Patent attributes
Components for gas turbine engines are described. The components include an airfoil having a leading edge cavity with a baffle portion and a leading edge portion. A baffle is installed within the baffle portion and includes a first metering flow aperture. A first support element retention feature is located within the leading edge cavity. A first axial extending rib extends between an aft end of the cavity and a forward end proximate the first support element retention feature and is formed on an interior surface of the airfoil. A first axial extending flow channel extends along the first axial extending rib between an exterior surface of the baffle and an interior surface of the airfoil and the first metering flow aperture is located proximate the aft end of the first axial extending flow channel to generate a forward flowing cooling flow.
