predicting the stage performance of a centrifugal compressor. Based on some assumptions and according to the boundary layer theory, this paper offers a fomula for computing directly the stagnation pressure loss in the vaned diffuser. These assumptions are1. It is an incompressible steady turbulent flow.2. At the inlet of the diffuser, the flow direction coincides with the vane angle, i. e. , no shock loss occurs at the entry of the vane.3. Both the equivalent divergent angle of the passage and the curvature of the vane are not large. The formula obtained is expressed aswhereWith the geometric parameters of the vaned diffuser and the inlet velocity being given, the result can be obtained by use of this formula. Compared with the experimental data, the result is a good approximation and its error is rather smaller than those calculated by the prevailing methods of "flow passage" and "loss coefficient" .NOMENCLATUREdh——hydraulic diameter;l——vane length along the mean arc;P——static p re ssure;P*——stagnation pressure;R——radius;V——velocity of main flow;β——vane angle;βl= (β5 +βl )/2, average \alue of the inlet and outlet vane angle;Δ——absolute roughness of wall surface;v——kinematic visco ity of gas;ρ——density of gasσ=1-(zs)/(πDsinβ), reducing coefficient of crose- ecliunal aieb;z——number of vanes;s——thickness of vane;σl = (σ5+σl)/2, average value of reducing coefficients of the inlet and outlet cross-sectional area.Subscripts5——at vane inlct;6——at vane outlet.

    准确计算流道内的能量损失对预测离心式压缩机的级性能十分重要。本文根据附面层理论,在某些假定的条件下,推导出直接计算叶片扩压器内总压损失的公式。用此公式计算的结果与实验数据非常接近,其相对误差比按照常用的“流道法”和“损失系数法”的误差小得多。

    The performance data and flow characteristics for two-dimensional single-plane diffuser designed by dM/dx=constant have been studied experimentally at high subsonic speeds in a small diffuser tunnel. The tests were carried out at M1( diffuser entrance Mach number)≈0.2-0.8, corresponding to a Reynolds number range of 2.08×105-8.32×05. Both time-mean flow properties and fluctuating flow properties have been measured.The test results show that the value of steady-state performance is affected to a great extent...

    The performance data and flow characteristics for two-dimensional single-plane diffuser designed by dM/dx=constant have been studied experimentally at high subsonic speeds in a small diffuser tunnel. The tests were carried out at M1( diffuser entrance Mach number)≈0.2-0.8, corresponding to a Reynolds number range of 2.08×105-8.32×05. Both time-mean flow properties and fluctuating flow properties have been measured.The test results show that the value of steady-state performance is affected to a great extent by inlet conditions and geometry parameters of diffusers. The maximum total pressure fluctuation occurring in the turbulent shear layer and the location of value is nearly equal to 0.6-0.75.

    本文介绍一种按dM/dx=常数设计的二元高亚音速扩压器的试验研究结果。所试验的扩压器进口M数为0.2—0.8,其相应的雷诺数为2.08×10~5—8.32×10~5。该扩压器的进口堵塞比B=2δ_1~*/W_1≈0.049;展弦比AS=1.33;扩压器长度与进口高度之比L/W_1≈6.35;面积比AR=2.08。对该扩压器进行了静态性能和动态性能的测量,并仔细地测量了扩压器沿程紊流附面层的发展,通过流谱观察,测得气流分离点的位置及分离区的大小。试验结果指出:扩压器静态性能与一元理想流的数值相比差别较大,靠近扩压器出口有较大分离区。扩压器内的最大总压脉动发生在紊流剪切层内,其位置高度与剪切层厚度的比值大约在0.6—0.75之间。

    This paper presents a comparison of the experimental results of the flow between two S-shaped air intake models. model A is an S-shaped diffuser with a horizontal offset only, and model B is space S-shaped with horizontal and vertical offsets. The performance under comparison comprises the static pressure distribution along the walls,the total pressure field and swirl at the nominal engine face and the power spectral density of the flow in the region of flow reattachmant at high incidence. The results shows...

    This paper presents a comparison of the experimental results of the flow between two S-shaped air intake models. model A is an S-shaped diffuser with a horizontal offset only, and model B is space S-shaped with horizontal and vertical offsets. The performance under comparison comprises the static pressure distribution along the walls,the total pressure field and swirl at the nominal engine face and the power spectral density of the flow in the region of flow reattachmant at high incidence. The results shows that the flow performance of model A is better than that of model B and, in particular, the performance of model B is seriously deteriorating at high incidence.

    本文比较了两个不同S形亚音速进气管道模型的实验性能,模型A是一个平面S形扩压器,即其中心线仅在水平面内有偏距。模型B则是一个空间S形扩压器,它的中心线在水平和垂直两个方向有相同的偏距。所比较的性能包括沿流程的静压分布,出口截面总压场和旋流特性以及在大迎角下分离区再附点附近气流的功率频谱密度。结果表明,模型B中气流的特性比模型A要差,尤其在大迎角时,空间S形扩压器性能恶化严重得多。

     
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