Cooling method and cooling device for engine core compartment

Abstract

The invention provides a cooling method and a cooling device for an engine core compartment. In this method, the cooling airflow of the fan compartment is introduced into the core compartment through secondary utilization, so that the cooling of the core compartment can be realized. In the state of the ground test vehicle, the ambient air flow enters the fan compartment from the exhaust port of the fan compartment through natural convection for ventilation and cooling, and finally exits from the intake port of the fan compartment. In other flight states, the ambient air flow enters from the air inlet of the fan cabin through ramming, and is divided into two streams to ventilate and cool the fan cabin. The cabin is ventilated and cooled, and at the same time, under the guidance of the draft tube, the local high temperature area in the cabin can be directional and concentrated cooling. In this way, the ventilation and cooling of the core cabin can be realized, the amount of bleed air in the flow channel of the outer culvert can be reduced, the loss of bleed air in the outer culvert can be reduced, and the secondary utilization of the ventilation and cooling airflow of the fan cabin can be realized at the same time.

Description

technical field [0001] The invention relates to a flight engine, in particular to a cooling method and a cooling device for a core compartment of an aircraft engine. Background technique [0002] The engine core compartment contains the engine core, the casing, and various engine accessories. When the engine is working, a large amount of heat is transferred to the core cabin through the casing. If the heat cannot be dissipated in time or quickly accumulated, the pipes and accessories in the cabin will not work properly, and even cause a fire. On the one hand, the ventilation and cooling system of the core cabin can cool down On the other hand, various accessories mounted on the engine case and the case itself can ensure the circulation of air inside the cabin, thereby preventing the accumulation of flammable gas in the cabin and eliminating fire hazards. Therefore, the ventilation and cooling technology of the core cabin is of great significance to ensure the normal operati...

AI Technical Summary

Problems solved by technology

[0004] However, for civil turbofan engines, the cooling airflow of the current core cabin ventilation and cooling technology comes from the outer clump, and the simple use of bleed air through the bleed hole has little effect on the aerodynamic performance of the outer clump, but it is difficult to meet the requirements of each pipeline in the high temperature and plateau takeoff state. For the temperature requirements of the accessories, only the bleed air of the wind bucket can meet the temperature requirements of the high-temperature plateau take-off state, but the aerodynamic performance of the external culvert is relatively large, and in the cruising state because the external ambient temperature is very low, it does not need a large amount of bleed air. Meet the temperature requirements of the accessories in the cabin, which causes redundant aerodynamic losses in the cruise state

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