EP2735704A2 - Procédé pour modifier un plateau de connexion d'aube à aube et aube - Google Patents

Procédé pour modifier un plateau de connexion d'aube à aube et aube Download PDF

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Publication number
EP2735704A2
EP2735704A2 EP20130193500 EP13193500A EP2735704A2 EP 2735704 A2 EP2735704 A2 EP 2735704A2 EP 20130193500 EP20130193500 EP 20130193500 EP 13193500 A EP13193500 A EP 13193500A EP 2735704 A2 EP2735704 A2 EP 2735704A2
Authority
EP
European Patent Office
Prior art keywords
airfoil
shroud
bucket
end edge
relief cut
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP20130193500
Other languages
German (de)
English (en)
Other versions
EP2735704A3 (fr
Inventor
John David Ward
Kelvin Rono Aaron
James Ryan Connor
Melbourne James Myers
Brad Wilson Van Tassel
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
Original Assignee
General Electric Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Publication of EP2735704A2 publication Critical patent/EP2735704A2/fr
Publication of EP2735704A3 publication Critical patent/EP2735704A3/fr
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/005—Repairing methods or devices
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/80—Repairing, retrofitting or upgrading methods
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/307—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the tip of a rotor blade
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/332—Maximum loads or fatigue criteria
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49229—Prime mover or fluid pump making
    • Y10T29/49231—I.C. [internal combustion] engine making
    • Y10T29/49234—Rotary or radial engine making
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T83/00—Cutting
    • Y10T83/04—Processes

Definitions

  • the subject matter disclosed herein relates to turbine engines. More particularly, the subject matter relates to modifying of turbine engine parts.
  • a compressor provides pressurized air to one or more combustors wherein the air is mixed with fuel and burned to generate hot combustion gas. These gases flow downstream to one or more turbines that extract energy therefrom to produce a mechanical energy output as well as power to drive the compressor.
  • turbine parts such as parts of the turbine, may experience fatigue, due to extreme conditions within the turbine, including high temperatures and pressures caused by flow of hot gas.
  • certain turbine parts such as buckets located on a turbine rotor, may experience fatigue that requires servicing or replacement.
  • a method for modifying an airfoil shroud located at a tip of an airfoil of a airfoil, the airfoil shroud having a first end edge, a second end edge, a leading edge and a trailing edge.
  • the method includes locating a reference location in the first end edge of the airfoil shroud, the reference location being proximate a seal rail extending circumferentially from the substantially horizontal surface and forming a relief cut in the airfoil shroud to remove the reference location, wherein a modifying of the airfoil shroud is complete following forming of the relief cut.
  • a bucket to be placed on a rotor of a turbine engine includes an airfoil having an airfoil axis, a shroud disposed at a tip of the airfoil, the shroud having a first end edge, a second end edge, a leading edge and a trailing edge, a seal rail extending circumferentially from a radially outer surface of the shroud and a recess formed in the first end edge proximate the seal rail and a trailing edge of the airfoil.
  • FIG. 1 is a schematic diagram of an embodiment of a gas turbine system 100.
  • the system 100 includes a compressor 102, a combustor 104, a turbine 106, a shaft 108 and a fuel nozzle 110.
  • the system 100 may include a plurality of compressors 102, combustors 104, turbines 106, shafts 108 and fuel nozzles 110.
  • the compressor 102 and turbine 106 are coupled by the shaft 108.
  • the shaft 108 may be a single shaft or a plurality of shaft segments coupled together to form shaft 108.
  • the combustor 104 uses liquid and/or gas fuel, such as natural gas or a hydrogen rich synthetic gas, to run the turbine engine.
  • fuel nozzles 110 are in fluid communication with a fuel supply 112 and pressurized air from the compressor 102.
  • the fuel nozzles 110 create an air-fuel mix, and discharge the air-fuel mix into the combustor 104, thereby causing a combustion that creates a hot pressurized exhaust gas.
  • the combustor 104 directs the hot pressurized exhaust gas through a transition piece into a rotor and stator assembly, causing turbine 106 rotation as the gas exits nozzles where the gas is then directed to the turbine buckets or blades.
  • the rotation of the buckets coupled to the rotor in turbine 106 causes the shaft 108 to rotate, thereby compressing the air as it flows into the compressor 102.
  • a relief cut is formed in a shroud of an airfoil in the turbine engine.
  • the shroud is positioned on an airfoil such as a turbine bucket or a nozzle.
  • the relief cut is formed to modify the shroud and remove a reference location in the airfoil shroud.
  • the reference location is a flaw, such as a crack, that has been identified on the shroud.
  • the reference location may be caused by fatigue from exposure to extreme heat and pressure during turbine engine operation.
  • the relief cut is formed without welding the shroud, thus reducing incidence of additional fatigue that may be introduced to the shroud by a welding process.
  • the relief cut provides a structurally sound repair to the airfoil shroud to enable reuse and reinstallation of the airfoil following forming of the relief cut. Accordingly, the repair process provides savings in time and costs when servicing the airfoil.
  • downstream and upstream are terms that indicate a direction relative to the flow of working fluid through the turbine.
  • downstream refers to a direction that generally corresponds to the direction of the flow of working fluid
  • upstream generally refers to the direction that is opposite of the direction of flow of working fluid.
  • leading edge and “trailing edge” indicate a position of a part relative to the flow of working fluid. Specifically, a leading edge of an airfoil encounters hot gas flow before a trailing edge of the airfoil.
  • radial refers to movement or position perpendicular to an axis or center line of a reference part or assembly.
  • first component resides closer to the axis than a second component, it may be stated herein that the first component is “radially inward” of the second component. If, on the other hand, the first component resides further from the axis than the second component, it can be stated herein that the first component is “radially outward” or “outboard” of the second component.
  • axial refers to movement or position parallel to an axis.
  • circumferential refers to movement or position around an axis.
  • FIG. 2 is a side view of an airfoil 200 according to an embodiment.
  • FIG. 3 is a top view of the airfoil 200 shown in FIG. 3 .
  • a plurality of airfoils 200 is coupled to a rotor wheel in a turbine engine assembly, such as the turbine engine system 100.
  • the airfoil 200 includes a blade 202.
  • the blade 202 converts the energy of a hot gas flow 206 into tangential motion of the bucket, which in turn rotates the rotor to which the bucket is attached.
  • a seal rail 204 is provided to prevent the passage of hot gas flow 206 through a gap between the bucket tip and the inner surface of the surrounding stationary components (not shown).
  • the seal rail 204 extends circumferentially from a surface of a radially outer side 214 of a shroud 208 located at the bucket tip.
  • the shroud 208 includes the radially outer side 214 and a radially inner side 216.
  • the seal rail 204 extends circumferentially around a bucket row on the rotor, beyond the airfoil 12 sufficiently to line up with seal rails provided at the tip of adjacent buckets, effectively blocking flow from bypassing the bucket row so that airflow must be directed to the working length of the blade 202.
  • the bucket row and rotor rotate about rotor axis 212.
  • an airfoil axis 210 extends longitudinally through the blade 202.
  • the shroud 208 is a flat plate supported towards its center by the blade 202, where the shroud 208 is subject to high temperatures and centrifugal loads during turbine operation. As a result, portions of the shroud 208 may experience fatigue over time, where embodiments of the modifying process described herein repair fatigue, such as reference locations in the airfoil shroud.
  • FIG. 4 is a top view of an embodiment of an airfoil shroud 400 disposed at a tip of an airfoil as described above.
  • the airfoil shroud 400 has a leading edge 402, a trailing edge 404, a first end edge 406 and a second end edge 408 defining the shroud.
  • a seal rail 412 extends from a radially outer side 416 of the shroud in a circumferential direction from the first end edge 406 to the second end edge 408.
  • the first end edge 406 is configured to be placed adjacent the second end edge 408 of an adjacent airfoil shroud to provide a substantially continuous circumferential seal rail assembly in the turbine stage.
  • the circumferential seal rail assembly blocks hot gas flow (e.g., 206) from bypassing the bucket row so that flow is directed along a working length of the bucket airfoil.
  • the seal rail 412 has fillets 414 on each side extending from the radially outer surface 416 to provide support for the seal rail 412.
  • the reference location 410 is a crack proximate the fillet 414 of seal rail 412.
  • a relief cut may be used to repair and remove the reference location 410, as described below. The relief cut may be formed without performing a weld process on the shroud. In contrast, processes using welding to repair reference locations may adversely affect material structural regions of the airfoil shroud 400, such as fillets 414.
  • FIG. 5 is a top view of the airfoil shroud 400 following a modifying of the airfoil shroud.
  • the method for modifying the airfoil shroud 400 includes locating the reference location 410 in the first end edge 406 of the shroud.
  • the modifying also includes forming a relief cut 500 in the first end edge 406 proximate the fillet 414.
  • the relief cut 500 has any suitable geometry, such as a V-shape, parabolic, or polyhedron shape.
  • the relief cut 500 forms an arc-shaped recess.
  • the relief cut 500 may be formed using any suitable process, such as machining or drilling, to remove material including the reference location 410 from the airfoil shroud 400.
  • the airfoil shroud 400 is made from any suitable material, such as a steel alloy, stainless steel or other alloy.
  • the modifying process services or repairs the airfoil shroud 400 without a welding process, thus ensuring structural integrity is maintained in the region repaired.
  • the structural integrity provided by the relief cut 500 enables the airfoil shroud 400 to be reinstalled in the bucket row of the rotor and to withstand loads and stress caused by extreme temperatures and pressures.
  • the resulting geometry including the fillet 414 and first end edge 406, maintains structural integrity to improve part life for the shroud, thus reducing operating costs for the turbine engine.
  • repair techniques that use a welding process may further fatigue the region being repaired.
  • the service process utilizing the relief cut 500 may be used to repair a reference location located in any suitable location, such as second end edge 408, leading edge 402 and trailing edge 404.
  • the relief cut 500 may remove a portion of the fillet 414 without resulting in significant structural losses.
  • the relief cut 500 is formed along a shroud edge and outside of the fillet 414. In cases where the relief cut 500 forms an arc-shaped recess, a radius of the arc may vary depending on application needs.
  • FIG. 6 is a flow chart of an exemplary process for modifying an airfoil shroud, such as airfoil shroud 400.
  • a reference location such as a crack
  • the reference location is located in an end edge of an airfoil shroud, where the reference location is proximate a seal rail on the shroud. In embodiments, the reference location is on or proximate a fillet of the seal rail.
  • a relief cut is formed in the airfoil shroud surrounding the reference location, thus removing the reference location and repairing the shroud.
  • the airfoil with the repaired shroud is replaced in a turbine engine. In an embodiment, the airfoil is placed in a first or second stage of the turbine engine.
  • the modifying process is complete after forming the relief cut, where the modifying does not include any welding of the shroud.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP13193500.9A 2012-11-27 2013-11-19 Procédé pour modifier un plateau de connexion d'aube à aube et aube Withdrawn EP2735704A3 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/685,950 US20140147283A1 (en) 2012-11-27 2012-11-27 Method for modifying a airfoil shroud and airfoil

Publications (2)

Publication Number Publication Date
EP2735704A2 true EP2735704A2 (fr) 2014-05-28
EP2735704A3 EP2735704A3 (fr) 2017-12-13

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ID=49596166

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13193500.9A Withdrawn EP2735704A3 (fr) 2012-11-27 2013-11-19 Procédé pour modifier un plateau de connexion d'aube à aube et aube

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US (1) US20140147283A1 (fr)
EP (1) EP2735704A3 (fr)

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Publication number Priority date Publication date Assignee Title
US10486255B2 (en) * 2013-02-28 2019-11-26 United Technologies Corporation Method of short circuit pulse metal inert gas welding
US10260350B2 (en) 2014-09-05 2019-04-16 United Technologies Corporation Gas turbine engine airfoil structure
US10174617B2 (en) 2015-12-10 2019-01-08 General Electric Company Systems and methods for deep tip crack repair
US10519783B2 (en) 2016-12-22 2019-12-31 General Electric Company Method for modifying a shroud and blade
US10513934B2 (en) 2017-01-19 2019-12-24 General Electric Company Z-notch shape for a turbine blade tip shroud
US10400610B2 (en) 2017-02-14 2019-09-03 General Electric Company Turbine blade having a tip shroud notch
JP2021110291A (ja) * 2020-01-10 2021-08-02 三菱重工業株式会社 動翼、及び軸流回転機械

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US5482435A (en) * 1994-10-26 1996-01-09 Westinghouse Electric Corporation Gas turbine blade having a cooled shroud
US6490791B1 (en) * 2001-06-22 2002-12-10 United Technologies Corporation Method for repairing cracks in a turbine blade root trailing edge
US6491498B1 (en) * 2001-10-04 2002-12-10 Power Systems Mfg, Llc. Turbine blade pocket shroud
DE10328310A1 (de) * 2003-06-23 2005-01-13 Alstom Technology Ltd Verfahren zum Modifizieren der Kopplungsgeometrie bei Deckbandsegmenten von Turbinenlaufschaufeln
FR2860741B1 (fr) * 2003-10-10 2007-04-13 Snecma Moteurs Procede de reparation de pieces metalliques notamment d'aubes de turbine de moteur a turbine a gaz
US6913445B1 (en) * 2003-12-12 2005-07-05 General Electric Company Center located cutter teeth on shrouded turbine blades
US7094032B2 (en) * 2004-02-26 2006-08-22 Richard Seleski Turbine blade shroud cutter tip
US7270518B2 (en) * 2005-05-19 2007-09-18 General Electric Company Steep angle turbine cover buckets having relief grooves
US7934315B2 (en) * 2006-08-11 2011-05-03 United Technologies Corporation Method of repairing shrouded turbine blades with cracks in the vicinity of the outer shroud notch
US8807928B2 (en) * 2011-10-04 2014-08-19 General Electric Company Tip shroud assembly with contoured seal rail fillet

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Title
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Publication number Publication date
EP2735704A3 (fr) 2017-12-13
US20140147283A1 (en) 2014-05-29

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