Stator of an aircraft turbine engine
A stator of an aircraft turbine engine, comprising an annular row of fixed vanes and an annular row of arms, wherein the trailing edges of the fixed vanes are positioned substantially in a first transverse plane that is positioned downstream of a second transverse plane that passes substantially through the leading edges of the arms.
1. A stator of an aircraft turbine engine, comprising an annular row of fixed vanes having leading edges and trailing edges and an annular row of arms having leading edges and trailing edges, the stator having an axis of revolution, wherein:
the trailing edges of the fixed vanes are positioned substantially in a first plane that is transverse to said axis of revolution and is positioned downstream of a second plane that is transverse to said axis of revolution and passes substantially through the leading edges of the arms, and
the leading edges of the fixed vanes are positioned substantially in a third plane that is transverse to said axis of revolution and is positioned upstream of the second plane,
and wherein the stator further comprises an annular row of variable-pitch vanes that is positioned directly downstream of the annular row of arms, the annular row of variable-pitch vanes comprising first variable-pitch vanes that are positioned substantially along an extension of a chord of the arms, and second variable-pitch vanes that are each positioned between a corresponding two of the first variable-pitch vanes, the first variable-pitch vanes having different aerodynamic profiles than the second variable-pitch vanes.
2. The stator according to claim 1 , wherein the arms are inclined relative to the axis of revolution of the stator.
3. The stator according to claim 2 , wherein the arms and the fixed vanes are substantially parallel.
4. The stator according to claim 1 , further comprising two annular walls that are inner wall and outer wall, respectively, between which the rows of fixed vanes and arms extend.
5. The stator according to claim 4 , wherein each variable-pitch vane comprises, at its outer radial end, a cylindrical pivot that is mounted in a duct on the outer wall.
6. The stator according to claim 4 , wherein the outer wall comprises:
upstream of the arms, an annular row of discharge air through-slots and means for closing said slots, or
between the arms, at least one discharge air through-opening and at least one door for closing said through-opening.
7. The stator according to claim 1 , wherein the first variable-pitch vanes have aerodynamic profiles or curvatures that are more accentuated than those of the second variable-pitch vanes.
8. An aircraft turbine engine comprising at least one stator according to claim 1 .