WO2015106873A1 - Procédé de réparation d'un segment d'aube - Google Patents

Procédé de réparation d'un segment d'aube Download PDF

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Publication number
WO2015106873A1
WO2015106873A1 PCT/EP2014/076231 EP2014076231W WO2015106873A1 WO 2015106873 A1 WO2015106873 A1 WO 2015106873A1 EP 2014076231 W EP2014076231 W EP 2014076231W WO 2015106873 A1 WO2015106873 A1 WO 2015106873A1
Authority
WO
WIPO (PCT)
Prior art keywords
blade
platform
blade platform
remelting
side edge
Prior art date
Application number
PCT/EP2014/076231
Other languages
German (de)
English (en)
Inventor
Georg Bostanjoglo
Bernd Burbaum
Original Assignee
Siemens Aktiengesellschaft
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 Siemens Aktiengesellschaft filed Critical Siemens Aktiengesellschaft
Publication of WO2015106873A1 publication Critical patent/WO2015106873A1/fr

Links

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
    • 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
    • B23K26/00—Working by laser beam, e.g. welding, cutting or boring
    • B23K26/02—Positioning or observing the workpiece, e.g. with respect to the point of impact; Aligning, aiming or focusing the laser beam
    • B23K26/06—Shaping the laser beam, e.g. by masks or multi-focusing
    • B23K26/0604—Shaping the laser beam, e.g. by masks or multi-focusing by a combination of beams
    • B23K26/0619—Shaping the laser beam, e.g. by masks or multi-focusing by a combination of beams with spots located on opposed surfaces of the workpiece
    • 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
    • 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
    • F05D2230/234—Laser 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
    • 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
    • F05D2240/80—Platforms for stationary or moving blades
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/17—Alloys
    • F05D2300/175—Superalloys

Definitions

  • the present invention relates to a method for repairing a blade segment of a polycrystalline solidified nickel-based superalloy with at least one blade and at least one blade platform connected thereto.
  • Vane segments of the type mentioned are used in turbines as in particular, are exposed during loading ⁇ drive extreme conditions, which is associated with a high wear. Accordingly, blade segments are to be repaired or replaced at regular intervals.
  • damage to the platform side surfaces can significantly reduce the service life of a blade segment.
  • the present invention provides a method of the type mentioned, comprising the steps of: a) providing said to be repaired Schaufelseg ⁇ ments, the blade platform having at least one for worn ⁇ NEN side edge portion; b) removing at least the worn side edge portion; c) preparing a spare part, the dimensions and material in Wesent ⁇ union correspond to the dimensions and the material of the remote-side edge portion; d) positioning and prefixing the replacement part to the blade platform; and e) remelting the replacement part and blade platform material along the butt joint existing between the replacement part and the blade platform.
  • a worn side edge portion is replaced by a new side edge portion in the form of the replacement part, which is advantageously made of an identical nickel-base superalloy.
  • the replacement part in step c) is advantageously produced by means of casting, milling and / or selective laser melting (SLM). The selection of the manufacturing process may depend on ver ⁇ various factors such as the number-make spare parts with identical geometry, the complexity of the geometry of the replacement part or ⁇ same.
  • step d The prefixing of the replacement part on the blade platform in step d) takes place mechanically according to an embodiment of the present invention.
  • the prefixing takes place at least via a feather-type connecting element, which in the above in the Butt joint defining abutting edges of the spare part and the blade platform trained grooves engages, in particular to form a transition fit or a slight interference fit.
  • the connecting element is advantageously provides Herge ⁇ from a sheet metal, which serves as a weld pool during the remelting ⁇ support.
  • the at least one connecting element extends substantially centrally along the abutting edges or at half the height of the abutting edges, whereby a good pre-fixing is ensured.
  • the remelting in step e) is carried out according to a preferred embodiment of the method according to the invention using a laser beam.
  • the remelting of the laser beam is characterized in particular by the fact that the heat energy can be introduced very locally in the region of the butt joint, as a result of which appreciable component distortion can be avoided. Also conceivable is the use of an electron beam, the use of a laser beam being preferred.
  • the remelting in step e) is advantageously carried out on both sides, whereby an optimized work result is achieved.
  • the repaired component is advantageously subjected to a heat treatment which influences the component structure in order to set the desired material properties.
  • Figure 1 is a schematic perspective view of a
  • Figure 2 is a schematic perspective view of the arrangement shown in Figure 1, in which the worn side edge portion is removed and replaced by the spare part;
  • Figure 3 is an enlarged side view of the designated in Figure 2 by the reference numeral III section.
  • the blade segment 1 shows a blade segment 1, which is produced in one piece from a polycrystalline solidified nickel-base superalloy with a large proportion of intermetallic phase ( ⁇ '), in this case from Rene 80.
  • the blade segment 1 comprises a blade 2, a lower blade platform 3 and a upper blade platform 4, wherein a side edge portion 5 of the lower blade platform 3 is worn.
  • the blade segment 1 is presently designed as a vane segment. However, it should be clear that the blade segment 1 can basically also be a blade segment .
  • the worn side edge portion is separated 5 along the parting line 6 in accordance with an exporting ⁇ approximate shape of a method according to the invention, first, for which purpose any suitable separation method can be used, such as wire electrical discharge machining process, to name just one example.
  • a replacement part 7 is produced, the dimensions and material of which are substantially the same as the dimensions. gene and the material of the removed side edge portion 5 correspond.
  • the spare part as well as the blade segment 1 is made of Rene 80.
  • the production of the replacement part 7 can take place, for example, by means of casting, milling and / or selective laser melting (SLM).
  • SLM selective laser melting
  • the choice of the manufacturing process depends on various factors. In the production of a plurality of spare parts 7 with identical dimensions, in particular, the casting with subsequent mechanical reworking offers. For smaller quantities milling is economical. For the production of individual parts 7 also provides selective laser melting is an alternative.
  • the replacement part 7 receives a ⁇ fold geometry, which is why this is make simple and inexpensive near, ⁇ .
  • the replacement part 7 is positioned at the unte ⁇ ren blade platform 3 and pre-fixed at this, wherein the pre-fixing presently mechanically follows it ⁇ .
  • opposing grooves 8 and 9 are introduced into the abutting edges 10 and 11 of the replacement part 7 and the lower blade platform 3, in the formation of a transition fit or a slight press fit a feather-key connection ⁇ element 12 is inserted is, which is formed here as a continuous sheet.
  • the parts and the blade platform material along the plane formed by the abutting edges 10 and 11 butt joint using a laser beam is remelted 13, wherein the remelting takes place on both sides, as is ⁇ indicated in Figure 3 by two laser beams 13 is.
  • the blade segment 1 is subjected to a heat treatment to set a desired texture.
  • the essential advantage of the method according to the invention resides in the fact that the high-temperature properties of the nickel-base superalloy, from which both the lower blade platform, are produced by the laser beam remelting along the butt joint between the lower blade platform 3 and the replacement part 7 and the subsequent heat treatment 3 and the spare part 7 is made, can be restored ⁇ NEN. Investigations have shown that a failure of the blade segment 1 during the subsequent operation in the area of the remelted butt joint can be excluded. This is due to the fact that the remelted areas are free of pores, carbides are largely released during the remelting process and the structure solidifies with small dendrite intervals in the range of about 30 ⁇ m. The final heat treatment allows complete reconstruction of the ⁇ / ⁇ 'microstructure at Rene 80.

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Optics & Photonics (AREA)
  • Mechanical Engineering (AREA)
  • Plasma & Fusion (AREA)
  • General Engineering & Computer Science (AREA)
  • Laser Beam Processing (AREA)

Abstract

L'invention concerne un procédé de réparation d'un segment d'aube (1) en superalliage à base de nickel à solidification polycristalline, comportant au moins une aube (2) et au moins une plate-forme (3, 4) reliée à celle-ci, ledit procédé comprenant les étapes consistant à : a) fournir le segment d'aube (1) à réparer dont la plate-forme (3, 4) comporte au moins une partie de bord latérale usée (5) ; b) retirer au moins la partie de bord latérale usée (5) ; c) réaliser une pièce de remplacement (7) dont les dimensions et la matière correspondent sensiblement aux dimensions et à la matière de la partie de bord latérale (5) qui a été retirée ; d) positionner et préfixer la pièce de remplacement (7) au niveau de la plate-forme (3, 4) et e) refaire fondre la matière de la pièce de remplacement et de la plate-forme le long du joint situé entre la pièce de remplacement (7) et la plate-forme (3, 4).
PCT/EP2014/076231 2014-01-20 2014-12-02 Procédé de réparation d'un segment d'aube WO2015106873A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102014200897.2A DE102014200897A1 (de) 2014-01-20 2014-01-20 Verfahren zur Reparatur eines Schaufelsegments
DE102014200897.2 2014-01-20

Publications (1)

Publication Number Publication Date
WO2015106873A1 true WO2015106873A1 (fr) 2015-07-23

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2014/076231 WO2015106873A1 (fr) 2014-01-20 2014-12-02 Procédé de réparation d'un segment d'aube

Country Status (2)

Country Link
DE (1) DE102014200897A1 (fr)
WO (1) WO2015106873A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114515837A (zh) * 2022-04-21 2022-05-20 北京煜鼎增材制造研究院有限公司 一种单晶涡轮叶片叶尖的激光选区熔化修复方法

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0596796A1 (fr) * 1992-11-04 1994-05-11 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Procédé d'assemblage par soudage d'un disque garni d'ailettes par faisceau d'énergie
US6238187B1 (en) * 1999-10-14 2001-05-29 Lsp Technologies, Inc. Method using laser shock peening to process airfoil weld repairs pertaining to blade cut and weld techniques
US6568077B1 (en) * 2000-05-11 2003-05-27 General Electric Company Blisk weld repair

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH09168927A (ja) * 1995-12-19 1997-06-30 Hitachi Ltd ガスタービン用動翼，静翼の補修方法
DE102005032739B3 (de) * 2005-07-08 2007-03-22 Siemens Ag Fügeverfahren
US7648341B2 (en) * 2005-12-23 2010-01-19 Sulzer Hickham Industries, Inc. Process for restoring a turbine blade
EP2078579A1 (fr) * 2008-01-10 2009-07-15 Siemens Aktiengesellschaft Procédé de soudage d'un composant et composant doté d'emplacements de soudure et de brasure

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0596796A1 (fr) * 1992-11-04 1994-05-11 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Procédé d'assemblage par soudage d'un disque garni d'ailettes par faisceau d'énergie
US6238187B1 (en) * 1999-10-14 2001-05-29 Lsp Technologies, Inc. Method using laser shock peening to process airfoil weld repairs pertaining to blade cut and weld techniques
US6568077B1 (en) * 2000-05-11 2003-05-27 General Electric Company Blisk weld repair

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114515837A (zh) * 2022-04-21 2022-05-20 北京煜鼎增材制造研究院有限公司 一种单晶涡轮叶片叶尖的激光选区熔化修复方法

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DE102014200897A1 (de) 2015-07-23

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