Abstract: The ends of cooling air passages in turbine blades and/or vanes of a gas turbine engine are provided with turbulation promoters to enhance the cooling of such structures as inner and outer shrouds and the like to accommodate thermal loads thereon.

Abstract: Methods for repairing the gas turbine engine components are provided. In this regard, a representative method includes: determining the presence of a previous repair to a component; determining a characteristic of the previous repair using X-ray fluorescence analysis; and repairing the component.

Abstract: The ends of cooling air passages in turbine blades and/or vanes of a gas turbine engine are provided with turbulation promoters to enhance the cooling of such structures as inner and outer shrouds and the like to accommodate thermal loads thereon.

Abstract: Methods for repairing metallic components are described herein. Embodiments of these methods comprise: removing coatings from the component; removing the damage from the component; welding the component; restoring the original dimensions of the component; heat treating the component; inspecting the component; and recoating the component.

Abstract: A process for coating an article includes the steps of applying a bond coat layer onto at least one surface of an article; applying upon said bond coat layer a thermal barrier coating composition comprising a particle size distribution of no less than about 8 microns and no more than about 88 microns; heat treating said thermal barrier coating composition at a temperature of between about 1,800° F. to 2,200° F. for about 2 hours to 4 hours at a pressure of about 1×10?3 torr to 1×10?6 torr; and forming a thermal barrier coating layer comprising a cracking density of no more than about twenty cracks per linear inch of said thermal barrier coating.