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.
B23P 15/02 - Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from one piece
B23P 15/04 - Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from several pieces
F01D 5/18 - Hollow bladesHeating, heat-insulating, or cooling means on blades
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.
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.
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.
F16K 1/12 - Lift valves, i.e. cut-off apparatus with closure members having at least a component of their opening and closing motion perpendicular to the closing faces with streamlined valve member around which the fluid flows when the valve is opened
F01D 17/14 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
F01D 17/00 - Regulating or controlling by varying flow
F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
F16K 25/00 - Details relating to contact between valve members and seats
F16K 25/04 - Arrangements for preventing erosion, not otherwise provided for
5.
Repair or remanufacture of blade platform for a gas turbine engine
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.
B23H 1/00 - Electrical discharge machining, i.e. removing metal with a series of rapidly recurring electrical discharges between an electrode and a workpiece in the presence of a fluid dielectric
B23H 1/04 - Electrodes specially adapted therefor or their manufacture
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.
B32B 3/00 - Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shapeLayered products comprising a layer having particular features of form
F01D 9/04 - NozzlesNozzle boxesStator bladesGuide conduits forming ring or sector
F01D 5/28 - Selecting particular materialsMeasures against erosion or corrosion
8.
Turbine bucket lockwire anti-rotation device for gas turbine engine
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.
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.
F16K 1/12 - Lift valves, i.e. cut-off apparatus with closure members having at least a component of their opening and closing motion perpendicular to the closing faces with streamlined valve member around which the fluid flows when the valve is opened
F01D 17/14 - Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
F01D 17/00 - Regulating or controlling by varying flow
F01D 25/00 - Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
F16K 25/00 - Details relating to contact between valve members and seats
10.
Modified attachment system for springs in a generator rotor
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.
H02K 3/24 - Windings characterised by the conductor shape, form or construction, e.g. with bar conductors with channels or ducts for cooling medium between the conductors
H02K 3/52 - Fastening salient pole windings or connections thereto
11.
Repair or remanufacture of blade platform for a gas turbine engine
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.
F01D 5/00 - BladesBlade-carrying membersHeating, heat-insulating, cooling, or antivibration means on the blades or the members
B23H 1/04 - Electrodes specially adapted therefor or their manufacture
B23H 1/00 - Electrical discharge machining, i.e. removing metal with a series of rapidly recurring electrical discharges between an electrode and a workpiece in the presence of a fluid dielectric
37 - Construction and mining; installation and repair services
42 - Scientific, technological and industrial services, research and design
Goods & Services
maintaining, repairing, aligning, overhauling, and refurbishing turbines and generators engineering services relating to turbo machinery; inspecting, testing and evaluating turbines and generators
13.
Gas turbine engine systems involving cooling of combustion section liners
Gas turbine engine systems involving cooling of combustion section liners are provided. A representative liner includes: an outer side, an inner side, an upstream end, and a downstream end, the outer side being configured to face away from a combustion reaction, the inner side being configured to face the combustion reaction; a cooling air channel, a portion of the cooling air channel being located proximate the downstream end; and cooling holes formed through the inner side of the liner, the cooling holes being in fluid communication with the cooling air channel such that cooling air provided to the cooling air channel is directed through the cooling holes and to the inner side of the liner such that at least a portion of the inner side of the liner receives cooling air despite a corresponding portion located on the outer side of the liner being obstructed from receiving cooling air.
A combustor liner cap assembly is provided for use in a multiple fuel nozzle combustor of a gas turbine. The combustor liner cap assembly includes a tube plate having a plurality of fuel nozzle openings and a plurality of open ended premix tubes extending aft from the tube plate. Each premix tube has a forward end having a forward edge, the forward end being received in a corresponding one of the fuel nozzle openings. Each premix tube is secured to the tube plate aft of the forward edge of the forward end of the premix tube, for example, metallurgically bonded, such as by welding or brazing, to the tube plate or threaded into the tube plate.
37 - Construction and mining; installation and repair services
42 - Scientific, technological and industrial services, research and design
Goods & Services
Maintaining, repairing, aligning, overhauling, and refurbishing turbines and generators Engineering services relating to turbo machinery; inspecting, testing and evaluating turbines and generators
37 - Construction and mining; installation and repair services
42 - Scientific, technological and industrial services, research and design
Goods & Services
Maintaining, repairing, aligning, overhauling, and refurbishing turbines and generators Engineering services relating to turbo machinery; inspecting, testing and evaluating turbines and generators
17.
Transition duct assemblies and gas turbine engine systems involving such assemblies
Transition duct assemblies and gas turbine engine systems involving such assemblies are provided. In this regard, a representative a transition duct assembly for a gas turbine engine includes: an impingement sheet having cooling holes formed therethrough, an inlet end and a non-flanged outlet end, the impingement sheet being operative to be positioned about an exterior of a transition duct such that cooling air is directed to flow about the transition duct; the non-flanged outlet end of the impingement sheet being operative to attach the impingement sheet to the transition duct such that the inlet end is positioned adjacent to an intake end of the transition duct and the outlet end is positioned adjacent to an exhaust end of the transition duct.
A combustion duct assembly has a transition duct and a combustion liner having a hula seal at a downstream end that is forced within an inner wall of the transition duct. The combustion liner is held within the transition duct by the hula seal, but allowed to move relative to the transition duct. The combustion liner is formed with heat transfer columns adjacent the downstream end, and radially inwardly of the hula seal.
An impingement cooling sleeve includes a sleeve body having an inner surface to face a transition duct and an outer surface facing opposite the inner surface. At least one cooling hole is formed within the sleeve body and is used to direct cooling air toward the transition duct. At least one conduit member is attached to the sleeve body and is associated with the at least one cooling hole. The conduit member has a first opening to define an air inlet and a second opening to define an air outlet. In one example, the first opening is spaced apart from the outer surface of the sleeve body by a distance. In one example, the first opening comprises an annular end face surface that defines a plane that is obliquely orientated relative to the outer surface of the sleeve body.
Gas turbine engine systems involving cooling of combustion section liners are provided. In this regard, a representative liner includes: an outer side, an inner side, an upstream end and a downstream end, the outer side being configured to face away from a combustion reaction, the inner side being configured to face the combustion reaction; a cooling air channel, at least a portion of the cooling air channel being located in a vicinity of the downstream end; and cooling holes formed through the inner side of the liner, the cooling holes being in fluid communication with the cooling air channel such that cooling air provided to the cooling air channel is directed through the cooling holes and to the inner side of the liner such that at least a portion of the inner side of the liner receives cooling air despite a corresponding portion located on the outer side of the liner being obstructed from directly receiving cooling air.
