Aircraft engine annular shroud comprising an opening for the insertion of blades

1. An aircraft engine annular shroud, comprising:

on its internal surface, a peripheral annular groove able to accept a plurality of blade roots;

an insertion opening for inserting the blade roots into the annular groove;

a closure device constructed and arranged to close off the insertion opening,

wherein the closure device comprises:

a lock blade, said lock blade comprising a projecting part able to pass through an opening formed in the insertion opening, and

a fastener able to be fixed on the projecting part of the lock blade.

2. The annular shroud according to claim 1 , wherein the insertion opening is arranged on the annular groove.

3. The annular shroud according to claim 1 , wherein the insertion opening does not pass through the annular shroud and wherein the annular shroud further comprises two notches arranged on either side of the annular groove.

4. The annular shroud according to claim 1 , wherein the projecting part is formed by a screw, and wherein the fastener is formed by a nut.

5. An aircraft engine downstream guide vane comprising an annular shroud according to claim 1 .

6. A method of mounting blades on an aircraft engine annular shroud according to claim 1 , said method comprising:

inserting a blade into the insertion opening;

sliding of the blade root in the annular groove;

closing the insertion opening.

7. The method of mounting blades on an aircraft engine annular shroud according to claim 6 , wherein the insertion opening is in the form:

of two notches arranged on either side of the annular groove.

8. An aircraft engine annular shroud comprising:

an external and an internal surface;

a peripheral annular groove formed in the internal surface and configured to receive a plurality of blade roots;

an aperture formed in the peripheral annular groove and extending through the annular shroud so that said aperture has a first opening formed on the external surface and a second opening formed in the internal surface, the second opening having a lateral dimension larger than a lateral dimension of the annular groove so that blade roots are slidable into the annular groove after being received in the aperture;

a cover configured to close the aperture, and

a fastener constructed and arranged to maintain the cover on the aperture.

9. An aircraft engine annular shroud comprising:

an external and an internal surface;

a peripheral annular groove formed in the internal surface and configured to receive a plurality of blade roots;

an aperture formed in the peripheral annular groove and extending through the annular shroud so that said aperture has a first opening formed on the external surface and a second opening formed on the internal surface, the aperture configured to receive the blade roots so that the blade roots are slidable into the annular groove after being received in the aperture;

a cover configured to close the aperture, and

a fastener constructed and arranged to maintain the cover on the aperture.

10. The annular shroud according to claim 9 , wherein the fastener includes a plurality of fastening elements, which are screws.

11. An aircraft engine downstream guide vane comprising an annular shroud according to claim 9 .

12. A method of mounting blades on an aircraft engine annular shroud according to claim 9 , said method comprising:

inserting a blade into the aperture;

sliding of the blade root in the annular groove;

closing the aperture with the cover.