Gas film ice prevention structure of leading edge of nacelle of airplane

Abstract

The invention discloses a gas film ice prevention structure of the leading edge of a nacelle of an airplane. The structure comprises a nacelle outer wall, an annular hot gas pipe and a support plate, wherein the annular hot gas pipe is positioned in an ice prevention cavity formed by the nacelle outer wall and the support plate; the two ends of the support plate are fixedly connected with the nacelle outer wall; one side of the annular hot gas pipe close to the top of the leading edge of the nacelle outer wall is provided with an outflow hole; and the nacelle outer wall is provided with a gas film hole. By using a proactive protection strategy and introducing air through the gas film hole on an outer wall surface to quickly form hot coverage of high-temperature gas on the frozen surface, the gas film ice prevention structure has great advantages in the aspect of ice prevention timeliness; and by forming the outflow hole at the front end of the annular hot gas pipe, the head loss of hot gas in the annular hot gas pipe can be reduced, strong impact heat exchange can also be performed on an inner wall surface and heat utilization rate is improved.

Description

technical field [0001] The invention belongs to the technical field of aviation, and in particular relates to an anti-icing structure of an anti-icing system for an aircraft nacelle leading edge. Background technique [0002] When the aircraft passes through clouds with supercooled water droplets or works on the ground with freezing fog, the leading edge of the nacelle where the engine is loaded will freeze. If these places are frozen, the air flow through the engine will be greatly restricted, causing The loss of engine performance may cause the engine to fail. In addition, the falling ice may cause damage when it is sucked into the engine or hits the sound-absorbing material lining of the air inlet. Therefore, the anti-icing design of the leading edge of the nacelle is necessary. The front edge of the nacelle of the aircraft is generally anti-iced by hot air. The first reason is that the hot air source of the engine is very close. The second is that the anti-icing effect i...

AI Technical Summary

Problems solved by technology

[0004] In view of the fact that the traditional hot gas anti-icing mainly relies on the heat conduction of the wall surface, we know that heat conduction is a relatively low-level heat transfer method in heat transfer, and there are two main problems in the application here: the first heat conduction The transmission speed is very slow, that is to say, the timeliness of the outer wall surface reaching the anti-icing temperature is poor; second, in this anti-icing method, the hot air only completes its mission through the heat exchange of the inner wall surface, resulting in a lot of potential for hot air waste of energy, which in turn affects the thermal efficiency of the engine, thereby affecting the performance of the entire aircraft

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