Turbine engine guide vane

1. A guide vane for a set of guide vanes of a turbine engine the guide vane comprising a plurality of vane sections stacked between a root and a tip along a radial axis Z that defines the height direction of the vane, each vane section:

extending along a longitudinal axis X between a leading edge and a trailing edge, and along a tangential axis Y between a pressure side face and a suction side face;

having a chord defined by the length of the segment extending from the leading edge to the trailing edge; and

having a thickness defined by the distance between the pressure side and suction side faces that varies along the chord;

dimensionless coordinates x′ and z′ being defined for each point of the vane of coordinates x, y, and z along the axes X, Y, and Z by the quotients x/Ht and z/Ht, where Ht represents the total height of the vane, the leading edge of the vane at its total height Ht defining a coordinate at the origin x′=0 from which the coordinate x′ increases going towards the trailing edge;

wherein over a bottom portion of the vane extending from z′=0 to z′=0.5, the coordinate x′ of the leading edge is negative and the maximum thicknesses are located at positions that are offset from the leading edge by at least 50% of the chord,

wherein the coordinate x′ increases continuously from the root, passes through a value of zero at about ⅔ of the height of the vane and reaches a maximum positive value at a position located in a range from 80% to 90% of the total height, prior to decreasing and returning to zero at 100% of the maximum height.

2. The vane as claimed in claim 1 , wherein for the section of coordinate z′=0, the coordinate x′ is less than or equal to −0.15.

3. The vane as claimed in claim 1 , wherein over a portion of the vane extending from z′=0 to z′=0.3, the coordinate x′ is less than or equal to −0.1.

4. The vane as claimed in claim 2 , wherein over a portion of the vane extending from z′=0 to z′=0.3, the coordinate x′ is less than or equal to −0.1.

5. The vane as claimed in claim 1 , wherein the coordinate x′ increases continuously over the bottom portion of the vane with increasing coordinate z′.

6. The vane as claimed in claim 2 , wherein the coordinate x′ increases continuously over the bottom portion of the vane with increasing coordinate z′.

7. The vane as claimed in claim 3 , wherein the coordinate x′ increases continuously over the bottom portion of the vane with increasing coordinate z′.

8. The vane as claimed in claim 4 , wherein the coordinate x′ increases continuously over the bottom portion of the vane with increasing coordinate z′.

9. The vane as claimed in claim 1 , wherein for the section of coordinate z′=0, the maximum thickness is located at a position offset from the leading edge by at least 60% of the chord.

10. The vane as claimed in claim 2 , wherein for the section of coordinate z′=0, the maximum thickness is located at a position offset from the leading edge by at least 60% of the chord.

11. The vane as claimed in claim 3 , wherein for the section of coordinate z′=0, the maximum thickness is located at a position offset from the leading edge by at least 60% of the chord.

12. The vane as claimed in claim 9 , wherein over a portion of the vane extending in the range z′=0 to z′=0.15, the maximum thickness is located at a position that is offset from the leading edge by at least 60% of the chord.

13. The vane as claimed in claim 1 , wherein the vane presents a first portion extending from z′=0 to z′=0.20, over which the position of the maximum thickness relative to the chord remains substantially constant, and a second portion extending beyond the first portion to the tip of the vane, over which the position of the maximum thickness advances towards the leading edge.

14. An annular set of outlet guide vanes for a turbine engine comprising a plurality of vanes as claimed in claim 1 .

15. A turbine engine including at least one OGV set according to claim 14 .