英语翻译In this section the simulations will be compared to the

sandy382022-10-04 11:39:543条回答

英语翻译
In this section the simulations will be compared to the experimental results .This assessment will be made in terms of the noise source distribution in the rotor plane (Section 4,1) ,the rotor noise spectra (Section 4,2),and the overall noise levels as a function of rotor power(Section 4,3).
the measured and simulated source maps for both turbines are shown in Figure 3 to Figure 6.note that these source maps correspond to the upwind measurement position on the ground.the range of the colour scale is always 12 db,and the maximum is adjusted for each individual frequency band.The experimental source maps were averaged over all measurements,which were carried out for misalignment angles ά (see figure 1) around 00 and wind speeds (normalized to 10 m height ) between 6 and 10 m/s .the simulations were done for a misalignment angle of 00 and a wind speed close to the average experimental wind speed.
In general a very good qualitative agreement is ob served between experiments and simulations .as in the experiments ,the simulated source maps show dominant noise radiation from the outer part of the blades ,during their downward movement .similar frequency,which can be attributed to the thinner trailing edge boundary layer at higher radius .in some cases even the minor side-lobes (e.g.around “11 o’clock for 400-500 Hz in the GE results),which are an artifact of the array method,are reproduced in the simulations .obviously ,the minor experimental noise sources,at the nacelle and the tower ,are not reproduced in the simulation,because these are not simulated in the trailing edge noise prediction model.
For the GAMESA turbine ,the simulated source radius seems to be slightly higher than in the experiments.This may be due to the fact that the measured rotor had one tripped,one clean,and one untreated blade ,while he simulations are done for clean blades.Tripping results in a thicker trailing edge boundary layer ,so that the trailing edge noise at a given radius shifts to lower frequencies.

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lxz_29 共回答了19个问题 | 采纳率89.5%
在这一节中的模拟,将比较实验结果.这项评估将在条件的噪声源分布在旋翼飞机(第4,1 ) ,转子噪声谱(第4,2 ) ,以及整体噪音水平作为一个函数的转子功率(第4,3 ) .
实测和模拟源地图,为轮机如图3所示,以图6 .注意的是,这些地图的来源,对应到上风处测量位置在地面上.范围颜色的规模是历来12分贝,并把最高的是调整为每频段.实验源地图平均每场超过所有测量结果,分别进行了偏心角度ά (见图1 )约00和风速(归一,以10米高) ,6至10米/秒.仿真人做的失调角的00和风速接近平均实验风速.
在总体上是一个很好的定性协议是转播服务之间的实验和模拟.由于在实验中,模拟源地图显示显性噪声辐射外部分的叶片,在其向下运动.类似的频率,这可以归功于以瘦,尾缘边界层在更高的半径.在某些情况下,甚至轻微的副作用,叶(如围绕" 11时为400-500赫兹在葛结果) ,这是一种伪的数组方法,是转载于模拟.很明显,小实验噪音来源,在吊篮和塔,则不予转载在模拟演习中,因为这些都不是模拟在尾缘噪声预测模型.
为gamesa汽轮机,模拟源半径似乎稍微高于在实验中.这可能是由于这一事实,即测量转子有一个摔了,其中一个干净,其中未经处理的叶片,而他的模拟是做清洁的刀片.跳闸成果在厚尾缘边界层,使该尾缘噪声在某一半径转向较低频率.
1年前
沉醉梦 共回答了4个问题 | 采纳率
n 这一个区段模拟将会被与实验的结果相较。这一个评估将会根据如一个转子力量 (第 4,3 节) 的功能转子飞机 (第 4,1 节) ,转子噪音频谱 (第 4,2 节) 的噪音来源分配 , 和全部的噪音水平被订定。
为两者的涡轮标准的而且模拟来源地图在图 3 中被显示到图 6 。 注意这些来源地图符合逆风的测量在地面上的位置。 颜色刻度的范围总是 12个分贝,而且最大值被为每个个别的频率乐...
1年前
阿枫cn 共回答了8个问题 | 采纳率
在这一节中的模拟,将比较实验结果。这项评估将在条件的噪声源分布在旋翼飞机(第4,1) ,转子噪声谱(第4,2) ,以及整体噪音水平作为一个函数的转子功率(第4,3) 。
实测和模拟源地图,为轮机如图3所示,以图6 。注意的是,这些地图的来源,对应到上风处测量位置在地面上。范围颜色的规模是历来12分贝,并把最高的是调整为每频段。实验源地图平均每场超过所有测量结果,分别进行了偏心角度 (见图...
1年前

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