An assembly for an aircraft turbojet engine is described. The assembly includes a central gas-exhaust element and a connecting flange interposed between, upstream, a metallic outlet of a turbojet engine and, downstream, the central element. The connecting flange consists of an annular part and flexible lugs having axially: a first end where the lug is connected to the annular part, and a second free end, projecting radially outwards from the first end and towards which the lug is fixed with the central element.
Exhaust cone with flexible fitting
2022-12-06
Patent
Elektronische Ressource
Englisch
SAE Technical Papers | 2015
FITTING DESIGN STANDARD 24 DEGREE CONE
SAE Technical Papers | 1986