用于飞机发动机核心区降温的冷却系统和冷却方法

By introducing external gas into the aircraft engine through the gas outlet of the transient vent valve, and designing multiple connecting pipes and adapters, the problems of engine core area reheating and high-cost cooling equipment were solved, achieving efficient, fast, and low-cost cooling.

CN120798539BActive Publication Date: 2026-07-17COMMERCIAL AIRCRAFT CORP OF CHINA LTD +1
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Patent Information

Application Number
CN202511173736.3
Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
Filing Date
2025-08-20
Publication Date
2026-07-17
Estimated Expiration
2045-08-20

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Abstract

本发明提供了一种用于飞机发动机核心区降温的冷却系统和冷却方法。飞机发动机包括用于在飞机发动机在瞬态工况下对压气机工作状态进行调节的瞬态放气阀，冷却系统包括：风机，风机布置成向发动机的内部引入外界气体；连接管路，连接管路具有进气端和出气端，进气端连接到风机，由风机引入的气体通过进气端进入连接管路；以及适配器接头，适配器接头设置在连接管路的出气端，并且构造成能与瞬态放气阀的气路出口可拆卸地连接。根据本发明的冷却系统和冷却方法，冷却效率高，连接安装便捷，占用空间小，制造成本低，使用机动灵活。
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Citation Information

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