Turbine engine comprising improved harness support means
An aircraft turbine engine with a main axis includes: an arm that is radial with respect to the main axis, extending through an air flow duct; a support wall belonging to the radial arm and which has two openings; a plurality of electric harnesses extending partially through the radial arm and for which a section of each harness is secured to the support wall of the arm; and two mounting blocks, in which each mounting block is associated with a group of sections of harness.
1. An aircraft turbine engine with a main axis comprising:
an arm that is radial with respect to the main axis extending throughout an air flow duct;
a support wall belonging to the radial arm and which includes two openings;
a plurality of harnesses partially extending throughout the radial arm and a section of each harness of which is fastened to said support wall of the arm; and
two mounting blocks, each mounting block of the two mounting blocks is associated with a group of sections of the harnesses.
2. The aircraft turbine engine according to claim 1 , further comprising means for fastening a mounting block on the support wall which are independent of the means for fastening the other block of mounting on the support wall.
3. The aircraft turbine engine according to claim 1 , wherein each mounting block is fastened to the support wall by bolting.
4. The aircraft turbine engine according to claim 1 , wherein each mounting block includes a body which is connected to the support wall and a barrel which receives an associated section of the harness.
5. The aircraft turbine engine according to claim 4 , wherein the body includes a face which is in contact with the support wall and includes a shoulder projecting with respect to said face of the body, a section of the shoulder being complementary with said opening.
6. The aircraft turbine engine according to claim 5 , wherein the support wall extends in a plane substantially perpendicular to a direction that is radial with respect to the main axis of the aircraft turbine engine, and
wherein said face of the body is fastened to a face of the support wall which is radially external with respect to the main axis of the aircraft turbine engine.
7. The aircraft turbine engine according to claim 1 , wherein each mounting block includes two portions mounted on either side of the sections of the harnesses with which the mounting block is associated.
8. The aircraft turbine engine according to claim 7 , wherein the two portions of each mounting block are connected with the associated sections of the harnesses before assembly of the mounting block on the support wall.
9. The aircraft turbine engine according to claim 8 , wherein the body includes a face which is in contact with the support wall and includes a shoulder projecting with respect to said face of the body, a section of the shoulder being complementary with an opening, and
wherein each portion of the mounting block includes a portion of each barrel of said mounting block.
10. The aircraft turbine engine according to claim 9 , wherein the radial arm is located at a lower vertical portion of the aircraft turbine engine.