A single-hole impingement heat transfer structure of an arc-guided aero-engine cap

Abstract

The invention discloses a single-hole impingement heat transfer structure of an arc diversion type aero-engine cap, in which an arc-shaped deflector structure is arranged on the impingement hole plate on the side of the impact inner cavity; It is composed of two layers of thin walls inside and outside, and a heat exchange channel is formed in the middle of the two layers of thin walls. The hot gas introduced from the compressor is injected from the impact hole and flows through the impact orifice plate with arc-shaped deflector to the inner cavity area of ​​the leading edge. Impact to the wall of the front edge of the cap, flow in the circumferential direction of the wall of the front edge through the hot gas passage, and flow out from the annular outlet of the hot gas. The impact heat exchange structure squeezes the tumbling flow field formed in the inner cavity of the front edge of the cap forward through the forward-protruding arc-shaped deflector, so that the flow velocity of the airflow impacting the wall of the front edge area is higher, thereby improving the cap. Impulse heat transfer performance in the wall region of the front edge of the shroud. The deflector can improve the impact heat transfer performance of the wall area of ​​the front edge of the cowling, and has good processing implementation, and can be applied to various aero-engine cowling cowlings.

Description

technical field [0001] The invention relates to an anti-icing technology of an engine cowl, in particular to a single-hole impingement heat exchange structure of an arc-guided aero-engine cowl. Background technique [0002] When the aircraft flies through the low-temperature atmospheric cloud layer with supercooled water droplets, ice crystals, freezing rain and snowfall, many parts such as the leading edge of the wing and empennage, windshield glass, leading edge of the air inlet, and the support plate of the engine air intake part, rectification Covers, etc. will generate ice accumulation. Icing occurs when insufficient anti-icing measures are implemented for engine inlet components. The generation of ice accretion will cause serious damage to the engine, not only hinder the normal operation of the engine, but also cause serious damage to the engine. Therefore, the anti-icing device of the engine is an important part of ensuring the safe flight of the aircraft. [0003] ...

AI Technical Summary

Problems solved by technology

Although there is a large demand for anti-icing heat per unit area in the front edge area in this structure, the impact heat exchange structure is applied, but there is a large cavity between the impact hole and the impact heat exchange area, which will make the impact of hot air The speed is reduced, which in turn reduces the convective heat transfer intensity at the front edge of the cowl and the utilization efficiency of hot gas

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