Mounting an AGB on an intermediate casing for a turbojet fan compartment
View Patent ↗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.
1. An intermediate casing for a turbojet fan compartment, comprising:
a shroud centered along a longitudinal axis of a 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 accessory gearbox (AGB) suspended from the beam and comprising 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.
2. A casing according to claim 1 , wherein the AGB is fastened at one end to the beam and at its opposite end to a yoke that is fastened to the cheek plate,
the casing further comprising a fuel unit fastened at one end to the yoke of the cheek plate and at its opposite end to the beam.
3. A casing according to claim 2 , wherein the fuel unit comprises an upstream side face spaced apart axially from the cheek plate, a downstream side face opposite the upstream side face, and a plurality of pieces of fuel-handling equipment mounted against its downstream side face.
4. A casing according to claim 1 , wherein the AGB further comprises a transfer unit mounted against its upstream side face.
5. A casing according to claim 1 , further comprising at least one axial force take-up link fastened at one end to the cheek plate and at its opposite end to the upstream side face of the AGB.
6. A casing according to claim 1 , wherein the accessories comprise:
at least one electricity generator for supplying electrical power to the airplane;
an alternator for supplying electricity to electrical equipment of the turbine engine;
a starter for starting the turbine engine;
at least one hydraulic pump for supplying hydraulic power to the airplane;
a fuel pump; and
a lubricant pump.
7. A fan compartment for a turbojet comprising:
a containment casing centered on the longitudinal axis of the turbine engine; and
an intermediate casing according to claim 1 , the intermediate casing being fastened to the containment casing.
8. A turbojet comprising an intermediate casing according to claim 1 .