Hot air anti-icing structure of aero-engine rectifying support plate

Abstract

The invention discloses a hot air anti-icing structure of an aero-engine rectifying support plate. The hot air anti-icing structure comprises an anti-icing component, a hot air inlet is formed in the middle of the upper end surface of the anti-icing component and extends to the lower end of the anti-icing component along the uniform section in the spanwise direction of the rectifying support plate to form a hot air cavity; the anti-icing part is provided with a third hot air outlet along the lower end surface; a support plate front cavity is formed in the front end in the anti-icing part, and hot air flow in the hot air cavity is injected into the support plate front cavity in the tangential direction through the upper row of fine channels and flows into the rear end air collection cavity through the lower row of fine channels; the upper row of fine channels are a channel set which is uniformly arranged at intervals in the spanwise direction of the rectifying support plate, and the lower row of fine channels and the upper row of fine channels are correspondingly arranged according to a sequence or staggered arrangement mode; a plurality of splitter plates are arranged in the middle of the gas collecting cavity in the vertical direction, and a plurality of gas outlet holes are formed in the wall surfaces of the rear sections of the splitter plates; the supporting plate front cavity extends from the upper end face to the lower end face in the spanwise direction of the rectifying supporting plate, the upper end face forms a first hot air outlet, and the lower end face forms a second hot air outlet.

Description

technical field [0001] The invention relates to the technical field of aero-engine anti-icing, and mainly relates to a hot air anti-icing structure for a rectifying support plate of an aero-engine. Background technique [0002] When the aircraft is flying under low temperature, humidity and meteorological conditions containing supercooled water droplets, icing will occur in the intake components of the front end of the aircraft engine, and the fairing struts are more prone to icing. Ice accretion will reduce engine air intake, reduce thrust, and degrade engine air quality. Icing will seriously affect the safety of aircraft flight, so a safe and reliable anti-icing system is required. [0003] The anti-icing system of the engine rectifier support plate mainly adopts the hot gas anti-icing system. The anti-icing hot gas comes from the high pressure stage of the engine, and the amount of bleed air will seriously affect the thrust performance of the engine. With the increase o...

AI Technical Summary

Problems solved by technology

[0004] At present, the anti-icing structure is mainly a jet impingement-air film composite heat exchange structure, which has a good heat exchange effect, but for the load-bearing parts at the front end of the engine and the anti-icing parts with a large span span and small thickness, the leading edge wall Air film hole structure will lead to insufficient strength of anti-icing components

Secondly, due to the large span span, the temperature and flow of hot air at the upper end and the lower end differ greatly, which will lead to a large difference in surface temperature between the support plate and the lower end. Therefore, a more in-depth design of the anti-icing structure is required to meet the anti-icing requirements Under the premise of taking into account the strength of components and the uniformity of protection, etc.

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