초록 ▼

A device for positioning and maintaining electric harnesses on the casing of a turbo-jet engine includes harness supports standardized for directions substantially perpendicular to the axis of the turbojet engine and harness supports standardized for directions substantially parallel to the axis of

A device for positioning and maintaining electric harnesses on the casing of a turbo-jet engine includes harness supports standardized for directions substantially perpendicular to the axis of the turbojet engine and harness supports standardized for directions substantially parallel to the axis of the turbo-jet engine.

대표청구항 ▼

The invention claimed is: 1. A turbo-jet engine, said turbo-jet engine comprising: at least a casing, forming a peripheral envelop around a longitudinal axis of the turbo-jet engine, a duct mounted on the casing of the turbo-jet engine, electric harnesses laid out at the periphery of the casing, sa

The invention claimed is: 1. A turbo-jet engine, said turbo-jet engine comprising: at least a casing, forming a peripheral envelop around a longitudinal axis of the turbo-jet engine, a duct mounted on the casing of the turbo-jet engine, electric harnesses laid out at the periphery of the casing, said electrical harnesses including at least a first electrical harness, a second electrical harness and a third electrical harness, each of said first, second and third electrical harnesses having a conducting wire inserted in an insulating material, and a device for positioning and maintaining the electric harnesses on the casing of said turbo-jet engine, wherein the device comprises harness supports standardized for directions substantially perpendicular to the longitudinal axis of the turbo-jet engine and harness supports standardized for directions substantially parallel to the longitudinal axis of the turbo-jet engine, wherein each of said harness supports standardized for directions substantially perpendicular to the longitudinal axis of the turbo-jet engine comprises a body defining a plurality of perpendicular housings that each extend substantially perpendicular to the longitudinal axis of said turbo-jet engine, said plurality of perpendicular housings including at least a first perpendicular housing, a second perpendicular housing and a third perpendicular housing, wherein said first electrical harness is received in said first perpendicular housing, said second electrical harness is received in said second perpendicular housing and said third electrical harness is received in said third perpendicular housing, wherein said first, second and third perpendicular housings extend within a same plane and are aligned with each other, wherein each of said harness supports standardized for directions substantially parallel to the longitudinal axis of the turbo-jet engine comprises a cylindrical body defining a plurality of parallel housings that each extend substantially parallel to the longitudinal axis of the turbo-jet engine, each parallel housing being positioned at a periphery of said cylindrical body and around a central core of said cylindrical body, said plurality of parallel housings including at least a first parallel housing, a second parallel housing and a third parallel housing, wherein said first electrical harness is received in said first parallel housing, said second electrical harness is received in said second parallel housing and said third electrical harness is received in said third parallel housing such that said first, second and third electric harnesses are positioned around said central core, wherein the cylindrical body includes a central bore that extends through said central core substantially parallel to the longitudinal axis of the turbo-jet engine, and wherein at least one of said harness supports standardized for directions substantially parallel to the longitudinal axis of the turbo-jet engine is mounted on said duct at said central bore such that said duct passes through said central bore. 2. A device according to claim 1, wherein the body defining a plurality of perpendicular housings of at least one of the harness supports standardized for directions substantially perpendicular to the longitudinal axis of the turbo-jet engine includes at least one elongated lug that includes said plurality of perpendicular housings. 3. A device according to claim 2, wherein the lug is at least partially composed of plastic material. 4. A device according to claim 2, wherein the lug includes a means for attachment to a flange of the casing of the turbo-jet engine. 5. A device according to claim 1, wherein the cylindrical body defining a plurality of parallel housings of at least one of the harness supports standardized for directions substantially parallel to the axis of the engine comprises at least one cylindrical barrel that includes said plurality of parallel housings. 6. A device according to claim 5, wherein the barrel is at least partially composed of plastic material. 7. A device according to claim 5, wherein the at least one cylindrical barrel includes a means for attachment to the duct. 8. A device according to claim 7, wherein the duct includes at least one ring that supports the at least one barrel. 9. A device according to claim 7, wherein the duct is a dummy duct. 10. A device according to claim 5, wherein said central bore includes a radial recess extending from a center of said cylindrical body to a periphery of said cylindrical body. 11. A device according to claim 10, wherein said radial recess delineates two fastening tabs. 12. A device according to claim 11, wherein said cylindrical body defines said plurality of parallel housings at said periphery of said cylindrical body, each of said housings being configured to receive a harness. 13. A device according to claim 12, wherein at least two of said plurality of parallel housings are diametrically opposed to each other relative to said central bore. 14. A device according to claim 1, wherein the harness supports standardized for directions substantially perpendicular to the axis of the engine and the harness supports standardized for directions substantially parallel to the axis of the engine are attached by screw-nut systems. 15. A device according to claim 1, wherein the harness supports standardized for directions substantially perpendicular to the axis of the engine and the harness supports standardized for directions substantially parallel to the axis of the engine are attached by quick-release fastening systems. 16. A device according to claim 1, wherein at least two of said perpendicular housings defined in said body of said harness supports standardized for directions substantially perpendicular to the longitudinal axis of the turbo-jet engine have different sizes with respect to each other, and wherein at least two of said parallel housings defined in said body of said harness supports standardized for directions substantially parallel to the longitudinal axis of the turbo-jet engine have different sizes with respect to each other. 17. A device according to claim 1, wherein said first, second and third perpendicular housings are arrayed in a single row. 18. A device according to claim 1, wherein each parallel housing is positioned circumferentially around said central core of said cylindrical body, and said first, second and third electric harnesses are positioned circumferentially around said central core. 19. A device according to claim 1, wherein said at least one of said harness supports standardized for directions substantially parallel to the longitudinal axis of the turbo-jet engine is mounted on said duct such that said first, second, and third electric harnesses are positioned circumferentially around said duct.