Abstract: A waterjet ablation process is performed to remove a volume of material from a service area of a component, the volume of material including at least one defect and any oxides and contaminants located at the service area. After performing the waterjet ablation process, the service area of the component is repaired by a welding or brazing process to restore material to the service area. The component is put into service in an engine without requiring affixation of a replacement coupon to the component.

Abstract: A catalytic oxidation module for a catalytic combustor of a gas turbine engine is provided. The catalytic oxidation module comprises a plurality of spaced apart catalytic elements for receiving a fuel-air mixture over a surface of the catalytic elements. The plurality of catalytic elements includes at least one primary catalytic element comprising a monometallic catalyst and secondary catalytic elements adjacent the primary catalytic element comprising a multi-component catalyst. Ignition of the monometallic catalyst of the primary catalytic element is effective to rapidly increase a temperature within the catalytic oxidation module to a degree sufficient to ignite the multi-component catalyst.

Abstract: A thermal barrier coating system is provided. The thermal barrier coating system may include a first layer of ceramic insulating material (21) (see FIG. 1) disposed on a substrate surface. The thermal barrier coating system may also include a second layer of ceramic insulating material (25) disposed on the first layer of ceramic insulating material. The second layer of ceramic insulating material may include one or more crack arrestors therein. A third layer of ceramic insulating material (26) is disposed on the second layer of ceramic insulating material. The third layer may be configured as a sacrificial layer to absorb mechanical shock generated in the event of a foreign object collision with the third layer. The one or more crack arrestors in the second layer can avoid propagation towards the first layer of one or more cracks that can form in the event of the foreign object collision with the third layer.

Abstract: A catalytic oxidation module for a catalytic combustor of a gas turbine engine is provided. The catalytic oxidation module comprises a plurality of spaced apart catalytic elements for receiving a fuel-air mixture over a surface of the catalytic elements. The plurality of catalytic elements includes at least one primary catalytic element comprising a monometallic catalyst and secondary catalytic elements adjacent the primary catalytic element comprising a multi-component catalyst. Ignition of the monometallic catalyst of the primary catalytic element is effective to rapidly increase a temperature within the catalytic oxidation module to a degree sufficient to ignite the multi-component catalyst.

Abstract: A thermal barrier coating system is provided. The thermal barrier coating system may include a first layer of ceramic insulating material (21) (see FIG. 1) disposed on a substrate surface. The thermal barrier coating system may also include a second layer of ceramic insulating material (25) disposed on the first layer of ceramic insulating material. The second layer of ceramic insulating material may include one or more crack arrestors therein. A third layer of ceramic insulating material (26) is disposed on the second layer of ceramic insulating material. The third layer may be configured as a sacrificial layer to absorb mechanical shock generated in the event of a foreign object collision with the third layer. The one or more crack arrestors in the second layer can avoid propagation towards the first layer of one or more cracks that can form in the event of the foreign object collision with the third layer.