Blade equipped with platforms comprising a retaining leg
A preform for a turbine engine blade, the preform being obtained by three-dimensional weaving and comprising a first longitudinal segment ( 31 ) suitable for forming at least a portion of a blade root, a second longitudinal segment ( 32 ) extending the first longitudinal segment ( 31 ) upwards, and suitable for forming at least a portion of a stilt portion, a third longitudinal segment ( 33 ) extending the second longitudinal segment ( 32 ) upwards, and suitable for forming an airfoil portion, a first transverse segment ( 34 ) extending transversely from the junction between the second and third longitudinal segments ( 32, 33 ), and suitable for forming a first platform, and a first oblique segment ( 36 ) extending from the junction between the first and second longitudinal segments ( 31, 32 ) to the first transverse segment ( 34 ), and suitable for forming a retaining leg ( 26 ) for the first platform.
1. A preform for a turbine engine blade, comprising:
a first longitudinal segment configured to form at least a portion of a blade root;
a second longitudinal segment extending the first longitudinal segment upwards, and configured to form at least a portion of a stilt portion;
a third longitudinal segment extending the second longitudinal segment upwards, and configured to form an airfoil portion;
a first transverse segment extending transversely from a junction between the second and third longitudinal segments, and configured to form a first platform; and
a first oblique segment, extending from a junction between the first and second longitudinal segments to the first transverse segment, and configured to form a retaining leg for the first platform, a gap being provided between the first oblique segment and the second longitudinal segment,
wherein the preform is obtained in a single-piece manner by three-dimensional weaving.
2. The preform according to claim 1 , wherein a distal end of the first oblique segment runs along a distal end of the first transverse segment.
3. The preform according to claim 1 , wherein a distal end of the first oblique segment is attached to the first transverse segment.
4. The preform according to claim 1 , wherein the first longitudinal segment includes a length that is constant from an upstream end to a downstream end of the preform; and
wherein the length of the second longitudinal segment increases going from the upstream end of the preform to its downstream end.
5. The preform according to claim 1 , further comprising:
a second transverse segment extending transversely from the junction between the second and third longitudinal segments, level with and going away from the first transverse segment, being configured to form a second platform; and
a second oblique segment extending from the junction between the first and second longitudinal segments to the second transverse segment, and intended to form a retaining leg for the second platform.
6. The preform according to claim 1 , further comprising an interface provided at the junction between the second and third longitudinal segments on its surface opposite from the first transverse segment.
7. The preform according to claim 6 , wherein the interface is a fitted metal strip.
8. A turbine engine blade comprising:
a blade root;
a stilt portion extending upwards from the blade root;
an airfoil portion extending upwards from a stilt portion;
a platform extending transversely to the airfoil portion from a junction between the stilt portion and the airfoil portion; and
a retaining leg extending between the root or the stilt portion at one end and the platform at the other end,
wherein the turbine engine blade is made in single-piece manner out of composite material by means of the preform according to claim 1 , said preform being shaped in a mold and embedded in a matrix.
9. The turbine engine blade according to claim 8 , wherein the matrix is organic.
10. A bladed wheel for a turbine engine comprising a plurality of blades according to claim 8 .
11. A turbine engine comprising at least one compressor, at least one combustion chamber, at least one turbine, and at least one blade according to claim 8 .