| 摘要 |
<p>An intermediate casing for a turbojet fan compartment, including: a shroud centered along a longitudinal axis of the turbine engine; an annular cheek plate centered along the longitudinal axis of the turbine engine and mounted against a downstream face of the shroud; a suspension beam fastened to the cheek plate and extending downstream parallel to the longitudinal axis of the turbine engine; and an AGB suspended from the beam and including an upstream side face spaced apart axially from the cheek plate, a downstream side face opposite the upstream side face, and a plurality of accessories mounted against its downstream side face and distributed about the longitudinal axis of the turbine engine.</p> |
