Shell for aircraft turbo-engine stator with mechanical blade load transfer slits
View Patent ↗A shell of a stator for a module of an aircraft turbo-engine including a plurality of through openings each configured to house a stator blade, each opening forming a skeleton extending between a first end configured to house the trailing edge of the blade and a second end configured to house the leading edge of the blade. At least one of the openings is associated with a mechanical load transfer slit passing through the shell, and arranged facing and at a distance from the first end of the opening along the direction of the skeleton.
1. A shell for a stator of an aircraft turbo-engine module, comprising:
a plurality of through openings each configured to house a stator blade, each stator blade having a trailing edge and a leading edge, each opening forming a skeleton extending between a first end configured to house the trailing edge of the blade and a second end configured to house the leading edge of the blade,
a mechanical load transfer slit passing through the shell, said slit being associated with one of said openings and arranged facing and at a distance from the first end of the opening along the direction of the skeleton,
wherein the slit has a generally horseshoe shape with a bottom portion and two branches extending from said bottom portion,
wherein the first end of the opening is located between said branches of said slit, and
wherein the slit is separated from said opening by a portion of said shell.
2. A shell according to claim 1 , wherein the slit extends along a curved line towards the opening.
3. A shell according to claim 1 , wherein the opening presents an intrados part and an extrados part on each side of the skeleton, that come together at the first and second ends of the opening, and wherein the slit also extends facing and at a distance from portions of the intrados and extrados parts that come together at the first end of the opening.
4. A shell according to claim 1 , wherein the slit is filled in by an infill material.
5. A shell according to claim 1 , forming a continuous approximately annular structure.
6. A shell according to claim 1 , forming an approximately annular structure made by placement of angular shell sectors end to end.
7. A stator part for an aircraft turbo-engine module comprising:
at least one shell according to claim 1 ; and
a plurality of stator blades.
8. A stator part according to claim 7 , wherein the shell is an outer shell, and each of the through openings houses a head of one of the blades, fixed to the outer shell by a weld arranged in its opening and extending continuously all around the head of the blade.
9. A stator part according to claim 8 , further comprising an inner shell comprising a plurality of through openings each housing a root of one of the blades, fixed to the inner shell by a weld formed in its opening and extending continuously all around the blade root.
10. A module of an aircraft turbo-engine comprising at least a stator part according to claim 7 .
11. A module according to claim 10 , which is a compressor, or a high pressure compressor.
12. A turbo-engine for an aircraft, comprising at least one module according to claim 10 .
13. A shell according to claim 1 , wherein the slit is separated from said opening by a distance along the direction of said skeleton, said distance being between 0.02 and 0.1 times a total length of said blade along said skeleton.
14. A shell according to claim 13 , wherein said distance is between 0.03 and 0.05 times the total length of said blade along said skeleton.
15. A shell according to claim 1 , wherein the branches and the bottom portion of said slit are separated from said opening by a distance.
16. A shell according to claim 15 , wherein the distance separating the branches and the bottom portion of said slit from said opening is approximately constant.