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   叶片尾迹 的翻译结果: 查询用时:0.019秒
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叶片尾迹
相关语句
  blade wake
     On the rotor blade pressure surface,the dominant frequencies of unsteady surface pressure are the up-stream blade wake passing frequency and its harmonics,and the amplitudes of pressure fluctuations decrease from leading edge to trailing edge.
     对转子叶片非定常压力分布的分析显示:转子叶片压力面非定常表面压力主要受上游叶片尾迹影响,其主导频率为上游叶片尾迹频率及其倍频,压力波动幅度随上游叶片尾迹的衰减而沿流向减弱。
短句来源
     Near the designed working condition the effect area of the blade wake is small while the effect region increases under the off-design working condition. The radial width of the blade wake accounts for 15%-25% of the radial width of volute and is about 2-3 times of the blade chord height.
     在设计工况附近叶片尾迹影响区域小,在非设计工况下叶片尾迹影响区域大,尾迹区域占到蜗壳径向宽度的15%~25%,约是叶片弦高的2~3倍;
短句来源
     A particle image velocimetry system was used to measure the secondary flow in the volute cross-section and the blade wake flow.
     用粒子图像速度场仪技术对叶片尾迹区及蜗壳出口横截面上的二次流做了详细的变工况测量与分析.
短句来源
     Experimental Study on the Blade Wake and Secondary Flow in Volute of a Forward Curved Multi-Blades Centrifugal Fan
     前向多翼离心风机叶片尾迹和蜗壳二次流动的试验研究
短句来源
     Flow separation produces pressure fluctuations of large amplitudes,possibly with the dominant frequencies differ from up-stream blade wake passing frequency and its harmonics.
     在存在尾缘分离的情况下,在分离区附近产生较大压力波动。 尾缘气流分离产生的压力波动频谱中含有上游叶片尾迹频率及其倍频的分量,但其频谱可能比较复杂,并非单一地受上游叶片尾迹影响。
短句来源
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  “叶片尾迹”译为未确定词的双语例句
     The result shows that the fluctuation intensity of the wake flow reaches about 20%-70%.
     结果表明:叶片尾迹区脉动强度达20%~70%;
短句来源
     THE AXIALLY ATTENUATION OF WAKE FOR AXIAL COMPRESSOR BLADE
     轴流压气机叶片尾迹沿轴向的衰减
短句来源
     Effects of the up-stream blade wakes on the spectrum of rotor blade unsteady surface pressure
     上游叶片尾迹对转子叶片非定常表面压力频谱特性影响的研究
短句来源
     According to the Prandtl's theory of Mixing-Length in reference to the incompressible free-turbulence, the law of axially attenuation of wake for axial compressor blade was studied in this paper.
     本文参考Prandtl关于不可压自由湍流的混合长度理论,研究了轴流压气机叶片尾迹沿轴向的变化规律。
短句来源
     Show in the experiment these results, which presents in the paper, may be used for predicting the axially attenuation of wake for the axial compressor blade.
     理论分析结果与实测结果的比较表明,本文所提供的分析结果可以用来初步预计轴流压气机叶片尾迹沿轴向的衰减程度。
短句来源
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  相似匹配句对
     THE AXIALLY ATTENUATION OF WAKE FOR AXIAL COMPRESSOR BLADE
     轴流压气机叶片尾迹沿轴向的衰减
短句来源
     leaf> leafstalk.
     叶片>叶柄。
短句来源
     leaf>leafstalk.
     叶片>叶柄。
短句来源
     The Effect of Unsteady Wake on Leading Edge Film Cooling
     非定常尾迹叶片头部气膜冷却的影响
短句来源
     Effects of the cascade wake are taken into account.
     考虑了叶栅尾迹的影响。
短句来源
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  blade wake
The balance of transport equation terms in the blade wake is also presented.
      
The near wake flow is characterised by strong deformations, due to the bending of the blade wake sheets, to the contraction of the slipstream and to the trajectory of the tip vortex.
      
In this flow, a primary tip-leakage vortex interacts with a secondary, co-rotating trailing edge vortex and other co- and counter-rotating vorticity found in the blade wake.
      
Empirically validated rotor blade wake models are becoming more integrated into comprehensive rotor codes.
      


According to the Prandtl's theory of Mixing-Length in reference to the incompressible free-turbulence, the law of axially attenuation of wake for axial compressor blade was studied in this paper. The figure of velocity in the region of wake, the relation between the width of wake and maximum, loss of velocity, and the relation of axially attenuation for maximum loss of velocity were obtained. Show in the experiment these results, which presents in the paper, may be used for predicting the axially attenuation...

According to the Prandtl's theory of Mixing-Length in reference to the incompressible free-turbulence, the law of axially attenuation of wake for axial compressor blade was studied in this paper. The figure of velocity in the region of wake, the relation between the width of wake and maximum, loss of velocity, and the relation of axially attenuation for maximum loss of velocity were obtained. Show in the experiment these results, which presents in the paper, may be used for predicting the axially attenuation of wake for the axial compressor blade.

本文参考Prandtl关于不可压自由湍流的混合长度理论,研究了轴流压气机叶片尾迹沿轴向的变化规律。得到了尾迹区内的速度分布,尾迹宽度与尾迹区内最大速度亏损值之间的关系式,以及最大速度亏损值沿轴向的衰减公式。理论分析结果与实测结果的比较表明,本文所提供的分析结果可以用来初步预计轴流压气机叶片尾迹沿轴向的衰减程度。

A general model for calculating harmonic and broadband noise in an axial flow compressor is proposed using the random pulse modulation theory,and tlie theoretical investigation of stator source and its radiation is presented.Based on experience formulation of viscous wake and thc theory of thin airfoil gusts response,the calculating formaulation of the fluctuating lift of moving cascade blades under upstream stator blade row wakes considering tle influence of airfoil camber and angle of attack is derived.The...

A general model for calculating harmonic and broadband noise in an axial flow compressor is proposed using the random pulse modulation theory,and tlie theoretical investigation of stator source and its radiation is presented.Based on experience formulation of viscous wake and thc theory of thin airfoil gusts response,the calculating formaulation of the fluctuating lift of moving cascade blades under upstream stator blade row wakes considering tle influence of airfoil camber and angle of attack is derived.The effects of cascade geometry parameters and aerodynamic parameters to the unsteady fluctuating lift and sound radiation are ana-lysed.The vaiied tendency is exprssed in its spectrum.The present meth-od is a new idea for the investigation of compressor noise that provides a theoretical basis of designing low noise axial flow compressor.

本文利用随机脉动调制理论,建立了轴流压气机静子离散噪声和宽频噪声通用的计算模型,对静子声源及其辐射场进行了理论研究。依据现有粘性尾迹经验公式,基于薄翼阵风响应理论,给出了考虑翼型弯度及攻角影响时静叶叶片和上游动叶片尾迹相互作用的脉动升力响应计算公式,分析了压气机几何参数和气动参数对声辐射的影响,并在声功率级频谱图上展示其变化趋势。本文对压气机气动噪声机理的探讨结果将为低噪声轴流压气机的设计提供理论依据。

This paper is focused on the aeroacoustic properties of low speed axial fan running in inlet turbulence with high intensity and small correlation scales. The acoustic testing was carried out with three kinds of inlet turbulence whose intensity and scales were different from each other. Aerodynamic performance measurements include turbulence intensity and scales, blade wake width, mean flow velocity profiles and mean pressure. Acoustic measurements include overall SPL and 1/3 octove spectra. Theoretical study...

This paper is focused on the aeroacoustic properties of low speed axial fan running in inlet turbulence with high intensity and small correlation scales. The acoustic testing was carried out with three kinds of inlet turbulence whose intensity and scales were different from each other. Aerodynamic performance measurements include turbulence intensity and scales, blade wake width, mean flow velocity profiles and mean pressure. Acoustic measurements include overall SPL and 1/3 octove spectra. Theoretical study includes computation of OSPL and sound Spectra. The theoretical and experimental results show that both of inlet turbulence and blade vortex shedding are major sources of axial fan, but inlet turbulence is more responsible than vortex and turbulence intensity is more importent than correlation scale for the noise generation.

详细描述紊流进气条件下低速轴流风机的气动噪声的试验和理论研究气动试验包括测量了三种不同紊流进气条件下风机进口的紊流强度、紊流尺度、风机叶片的尾迹宽度以及平均速度、压力等参数声学试验包括测量了风机排气端的总声级和1/3倍频程频谱理论上首次把尾涡脱落和进气紊流结合起来完整地研究了风机的宽频噪声,给出了轴流风机宽频源的声压谱密度函数的表达式,在计算叶片脉动力时,首次采用可分离的波数函数模型,使得计算过程大为简化理论和试验都表明,尾涡脱落和进气紊流同是风机的主要声源,相对而言,紊流进气对噪声的影响要大于尾涡脱落,其中紊流强度是影响风机噪声的最主要参数

 
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