Abstract: An airfoil component having a body having a leading edge and a trailing edge, a ceramic casting insert for making the component and the method for making the component. The component includes an internal cooling passageway and an elongated opening in communication with the internal cooling passageway. The opening is configured with a geometry that provides structural stability during casting and has a cross-section that sufficiently restricts airflow through the opening to provide efficient component operation. The casting insert includes outer edge projections and a web portion corresponding to the geometry of the openings when cast around the insert. The method includes casting the airfoil component around the casting insert and removing the insert to provide the component having the openings.

Abstract: A turbine rotor for a gas turbine engine includes a rotor disk having a plurality of circumferentially alternating dovetail slots and disk posts and a plurality of blades disposed in the dovetail slots. A cooling air plenum is defined in the portion of each dovetail slot located radially inward of the corresponding blade. Air from the plenums is directed through slots formed in axial surfaces of the blades or disk posts into an adjacent wheel cavity, thereby purging the wheel cavity.

Abstract: A gas turbine engine hollow airfoil includes an airfoil outer wall having width wise spaced aparted pressure and suction side walls joined together at chordally spaced apart leading and trailing edges of the airfoil and extending longitudinally from a root to a tip. At least one internal aft flowing serpentine cooling circuit inside the airfoil has an exit that is positioned aft of the entrance so as to have a chordal flow direction afterwards from the leading edge to the trailing edge within the serpentine circuit. At least one longitudinally extending first side wall impingement chamber is in downstream fluid communication with the serpentine cooling circuit within the airfoil and positioned between one of the side walls, preferably the pressure side wall, and a first inner wall bounding the serpentine cooling circuit. Impingement cooling apertures are disposed in the first inner wall between one of the serpentine channels and the side wall impingement chamber.

Abstract: A coated article comprises a base article having a substrate made of a material selected from the group consisting of a nickel-base alloy and a cobalt-base alloy, an intermediate metallic coating structure, and a thermal barrier coating. The intermediate metallic coating structure may be a protective layer of platinum, rhodium, or palladium on the base article, with no bond coat. The intermediate metallic coating may also be a bond coat, either oxidized or unoxidized, with a protective layer of platinum, rhodium, or palladium thereon. The protective layer typically partially interdiffuses with the underlying metallic structure.