Aero-engine rectification cover hood anti-icing device adopting loop type heat pipe and anti-icing method of aero-engine rectification cover hood anti-icing device

Abstract

The invention discloses an aero-engine rectification cover hood anti-icing device adopting a loop type heat pipe and belongs to the field of protection of aero-engines. The aero-engine rectification cover hood anti-icing device comprises a loop type axial rotary heat pipe, wherein the axial rotary heat pipe sequentially comprises a condensation section, a heat insulation section and an evaporation section from front to back; the front end of the condensation section is fitted to an aero-engine rectification cover hood; the inner diameter of the front part of the condensation section is greater than that of the back part of the condensation section; the inner diameter from the evaporation section to the heat insulation section is gradually reduced; the inner diameter of the heat insulation section is greater than the maximum inner diameter of the condensation section; a liquid reflowing channel is communicated between the condensation section and the heat insulation section; an inlet of the liquid reflowing channel is located at the condensation section and an outlet of the liquid reflowing channel is located at the heat insulation section; a heating device is mounted on the evaporation section. The loop type axial rotary heat pipe is integrated on the inner surface of the aero-engine rectification cover hood so that generated heat is efficiently and stably transmitted to the surface of the aero-engine rectification cover hood, and anti-icing of the aero-engine rectification cover hood is realized.

Description

technical field [0001] The invention relates to an anti-icing device for an aero-engine cowling cover, in particular to an aero-engine cowling anti-icing device and method using a loop-type heat pipe, belonging to the field of aero-engine protection. Background technique [0002] The icing phenomenon of aero-engine fairing cover seriously affects the normal performance of aero-engine, and even endangers the safety of aero-engine, causing aviation accidents. In order to prevent the aero-engine fairing cover from freezing during flight, it is usually necessary to heat it. The traditional hot gas anti-icing technology needs to bleed air from the compressor for anti-icing. This part of the consumed steam will affect the normal working efficiency of the engine. Moreover, its structure is complex, its stability is poor, and it increases the difficulty of daily maintenance. The electric heating anti-icing system currently used in part has a simple structure and convenient control,...

AI Technical Summary

Problems solved by technology

[0002] The icing phenomenon of the aero-engine fairing cover seriously affects the normal performance of the aero-engine, and even endangers the safety of the aero-engine, causing aviation accidents

In order to prevent the aero-engine fairing cover from freezing during flight, it is usually necessary to heat it. The traditional hot gas anti-icing technology needs to bleed air from the compressor for anti-icing. This part of the consumed steam will affect the normal working efficiency of the engine. Moreover, its structure is complex, its stability is poor, and it increases the difficulty of daily maintenance.

The electric heating anti-icing system currently used in part has a simple structure and convenient control, but it inevitably consumes a considerable amount of high-grade electric energy.

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