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Experimental study of icing accretion on a rotating conical spinner

机译:旋转圆锥形旋转器上积冰的实验研究

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摘要

A reduced scale experiment has been conducted to investigate the icing accretion procedure on a rotating spinner of 60° cone angle. The experiment was carried out in a small scale ice wind tunnel with three different rotating speeds of the spinner. The experimental conditions were determined from the actual icing condition of the spinner of a turbofan engine by using the similarity theory, which considers the rotating effects. The ice thickness on the spinner was got from the image taken by the high speed camera, by image processing. The results of this investigation show that under the experimental condition, ice on the spinner’s tip of three different rotating speeds are all glaze ice and about the same thick. However, on the downstream surface of the spinner, ice shape on the rotating spinner is different from that on the stationary spinner. It is uneven glaze ice on the stationary spinner while it is ‘particle ice’ when the rotating speed is 8240 rpm and it is ‘needle ice’ when the rotating speed is 15,200 rpm. The experiment also reveals that when the rotating speed is higher, the ice layer is thicker.
机译:进行了缩小规模的实验,以研究锥角为60°的旋转旋转器上的结冰过程。实验是在小型冰风洞中进行的,旋转器具有三种不同的转速。实验条件是根据涡轮风扇发动机旋转器的实际结冰条件,利用相似性理论确定的,其中考虑了旋转效应。旋转器上的冰厚通过图像处理从高速相机拍摄的图像中得出。这项调查的结果表明,在实验条件下,三种不同转速的旋转器尖端上的冰都是釉冰,并且厚度大致相同。然而,在旋转器的下游表面上,旋转旋转器上的冰形状不同于固定旋转器上的冰形状。它是固定旋转器上不均匀的釉冰,而转速为8240 rpm时为“颗粒冰”,而转速为15200 rpm时为“针冰”。实验还表明,转速越高,冰层越厚。

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  • 来源
    《Heat and Mass Transfer》 |2015年第12期|1717-1729|共13页
  • 作者单位

    College of Energy and Power Engineering Nanjing University of Aeronautics and Astronautics">(1);

    College of Energy and Power Engineering Nanjing University of Aeronautics and Astronautics">(1);

    College of Energy and Power Engineering Nanjing University of Aeronautics and Astronautics">(1);

    College of Energy and Power Engineering Nanjing University of Aeronautics and Astronautics">(1);

    College of Energy and Power Engineering Nanjing University of Aeronautics and Astronautics">(1);

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