US20050235492A1 - Turbine airfoil trailing edge repair and methods therefor - Google Patents

Turbine airfoil trailing edge repair and methods therefor Download PDF

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Publication number
US20050235492A1
US20050235492A1 US10/829,281 US82928104A US2005235492A1 US 20050235492 A1 US20050235492 A1 US 20050235492A1 US 82928104 A US82928104 A US 82928104A US 2005235492 A1 US2005235492 A1 US 2005235492A1
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US
United States
Prior art keywords
coupon
trailing edge
airfoil
pressure
side wall
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
US10/829,281
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English (en)
Inventor
Brian Arness
Graham Sherlock
Joseph Moroso
Stewart Beitz
Graydon Peters
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
Individual
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 Individual filed Critical Individual
Priority to US10/829,281 priority Critical patent/US20050235492A1/en
Assigned to GENERAL ELECTRIC COMPANY reassignment GENERAL ELECTRIC COMPANY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: ARNESS, BRIAN PETER, BEITZ, STEWART WILLIAM, MOROSO, JOSEPH LEONARD, PETERS, GRAYDON WAYNE, SHERLOCK, GRAHAM DAVID
Priority to FR0503397A priority patent/FR2869250B1/fr
Priority to GB0507906A priority patent/GB2413599B/en
Priority to JP2005123330A priority patent/JP2005307983A/ja
Priority to CNB2005100696343A priority patent/CN100422508C/zh
Publication of US20050235492A1 publication Critical patent/US20050235492A1/en
Priority to US11/723,742 priority patent/US20070184182A1/en
Priority to US11/723,739 priority patent/US7484928B2/en
Abandoned legal-status Critical Current

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P6/00—Restoring or reconditioning objects
    • B23P6/002—Repairing turbine components, e.g. moving or stationary blades, rotors
    • B23P6/005—Repairing turbine components, e.g. moving or stationary blades, rotors using only replacement pieces of a particular form
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P6/00—Restoring or reconditioning objects
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K9/00—Arc welding or cutting
    • B23K9/0026—Arc welding or cutting specially adapted for particular articles or work
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
    • B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
    • B23P15/04—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
    • 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
    • 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
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K2101/00—Articles made by soldering, welding or cutting
    • B23K2101/001—Turbines
    • 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
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • 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
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/202—Heat transfer, e.g. cooling by film cooling
    • 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
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
    • 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
    • Y10T29/49316—Impeller making
    • Y10T29/49318—Repairing or disassembling
    • 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
    • Y10T29/49718—Repairing
    • Y10T29/49721—Repairing with disassembling
    • Y10T29/4973—Replacing of defective part

Definitions

  • the present invention relates to a repair of the trailing edge of an airfoil and particularly relates to a coupon having a trailing edge cooling configuration for replacement of a damaged trailing edge portion of a nozzle airfoil for a gas turbine.
  • the present invention also relates to methods for repairing the trailing edge portion of the airfoil.
  • one such cooling system includes a plurality of radially spaced apertures opening through the trailing edge in combination with radially spaced film cooling holes axially spaced from and adjacent the trailing edge.
  • the film cooling holes are provided along the pressure side, i.e., the hotter side, of the airfoil for film cooling the remaining trailing edge surfaces.
  • Airfoils with such advanced cooling configurations have been provided in gas turbines and have extended the operating life of the turbine nozzles to nearly twice the operating hours of prior cooling configurations.
  • the gas turbines may be operated, e.g., by a utility, for a significantly longer period of time before maintenance is required with the attendant cost advantages not only in terms of turbine efficiency but also turbine downtime.
  • Turbine airfoils have also been previously repaired by replacing damaged trailing edge portions with a new replacement trailing edge portion. Coupons which constitute a replacement trailing edge portion for a nozzle airfoil have previously been welded to the remaining leading and intermediate sections of an airfoil where the damaged trailing edge sections of the airfoil have been removed. Trailing edge coupons, however, have not heretofore been utilized to significantly extend the operating life of the turbine airfoil as they have lacked the required cooling configurations. The nozzles in current use have only a limited number of hours of operation before the airfoils of those nozzles are so severely damaged as to marginalize the efficiency of the turbine and require repair. For example, many existing turbines have airfoils with a 24,000 hour operation capability.
  • Nozzle airfoils are typically provided in a plurality of nozzle segments arranged in a circumferential array about the turbine axis. Each segment includes inner and outer bands or platforms between which extend one or more nozzle vanes, i.e., airfoils.
  • the segments are typically cast of expensive materials. While it is possible to replace the nozzle segments in their entirety with new nozzles, segments having improved cooling configurations permitting longer term operation, such replacement nozzle segments are prohibitively costly particularly in view of the materials and machining necessary to effect that replacement. Accordingly, there is a need for a trailing edge coupon and a method of repairing turbine airfoils which will extend the operating life of the repaired nozzles beyond the life cycle of the nozzle airfoils originally provided in the turbine.
  • a trailing edge coupon having enhanced cooling capability for use as a replacement for a damaged trailing edge portion of a nozzle airfoil enabling an airfoil repair to increase the operating life cycle of the turbine nozzle.
  • the trailing edge coupon includes a plurality of film cooling holes generally radially spaced from one another along a pressure side of the coupon together with a plurality of radially spaced openings through the trailing edge.
  • a plurality of radially spaced ribs extend between opposite pressure and suction sides of the coupon and forward edges of the coupon are chamfered for welding to remaining portions of nozzle airfoil from which the damaged trailing edge section has been removed.
  • the upgraded airfoil has a cooling configuration corresponding to newer airfoil configurations with advanced cooling configurations enabling extended operating life of the nozzle segments.
  • an article for repairing turbine nozzle segments each having an airfoil between inner and outer platforms with a trailing edge portion of the airfoil removed leaving intermediate and leading edge portions of the airfoil between the platforms comprising: a trailing edge coupon having pressure and suction side wall portions; a plurality of film cooling holes generally radially spaced one from the other along the pressure side wall portion of the coupon, the coupon including a trailing edge having a plurality of radially spaced openings and a plurality of radially spaced ribs extending between opposite pressure and suction sides of the coupon, edges of the pressure and suction side wall portions being chamfered for welding to pressure and suction side wall portions of the intermediate portion of the airfoil.
  • a repaired turbine nozzle comprising: leading edge and intermediate airfoil sections and inner and outer platforms forming remaining portions of a nozzle segment having a removed damaged trailing edge section; a trailing edge coupon having a trailing edge, pressure and suction side wall portions, a plurality of film cooling holes generally radially spaced one from the other along a pressure side wall portion of the coupon, a plurality of radially spaced openings along the trailing edge, and a plurality of radially spaced ribs extending between opposite pressure and suction sides of the airfoil, welds along opposite pressure and suction side edges of the remaining section and respective pressure and suction side edges of the trailing edge coupon whereby the remaining section and the coupon form a complete airfoil between the inner and outer platforms.
  • a method of repairing an airfoil of a turbine nozzle segment comprising the steps of: (a) removing a damaged trailing edge portion of the airfoil leaving a remaining airfoil section including leading edge and intermediate sections; (b) providing a trailing edge coupon having pressure and suction side wall portions, a plurality of film cooling holes generally radially spaced one from the other along a pressure side wall portion of the coupon and a plurality of radially spaced openings and a plurality of radially spaced ribs extending between opposite pressure and suction sides of the airfoil; and (c) welding along opposite pressure and suction sides of each the remaining airfoil section and the coupon respectively to secure the coupon to the remaining airfoil section.
  • FIG. 1 is a fragmentary axial view of a plurality of nozzle segments forming part of an annular array of nozzles for a turbine stage;
  • FIG. 2 is a side elevational view of a nozzle segment installed between portions of an inner and outer casing
  • FIG. 3 is an enlarged cross-sectional view through the airfoils of a nozzle segment illustrating a coupon welded to a reusable portion of the original airfoil;
  • FIG. 4 is an enlarged cross-sectional view of the coupon for repairing the nozzle airfoil
  • FIG. 5 is an enlarged side elevational view of the coupon of FIG. 4 ;
  • FIG. 6 is an enlarged view of the film cooling holes along the pressure side of the coupon.
  • FIGS. 7-9 are schematic illustrations of the manner of repairing the nozzle airfoil.
  • each of the segments 10 includes one or more nozzle vanes or airfoils 12 which extend between an inner platform 14 and outer platform 16 .
  • the nozzle airfoils 12 as well as the platforms 14 and 16 define in part a generally axially extending hot gas path through the turbine as well as defining a portion of a turbine stage.
  • FIGS. 2 and 3 the nozzle segments 10 are illustrated in greater particularity.
  • each segment 10 may include one or more airfoils between the platforms.
  • FIG. 2 Also illustrated in FIG. 2 is an retaining ring 20 to which the nozzle segment is secured and an inner support ring 22 having a slot 24 for receiving a radially inwardly extending rail 26 of the inner platform 14 for securing the nozzle segment against axial movement in an aft direction.
  • the nozzle airfoils 12 frequently become cracked and oxidized in use and must be replaced. It will be appreciated that to replace the nozzle segments in their entirety is not cost effective in view of the cost of the segments and involved labor, as well as the downtime required for replacement. Moreover, replacement of worn nozzle airfoils with new airfoils typically leads to similar cracking and oxidation over time necessitating replacement once again over a similarly limited operating cycle. Consequently, there is a need for an effective repair which will not only reduce repair costs but will also extend the life of the nozzle airfoil to a greater extent that the original airfoil.
  • the portion of the nozzle airfoil subjected to the majority of the cracking and oxidation is the trailing edge region. Regions of the nozzle airfoil forward of the trailing edge region are not subjected to the same magnitude of cracking and oxidation and therefore have extended life as compared with the trailing edge region. As a consequence, it is possible to remove the damaged trailing edge portion of the nozzle airfoil and replace that portion with a trailing edge portion or coupon which has improved cooling characteristics enabling the life of the repaired nozzle airfoil to be extended significantly beyond the life of the original airfoil, e.g., twice the life of the original airfoil.
  • a trailing edge coupon 30 is provided having pressure and suction side wall portions 32 and 34 respectively terminating in a trailing edge 36 .
  • Coupon 30 constitutes a replacement for a removed damaged trailing edge portion of the original airfoil.
  • the coupon 30 is provided with a cooling configuration which slows the rate of oxidation of the trailing edge of the repaired airfoil and hence the coupon therefore enables the repaired airfoil to have an extended operating life cycle. While the cooling configuration of the coupon 30 is similar to the cooling configuration of original airfoils currently in use, those cooling configurations have not heretofore been utilized in a coupon for repair of damaged nozzle airfoils.
  • the coupon 30 includes a plurality of ribs 38 which extend in the trailing edge region 40 at generally radially spaced positions between the pressure and suction sides 32 and 34 respectively.
  • the radial spacing between the ribs 38 forms radially spaced flow channels for directing cooling air from the interior of the repaired airfoil in a generally axially aft direction for reception in a plenum 42 .
  • Plenum 42 extends substantially radially between the inner and outer extremities of the nozzle airfoil.
  • a plurality of radially spaced passages 44 are in communication with the plenum 42 and extend in a generally axial direction terminating in exit apertures in the trailing edge 36 of the coupon 30 .
  • cooling air flowing within the repaired airfoil flows generally in an axial direction through the channels between the ribs 38 for convectively cooling the sides of the airfoil and exits into the plenum 42 .
  • the cooling air is then discharged through the passages 44 and the trailing edge 36 cooling the opposite sides of the airfoil as the air traverses from plenum 42 to the trailing edge 36 .
  • a plurality of generally spaced film cooling holes 46 Cooling air within the repaired airfoil also flows through the film cooling holes 46 and along the pressure side wall 32 of the repaired airfoil to film cool the pressure side trailing edge region.
  • the film cooling holes 46 have external surfaces along the pressure side which are flared as indicated at 48 in FIG. 6 .
  • the flare enlarges in the radial and axially aft directions such that the film of cooling air is distributed to overlie substantially the entirety of the pressure side surface of the trailing edge region 40 to the trailing edge 36 .
  • the nozzle segments are removed from the turbine.
  • the damaged trailing edge regions 50 of the airfoils of the removed segments are removed from the airfoils 12 .
  • the airfoils are cut along both the pressure and suction sides a predetermined distance from the trailing edge and are also cut along the juncture of the trailing edge region being removed and the inner and outer platforms 14 and 16 , respectively.
  • the cutting may be effected by a water jet cutter, wire EDM or a plasma torch as schematically illustrated at 52 in FIG. 7 .
  • the trailing edge region 50 which has been damaged is thus removed as illustrated in FIG. 8 leaving discrete edges along the pressure and suction sides of the original airfoil. Those edges are cleaned and shaped to receive corresponding edges 54 and 56 ( FIG. 4 ) of the coupon 30 .
  • the remaining portions of the airfoil include leading edge of intermediate portions 53 and 55 , respectively.
  • the coupon 30 is disposed between the inner and outer platforms and the pressure and suction side edges 54 and 56 are welded to the pressure and suction side edges of the remaining portion of the airfoil to form a repaired airfoil having the same aerodynamic configuration as the original airfoil. Additionally, however, it will be appreciated that the cooling configuration of the trailing edge of the repaired airfoil has been changed by the removal of the damaged trailing edge region 50 and the addition of the coupon 30 with the aforedescribed cooling configuration.
  • the weld-up of the coupon 30 to the remaining portion of the airfoil may be accomplished for example by a TIG welding process.
  • the welds 57 proceed along the opposite sides of the airfoil between the inner and outer platforms and also between the radial outer and inner edges of the coupon and the outer and inner platforms.
  • the welds are cleaned to provide a smooth surface and fillets 59 ( FIG. 9 ) are applied as necessary and blended with the repaired airfoils having the advanced cooling configuration in each of these segments.
  • the segments are then replaced into the turbine. Because of the new cooling configuration provided by the coupon repair, the operating life cycle of the nozzle airfoils is significantly increased. Cracking and oxidation are reduced and the interval between repairs is greatly increased, e.g., by a factor of two.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Plasma & Fusion (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US10/829,281 2004-04-22 2004-04-22 Turbine airfoil trailing edge repair and methods therefor Abandoned US20050235492A1 (en)

Priority Applications (7)

Application Number Priority Date Filing Date Title
US10/829,281 US20050235492A1 (en) 2004-04-22 2004-04-22 Turbine airfoil trailing edge repair and methods therefor
FR0503397A FR2869250B1 (fr) 2004-04-22 2005-04-06 Reparation du bord de fuite d'une aube profilee de turbine et procedes a cet effet
GB0507906A GB2413599B (en) 2004-04-22 2005-04-19 Turbine airfoil trailing edge repair and methods therefor
JP2005123330A JP2005307983A (ja) 2004-04-22 2005-04-21 タービン翼形部後縁の補修及びその方法
CNB2005100696343A CN100422508C (zh) 2004-04-22 2005-04-22 涡轮机翼片尾缘修理及其方法
US11/723,742 US20070184182A1 (en) 2004-04-22 2007-03-21 Method of repairing the turbine airfoil nozzle segment
US11/723,739 US7484928B2 (en) 2004-04-22 2007-03-21 Repaired turbine nozzle

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US10/829,281 US20050235492A1 (en) 2004-04-22 2004-04-22 Turbine airfoil trailing edge repair and methods therefor

Related Child Applications (2)

Application Number Title Priority Date Filing Date
US11/723,739 Division US7484928B2 (en) 2004-04-22 2007-03-21 Repaired turbine nozzle
US11/723,742 Division US20070184182A1 (en) 2004-04-22 2007-03-21 Method of repairing the turbine airfoil nozzle segment

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US20050235492A1 true US20050235492A1 (en) 2005-10-27

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US10/829,281 Abandoned US20050235492A1 (en) 2004-04-22 2004-04-22 Turbine airfoil trailing edge repair and methods therefor
US11/723,742 Abandoned US20070184182A1 (en) 2004-04-22 2007-03-21 Method of repairing the turbine airfoil nozzle segment
US11/723,739 Expired - Fee Related US7484928B2 (en) 2004-04-22 2007-03-21 Repaired turbine nozzle

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US11/723,742 Abandoned US20070184182A1 (en) 2004-04-22 2007-03-21 Method of repairing the turbine airfoil nozzle segment
US11/723,739 Expired - Fee Related US7484928B2 (en) 2004-04-22 2007-03-21 Repaired turbine nozzle

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US (3) US20050235492A1 (enrdf_load_stackoverflow)
JP (1) JP2005307983A (enrdf_load_stackoverflow)
CN (1) CN100422508C (enrdf_load_stackoverflow)
FR (1) FR2869250B1 (enrdf_load_stackoverflow)
GB (1) GB2413599B (enrdf_load_stackoverflow)

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US20070011872A1 (en) * 2005-07-15 2007-01-18 United Technologies Corporation System and method for repairing a gas turbine engine component
US20090165275A1 (en) * 2007-12-29 2009-07-02 Michael Scott Cole Method for repairing a cooled turbine nozzle segment
US20090169361A1 (en) * 2007-12-29 2009-07-02 Michael Scott Cole Cooled turbine nozzle segment
US20090165301A1 (en) * 2007-12-29 2009-07-02 General Electric Company Method for Repairing a Turbine Nozzle Segment
WO2013134181A1 (en) * 2012-03-05 2013-09-12 General Electric Company Turbine diaphragm airfoil, diaphragm assembly, and method of repair
US20170370221A1 (en) * 2016-06-24 2017-12-28 General Electric Company Methods for repairing a damaged component of an engine
US9926785B2 (en) * 2013-03-19 2018-03-27 Ansaldo Energia Ip Uk Limited Method for reconditioning a hot gas path part of a gas turbine
EP3287594A3 (en) * 2016-07-08 2018-06-20 General Electric Company Coupon for hot gas path component having manufacturing assisting features
US10815782B2 (en) * 2016-06-24 2020-10-27 General Electric Company Methods for repairing airfoil trailing edges to include ejection slots therein

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DE102006034055A1 (de) * 2006-07-20 2008-01-24 Mtu Aero Engines Gmbh Verfahren zur Reparatur eines Leitschaufelsegments für ein Strahltriebwerk
US8887390B2 (en) 2008-08-15 2014-11-18 Dresser-Rand Company Method for correcting downstream deflection in gas turbine nozzles
US7934302B2 (en) 2008-12-31 2011-05-03 General Electric Company Apparatus and method for removing compressor blades
US8123474B2 (en) * 2009-05-12 2012-02-28 Dresser-Rand Company Repair of industrial gas turbine nozzle diaphragm packing
FR2954200B1 (fr) * 2009-12-23 2012-03-02 Snecma Procede de realisation d'un renfort metallique d'aube de turbomachine
US8671691B2 (en) 2010-05-26 2014-03-18 General Electric Company Hybrid prefilming airblast, prevaporizing, lean-premixing dual-fuel nozzle for gas turbine combustor
US8814510B2 (en) * 2010-12-21 2014-08-26 Hamilton Sundstrand Corporation Turbine nozzle for air cycle machine
US8790084B2 (en) 2011-10-31 2014-07-29 General Electric Company Airfoil and method of fabricating the same
US9765623B2 (en) 2013-07-23 2017-09-19 General Electric Company Methods for modifying cooling holes with recess-shaped modifications
US9416667B2 (en) 2013-11-22 2016-08-16 General Electric Company Modified turbine components with internally cooled supplemental elements and methods for making the same
US10766105B2 (en) 2015-02-26 2020-09-08 Rolls-Royce Corporation Repair of dual walled metallic components using braze material
US10450871B2 (en) 2015-02-26 2019-10-22 Rolls-Royce Corporation Repair of dual walled metallic components using directed energy deposition material addition
WO2017095438A1 (en) * 2015-12-04 2017-06-08 Siemens Aktiengesellschaft Turbine airfoil with biased trailing edge cooling arrangement
US20180010457A1 (en) * 2016-07-08 2018-01-11 General Electric Company Coupon for hot gas path component having manufacturing assist features
US10544683B2 (en) 2016-08-30 2020-01-28 Rolls-Royce Corporation Air-film cooled component for a gas turbine engine
US20180073390A1 (en) 2016-09-13 2018-03-15 Rolls-Royce Corporation Additively deposited gas turbine engine cooling component
US10689984B2 (en) 2016-09-13 2020-06-23 Rolls-Royce Corporation Cast gas turbine engine cooling components
US11338396B2 (en) 2018-03-08 2022-05-24 Rolls-Royce Corporation Techniques and assemblies for joining components
US11090771B2 (en) 2018-11-05 2021-08-17 Rolls-Royce Corporation Dual-walled components for a gas turbine engine
US11305363B2 (en) 2019-02-11 2022-04-19 Rolls-Royce Corporation Repair of through-hole damage using braze sintered preform
KR102626244B1 (ko) * 2019-07-30 2024-01-17 지멘스 에너지, 인코포레이티드 고온 가스 터빈 컴포넌트들을 보수하기 위한 시스템 및 방법
US11692446B2 (en) 2021-09-23 2023-07-04 Rolls-Royce North American Technologies, Inc. Airfoil with sintered powder components

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US20070184182A1 (en) 2007-08-09
US7484928B2 (en) 2009-02-03
CN1721660A (zh) 2006-01-18
CN100422508C (zh) 2008-10-01
FR2869250A1 (fr) 2005-10-28
FR2869250B1 (fr) 2007-04-13
US20070172351A1 (en) 2007-07-26
GB2413599B (en) 2009-03-18
GB2413599A (en) 2005-11-02
JP2005307983A (ja) 2005-11-04

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