US Patent 9598967 Airfoil member and composite platform having contoured endwall

An airfoil member and platform assembly for a gas turbine engine is provided. The platform to which the airfoil member is anchored is made of a composite material and includes an endwall defining a contoured region for improved aerodynamics. The contoured region influences the flow of gases through the flow passages between the airfoil members, thereby reducing endwall losses due to horseshoe vortexing. The composite material may be woven ceramic matrix composite fibers infiltrated with a ceramic matrix material or woven organic matrix composite fibers infiltrated with an organic matrix material.