Abstract The experiment method for studying the hot air antiicing system of inlet guide vane was introduced. Some antiicing tests were performed in different external icing flow conditions. In experiments, the blade surface temperature change was measured by thermalcouples thermal couple and the experiment process was recorded by an image recording system. The experiment results show that the ice accretion is located at the leading edge and suction side, and the guide vane internal hot air channel should be designed efficiently in the hot air antiicing system to improve antiicing performance.
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Received: 25 September 2009
Published: 30 November 2010
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