Turbine vane comprising a blade with a tub including a curved pressure side in a blade apex region
A turbine vane of a turbine engine such as a turbojet. The vane includes a base supporting a blade that extends in a spanwise direction and ends in an apex. The blade includes a pressure-side wall and a suction-side wall, each ending at an end edge at the apex of the blade. The blade includes, at the apex thereof, a closed wall extending from the pressure-side wall to the suction-side wall so as to define, with the end edges, a tub shape. The pressure-side wall is curved inward so as to deviate from the spanwise direction in the region of the blade apex preceding the tub, between the base and the pressure-side end edge.
1. A turbine vane of a turbomachine, the turbine vane comprising:
a root carrying a blade which extends along a span direction terminating with a blade apex, said blade comprising a pressure-side wall and a suction-side wall each terminating with a terminal edge at the blade apex, the blade including at the blade apex a closing wall extending from the pressure-side wall to the suction-side wall, the terminal edge of the pressure-side wall and the terminal edge of the suction-side wall projecting from the closing wall to delimit with the terminal edges of the pressure-side wall and the suction-side wall a tub shape,
wherein the pressure-side wall is curved so as to deviate from the span direction in a region of the blade apex, from a region located between the blade root and the tub, the pressure-side wall having a curvature determined by a relationship:
Δ
(
R
)
=
Δmax
*
(
R
-
R
min
)
n
(
R
max
-
R
min
)
n
wherein:
Δ(R) designates an offset value of the pressure-side wall, for a section located at a radius R from an axis of rotation of the blade;
Rmax designates a maximum radius of the blade from an end of the blade apex to the axis of rotation;
Rmin designates a radius of the blade where the curvature of the pressure-side wall starts;
Δmax designates a maximum offset at the end of the blade apex; and
n designates a smoothing power between 2 and 6.
2. The vane according to claim 1 , wherein the terminal edge of the suction-side wall is curved towards the span direction.
3. The vane according to claim 1 , wherein the suction-side wall is curved towards the span direction in the region of the blade apex preceding the tub.
4. The vane according to claim 1 , wherein the terminal edge of the pressure-side wall is curved away from the span direction.
5. The vane according to claim 1 , wherein the terminal edge of the suction-side wall is oriented in parallel to the span direction.
6. The vane according to claim 1 , wherein the terminal edge of the suction-side wall is curved away from the span direction.
7. A turbine of a turbomachine comprising the vane according to claim 1 .
8. A turbomachine comprising the turbine according to claim 7 .