The invention provides an aero-engine compartment accessory cooling protection structure and an optimization method thereof. The cooling protection structure comprises an air inlet pipe and a protection cover. The size of the protective cover is larger than that of the sensor accessory, the protective cover covers the sensor accessory and is used for protecting the sensor accessory to separate the sensor accessory from a high-temperature environment in an engine compartment on the premise that normal work of the sensor accessory is not affected, and a cooling air outlet is formed in the bottom of the protective cover and used for cooling the sensor accessory. The cooling gas outlet is in a slot shape; one end of the air inlet pipe is a cold air inlet used for introducing cold air, the other end of the air inlet pipe extends into the protective cover, a plurality of air outlet holes are formed in the air inlet pipe extending into the protective cover, and the air outlet holes face the sensor accessory and are used for carrying out impact cooling on the sensor accessory. Precise cooling of a single accessory in the engine compartment can be achieved, the using amount of cooling gas is saved, and the cooling requirement can be met.
本申请提供了一种航空发动机舱附件冷却防护结构及其优化方法,所述冷却防护结构包括:进气管和防护罩;所述防护罩尺寸大于传感器附件且所述防护罩覆盖在所述传感器附件上,用于在不影响传感器附件正常工作的前提下,将传感器附件防护起来而使传感器附件与发动机舱内的高温环境分隔开,所述防护罩底部设有冷却气出口,所述冷却气出口的形状为条缝状;所述进气管一端为冷气进口,用于引入冷气,所述进气管的另一端伸入至防护罩内,且伸入至防护罩内的进气管设有多个出气孔,所述出气孔面对传感器附件,用于对传感器附件进行冲击冷却。本申请可以实现发动机舱内单个附件的精准冷却,即节省冷却气用量,又能达到冷却需求。
Aero-engine compartment accessory cooling protection structure and optimization method thereof
一种航空发动机舱附件冷却防护结构及其优化方法
2023-09-22
Patent
Elektronische Ressource
Chinesisch
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