Abstract: A turbine blade includes a root, tip, and airfoil. The turbine blade defines a serpentine interior passage having first through third legs, and first and second junctions. The first leg receives pressurized gas from a supply channel of the root. The first leg extends radially and the first junction connects it to the second leg proximate the tip. The second leg extends radially between the first and second junctions. The second junction connects the second and third legs. The third leg extends radially toward the tip. The tip defines cooling apertures open through a pressure side thereof. The cooling apertures include a forward aperture with a forward end opening into the first junction and an aftward end opening through the pressure side surface of the tip at a location that is radially outward of the third leg and axially aftward of at least a portion of the third leg.

Abstract: A turbine blade includes a blade tip defining pressure side cooling apertures. The turbine blade defines a serpentine cooling passage having a first, second, and third legs, and first and second junction portions. The first leg extends radially and is connected to the second leg by the first junction portion proximate the blade tip. The second leg extends radially between the first and second junction portions. The second junction portion connects the second leg to the third leg which extends radially toward the blade tip and is connected to a trailing edge cooling aperture to exhaust the gas to an exterior of the turbine blade. The turbine blade defines a plenum connected to the first junction portion. At least one tip cooling aperture connects to the plenum and is radially outward of the third leg and axially aftward of at least a portion of the third leg.

Abstract: A turbine rotor blade includes an airfoil, root, and platform that is between the root and a proximate end portion of the airfoil. The blade defines a passage having a first leg, second leg, and arcuate portion. The arcuate portion is at least partially within the platform and connects the first and second legs. The first leg extends between a distal end portion of the airfoil and an inlet of the arcuate portion. The second leg extends from an outlet of the arcuate portion to the distal end portion of the airfoil. The platform includes a first feed passage and branch passages. The first feed passage is open through an extrados of the arcuate portion and is in fluid communication with the branch passages. The inlet of each branch passage is connected with the first feed passage while the outlet is open to an exterior of the platform.

Abstract: A bypass valve assembly for a turbine generator includes a valve body, bypass seats, valve stem, valve cap, bypass valve disc, bypass valves, and pressure seal head. The valve body defines a central bore and a plurality of passageways. Each passageway has an inlet smaller than its outlet. Each bypass seat is within the inlet of a corresponding passageway. The bypass seats have a higher wear resistance than the valve body. The valve stem is within the central bore. The valve cap is secured to the valve body. The bypass valve disc is secured to the valve stem. Each bypass valve has a base portion and a nose portion. Each nose portion defines a contoured surface area with a wear coating and extends into a corresponding passageway. The pressure seal head is disposed around the valve stem and defines steps having a wear coating.

Abstract: A turbine blade includes a blade tip defining pressure side cooling apertures. The turbine blade defines a serpentine cooling passage having a first, second, and third legs, and first and second junction portions. The first leg extends radially and is connected to the second leg by the first junction portion proximate the blade tip. The second leg extends radially between the first and second junction portions. The second junction portion connects the second leg to the third leg which extends radially toward the blade tip and is connected to a trailing edge cooling aperture to exhaust the gas to an exterior of the turbine blade. The turbine blade defines a plenum connected to the first junction portion. At least one tip cooling aperture connects to the plenum and is radially outward of the third leg and axially aftward of at least a portion of the third leg.

Abstract: A gas turbine spacer disk includes a disk portion, a rim portion, a first fillet, and a second fillet. The disk portion is disposed about a rotational axis. The rim portion is disposed about the disk portion. An outer face of the rim portion defines a plurality grooves extending circumferentially about the rotational axis. The first fillet transitions from the rim portion to a first side of the disk portion. The second fillet transitions from the rim portion to a second side of the disk portion. The plurality of grooves includes a pair of first grooves having a first diameter and a pair of second grooves having a second diameter that is less than the first diameter. A first one of the first grooves overlaps in an axial direction with the first fillet. A second one of the first grooves overlaps in the axial direction with the second fillet.

Abstract: A turbine rotor blade includes an airfoil, root, and platform that is between the root and a proximate end portion of the airfoil. The blade defines a passage having a first leg, second leg, and arcuate portion. The arcuate portion is at least partially within the platform and connects the first and second legs. The first leg extends between a distal end portion of the airfoil and an inlet of the arcuate portion. The second leg extends from an outlet of the arcuate portion to the distal end portion of the airfoil. The platform includes a first feed passage and branch passages. The first feed passage is open through an extrados of the arcuate portion and is in fluid communication with the branch passages. The inlet of each branch passage is connected with the first feed passage while the outlet is open to an exterior of the platform.

Abstract: A gas turbine spacer disk includes a disk portion, a rim portion, a first fillet, and a second fillet. The disk portion is disposed about a rotational axis. The rim portion is disposed about the disk portion. An outer face of the rim portion defines a plurality grooves extending circumferentially about the rotational axis. The first fillet transitions from the rim portion to a first side of the disk portion. The second fillet transitions from the rim portion to a second side of the disk portion. The plurality of grooves includes a pair of first grooves having a first diameter and a pair of second grooves having a second diameter that is less than the first diameter. A first one of the first grooves overlaps in an axial direction with the first fillet. A second one of the first grooves overlaps in the axial direction with the second fillet.

Abstract: A method of remanufacturing a turbine blade having a platform includes placing a puck against a surface of the platform. The method may include electrical discharge machining an interface between the puck and the platform and brazing the puck to the platform. A total radial thickness of a finally remanufactured platform of the remanufactured turbine blade is greater than an initial radial thickness of the platform before remanufacturing the turbine blade.

Abstract: A bypass valve assembly for a turbine generator includes a valve body, bypass seats, valve stem, valve cap, bypass valve disc, bypass valves, and pressure seal head. The valve body defines a central bore and a plurality of passageways. Each passageway has an inlet smaller than its outlet. Each bypass seat is within the inlet of a corresponding passageway. The bypass seats have a higher wear resistance than the valve body. The valve stem is within the central bore. The valve cap is secured to the valve body. The bypass valve disc is secured to the valve stem. Each bypass valve has a base portion and a nose portion. Each nose portion defines a contoured surface area with a wear coating and extends into a corresponding passageway. The pressure seal head is disposed around the valve stem and defines steps having a wear coating.

Abstract: A bypass valve assembly for use in turbine generators includes a valve body defining a central bore and a plurality of passageways. Each passageway has a smaller area at an inlet portion and a larger area at an outlet portion to define a flared passageway. A plurality of bypass valves is disposed within the plurality of passageways within the valve body. Each bypass valve includes a base portion and a nose portion, with each nose portion defining a predefined contoured surface area. At least a portion of the contoured surface area includes a wear coating disposed thereon. Optionally, the wear coating includes a plasma enhanced magnetron sputtering nanocoating.

Abstract: A turbine engine component can include a surface comprising at least one edge and a coating disposed upon the surface that can extend to the edge. A spall break can be disposed along a line upon the surface adjacent the edge to prevent spallation of the coating from spreading from the edge onto the surface beyond the spall break. The spall break can comprise a discontinuity of the coating. A method of coating a turbine component can include preparing a substrate to receive a coating and selecting a fail location along the substrate for a coating. One or more coating can be applied to the substrate and a spall break can be incorporated into the one or more coatings. The spall break can comprise a line of discontinuity in the one or more coatings along the fail location.

Abstract: A method of remanufacturing a turbine blade having a platform includes placing a puck against a surface of the platform. The method may include electrical discharge machining an interface between the puck and the platform and brazing the puck to the platform. A total radial thickness of a finally remanufactured platform of the remanufactured turbine blade is greater than an initial radial thickness of the platform before remanufacturing the turbine blade.

Abstract: A method of remanufacturing a turbine component includes electrical discharge machining a puck via the turbine component to form an electrical discharged machined puck; and brazing the electrical discharged machined puck to the turbine component.

Abstract: A gas turbine engine system comprises a rotor wheel, a plurality of blades, a lockwire and a locking key. The rotor wheel comprises a plurality of axial grooves extending through a periphery of the rotor wheel, and a plurality of posts formed between adjacent slots, each post having a circumferential slot. The blades are mounted in the axial grooves of the rotor wheel, each blade having a circumferential slot circumferentially aligned with the circumferential slots of the posts. The lockwire extends across the plurality of axial grooves of the rotor wheel within each of the circumferential slots of the posts and the blades from a first end to a second end to inhibit axial displacement of the blades within the grooves. The locking key is disposed between the first and second ends of the lockwire and provides support to at least one of the ends of the lockwire to prevent radially inward displacement.

Abstract: An assembly for use in a rotor of a turbine generator is provided that includes at least one creepage disposed on an upper load surface of copper windings. At least one slot spring is disposed on the creepage, and at least one amortisseur is disposed on the slot spring. A plurality of hollow locking members are disposed within apertures of the creepage, the slot spring, and the amortisseur. At least one slot wedge is disposed on the slot spring and the plurality of hollow locking members. At least one field retaining ring is disposed against one of the end portions of the rotor body and against the slot wedge.

Abstract: A method for repairing a rotor of a turbine includes providing a rotor having a groove portion defined by a circumferential portion of the rotor. The circumferential portion of the rotor is removed to create an opening to provide access to the groove such that the opening, immediately adjacent the groove, is narrower than the groove. A guide block may be extended into a receiving slot separating a first protruding surface from a second protruding surface of the rotor such that a weld area slot of the guide block extends over at least a portion of the opening. The opening may be welded adjacent the guide block to close at least a portion of the opening.

Abstract: A method for repairing a rotor of a turbine includes providing a rotor having a groove portion defined by a circumferential portion of the rotor. The circumferential portion of the rotor is removed to create an opening to provide access to the groove such that the opening, immediately adjacent the groove, is narrower than the groove. A guide block may be extended into a receiving slot separating a first protruding surface from a second protruding surface of the rotor such that a weld area slot of the guide block extends over at least a portion of the opening. The opening may be welded adjacent the guide block to close at least a portion of the opening.

Abstract: A method for repairing a rotor of a turbine includes providing a rotor having a groove portion defined by a circumferential portion of the rotor. The circumferential portion of the rotor is removed to create an opening to provide access to the groove such that the opening, immediately adjacent the groove, is narrower than the groove. A guide block may be extended into a receiving slot separating a first protruding surface from a second protruding surface of the rotor such that a weld area slot of the guide block extends over at least a portion of the opening. The opening may be welded adjacent the guide block to close at least a portion of the opening.