| 摘要 |
A support arm ( 13 ) is intended to be installed in a radial position in an afterburner device of a bypass turbojet. The device comprises first and second inner annular casings defining a passage for a primary flow and an outer annular casing defining together with the first inner annular casing a passage for a secondary flow. The arm ( 13 ) comprises a monobloc structure made of composite material including two integral walls ( 14, 15 ), on the one hand, designed to define a groove ( 16 ) having a substantially V-shaped profile and, on the other hand, including first end parts ( 17 ) joined together and adapted to define a foot ( 18 ) and second end parts ( 19 ) adapted each to define at least one flange ( 20, 21 ) intended to be positively connected to the outer annular casing.
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