Abstract: A tip cap piece for use in a turbine bucket. The tip cap piece may include a cold side and a number of pins positioned on the cold side.

Abstract: A method of assembling a combustor assembly is provided, wherein the method includes providing a combustor liner having a centerline axis and defining a combustion chamber therein, and coupling an annular flowsleeve radially outward from the combustor liner such that an annular flow path is defined substantially circumferentially between the flowsleeve and the combustor finer. The method also includes orienting the flowsleeve such that a plurality of inlets formed within the flowsleeve are positioned to inject cooling air in a substantially axial direction into the annular flow path to facilitate cooling the combustor finer.

Abstract: A method of enhancing the heat transfer coefficient of a tube flowing a fluid in the tube in heat exchange relation with a second fluid external to the tube includes applying metal particles to an interior surface of the tube to thereby create an increased wetted area for interaction with fluid flowing through the tube; wherein the particles are applied by: providing an applicator head including an electric arc and at least one metal wire; displacing the head along the interior of the tube; feeding the wire into the electric arc as the head is displaced along the interior of the tube; melting the wire to form molten metal particles; and applying the molten metal particles about and along the length of the interior wall surface of the tube as the head is displaced along the interior of the tube.

Abstract: A method of enhancing the heat transfer coefficient of a tube flowing a fluid in the tube in heat exchange relation with a second fluid external to the tube includes forming a patterned array of grooves on the interior surface of the tube. Each tube has a depth-to-width ratio of 0.10 to 0.30, and the grooves may be formed by mechanical pressing, pulsed ECM or electrodischarge processes.

Abstract: A hybrid power plant includes a turbine, a compressor driven by the turbine and a recuperator in flow communication with the compressor. The recuperator is configured to transfer heat from turbine exhaust to compressed air, and at least one fuel cell is in flow communication with said recuperator to provide fresh air for said fuel cell.

Abstract: The cooling scheme of a gas turbine engine component is modified to improve local cooling without redesigning the investment casting. The modification includes forming at least one channel in the component such that the channel is in fluid communication with a cooling medium source associated with the component. The channel is then partially filled with a removable material, and the removable material is covered with a patch material so as to completely fill the channel. Lastly, the removable material is removed from the channel so as to create an internal cooling passage in the component that is in fluid communication with the cooling medium source.

Abstract: A stator core assembly comprising adjacent packages of stacked lamination sheets that are separated by a plurality of radially extending spacer blocks, and each adjacent pair of spacer blocks define in cooperation with adjacent axially spaced laminations, a plurality of radial cooling ducts, each duct having a least one lamination surface having plurality of concavities.

Abstract: The cooling scheme of a gas turbine engine component is modified to improve local cooling without redesigning the investment casting. The modification includes forming at least one channel in the component such that the channel is in fluid communication with a cooling medium source associated with the component. The channel is then partially filled with a removable material, and the removable material is covered with a patch material so as to completely fill the channel. Lastly, the removable material is removed from the channel so as to create an internal cooling passage in the component that is in fluid communication with the cooling medium source.

Abstract: A gas turbine engine includes a compressor, combustor, and turbine, and a cooling air closed-circuit having an extraction line from the compressor to a hot turbine component such as vanes, blades, or shrouds, and a return line to the compressor. The extraction line may be joined to any suitable compressor stage for extracting air at a suitable pressure for flow to the turbine, with the return line being joined to any suitable injection stage of the compressor having a lower pressure than the extraction stage for driving the cooling air through the closed-circuit. The compressor itself therefore drives the closed-circuit and is self regulated.

Abstract: A coolable airfoil for use in gas turbine engine component such as a turbine blade or vane is provided with an integrally formed double shell outer wall surrounding at least one radially extending cavity. The inner and the outer shells are integrally formed of the same material together with tying elements which space apart the shells and mechanically and thermally tie the shells together. The present invention contemplates tying elements including pedestals, rods, and/or continuous or intermittent ribs. Impingement cooling means for the outer shell, in the form of impingement cooling holes, is provided on the inner shell to direct the coolant in impingement jet arrays against the outer shell, thereby, cooling the outer shell.