WO2016096382A1 - Procédé de réparation de dommages au niveau d'une aube de turbine au moyen de gabarits - Google Patents

Procédé de réparation de dommages au niveau d'une aube de turbine au moyen de gabarits Download PDF

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Publication number
WO2016096382A1
WO2016096382A1 PCT/EP2015/078014 EP2015078014W WO2016096382A1 WO 2016096382 A1 WO2016096382 A1 WO 2016096382A1 EP 2015078014 W EP2015078014 W EP 2015078014W WO 2016096382 A1 WO2016096382 A1 WO 2016096382A1
Authority
WO
WIPO (PCT)
Prior art keywords
turbine blade
damage
template
repair piece
piece
Prior art date
Application number
PCT/EP2015/078014
Other languages
German (de)
English (en)
Inventor
Martin Bremer
Matthias Kuhlee
Britta Laux
Uwe Paul
Radan RADULOVIC
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 WO2016096382A1 publication Critical patent/WO2016096382A1/fr

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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
    • 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
    • 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
    • F05D2230/22—Manufacture essentially without removing material by sintering
    • 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

Definitions

  • the invention relates to a method for repairing damage to a turbine blade.
  • a turbine blade usually consists of a profiled wing, which is closed at both ends in each case by a platform.
  • a metal usually a nickel-based alloy.
  • Each turbine stage consists of a set of vanes and a set of blades, wherein in each set the blades of the turbine blade are arranged in a spoke shape to each other, and the platforms of Turbinenschau ⁇ blades of a set each form an inner or an outer ring.
  • the vanes are arranged stationary in the turbine, the individual blades of the same turbine stage are mutually rigidly mounted, and rotatably mounted as a common set with respect to the axis of the gas turbine.
  • the invention is therefore based on the object to provide a method for repairing damage to a turbine blade, which takes into account the material structure of the turbine blade and should be feasible as inexpensively.
  • the invention further has for its object to provide a turbine blade which can be used following damage again for high performance applications.
  • the first object is achieved by a method for repairing damage to a turbine blade, wherein a predefined template is cooperatege ⁇ provides, which completely covers at least the damage, wherein in the region of damage, the material of the turbine blade to form a Abtragungs Schemees with a through the Sten predetermined form is removed and thereby at least the damage is removed in the ablation region, wherein a repair piece in the form of the template is inserted into the Abtragungs Scheme, and wherein the repair piece is connected to the turbine blade on ei ⁇ ner limited by the ablation region surface.
  • Advantageous and partly inherently inventive embodiments of the method are the subject of the dependent claims.
  • the second object is achieved by a turbine blade with a removal area and a in a form-fitting inserted stencil-like repair piece, which is connected to the turbine blade at a limited by the ablation area surface.
  • the damage is present a deviation from a preferably defined by the condition of the turbine blade prior to commissioning local target geometry.
  • the BE ⁇ reittakede template is present as a geometrical ⁇ ULTRASONIC patterns understood that at the surface of the turbine blade in the region of the damage can reproduce local Sollgeo ⁇ metry.
  • the at least complete covering of the damage by the template is in this sense understood that the geometrically reproduced by the template geometric pattern in a correct positioning in the region of damage this is completely covered in the geometric pattern. This means that by a decision-fernung of the material of the turbine blade in the area of Be ⁇ damage in the form imposed by the template as well as the damage is also removed.
  • the damage may be on a platform of the turbine blade, and in particular, the damage includes corrosion of the material of the turbine blade at the corresponding location.
  • the invention proceeds from the consideration that due to the high demands on the strength and the heat resistance of a turbine blade, the repair of a BeC ⁇ ending has to be made such that it at the repaired place the material structure of the turbine blade before the smallest possible deviation from the condition the start-up would take should have, and on the other hand, a nachträg ⁇ Liche heat protection coating is again possible, if necessary.
  • a common practice in repairing components of gas turbines is to use a presintered preform ("pre-sintered preform").
  • the template is provided by selecting from a plurality of predetermined, mutually different templates.
  • the Beby-digun ⁇ conditions can each vary more.
  • Pretending mutually different templates and the ability to select for the repair of a single damage a particular template from this makes it possible to react flexibly when repairing the possible local differences in BeCdi ⁇ supply, and at the same time take advantage of a series of prefabrication in claim to be able to.
  • the material of the turbine blade is removed in the region of the damage by means of spark erosion. Spark erosion allows the removal of metal with a precision of a few micrometers. Thereby, the denudation can be adapted to the repair piece supply area particularly accurately so that subsequently reaches a particularly firm Ver ⁇ tying the repair piece to the turbine who can ⁇ .
  • the material of the turbine blade in the area of the Be ⁇ damage by means of mechanical milling and / or laser cutting is removed. By milling can be removed relatively quickly and energetically favorable ver ⁇ tively large amounts of material.
  • the laser cutting is in particular advantageous if a removal area comprises the full thickness of a portion of the turbine blade to be repaired, for example, the platform, so that the supply area Abtra ⁇ manufacturedge ⁇ can be easily separated by means of laser cutting.
  • a removal area comprises the full thickness of a portion of the turbine blade to be repaired, for example, the platform, so that the supply area Abtra ⁇ manufacturedge ⁇ can be easily separated by means of laser cutting.
  • the said processes can also be combined to remove the material.
  • a pre-sintered preform is recognized as ⁇ repair piece.
  • a PSP be ⁇ stands typically consist of a mixture of a metalli ⁇ rule granules with a solder with a proportion of the granules of 40-75 wt .-%, preferably 50-65 wt .-%, by weight and a Lotanteil of 25-60. -%, preferably 35-50 wt .-%.
  • the granules and the solder are sintered in the PSP to a solid shape, so that the remaining during the sintering process microscopic spaces between the metallic granules are filled by the solder.
  • Preferred repair piece of the metal granules is in this case matched to the material of the turbine blade with respect to the intrinsic properties ⁇ during joining in the case of egg ner PSP. Particularly preferred is the granules of an alloy of components included in the material of the turbine blade.
  • the touchup ⁇ piece is preferably made of the same material as the turbine show ⁇ fel.
  • one of the two options is also selected according to time, energy and cost parameters, the latter may also depend on the geometry of the damage.
  • a patching piece of a fully crystalline material has in itself a higher Fes ⁇ ACTION to as a PSP, but the quality or strength of the connection between the repair piece and the turbine blade due to the higher strength is also higher by the geometry of the surface of the ablation preparation ⁇ ches Depending on which the patch has contact with the turbine blade, which may possibly speak for a PSP in individual cases.
  • the off ⁇ improvement piece is connected to the turbine blade by welding and / or brazing and / or sintering.
  • combinations of the mentioned process techniques are also advantageous.
  • the selection and possibly the sequence of the or each process for connecting the repair piece to the turbine blade is preferably adapted to the material and the internal structure of the repair piece.
  • the strength of the compound to be achieved by this first step should preferably favor a further step.
  • the repair piece is first connected to the turbine blade at a number of isolated locations on the surface defined by the ablation area by spot welding, in particular resistance spot welding, and then the repair piece is connected to the rest of the area delimited by the ablation area in a soldering process with the turbine blade ,
  • spot welding here has the advantage that at the welding points already a compound of high strength ent ⁇ stands, so that the repair piece is fixed sufficiently for the subsequent soldering in the removal area.
  • the soldering process is preferably adapted to the material and the internal structure of the repair piece.
  • FIG. 1 shows a schematic diagram of the sequence of a method 1 for repairing a damage 2 at a
  • Turbine blade 4 shown.
  • the turbine blade 4 has a platform 6 and a seated on the platform 6 profiled wing 8.
  • the material is locally corroded, which has caused damage 2.
  • the damage 2 to the platform 6 is now to be repaired by the material of the platform ⁇ form 6 is removed in this area, and then new ⁇ material used in the resulting gap, and is connected to the material of the platform 6.
  • a stencil 12 is selected for the form ei ⁇ nes repair piece 14 of the employed material from ⁇ .
  • a template 12 for the material to be removed in the region of the damage 2 to the platform 6 is assumed by a plurality of predetermined, mutually different shapes for the individual templates 12 and thus for the shape of the possible repair ⁇ piece 14. From this plurality of possible template shapes 12, the one which on the one hand completely covers the damage 2 and which on the other hand minimizes the material to be removed on the platform 6 in the region of the damage 2, in order to arrive there on a shape complementary to the selected template.
  • the template 12b would not be sufficient to completely cover the damage 2, since in a material removal on the platform 6 according to the template 12b, the damage 2 further into the depth would be enough.
  • the selection mask 12a would certainly guaranteed ⁇ provide that, with a corresponding removal of the material of the platform 6, the damage 2 would be removed completely, but this is ensured even when using the template 12c. Since only a smaller area of undamaged material of the platform 6 is removed with a removal according to the template 12c than with a removal according to the template 12a, the template 12c is selected for the further course of the method.
  • 16 18 or 20 laser cutting the material of the platform 6 will be removed in the area around the damaged or removed 2 around such that a mask 12c for Komple ⁇ mentärer removal area arises 22nd
  • the repair piece 14 can be present as a PSP 24, in which a
  • the Ausbesse ⁇ extension piece 14 also in the form of a fully crystalline material.
  • the Ausbesse ⁇ extension piece 14 is now inserted into the removal area 22, where it is connected with the platform 6 at the Abtragungsbe ⁇ rich 22 bounding surface 28th
  • the repair piece 14 is firstly fastened at isolated locations of the surface 28 delimiting the removal area 22 by means of resistance spot welding 30.
  • resistance spot welding 30 By the individual weld spots of resistance spot welding 30, a sufficient fixing of the repair pad 14 in Abtra ⁇ supply region 22 is ensured for the final bonding process.
  • the repair piece 14 is involved in a soldering process 32 under the action of pressure and heat joined the platform 6. If the repair piece 14 is given as a PSP 24, the solder processed in the PSP for the soldering process 32 is sufficient. If the Ausbesse ⁇ extension piece 14 of a fully crystalline material 26, then at the limiting this surface preferably also apply an additional solder 28 prior to insertion of the repair pad 14 in the supply area Abtra ⁇ 22nd

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne un procédé (1) de réparation de dommages (2) au niveau d'une aube de turbine (4). Un gabarit prédéfini (12c) est prévu qui recouvre complètement au moins le dommage (2). Dans la zone du dommage (2), on retire de la matière de l'aube de turbine (4) pour former une zone d'ablation (22) ayant une forme prescrite par le gabarit (12c) et on dissout ainsi au moins le dommage (2) dans la zone d'ablation (22). On insère un élément de réparation (14) avec la forme du gabarit (12c) dans la zone d'ablation (22) et on relie l'élément de réparation (14) à l'aube de turbine (4) au niveau d'une surface (28) délimitée par la zone d'ablation (22). L'invention concerne en outre une aube de turbine (4) pourvue d'une zone d'ablation (22) et d'un élément de réparation (14) de type gabarit qui est inséré à l'intérieur par complémentarité de formes et qui est relié à l'aube de turbine (4) au niveau d'une surface (28) délimitée par la zone d'ablation (22).
PCT/EP2015/078014 2014-12-16 2015-11-30 Procédé de réparation de dommages au niveau d'une aube de turbine au moyen de gabarits WO2016096382A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102014226055.8A DE102014226055A1 (de) 2014-12-16 2014-12-16 Verfahren zum Ausbessern einer Beschädigung an einer Turbinenschaufel
DE102014226055.8 2014-12-16

Publications (1)

Publication Number Publication Date
WO2016096382A1 true WO2016096382A1 (fr) 2016-06-23

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PCT/EP2015/078014 WO2016096382A1 (fr) 2014-12-16 2015-11-30 Procédé de réparation de dommages au niveau d'une aube de turbine au moyen de gabarits

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DE (1) DE102014226055A1 (fr)
WO (1) WO2016096382A1 (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10502058B2 (en) 2016-07-08 2019-12-10 General Electric Company Coupon for hot gas path component having manufacturing assist features
US10875128B2 (en) 2015-05-20 2020-12-29 Rolls-Royce Corporation Pre-sintered preform braze for joining alloy castings
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
US11692446B2 (en) 2021-09-23 2023-07-04 Rolls-Royce North American Technologies, Inc. Airfoil with sintered powder components

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102017200333A1 (de) * 2017-01-11 2018-07-12 Siemens Aktiengesellschaft Verfahren zum Verschließen einer länglich ausgebildeten Durchgangsöffnung eines Werkstücks
FR3135220A1 (fr) * 2022-05-06 2023-11-10 École Centrale De Nantes Procédé et système de réparation d’un objet

Citations (3)

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Publication number Priority date Publication date Assignee Title
GB1269598A (en) * 1970-10-01 1972-04-06 North American Rockwell Solid state repair method for metal articles
EP2305412A2 (fr) * 2009-09-30 2011-04-06 General Electric Company Procédé et système pour brasage d'énergie focalisée
EP2317075A2 (fr) * 2009-10-30 2011-05-04 Alstom Technology Ltd Procédé pour réparer un composant de turbine à gaz

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Publication number Priority date Publication date Assignee Title
DE2054549A1 (de) * 1970-11-05 1972-05-10 North American Rockwell Verfahren und Vorrichtung zur Wiederinstandsetzung eines festen Körpers
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
US8640942B1 (en) * 2013-03-13 2014-02-04 Siemens Energy, Inc. Repair of superalloy component

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1269598A (en) * 1970-10-01 1972-04-06 North American Rockwell Solid state repair method for metal articles
EP2305412A2 (fr) * 2009-09-30 2011-04-06 General Electric Company Procédé et système pour brasage d'énergie focalisée
EP2317075A2 (fr) * 2009-10-30 2011-05-04 Alstom Technology Ltd Procédé pour réparer un composant de turbine à gaz

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10875128B2 (en) 2015-05-20 2020-12-29 Rolls-Royce Corporation Pre-sintered preform braze for joining alloy castings
US10502058B2 (en) 2016-07-08 2019-12-10 General Electric Company Coupon for hot gas path component having manufacturing assist features
US11090771B2 (en) 2018-11-05 2021-08-17 Rolls-Royce Corporation Dual-walled components for a gas turbine engine
US11541488B2 (en) 2018-11-05 2023-01-03 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
US11731206B2 (en) 2019-02-11 2023-08-22 Rolls-Royce Corporation Repair of through-hole damage using braze sintered preform
US11692446B2 (en) 2021-09-23 2023-07-04 Rolls-Royce North American Technologies, Inc. Airfoil with sintered powder components

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Publication number Publication date
DE102014226055A1 (de) 2016-06-16

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