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湍流噪声
相关语句
  turbulent noise
     The wide-band shock associated noise was found to be predominant in the range of pressure ratio between 2.5 and 7, and screech only up to slightly more than 5. For pressure ratios less than 2 or more than 8.5, the jet noise is entirely dominated by turbulent noise.
     宽带谱在驻压比为2.5到7之间,离散谱在5到7之间最突出,驻压比小于2或大于8.5,阻塞喷注噪声则主要是湍流噪声
短句来源
     HIGH PRESSURE EXTENSION OF CHOKED JET TURBULENT NOISE THEORY
     高压阻塞喷注的湍流噪声
短句来源
     4. the efflux noise of silencers in the effective pressure range can be calculated according to the pressure dependence of turbulent noise and the correction to the ratio of expansion.
     4.有用压力范围内膨胀管的出流噪声,可用湍流噪声压力关系公式,加上膨胀比修正而求得。
短句来源
     The relationship between turbulent noise and pressure in the choked jet was obtained.
     同时,本文讨论了阻塞喷注中湍流噪声与压力的关系;
短句来源
     Ever since the fifties, profound theoretical and experimental investigations were spent on the noise production of subsonic and supersonic jets, but little has been done on the turbulent noise of a choked jet.
     自五十年代以来,对亚声速及超声速喷注噪声有大量的研究工作,但对阻塞喷注的湍流噪声研究甚少。
短句来源
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  turbulence noise
     To solve the signal fading problem induced by atmospheric turbulence in optical wireless system,a reception signal model involved turbulence noise and other multiplicative noise was proposed.
     为了解决大气湍流效应所引起的光无线通信系统中的衰落问题,建立了与大气湍流噪声及其它加性噪声有关的信号模型,实现了最大输出信噪比可提高3-20dB的匹配滤波器。
短句来源
     Suppression of turbulence noise based on adaptive filter
     基于LSM-Kalman滤波器的湍流噪声抑制
短句来源
     Suppression of turbulence noise based on adaptive filter
     基于自适应滤波器的大气湍流噪声抑制
短句来源
     Based on the hydrodynamic stability theory of distorted laminar flow and the kind of distortion profiles on the mean velocity in parallel shear flow given in paper [1], this paper investigates the nonlinear stability behaviour of parallel shear flow, carries on stability calculation taking account of the perturbations of background turbulence noise under certain assumption, and obtains some results in accordance qualitatively with those of experiment for plane Poiseuille flow and pipe Poiseuille flow.
     本文根据文[1]给出的经过修正的层流流动的流动稳定性理论及平行剪切流中平均速度的一类修正剖面,研究了平行剪切流的非线性稳定性性质,并在本文的假设下,把背景湍流噪声的干扰引入了流动稳定性计算,对于平面Poiseuille流动和圆管Poiseuille流动,得到了与实验趋势相一致的结果.
短句来源
     By simulations,the adaptive filter algorithm is shown significantly superior to the filter algorithm only considering speckle noise as multiplicative noise in the presence of speckle and turbulence noise.
     仿真结果表明,在同时存在斑纹和湍流噪声的情况下,本文给出的自适应滤波算法优于只考虑斑纹噪声的滤波算法。
短句来源
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  “湍流噪声”译为未确定词的双语例句
     The research results presented in this thesis have showed the importance in both practice and theory for the improvement of the low-noise performance of the grooves in hydraulic valve.
     对于液压阀而言,气穴噪声属于典型单极子声源是最有效的声辐射源,其他的流体动力噪声源如湍流噪声、脉动力等噪声辐射效率低,可以忽略。
短句来源
     In wireless OCDMA communication system, signals that a user receives are interfered by the other user’s signals (which is called multi-user interference or multi-access interference, MAI) and channel noise, like background light and atmospheric turbulence induced by wireless optical communication channel.
     W-OCDMA 系统中,预期用户接收的信号受到多用户干扰、接收机噪声以及由于无线信道的特殊性引入的信道噪声,如背景光噪声、大气湍流噪声等的影响。
短句来源
     The momentum thickness Reynolds number Re_θare 1241, 1635. The near-wall coherent structures in the turbulent boundary layer is the most significance in wall shear turbulent flows.
     这对于辨识壁湍流相干结构和进行湍流控制(包括表面摩擦、湍流噪声和传热传质的控制)有重要的实际意义。 本文实验的动量损失厚度雷诺数Re_θ为1241 和1635。
短句来源
     By the experiments, It is found that the effect is mainly due to the upstream noise radiated through the nozzle exit. The weak nonlinear interaction between upstream noise and downstream turbulence is supposed.
     通过实验证明这种影响主要是上游湍流噪声辐射到喷口外部而产生的,并且观察到上下游之间存在微弱的非线性相互作用。
短句来源
     The effect of pressure gradient was also discussed in this formula.
     定量地分析了阻塞喷注中压力梯度对源强度和湍流噪声的影响。
短句来源
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  turbulent noise
Analysis of Turbulent Noise Spectra of Electrochemical Reactions in Different Experimental Conditions
      
Results obtained by measuring the turbulent noise in a hydrodynamic channel with the use of piezoelectric composite receivers are reported.
      
The spectrum of ion-acoustic turbulent noise generated by the driven current and concentrated in a limited cone of angles along the propagation direction of the wave is found.
      
The dependence of the threshold density of the radiation flux on the angle between the scattering wave vector and the direction of anisotropy of the turbulent noise is described.
      
A new effect of STBS forbiddenness caused by anomalous turbulent heating of the ions is predicted for a plasma with a high level of turbulent noise.
      
更多          
  turbulence noise
In wind instruments, the turbulence noise is filtered by the resonances of the pipe.
      
The distinctiveness of this manner contrast can thus be enhanced by increasing the intensity of turbulence noise in the fricative.
      


Ever since the fifties, profound theoretical and experimental investigations were spent on the noise production of subsonic and supersonic jets, but little has been done on the turbulent noise of a choked jet. In a previous paper the authors derived the pressure dependence of the latter. In this paper it is shown that a slight modifica-tion of the formula in the above-mentioned paper will make it applicable to subsonic jets too, and an interpretation is obtained for turbulent jet noise in general. From this...

Ever since the fifties, profound theoretical and experimental investigations were spent on the noise production of subsonic and supersonic jets, but little has been done on the turbulent noise of a choked jet. In a previous paper the authors derived the pressure dependence of the latter. In this paper it is shown that a slight modifica-tion of the formula in the above-mentioned paper will make it applicable to subsonic jets too, and an interpretation is obtained for turbulent jet noise in general. From this it is inferred that turbulent jet noise has its origin in the quadrapole radiation of turbulent eddies, the only difference in that, for a choked jet, the turbulence velocity further increases with the stagnation pressure, although the mean jet velocity does not. From this point of view, the rule of increase of the turbulent velocity with increasing stagnation pressure is predicted. This interpretation seems plausible and the noise relations thus derived agree with experiment.

自五十年代以来,对亚声速及超声速喷注噪声有大量的研究工作,但对阻塞喷注的湍流噪声研究甚少。作者曾于文献[1]中提出阻塞喷注湍流噪声的压力关系。本文是以前工作的继续,作者发现只要将文献[1]中所提出的关系式略加修改,适用范围便可以延至亚声速喷注。并得到湍流喷注噪声的发生机理。根据这个关系,可以推论喷注中的湍流噪声,无论是阻塞或非阻塞,来源都是湍流脉动的四极子源,只是在阻塞喷注中湍流速度继续随驻点压力增加,虽然气流的平均速度不再改变。作者还提出了湍流速度变化的规律,它的合理性及导出的噪声公式为实验结果所证明。

Shock associated noise is an important part of choked jet noise. Sound field and spectra thereof were investigated experimentally by utilizing the heterodyne analysis technique, so that both the screech and the wide-band noise can be recorded and studied. The sound pressures and spectra vary widely with the stagnation pressure, but the overall sound pressure level at 90?to the jet shows good regularity, it is nearly a constant between pressure ratios 3 and 8.5, given by 97 + 201og d, dB, d being nozzle diameter...

Shock associated noise is an important part of choked jet noise. Sound field and spectra thereof were investigated experimentally by utilizing the heterodyne analysis technique, so that both the screech and the wide-band noise can be recorded and studied. The sound pressures and spectra vary widely with the stagnation pressure, but the overall sound pressure level at 90?to the jet shows good regularity, it is nearly a constant between pressure ratios 3 and 8.5, given by 97 + 201og d, dB, d being nozzle diameter in mm., and empirical formulae are given to facilitate the SPL prediction on the whole range of pressures. The wide-band shock associated noise was found to be predominant in the range of pressure ratio between 2.5 and 7, and screech only up to slightly more than 5. For pressure ratios less than 2 or more than 8.5, the jet noise is entirely dominated by turbulent noise. New formulae for screech frequency and peak frequency of wide-band shock associated noise are given, which agree well with experiments. The existance of non-harmonic components in screech is explained. Interference effect seems to exist in the upstream direction between shock associated noise and turbulent noise, but not in the 90°direction. This phenomenon is explained by considering the phase relations of the noise.

冲击噪声是阻塞喷注噪声的重要部份。我们对它的声场和频谱作了详细的实验测量,由于采用外差分析技术,冲击噪声的离散谱和宽带谱可同时记录。实验表明,声场和频谱与驻压比的关系很复杂,但在与喷注垂直的方向上,距喷口1米处的总声压级,如驻压比在3到8.5之间,约为97+20logd分贝,基本不受驻压变化的影响,其中d是喷口直径,以毫米计。进一步又给出了全部驻压比范围内的总声压级的表达式。宽带谱在驻压比为2.5到7之间,离散谱在5到7之间最突出,驻压比小于2或大于8.5,阻塞喷注噪声则主要是湍流噪声。本文还给出了计算离散谱频率和宽带谱峰频的新公式;对实验中观察到的离散谱的非谐频成份,也作了解释。在喷注上游方向,观察到阻塞喷注噪声频谱具有一个或几个凹陷部份,表明在这些频率范围存在干涉现象,可能是湍流噪声与宽带冲击噪声之间的干涉现象,文中说明了这种干涉的可能性。

Based on the low of the eighth power of speed of M.J.Lighthillthis article has derived the calculating formula for the air dynamic noisepower in the compressor,and analysed the factors to affect the noise,also indicated that the dynamic noise in the compressor mainly comesfrom the valve jet noise; the principle to reduce the dynamic noise isto get a small Reynolds number Re; the emphasis to reduce the noise ison the jet turbulent flow noise;the efficient way to reduce the noiseis to decrease the valve Mach number....

Based on the low of the eighth power of speed of M.J.Lighthillthis article has derived the calculating formula for the air dynamic noisepower in the compressor,and analysed the factors to affect the noise,also indicated that the dynamic noise in the compressor mainly comesfrom the valve jet noise; the principle to reduce the dynamic noise isto get a small Reynolds number Re; the emphasis to reduce the noise ison the jet turbulent flow noise;the efficient way to reduce the noiseis to decrease the valve Mach number.

本文以M.J.Lighthill 速度八次方定律为依据,从理论上导出了压缩机空气动力噪声声功率的计算式;对影响它的因素进行了分析,指出压缩机的空气动力噪声主要取决气阀的喷注湍流噪声;降低压缩机空气动力噪声的原则是小雷诺数R_e 原则,降噪的重点是气阀的喷注湍流噪声,降噪的有效措施是减小气阀马赫数M_v。

 
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