The invention belongs to the design field of helicopter air inlet channel anti-icing, and relates to a helicopter air inlet channel hot air anti-icing system with adjustable flow, which comprises an air inlet channel skin, a heat preservation skin, a multiple bulkhead, a flow control valve, an atmospheric temperature sensor, a control device and an air supply pipeline. The flow of hot air entering the anti-icing cavity can be automatically adjusted according to the environment temperature, and heat waste is avoided under the condition that the anti-icing requirement is met. Hot air in the anti-icing cavity of the air inlet channel flows from back to front, and the influence on air inlet distortion of the engine can be effectively reduced. Hot air in the anti-icing cavity is distributed through the multiple partition frames, the height of the anti-icing cavity can be reduced to 5-15 mm, and the heat exchange efficiency is improved. The heat insulation layer is wrapped on the heat insulation skin of the air inlet channel, so that heat loss can be effectively reduced.
本发明属于直升机进气道防冰的设计领域,涉及一种可调流量的直升机进气道热气防冰系统,所述直升机进气道防冰系统包括:进气道蒙皮、保温蒙皮、多重隔框、流量控制阀、大气温度传感器、控制装置和供气管路。可以根据环境温度,自动调节进入防冰腔的热空气流量,在满足防冰需求的情况下避免热量浪费。进气道防冰腔内的热空气从后向前流动,可以有效减少对发动机进气畸变的影响。采用多重隔框对防冰腔的热空气进行分配,可以将防冰腔的高度降低至5~15mm,提高换热效率。在进气道保温蒙皮上包裹保温层,可以有效减少热量散失。
Helicopter air inlet channel hot air anti-icing system capable of adjusting flow
一种可调流量的直升机进气道热气防冰系统
2023-06-27
Patent
Electronic Resource
Chinese
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
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