Turbomachine auxiliary lead-through device
Auxiliary lead-through device for a turbomachine, including two coaxial annular shell rings, respectively an inner and an outer one, between which there extend radial arms, through at least one of which auxiliaries ( 20 ) are led through. An auxiliary retention unit is housed inside the arm, on one wall, the arm includes an aperture that can be closed off by a cover that is attached and fixed to the arm. The retention unit includes at least one first member fixed to the internal surface of the arm and at least one second member fixed to the internal surface of the cover. The fixing of the cover to the arm causes the auxiliaries to be clamped and retained between the first and second members.
1. A device for leading through auxiliary systems for a turbine engine, comprising two respectively inner and outer coaxial annular collars, between which radial arms extend, and supports for supporting said auxiliary systems,
wherein at least one radial arm of said radial arms is used for leading through said auxiliary systems, and said supports for supporting said auxiliary systems are housed within said at least one radial arm,
wherein said at least one radial arm comprises at least a first wall and a second wall and one of said first and second walls includes a window covered by a cowl,
wherein the supports for supporting said auxiliary systems comprise at least one first supporting member that is fastened to an inner surface of said at least one radial arm and at least one second supporting member that is fastened to an inner surface of the cowl,
wherein the cowl is fastened to said at least one radial arm causing said auxiliary systems to be clamped and supported between said at least one first supporting member and said at least one second supporting member.
2. The device according to claim 1 , wherein, for each radial arm of the at least one radial arm, the window is formed on the first wall of said radial arm and the first supporting member is fastened to the inner surface of the second wall of said at least one radial arm, substantially opposite the window.
3. The device according to claim 1 , wherein, for each radial arm of the at least one radial arm, the window is located on a middle portion of said radial arm.
4. The device according to claim 1 , wherein, for each radial arm of the at least one radial arm, the window is parallelepiped in shape and is delimited by peripheral edges of said radial arm that are radially inner, radially outer, upstream and downstream respectively.
5. The device according to claim 1 , wherein, for each radial arm of the at least one radial arm, each said at least first supporting member and each said at least second supporting member comprises cavities that are complementary to parts of the auxiliary systems, wherein said parts of the auxiliary systems fit in the cavities.
6. The device according to claim 5 , wherein, for each radial arm of the at least one radial arm, each said at least first supporting member and each said at least second supporting member comprises a block of material in which the cavities are formed.
7. The turbine engine, comprising at least one device according to claim 1 .
8. The turbine engine according to claim 7 wherein the turbine engine is a turbojet engine for an airplane.
9. The turbine engine according to claim 7 wherein the turbine engine is a turboprop engine for an airplane.
10. A method for mounting a device according to claim 1 , comprising the steps of:
mounting said at least one radial arm intended for leading through said auxiliary systems between the inner and outer collars by moving said at least one radial arm in translation along a longitudinal axis of the turbine engine, said first supporting member, which is supported by the said at least one radial arm, extending on one side of said auxiliary systems,
closing the window on said at least one radial arm by means of the cowl, said second supporting member, which is supported by the cowl, extending on a side of said auxiliary systems opposite said one side of the auxiliary systems, and
fastening the cowl to said at least one radial arm such that said auxiliary systems are clamped and supported between the first supporting member and the second supporting member.
11. A radial arm of a device for leading through auxiliary systems of a turbine engine, wherein said radial arm comprises:
first and second walls,
a window on one of said first and second walls, said window that is covered by a cowl that is attached to the one of said first and second walls,
at least a first supporting member for supporting said auxiliary systems that is attached to an inner surface of said radial arm and;
a second supporting member that supports said auxiliary systems and is attached to an inner surface of the cowl, wherein the attachment of the cowl to said radial arm causes the auxiliary systems to be clamped and supported between the first and second supporting members.
12. The radial arm according to claim 11 , wherein said radial arm is substantially dihedral and the first and the second walls and connected by downstream edges thereof, the window being formed on a middle portion of the one of the first and the second walls and being spaced apart from each of upstream edges, the downstream edges, radially inner edges and radially outer edges of the one of the first and second walls.