US20140147283A1 - Method for modifying a airfoil shroud and airfoil - Google Patents

Method for modifying a airfoil shroud and airfoil Download PDF

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Publication number
US20140147283A1
US20140147283A1 US13/685,950 US201213685950A US2014147283A1 US 20140147283 A1 US20140147283 A1 US 20140147283A1 US 201213685950 A US201213685950 A US 201213685950A US 2014147283 A1 US2014147283 A1 US 2014147283A1
Authority
US
United States
Prior art keywords
airfoil
shroud
end edge
bucket
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.)
Abandoned
Application number
US13/685,950
Other languages
English (en)
Inventor
John David Ward, Jr.
Kelvin Rono Aaron
James Ryan Connor
Melbourne James Myers
Brad Wilson VanTassel
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
Priority to US13/685,950 priority Critical patent/US20140147283A1/en
Assigned to GENERAL ELECTRIC COMPANY reassignment GENERAL ELECTRIC COMPANY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: VANTASSEL, BRAD WILSON, WARD, JOHN DAVID, JR., AARON, KELVIN RONO, Connor, James Ryan, MYERS, MELBOURNE JAMES
Priority to US14/046,417 priority patent/US20140147284A1/en
Priority to EP13193500.9A priority patent/EP2735704A3/fr
Publication of US20140147283A1 publication Critical patent/US20140147283A1/en
Priority to US15/245,985 priority patent/US20160362988A1/en
Abandoned 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

  • FIG. 2 is a side view of an embodiment of a airfoil having a shroud
  • 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 .
  • 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.
  • FIG. 2 is a side view of a 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 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 .
  • 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.
  • 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 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.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US13/685,950 2012-11-27 2012-11-27 Method for modifying a airfoil shroud and airfoil Abandoned US20140147283A1 (en)

Priority Applications (4)

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
US14/046,417 US20140147284A1 (en) 2012-11-27 2013-10-04 Method for modifying an airfoil shroud
EP13193500.9A EP2735704A3 (fr) 2012-11-27 2013-11-19 Procédé pour modifier un plateau de connexion d'aube à aube et aube
US15/245,985 US20160362988A1 (en) 2012-11-27 2016-08-24 Method for modifying an airfoil shroud and airfoil

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

Related Child Applications (2)

Application Number Title Priority Date Filing Date
US14/046,417 Continuation-In-Part US20140147284A1 (en) 2012-11-27 2013-10-04 Method for modifying an airfoil shroud
US15/245,985 Continuation-In-Part US20160362988A1 (en) 2012-11-27 2016-08-24 Method for modifying an airfoil shroud and airfoil

Publications (1)

Publication Number Publication Date
US20140147283A1 true US20140147283A1 (en) 2014-05-29

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ID=49596166

Family Applications (1)

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

Country Status (2)

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

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20160001390A1 (en) * 2013-02-28 2016-01-07 United Technologies Corporation System and method low heat weld
US10174617B2 (en) 2015-12-10 2019-01-08 General Electric Company Systems and methods for deep tip crack repair
US10260350B2 (en) 2014-09-05 2019-04-16 United Technologies Corporation Gas turbine engine airfoil structure
US10400610B2 (en) 2017-02-14 2019-09-03 General Electric Company Turbine blade having a tip shroud notch
US10513934B2 (en) 2017-01-19 2019-12-24 General Electric Company Z-notch shape for a turbine blade tip shroud
US10519783B2 (en) 2016-12-22 2019-12-31 General Electric Company Method for modifying a shroud and blade
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

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5482435A (en) * 1994-10-26 1996-01-09 Westinghouse Electric Corporation Gas turbine blade having a cooled shroud
US6491498B1 (en) * 2001-10-04 2002-12-10 Power Systems Mfg, Llc. Turbine blade pocket shroud
US6490791B1 (en) * 2001-06-22 2002-12-10 United Technologies Corporation Method for repairing cracks in a turbine blade root trailing edge
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
US7509736B2 (en) * 2003-10-10 2009-03-31 Snecma Process for repairing metallic pieces especially turbine blades of a gas turbine motor
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

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE10328310A1 (de) * 2003-06-23 2005-01-13 Alstom Technology Ltd Verfahren zum Modifizieren der Kopplungsgeometrie bei Deckbandsegmenten von Turbinenlaufschaufeln
US7270518B2 (en) * 2005-05-19 2007-09-18 General Electric Company Steep angle turbine cover buckets having relief grooves

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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
US7509736B2 (en) * 2003-10-10 2009-03-31 Snecma Process for repairing metallic pieces especially turbine blades of a gas turbine motor
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
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

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20160001390A1 (en) * 2013-02-28 2016-01-07 United Technologies Corporation System and method low heat weld
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

Also Published As

Publication number Publication date
EP2735704A2 (fr) 2014-05-28
EP2735704A3 (fr) 2017-12-13

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Owner name: GENERAL ELECTRIC COMPANY, NEW YORK

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:WARD, JOHN DAVID, JR.;AARON, KELVIN RONO;CONNOR, JAMES RYAN;AND OTHERS;SIGNING DATES FROM 20121115 TO 20121126;REEL/FRAME:029354/0764

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION