The invention provides a ventilation and heat dissipation device of a nacelle core cabin, a control method and an aero-engine. The ventilation and heat dissipation device of the nacelle core cabin comprises an air entraining main pipe, a multi-way valve, a plurality of air entraining branch pipes and a heat insulation flow guide structure. One end of the air entraining main pipe introduces outer culvert air from the outside of the core cabin cover and communicates with the multiple air entraining branch pipes through the multi-way valve. The multi-way valve is used for controlling connection and disconnection of the air entraining main pipe and the air entraining branch pipes. The heat insulation flow guide structure wraps the engine case, on one hand, heat radiation of the engine case to the interior of the core cabin space can be isolated, and on the other hand, the heat insulation flow guide structure is further provided with a first flow channel arranged around the gas compressor section, a second flow channel arranged around the combustion chamber section and a third flow channel arranged around the turbine section. And the first flow channel, the second flow channel and the third flow channel communicate with the multi-way valve through air entraining branch pipes correspondingly, and therefore the air compressor section, the combustion chamber section and the turbine section are cooled in a targeted mode through introduced outer culvert air.
本发明提供了一种短舱核心机舱的通风散热装置、控制方法及航空发动机,该短舱核心机舱的通风散热装置包括引气主管、多通阀、多个引气支管以及隔热导流结构。引气主管的一端从核心机舱罩外引入外涵气体,并通过多通阀与多个引气支管连通。多通阀用于控制引气主管与引气支管的通断。隔热导流结构包裹发动机机匣,一方面可以隔离发动机机匣对核心机舱空间内的热辐射,另一方面,还具有围绕压气机段设置的第一流道,围绕燃烧室段设置的第二流道及围绕涡轮段设置的第三流道,第一流道、第二流道和第三流道分别通过一引气支管与多通阀连通,从而通过引入的外涵气体针对性的对压气机段、燃烧室段以及涡轮段进行冷却降温。
Ventilation and heat dissipation device of nacelle core cabin, control method and aero-engine
短舱核心机舱的通风散热装置、控制方法及航空发动机
2025-01-07
Patent
Electronic Resource
Chinese
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