Turbine engine comprising an upstream attachment means for a de-oiling pipe

1. A turbine engine in which an air flow circulates from upstream to downstream for an aircraft, comprising:

a rotary shaft extending axially and a de-oiling tube mounted to be rigidly connected to and on an inside of the rotary shaft by upstream fixing means;

the upstream fixing means comprising:

a first inner dog clutch extending on an inside from the rotary shaft,

a second dog clutch extending on an outside from the de-oiling tube, which is longitudinally aligned with the first inner dog clutch and positioned downstream of the first inner dog clutch,

an anti-rotation longitudinal locking latch extending between the rotary shaft and the de-oiling tube to prohibit rotation of the second dog clutch of the de-oiling tube relative to the first inner dog clutch of the rotary shaft, and

an axial locking ring, which is mounted between the de-oiling tube and the anti-rotation longitudinal locking latch, to prohibit axial displacement of the anti-rotation longitudinal locking latch relative to the rotary shaft.

2. A turbine engine according to claim 1 , wherein the anti-rotation longitudinal locking latch comprises an annular body.

3. A turbine engine according to claim 2 , wherein the anti-rotation longitudinal locking latch comprises at least one axial tab extending between two consecutive teeth of the first inner dog clutch and between two consecutive teeth of the second outer dog clutch.

4. A turbine engine according to claim 1 , wherein the de-oiling tube comprises an annular compartment in which the axial locking ring is mounted.

5. A turbine engine according to claim 1 , wherein the anti-rotation longitudinal locking latch comprises an annular groove configured to be in contact with the axial locking ring.

6. A turbine engine according to claim 1 , wherein the axial locking ring is resilient.

7. A turbine engine according to claim 1 , wherein the anti-rotation longitudinal locking latch comprises a radial demounting opening configured to allow a demounting tool to be inserted into the radial demounting opening from an upstream direction.

8. A turbine engine according to claim 1 , wherein the turbine engine comprises an annular cover plate that covers upstream ends of the de-oiling tube and of the rotary shaft.

9. A method for fixing a de-oiling tube in a rotary shaft of a turbine engine in which an air flow circulates from upstream to downstream for an aircraft, the rotary shaft including a first inner dog clutch extending on an inside, the de-oiling tube including a second dog clutch extending on an outside, the method comprising:

inserting the de-oiling tube into the rotary shaft from an upstream direction;

angularly orienting the de-oiling tube such that the second dog clutch is not longitudinally aligned with the first inner dog clutch;

axial displacement of the de-oiling tube in a downstream direction such that the second dog clutch is positioned downstream of the first inner dog clutch;

angularly orienting the de-oiling tube such that the second dog clutch is longitudinally aligned with the first inner dog clutch;

inserting an anti-rotation longitudinal locking latch between the rotary shaft and the de-oiling tube to prohibit rotation of the second dog clutch of the de-oiling tube relative to the first inner dog clutch of the rotary shaft; and

inserting an axial locking ring between the de-oiling tube and the anti-rotation longitudinal locking latch to prohibit axial displacement of the anti-rotation longitudinal locking latch relative to the rotary shaft.