Abstract: Disclosed is a turbine blade or vane including a blade or vane body including a leading edge and a trailing edge, a plurality of cooling openings disposed along the trailing edge, a first width of the trailing edge, the first width being disposed across the cooling openings, and a second width of the trailing edge the second width being disposed between the cooling openings, wherein the second width is smaller than the first width.

Abstract: Cooling channels through the interior of a machine component that include: a first set of cooling channels, the first set of cooling channels including a plurality of parallel channels that reside in a first plane; a second set of cooling channels, the second set of cooling channels including a plurality of parallel channels that reside in a second plane. Along a longitudinal axis, the cooling channels of the first and second set of cooling channels may include an alternating diverging-converging configuration, the alternating diverging-converging configuration creating a series of broader chamber sections connected by a series of narrower throat sections. The first set of cooling channels and the second set of cooling channels may be configured such that, when viewed from the side, a crisscrossing pattern with a plurality of intersections is formed.

Abstract: Disclosed is a coating for gas turbine components including at least one material having vibration-damping properties. Further disclosed is an airfoil of a gas turbine having damped vibrational characteristics including an airfoil substrate and a coating applied to the airfoil substrate including at least one material having vibration-damping properties. A method of damping vibration of a gas turbine component includes applying a coating including at least one material having damping properties to the turbine component.

Abstract: Disclosed is a turbine blade or vane including a blade or vane body including a leading edge and a trailing edge, a plurality of cooling openings disposed along the trailing edge, a first width of the trailing edge, the first width being disposed across the cooling openings, and a second width of the trailing edge the second width being disposed between the cooling openings, wherein the second width is smaller than the first width.

Abstract: A damping system for a turbine bucket. The damping system includes a damper pocket with a variable tangential depth and a damper pin positional within the damper pocket.

Abstract: A blade for a turbine includes: a support structure of high strength material as a central portion of the blade, the support structure including a root and a body extending to a tip, the body providing a leading edge, a trailing edge and mounting section; and a honeycomb skin attached to the mounting section for providing a lightweight airfoil portion of the blade. A method and a turbine are included.

Abstract: A turbomachine component includes a main body having a surface, and a damping structure mounted to the surface of the main body. The damping structure is formed from a material having a temperature dependent damping characteristic.

Abstract: An enhanced damping system for a turbine bucket. The damping system includes a damper pocket and a damper pin with an offset center of gravity positioned within the damper pocket.

Abstract: Disclosed is a coating for gas turbine components including at least one material having vibration-damping properties. Further disclosed is an airfoil of a gas turbine having damped vibrational characteristics including an airfoil substrate and a coating applied to the airfoil substrate including at least one material having vibration-damping properties. A method of damping vibration of a gas turbine component includes applying a coating including at least one material having damping properties to the turbine component.

Abstract: A damping system for a turbin bucket. The damping system includes a damper pocket with a variable tangential depth and a damper pin positional within the damper pocket.

Abstract: An enhanced damping system for a turbine bucket. The damping system includes a damper pocket and a damper pin with an offset center of gravity positioned within the damper pocket.