Ceramic matrix composite turbine vane

This invention relates generally to the field of gas turbine engines, and more particularly to a ceramic matrix composite airfoil member for a gas turbine engine and a method of manufacturing the same. A ceramic matrix composite material (CMC) vane for a gas turbine engine wherein the airfoil member () and the platform member () are formed separately and are then bonded together to form an integral vane component (). Airfoil member and the platform member may be bonded together by an adhesive () after being fully cured. Alternatively, respective joint surfaces () of the green body state airfoil member and platform member may be co-fired together to form a sinter bond (). A mechanical fastener () and/or a CMC doubler () may be utilized to reinforce the bonded joint (). A matrix infiltration process () may be used to create or to further strengthen the bond.