Device for supporting and housing auxiliaries in a bypass turbojet

1. A device for supporting and housing auxiliaries in a bypass turbojet, comprising:

a first coaxial case ring and a second coaxial case ring, the first coaxial case ring is arranged inside the second coaxial case ring; and

tubular radial arms which connect the first coaxial case ring and the second coaxial case ring, through which tubular radial arms fluid ducts and electric cables pass, a first tubular radial arm and a second tubular radial arm extending substantially in a vertical plane, the first radial arm being disposed above the second radial arm,

wherein a lateral face of the first radial arm comprises a first detachable panel whose removal allows access to turbojet equipment situated radially inside the first case ring in alignment with the radial arm, the first detachable panel includes a radial portion fastened to the first radial arm and a cylindrical portion connected to the first case ring, and

wherein a first portion of a fluid duct extends substantially radially inside the first radial arm and a second portion of the fluid duct extends substantially circumferentially inside the first case ring, a circumferential dimension of the second portion of the fluid duct is smaller than a circumferential dimension of the cylindrical portion of the first detachable panel.

2. The device as claimed in claim 1 , wherein the radial portion of the detachable panel is fastened by screws to the radial arm.

3. The device as claimed in claim 2 , wherein the radial portion of the detachable panel is placed and fastened, along at least one of its edges, on corresponding rims of the radial arm, and the cylindrical portion of the detachable panel is placed and fastened, along at least one of its edges, on corresponding rims of the first case ring.

4. The device as claimed in claim 1 , further comprising gaskets which are clamped between the detachable panel and at least one of the radial arm or the first case ring.

5. The device as claimed in claim 1 , wherein the fluid duct is a hot air circulation duct, a first end of the fluid duct opens into a compressor of the turbojet for bleeding air and a second end of the fluid duct is fastened to the second case ring and is connected to fluid circulation means.

6. The device as claimed in claim 5 , wherein the fluid duct includes a third portion which extends in an axial direction, a downstream end of the third portion is connected to a first elbow, the first elbow includes a flange which is fastened to the compressor, and an upstream end of the third portion is connected to a second elbow, the second elbow connects the upstream end of the third portion of the fluid duct to a downstream end of the second portion of the fluid duct.

7. The device as claimed in claim 6 , wherein the fluid duct includes a third elbow which connects an upstream end of the second portion of the fluid duct to a downstream end of the first portion of the fluid duct, an upstream end of the first portion of the fluid duct is the second end of the fluid duct and the fluid circulation means includes a conduit which feeds air to a nacelle of the turbojet.

8. The device as claimed in claim 1 , wherein the first detachable panel provides access to an equipment item situated inside the first case ring.

9. The device as claimed in claim 8 , wherein the equipment item accessible by removal of the detachable panel is an actuator for controlling variable-setting stators.

10. The device described in claim 1 , wherein the first detachable panel is substantially L-shaped and comprises a radial flat plate connected to a plate curved in a circular arc, this panel having a series of screw fitting holes along at least one of its longitudinal edges and along the terminating edge of the curved plate.

11. The device as claimed in claim 10 , wherein the first detachable panel comprises sealing gaskets along the edges of its radial and curved plates.

12. The device as claimed in claim 1 , wherein a lateral face of the second radial arm includes a detachable panel whose removal allows access to turbojet equipment situated radially inside the first case ring in alignment with the radial arm, the second detachable panel includes a radial portion fastened to the second radial arm and a cylindrical portion connected to the first case ring, and an oil duct passes inside the second radial arm.

13. The device as claimed in claim 12 , further comprising a third radial arm disposed between the first radial arm and the second radial arm and a fourth radial arm disposed opposite the third radial arm,

wherein electric cables pass inside the third radial arm and a fuel duct passes inside the fourth radial arm.

14. The device as claimed in claim 1 , wherein an air duct is mounted on the first radial arm, the air duct extends substantially parallel to an axis of the device, an upstream end of the air duct is connected to means for bleeding air from a bypass stream and a downstream end of the air duct is connected to air circulation means for cooling components of the turbojet and means for supplying air to a cockpit of an aircraft.