Turbine engine turbine blade made of a ceramic-matrix composite with recesses made by machining
View Patent ↗A turbine engine turbine blade of ceramic matrix composite. The root of the blade includes a single densified fiber preform including at least one recess made by machining, each point of the root of the blade being situated at a distance from a free surface of the root that is no greater than twice the maximum penetration distance into the preform of densification gas for densifying the preform, and the distal portion of the root of the blade includes a distal wall that is continuous and in a single piece.
1. A turbine engine turbine blade of ceramic matrix composite,
wherein a root of the blade comprises a single densified fiber preform including first and second branches, a tang extending along a general longitudinal axis of the blade, and at least one recess,
wherein the first branch and the second branch are symmetrical about a general plane defined by the general longitudinal axis and a general transverse axis of the blade,
wherein each point of the root of the blade being situated at a distance from a free surface of the root that is no greater than twice the maximum penetration distance into the preform of densification gas for densifying the preform,
wherein the first branch and the second branch join together on a side opposite the tang so as to form a distal wall that constitutes a distal portion of the root of the blade,
wherein a face defining the recess is an inside face of at least one of the first branch, of the second branch, or of the distal wall, and
wherein the distal wall is continuous and in a single piece.
2. A blade according to claim 1 , wherein the maximum penetration distance of the densification gas lies in the range 2 mm to 4 mm.
3. A blade according to claim 1 , wherein the at least one recess is of a shape such that, in a direction of a general longitudinal plane, it is narrower at its ends and wider in its middle portion.
4. A blade according to claim 1 , wherein the at least one recess does not open out into an outside face of the distal wall of the root of the blade.
5. A blade according to claim 1 , wherein the at least one recess opens out into an outside face of the distal wall of the root of the blade.
6. A method of fabricating a turbine engine turbine blade of ceramic matrix composite, the method comprising:
a) preparing a fiber preform including first and second branches, and a tang extending along a general longitudinal axis of the blade, the first branch and the second branch being symmetrical about at least one recess and a general plane defined by the general longitudinal axis and a general transverse axis of the blade, and the first branch and the second branch joining together on a side opposite the tang so as to form a distal wall that constitutes a distal portion of the root of the blade;
b) machining the preform so as to form at least one recess in the preform; and
c) densifying the preform with a densification gas;
the at least one recess being made such that each point of a root of the blade is situated at a distance from a free surface of the root that is no greater than twice the maximum penetration distance into the preform of densification gas for densifying the preform, a face defining the recess being an inside face of at least one of the first branch, of the second branch, or of the distal wall and the distal wall is continuous and in a single piece.
7. A method of fabricating a blade according to claim 6 , wherein the at least one recess is of a shape such that, in a direction of a general longitudinal plane it is narrower at its ends and wider in its middle portion.
8. A method of fabricating a blade according to claim 6 , wherein the at least one recess does not open out into an outside face of the distal wall of the root of the blade.
9. A method of fabricating a blade according to claim 6 , wherein the at least one recess opens out into an outside face of the distal wall of the root of the blade.