Asymmetrical member for locking ring sectors to a turbine engine casing

1. A locking member of a device for fastening ring sectors to an aircraft turbine engine casing, said member extending in a circumferential direction between a first circumferential end and a second circumferential end, said member having, in a cross-section along a plane perpendicular to said circumferential direction, first and second clamping branches connected together at rear ends thereof, by first and second curved joining portions, respectively, by a connecting branch extending substantially parallel to a general spacing direction of the two clamping branches, front ends of the two clamping branches being intended to press between them at least one ring sector against at least one casing element,

said member is such that, in said cross-section:

said first clamping branch has a first inside surface;

said second clamping branch has a second inside surface;

said connecting branch has an inside connecting surface;

said first curved joining portion has a first inside joining surface having a mean radius Rm 1 ; and

said second curved joining portion has a second inside joining surface having a mean radius Rm 2 ,

said first curved joining portion being defined by a first angular sector, which is defined by a normal to said first inside surface at a connecting point with said first inside joining surface, and by a normal to said inside connecting surface at a connecting point with said first inside joining surface, and said second curved joining portion being defined by a second angular sector which is defined by a normal to said second inside surface at a connecting point with said second inside joining surface, and by a normal to said inside connecting surface at a connecting point with said second inside joining surface,

in a direction of a bisectrix of the first angular sector, said first curving joining portion having a thickness E 1 , and, in a direction of a bisectrix of the second angular sector, said second curved joining portion having a thickness E 2 ,

wherein the thickness E 1 is strictly smaller than thickness E 2 , and the mean radius Rm 1 is strictly smaller than mean radius Rm 2 .

2. The locking member of claim 1 , wherein a ratio E 1 /E 2 is such that 0.3<E 1 /E 2 <1, and a ratio Rm 1 /Rm 2 is such that 0.3<Rm 1 /Rm 2 <1.

3. The locking member of claim 1 , wherein a ratio E 1 /E 2 is such that 0.5<E 1 /E 2 <0.85, and a ratio Rm 1 /Rm 2 is such that 0.5<Rm 1 /Rm 2 <0.85.

4. The locking member as claimed in claim 1 , wherein, in said cross-section, each first inside surface, second inside surface and inside connecting surface assumes the form of a straight line.

5. The locking member as claimed in claim 1 , wherein, in said cross-section, each of the first and second inside joining surfaces assumes the form of an arc of circle or a succession of arcs of circles.

6. The locking member as claimed in any one of claims 1 to 5 , wherein a thickness of said first curving joining portion decreases in a direction running from the connecting branch to said first clamping branch.

7. The locking member as claimed in any one of claims 1 to 5 , wherein a thickness of said first curved joining portion decreases and then increases in a direction running from the connecting branch to said first clamping branch.

8. The locking member as claimed in claim 1 , wherein the locking member forms an angular sector of an annular locking device.

9. A device for fastening ring sectors to a aircraft turbine engine casing, comprising:

casing elements formed with first rear circumferential rims onto which are applied second rear circumferential rims of ring sectors; and

a plurality of locking members as claimed in claim 1 , which are engaged on said first and second circumferential rims in order to hold the rims pressed against one another.

10. An aircraft turbine engine turbine comprising a ring sector fastening device of claim 9 .

11. The turbine as claimed in claim 10 , wherein said first clamping branch is oriented radially outward in relation to said second clamping branch.

12. The turbine as claimed in claim 10 , wherein said first clamping branch is oriented radially inward in relation to said second clamping branch.

13. An aircraft turbine engine comprising a turbine as claimed in any one of claims 10 to 12 .

14. The turbine engine of claim 13 , wherein the turbine engine is a turbojet engine or a turboprop engine.