Abstract: A blade for an engine includes an airfoil body having a pressure side and a suction side, a base, and a rib located on the pressure side of the airfoil body. The rib includes a radially outer surface inclined radially outwardly with respect to the pressure side of the airfoil body and a scoop formed by the radially outer surface. The radially outer surface is inclined radially outward with respect to a normal axis to the pressure side of the airfoil body. The rib is angled at a positive angle with respect to the platform. An engine for and a method of directing ingestion material in an engine may employ the rib.

Abstract: A gas turbine engine including a component having a first and a second component that are attached or integrally formed with each other. The first and the second component define an enclosed void. An insert is positioned within the enclosed void which is formed of a material having a relatively low Young's modulus. The insert may prevent resin from filling the enclosed void during assembly/manufacture of the component, while also reducing a weight of the component and an amount of stress on the component. The component may be a fan platform positioned between a plurality of fan blades, an outlet guide vane, or another component of the gas turbine engine.