Turbine vane assembly with reinforced end wall joints
The present disclosure is related to turbine vane assemblies comprising ceramic matrix composite materials. The turbine vane assemblies further including reinforcements that strengthen joints in the turbine vane assemblies.
1. A turbine vane adapted for use in an aerospace gas turbine engine, the turbine vane comprising
an airfoil comprising ceramic matrix composite materials having ceramic-containing fibers infiltrated with ceramic matrix, the airfoil shaped to redirect hot gasses moving along a primary gas path within the aerospace gas turbine engine,
an end wall comprising ceramic matrix composite materials having ceramic-containing fibers co-infiltrated with ceramic matrix along with the ceramic-containing fibers of the airfoil, the end wall including a panel that extends circumferentially from the airfoil about a central axis to define a boundary of the primary gas path and a rim that extends radially from the panel outside the primary gas path along an outer surface of the airfoil, and
reinforcements configured to interconnect the airfoil and the end wall and strengthen a joint therebetween, the reinforcements arranged to extend between the outer surface of the airfoil and the rim of the end wall, the reinforcements being provided by stitched fibers that extend through an inner surface of the airfoil facing a central cavity of the airfoil and an outer surface of the rim that faces away from the airfoil.
2. The turbine vane of claim 1 , wherein the stitched fibers are co-infiltrated with ceramic matrix along with the airfoil and the end wall.
3. The turbine vane of claim 2 , wherein the end wall extends circumferentially beyond the rim of the end wall and the stitched fibers that provide the reinforcements are located only in the rim such that they are radially apart from the panel.
4. The turbine vane of claim 2 , wherein the airfoil is shaped to include a leading edge, a trailing edge, a pressure side having a concave shape that extends from the leading edge to the trailing edge, and a suction side having a convex shape that extends from the leading edge to the trailing edge, and
wherein the stitched fibers that provide the reinforcements are located only along the suction side of the airfoil.
5. The turbine vane of claim 2 , wherein the airfoil is shaped to include a leading edge, a trailing edge, a pressure side having a concave shape that extends from the leading edge to the trailing edge, and a suction side having a convex shape that extends from the leading edge to the trailing edge, and
wherein the stitched fibers that provide the reinforcements are located only along the pressure side of the airfoil.