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本文主要针对民用飞机热气防冰系统机翼防冰腔进行了分析与研究,通过对流速、换热面积和结构影响等参数的分析,结合对现有民用飞机机翼防冰系统的调查,发现现有民用飞机采用微引射式——防冰前后两腔、前腔内布置分配管的型式;该型式防冰腔的换热效率与热气流流速、热气与蒙皮的接触面积等参数有关,并且防冰腔受到结构的约束。热气流速越大、热气与蒙皮的接触面积越大,换热效率越高。
This paper mainly analyzes and studies the wing anti-ice chamber of civil aircraft anti-ice system. Based on the analysis of parameters such as flow velocity, heat transfer area and structure influence, combined with the investigation of the anti-ice system of the existing civil aircraft wing, Existing civil aircraft using micro-injection - anti-ice before and after the two chambers, the former chamber layout of the distribution pipe type; the type of ice-proof chamber heat exchange efficiency and hot air flow velocity, hot air and skin contact area and other parameters , And the icebreaker is structurally restrained. The greater the hot gas flow rate, the greater the contact area between the hot gas and the skin, the higher the heat exchange efficiency.