A nacelle (2) of an aircraft engine (3) comprises an anti-icing protection system (1), and the nacelle (2) comprises an inner shroud (5), and an air inlet lip (7) forming a leading edge of the nacelle(2); the protection system comprises a heat exchanger arrangement (11) comprising at least one heat pipe (12) configured for transferring heat (14) emitted by a heat source to the inner shroud (5).
一种包括防冰保护系统(1)的飞行器发动机(3)的短舱(2),所述短舱(2)包括内护罩(5)、形成所述短舱(2)的前缘的进气口唇缘(7),所述保护系统包括热交换器装置(11),所述热交换器装置包括至少一个热管(12),所述至少一个热管被配置成用于将热源所发射的热量(14)传递至所述内护罩(5)。
AIRCRAFT ENGINE NACELLE COMPRISING ICE PROTECTION SYSTEM
包括防冰保护系统的飞行器发动机的短舱
2020-04-28
Patent
Elektronische Ressource
Chinesisch
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |
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