Patent ID: 9188013
Filing Date: 2015-11-17
Classification: C04B,F01D,F05D,Y10T

Abstract:
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.