EP1868766A1 - Procede pour reparer ou remettre en etat des trous de refroidissement d'un composant enduit d'une turbine a gaz - Google Patents

Procede pour reparer ou remettre en etat des trous de refroidissement d'un composant enduit d'une turbine a gaz

Info

Publication number
EP1868766A1
EP1868766A1 EP06725381A EP06725381A EP1868766A1 EP 1868766 A1 EP1868766 A1 EP 1868766A1 EP 06725381 A EP06725381 A EP 06725381A EP 06725381 A EP06725381 A EP 06725381A EP 1868766 A1 EP1868766 A1 EP 1868766A1
Authority
EP
European Patent Office
Prior art keywords
cross
coating
new
section
component
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Withdrawn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
EP06725381A
Other languages
German (de)
English (en)
Inventor
John William Fernihough
Matthias Hoebel
Maxim Konter
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.)
GE Vernova GmbH
Original Assignee
Alstom Technology AG
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 Alstom Technology AG filed Critical Alstom Technology AG
Publication of EP1868766A1 publication Critical patent/EP1868766A1/fr
Withdrawn legal-status Critical Current

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
    • B23K26/36—Removing material
    • B23K26/38—Removing material by boring or cutting
    • B23K26/382—Removing material by boring or cutting by boring
    • B23K26/389—Removing material by boring or cutting by boring of fluid openings, e.g. nozzles, jets
    • 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
    • B23K26/36—Removing material
    • B23K26/40—Removing material taking account of the properties of the material involved
    • 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
    • B23P6/007—Repairing turbine components, e.g. moving or stationary blades, rotors using only additive methods, e.g. build-up welding
    • 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
    • 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
    • B23K2101/34—Coated articles ; Surface treated articles
    • B23K2101/35—Surface treated articles
    • 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
    • B23K2103/00—Materials to be soldered, welded or cut
    • B23K2103/08—Non-ferrous metals or alloys
    • 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
    • B23K2103/00—Materials to be soldered, welded or cut
    • B23K2103/18—Dissimilar materials
    • B23K2103/26—Alloys of Nickel and Cobalt and Chromium
    • 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
    • B23K2103/00—Materials to be soldered, welded or cut
    • B23K2103/50—Inorganic materials other than metals or composite materials
    • 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
    • B23K2103/00—Materials to be soldered, welded or cut
    • B23K2103/50—Inorganic materials other than metals or composite materials
    • B23K2103/52—Ceramics
    • 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
    • B23P2700/00—Indexing scheme relating to the articles being treated, e.g. manufactured, repaired, assembled, connected or other operations covered in the subgroups
    • B23P2700/06—Cooling passages of turbine components, e.g. unblocking or preventing blocking of cooling passages of turbine components
    • 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
    • F05D2230/10—Manufacture by removing material
    • F05D2230/13—Manufacture by removing material using lasers
    • 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
    • F05D2230/90—Coating; Surface treatment
    • 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
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/611—Coating
    • 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
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24273—Structurally defined web or sheet [e.g., overall dimension, etc.] including aperture

Definitions

  • the present invention relates to a method for repairing or renewing cooling holes of a coated component of a gas turbine.
  • Components of gas turbines such as blades, vanes, heat shield elements, or other cooled parts, often contain voids which serve to distribute cooling air to a plurality of cooling holes in a wall of the respective component. These cooling holes lead the cooling air to an outer surface exposed to the hot working gases of the gas turbine.
  • Such components are usually provided with an oxidation and / or corrosion protection layer, which may also be referred to as a base coat.
  • the components may also be provided with a heat protection layer which serves to thermally insulate the component.
  • degradation of the coating or coatings often occurs before the coated component itself is attacked.
  • the base coat and, if necessary, the heat protection layer must be removed and reapplied.
  • the existing cooling holes are problematic. While in the manufacture of a new component, the cooling holes are introduced after the application of the coating in the component, the cooling holes are already present when re-applying a new coating. When applying the new coating, the coating material can penetrate into the cooling holes and change their cross sections.
  • the components of modern gas turbines can contain hundreds of such cooling holes whose cross sections or their cross-sectional profiles are within very narrow tolerance limits.
  • the upper tolerance limit for the cooling hole cross sections should avoid the injection of unnecessary cooling air, which would drastically reduce the efficiency of the gas turbine and its power output.
  • the lower tolerance limit for the cooling hole cross-sections should prevent overheating of the respective component, which would lead to a significant reduction in the lifetime of the respective component.
  • US 6,265,022 Another method that uses a covering agent is known from US 6,265,022.
  • the covering agent used there is based on a polymer and can be used for all those coating processes in which the temperatures do not exceed a temperature causing the destruction of the covering.
  • the covering means is introduced in such a way that it projects beyond the outer surface of the component at an outlet opening of the respective cooling hole.
  • US Pat. No. 6,042,879 it is known from US Pat. No. 6,042,879 to initially expand the cooling holes before applying the new coating, such that the subsequent coating, due to the penetration of the coating material into the cooling holes, reduces the cross section of the cooling holes more or less to a desired nominal cross section. That such a procedure is subject to extreme tolerances, is obvious.
  • the invention deals with the problem of providing for a method of the type mentioned in an improved embodiment, which is characterized in particular by an increased lifetime of the repaired or renewed th th cooling hole.
  • the invention is based on the general idea to carry out the repair or renewal of the cooling holes so that the cooling holes then have substantially the same cross-sections or substantially the same cross-sectional characteristics, as in the original unused state of the finished component.
  • a longitudinal section of the respective cooling hole which extends to the outside of the component, should also be provided with the new coating.
  • the restoration of the original geometry of the cooling hole ensures that the cooling hole can fulfill its intended function optimally. At the same time, this reduces the risk that hot working gas can penetrate into the cooling hole.
  • the effect of the new coating extending into the longitudinal section of the cooling hole is to intensively protect the material of the component from the aggressive hot working gases, if they should nevertheless penetrate into the respective cooling hole.
  • a cooling hole cross-section which widens due to corrosion during operation of the gas turbine facilitates the penetration of the aggressive working gas into the cooling hole and thereby increases the corrosive effect, which leads to an increased further cross-sectional widening.
  • the repaired cooling holes have at least the same, if not better, resistance to the aggressive hot working gases of the gas turbine.
  • the removal of the at least one old coating is carried out such that subsequently the borehole has an old cross-section or old cross-sectional profile at least in said longitudinal section whose opening width is greater than a SoII cross-section or desired cross-sectional profile that the borehole has when new with unused component.
  • the coating with the at least one new coating is selectively carried out so that this longitudinal section of the cooling hole has an intermediate cross-section or intermediate cross-sectional profile whose opening width is smaller than in SoII cross-section or desired cross-sectional profile.
  • this "drilling" is realized by a partial removal of the new coating within the cooling hole. such that the cooling hole subsequently in the longitudinal section and in particular in the new Coating penetrating hole area has a new cross-section or new cross-sectional profile, which substantially corresponds to the desired cross-section and the desired cross-sectional profile.
  • the partial removal of the new coating is suitably carried out with a suitable laser method.
  • Laser ablation methods or laser milling and / or drilling methods are particularly suitable for this purpose.
  • the problem underlying the invention is accordingly also solved by a component of a gas turbine, which has at least one cooling hole, which in an adjacent to the outside of the component
  • the longitudinal region is likewise coated, with the cooling hole otherwise having a desired nominal cross-section or a desired cross-sectional profile along its entire length.
  • 1 A to 1 E each show a cross section through a component in the region of a cooling hole at different states (A to E),
  • FIGS. 1A to 1E are views as in FIGS. 1A to 1E, but in another embodiment of the cooling hole,
  • 3A to 3E are views as in FIGS. 1 A to 1 E, but in a further embodiment of the cooling hole.
  • the component 1A, 2A and 3A each show a component 1 of a gas turbine, not shown otherwise, which is provided on its outer side 2 with at least one coating.
  • the component 1 is provided in each case with two coatings, namely with a first coating 3 and a second coating 4. While the first coating 3 is applied to the component 1, the second coating 4 is applied to the first coating 3.
  • the component 1 may also have only a single coating or even more than two coatings. The inventive method is then applicable accordingly.
  • the respective sections of the component 1 shown are provided with a cooling hole 5. It is clear that the component 1 can basically also have more than one such cooling hole 5.
  • the component 1 is, for example, a blade or a vane or a heat shield element or any other cooled component.
  • Each cooling hole 5 leads from a cavity, not shown, in the interior of the component 1 to the outside 2.
  • the respective cooling hole 5 is extended through the coatings 3, 4 through to an outer skin 10 of the coated component 1.
  • the first coating 3 is expediently an oxidation and / or corrosion protection layer.
  • Such an oxidation and / or corrosion protection layer can be formed, for example, by a metal coating, in particular from MCrAlY.
  • M is at least one member of the following group: iron (Fe), copper (Cu), nickel (Ni) and cobalt (Co) and combinations thereof. Particularly noteworthy in this connection are NiCrAlY, CoCrAlY, NiCoCrAlY.
  • the second coating 4 is preferably a heat protection layer.
  • a heat protection layer can be achieved for example by a ceramic coating, which consists for example of zirconium oxide.
  • the oxidation and / or corrosion protection layer that is to say the first coating 3 can have, for example, a layer thickness of 150 ⁇ m to 600 ⁇ m.
  • the heat protection layer that is to say the second coating 4 may preferably have a layer thickness of approximately 200 ⁇ m to 500 ⁇ m.
  • each cooling hole 5 has a desired desired cross-section or a desired desired cross-sectional profile in the longitudinal direction of the cooling hole 5.
  • the SoI I cross-section is denoted in Fig. 1A, 2A and 3A with 6, while the target Cross-sectional course is denoted by 7.
  • the embodiments of FIGS. 1, 2 and 3 differ by the design of the cooling holes 5.
  • the cooling hole 5 has in the embodiments of FIGS. 1A and 2A in its longitudinal direction a constant desired cross section 6.
  • the nominal cross section. 6 may be circular, for example.
  • the cooling hole 5 is provided with a desired cross-sectional profile 7, which widens toward an outlet opening 8 of the cooling hole 5.
  • the outlet opening 8 is located at the outflow end of the cooling hole 5 extending inside the component 1 and is thus at the level of the outside 2 of the component 1.
  • the cooling hole 5 is extended through the coatings 3, 4, whereby the outlet opening shifts to the outer skin 10 of the coated component 1, that is, to the outside of the second coating 4. This outer outlet opening is referred to below with 8 '.
  • an aerodynamically shaped outlet region 9 can thereby be achieved within the component 1 or within the coatings 3, 4.
  • An aerodynamically shaped outlet region 9 improves, for example, the formation of a cooling film which, during operation of the gas turbine, bears against the outer skin 10 of the coated component 1 and thereby improves the cooling effect or the thermal insulation of the coated component 1.
  • Other aerodynamically designed exit regions 9 are known, for example, from US Pat. No. 6,183,199, US Pat. No. 4,197,443 and EP 0 228 338, the contents of which are hereby included by express reference in the disclosure of the present invention.
  • FIGS. 2A and 3A also differ from those of FIG. 1A in that the longitudinal direction of the cooling holes 5 in the embodiments of FIGS. 2A and 3A is inclined relative to a normal direction of the outside 2, while in the embodiment according to FIGS FIG. 1A runs parallel to the normal direction.
  • the longitudinal direction of the cooling hole 5 for example, an angle of attack of about 45 °
  • the angle of attack in the embodiment of FIG. 3A is only about 30 °, however, by the widening discharge area 9 to about 60 ° increases.
  • the intended for the new condition of the component 1 target cross-section 6 and the target cross-sectional profile 7 is designed with regard to an optimal cooling effect at the same time optimized performance and optimized efficiency of the gas turbine.
  • the nominal cross-section 6 or the desired cross-sectional profile 7 is manufactured within relatively narrow tolerance limits.
  • FIGS. 1 B, 2 B and 3 B each show a state at a time when a repair or renewal of the Cooling holes 5 is advisable. This point in time is located, for example, approximately in the middle of the lifetime provided for the gas turbine or for its component 1. It can be clearly seen from FIGS. 1B, 2B and 3B that not only the outer second protective layer 4 but also the inner first protective layer 3 as well as a perforated wall 15 laterally enclosing the cooling hole 5 are removed at least in a longitudinal section 11 of the cooling hole 5 , This longitudinal section 11 adjoins the outer side 2 of the component 1 and is characterized in the figures in each case by a curly bracket.
  • the cooling hole 5 Due to the removal of material in the coatings 3, 4 and within the component 1 in the longitudinal section 11, the cooling hole 5 receives an enlarged cross-section e 'or an expanded cross-sectional profile 7' at least in the longitudinal section 11 and within the coatings 3, 4.
  • the original contours of the cooling hole 5 and the coatings 3, 4, ie the setpoint Cross-section e or the desired cross-sectional profile 7 is indicated in FIGS. 1 B, 2B and 3 B in each case by a broken line.
  • the old coatings 3, 4 are removed from the outside 2 of the component 1, namely at least in a hole area 12, which encloses the cooling hole 5.
  • this hole region 12 extends in each case over the entire section of the component 1 shown.
  • FIGS. 1C, 2C and 3C the original contour of the cooling hole 5 and of the coatings 3, 4 is indicated by a broken line.
  • the removal of the old coatings 3, 4 can be carried out in a conventional manner, for example by means of an acid or by means of a corrosive solution.
  • the cooling hole 5 in the longitudinal section 11 has an old cross-section 13 or an old cross-sectional profile 14.
  • This old cross-section 13 or the Alt cross-sectional profile 14 may coincide with the widened cross-section 6 'or cross-sectional profile 7' of the state of use shown in FIGS. 1B, 2B and 3B.
  • the process for removing the old coatings 3, 4 leads to a widening of the cross-section or the cross-sectional profile, which is the case, for example, if the removal of the old coatings 3, 4 simultaneously corrosion or oxidation deposits at the cooling hole 5 laterally delimiting hole wall 15 are also removed.
  • the old cross-section 13 or the old cross-sectional profile 14 is then determined by the process of removing the old coatings 3, 4.
  • the old Cross section 13 larger than the desired cross-section 6.
  • the old cross-sectional profile 14 is wider than the desired cross-sectional profile. 7
  • a new coating is applied to the component 1.
  • two coatings are again applied, namely a new first coating 3 ', which is applied directly to the component 1, and a new second coating 4', which is applied to the new first coating 3 '.
  • the new first coating 3 ' expediently corresponds to the original (old) first coating 3.
  • the new second coating 4' expediently corresponds to the original (old) second coating 4. It is clear that the new coatings 3 'and 4 Consider any technological advances in coating technology that may have occurred since the time of the original new state of FIGS. 1A, 2A and 3A and the time of repair.
  • the application of the new coatings 3 ', 4' can be carried out, for example, by means of a high-temperature spray method, for example plasma spraying.
  • a high-temperature spray method for example plasma spraying.
  • the first new coating 3 ' is applied in such a way that it extends into the cooling hole 5, at least in the longitudinal section 11.
  • this coating process is carried out in this way. that in the longitudinal section 11 and within the new coatings 3 ', 4', ie in the hole region 12, an intermediate cross-section 16 or an intermediate cross-sectional profile 17 results, which is smaller than the original desired cross-section 6 or desired cross-sectional profile 7.
  • the new second coating 4 'can thereby also extend into the cooling hole 5 and in addition to the new first coating 3 'build, whereby the intermediate cross-section 16 and the intermediate cross-sectional profile 17 is additionally narrowed.
  • the intermediate cross-section 16 may shrink to zero at some points, ie, the new coating 3 ', 4' completely closes the cooling hole 5 ,
  • a third step is followed by a partial removal of the new coatings 3 ', 4' from the perforated wall 15 in a third step.
  • This partial removal of the new coatings 3 ', 4 ' is thereby carried out so that the cooling hole 5 then in accordance with FIGS. 1 E, 2E and 3E at least in the longitudinal section 11 and in the hole area 12, ie within the new coatings 3', 4 'a new cross-section 18 or a Neu-
  • Cross-sectional profile 19 has.
  • the partial removal of the new coatings 3 ', 4' is specifically carried out so that the new cross-section 18 and the new cross-sectional profile 19 is about the same size as the desired cross-section 6 and the desired cross-sectional profile 7.
  • the Alt Cross section 13 or the AIt- cross-sectional profile 14 has a larger opening width than the desired cross-section 6 and the target cross-sectional profile 7, the component 1 in the longitudinal section 11 of the cooling hole 5 is provided with the material of the new first coating 3 '. Accordingly, along the longitudinal section 11, the hole wall 15 is formed by the region of the new first coating 3 'protruding into the cooling hole 5.
  • the cooling hole 5 after its repair or after its renewal has substantially the same dimension and shape as in the new state, the originally intended cooling performance can thus be achieved again during operation of the gas turbine. At the same time a high efficiency and a high power output of the gas turbine are again achieved as in new condition.
  • the perforated wall 15 is coated at least in the area of the longitudinal section 11 with the material of the new first coating 3 ', whereby the perforated wall 15 is protected against corrosion, which occurs when the aggressive hot working gases enter the cooling hole 5 can occur.
  • the durability of the repaired cooling hole 5 is thus at least equal to or even greater than the lifetime of the original cooling hole 5 in the new state of the component 1.
  • FIGS. 1E, 2E, 3E thus show a component 1 with repaired cooling hole 5, which differs from the original component 1 in the new state in that the new first coating 3 'extends into the longitudinal region 11.
  • a laser method is preferably used.
  • a laser milling and / or drilling process comes into question.
  • Such a laser milling and / or drilling method is distinguished, for example, by laser pulse energies which lie in a range from 1 J to 60 J. Pulse times in the range of 0.1 ms to 20 ms occur.
  • a laser ablation method which is characterized in particular by pulse times which lie in the range from approximately 10 ns to 1000 ns. This corresponds to pulse frequencies in the range of about 1 kHz to 100 kHz.
  • the energy density is individual pulse considerably larger than during laser milling or laser drilling. At the same time, less material volume is affected due to the considerably smaller pulse energy (1 mJ to 5OmJ). In this way, in particular a re-solidification of the melted areas of the new coating 3 ', 4' to be removed can be avoided. Accordingly, the laser ablation process leads to an extremely clean new cross-sectional profile 19.
  • the method according to the invention can, of course, also be carried out in the case of a component 1 which has a plurality of cooling holes 5, wherein it is then possible in particular to carry out the method at several cooling holes 5 at the same time or to offset one another with respect to the individual method steps.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Optics & Photonics (AREA)
  • Plasma & Fusion (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

La présente invention concerne un procédé pour réparer ou remettre en état des trous de refroidissement d'un composant enduit d'une turbine à gaz. Ce procédé consiste à retirer un ancien revêtement d'une face extérieure (2) du composant (1), le trou de refroidissement (5) présentant dans une partie longitudinale (11), une fois l'ancien revêtement retiré, une ancienne section transversale supérieure à une section transversale de consigne, que ce trou de refroidissement (5) présentait à un état neuf initial du composant fini dans cette partie longitudinale, à appliquer ensuite un nouveau revêtement (3', 4') sur le composant (1) au moins dans la partie longitudinale (11) du trou de refroidissement (5), de sorte que ce trou de refroidissement présente, dans la partie longitudinale (11), une section transversale intermédiaire (16) inférieure à la section transversale de consigne (6), puis à retirer partiellement le nouveau revêtement (3', 4') à l'intérieur du trou de refroidissement (5), de sorte que ce trou de refroidissement (5) présente, dans la partie longitudinale (11), une nouvelle section transversale (18) approximativement égale à la section transversale de consigne (6).
EP06725381A 2005-04-07 2006-03-29 Procede pour reparer ou remettre en etat des trous de refroidissement d'un composant enduit d'une turbine a gaz Withdrawn EP1868766A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH6362005 2005-04-07
PCT/EP2006/061125 WO2006106061A1 (fr) 2005-04-07 2006-03-29 Procede pour reparer ou remettre en etat des trous de refroidissement d'un composant enduit d'une turbine a gaz

Publications (1)

Publication Number Publication Date
EP1868766A1 true EP1868766A1 (fr) 2007-12-26

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP06725381A Withdrawn EP1868766A1 (fr) 2005-04-07 2006-03-29 Procede pour reparer ou remettre en etat des trous de refroidissement d'un composant enduit d'une turbine a gaz

Country Status (4)

Country Link
US (1) US20080085395A1 (fr)
EP (1) EP1868766A1 (fr)
CA (1) CA2602628A1 (fr)
WO (1) WO2006106061A1 (fr)

Families Citing this family (29)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7805822B2 (en) * 2003-12-15 2010-10-05 Turbocombustor Technology, Inc. Process for removing thermal barrier coatings
US20090142548A1 (en) * 2007-10-18 2009-06-04 David Bruce Patterson Air cooled gas turbine components and methods of manufacturing and repairing the same
US9434025B2 (en) 2011-07-19 2016-09-06 Pratt & Whitney Canada Corp. Laser drilling methods of shallow-angled holes
US20130020291A1 (en) * 2011-07-19 2013-01-24 Pratt & Whitney Canada Corp. Laser drilling methods of shallow-angled holes
US20130086784A1 (en) 2011-10-06 2013-04-11 General Electric Company Repair methods for cooled components
EP2604378B1 (fr) 2011-12-15 2015-04-01 Siemens Aktiengesellschaft Réouverture d'ouvertures pour air de refroidissement à l'aide d'un laser à nanosecondes dans le domaine des microsecondes
US9598979B2 (en) 2012-02-15 2017-03-21 United Technologies Corporation Manufacturing methods for multi-lobed cooling holes
CN103292691A (zh) * 2012-02-29 2013-09-11 西门子公司 一种用于检测燃气轮机叶片的冷却孔的方法
US8962066B2 (en) * 2012-06-04 2015-02-24 United Technologies Corporation Coating for cooling air holes
US10100650B2 (en) 2012-06-30 2018-10-16 General Electric Company Process for selectively producing thermal barrier coatings on turbine hardware
US9162306B2 (en) * 2012-07-24 2015-10-20 General Electric Company Method and system for reducing oversized holes on turbine components
US20140050938A1 (en) * 2012-08-14 2014-02-20 General Electric Company Electrospark deposition process for oxidation resistant coating of cooling hole
US11143030B2 (en) * 2012-12-21 2021-10-12 Raytheon Technologies Corporation Coating process for gas turbine engine component with cooling holes
US20140193664A1 (en) * 2013-01-07 2014-07-10 General Electric Company Recoating process and recoated turbine blade
JP5456192B1 (ja) * 2013-02-26 2014-03-26 三菱重工業株式会社 タービン翼の加工方法、加工工具及びタービン翼
US9868180B2 (en) * 2013-03-14 2018-01-16 Ansaldo Energia Ip Uk Limited Turbine blade tip repair using dual fusion welding
DE102013211047B4 (de) * 2013-06-13 2015-04-30 MTU Aero Engines AG Verfahren zum Verschließen von Kühlluftbohrungen
DE102013224103A1 (de) * 2013-11-26 2015-06-11 Siemens Aktiengesellschaft Sicherer Stopfenverschluss durch Diffusionsbeschichtung und Verfahren
US20150165569A1 (en) * 2013-12-18 2015-06-18 Petya M. Georgieva Repair of turbine engine components using waterjet ablation process
US10236622B2 (en) * 2014-07-16 2019-03-19 Siemens Aktiengesellschaft Subsea electrical connector component
US20160090843A1 (en) * 2014-09-30 2016-03-31 General Electric Company Turbine components with stepped apertures
US10132498B2 (en) * 2015-01-20 2018-11-20 United Technologies Corporation Thermal barrier coating of a combustor dilution hole
US20180010457A1 (en) * 2016-07-08 2018-01-11 General Electric Company Coupon for hot gas path component having manufacturing assist features
US10386067B2 (en) * 2016-09-15 2019-08-20 United Technologies Corporation Wall panel assembly for a gas turbine engine
US11752573B2 (en) 2017-08-07 2023-09-12 Rtx Corporation Laser clearance of coating
US11407067B2 (en) * 2018-06-29 2022-08-09 Pratt & Whitney Canada Corp. Method for repairing a part
AT521996B1 (de) * 2018-11-20 2021-08-15 Berndorf Innovations Und Tech Gmbh Verfahren zur Bearbeitung eines Bandes
US11585224B2 (en) * 2020-08-07 2023-02-21 General Electric Company Gas turbine engines and methods associated therewith
US20250345872A1 (en) * 2024-05-07 2025-11-13 Rtx Corporation Method of diffusion braze repair of cooling holes and cracks

Family Cites Families (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3891438A (en) * 1972-11-02 1975-06-24 Polychrome Corp Aqueous developing composition for lithographic diazo printing plates
US4055705A (en) * 1976-05-14 1977-10-25 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Thermal barrier coating system
US4332843A (en) * 1981-03-23 1982-06-01 General Electric Company Metallic internal coating method
US5514482A (en) * 1984-04-25 1996-05-07 Alliedsignal Inc. Thermal barrier coating system for superalloy components
US4762464A (en) * 1986-11-13 1988-08-09 Chromalloy Gas Turbine Corporation Airfoil with diffused cooling holes and method and apparatus for making the same
US5702288A (en) * 1995-08-30 1997-12-30 United Technologies Corporation Method of removing excess overlay coating from within cooling holes of aluminide coated gas turbine engine components
US5771577A (en) * 1996-05-17 1998-06-30 General Electric Company Method for making a fluid cooled article with protective coating
US5728227A (en) * 1996-06-17 1998-03-17 General Electric Company Method for removing a diffusion coating from a nickel base alloy
US5726267A (en) * 1997-01-31 1998-03-10 Nalco Chemical Company Preparation and utility of water-soluble polymers having pendant derivatized amide, ester or ether functionalities as ceramics dispersants and binders
US6544346B1 (en) * 1997-07-01 2003-04-08 General Electric Company Method for repairing a thermal barrier coating
FR2766490B1 (fr) * 1997-07-23 1999-10-08 Rhodia Chimie Sa Nouveaux systemes amorceurs de polymerisation et/ou de reticulation comprenant un borate d'onium et une benzophenone
US6172331B1 (en) * 1997-09-17 2001-01-09 General Electric Company Method and apparatus for laser drilling
ATE267412T1 (de) * 1998-01-09 2004-06-15 Nupro Technologies Inc Verfahren zum entwickeln von photopolymer- druckplatten
DE19845605A1 (de) * 1998-10-05 2000-04-06 Agfa Gevaert Ag Konzentrat und daraus hergestellter wäßriger Entwickler für bildmäßig bestrahlte Aufzeichnungsmaterialien
SG98433A1 (en) * 1999-12-21 2003-09-19 Ciba Sc Holding Ag Iodonium salts as latent acid donors
EP1160352B1 (fr) * 2000-05-31 2009-04-22 ALSTOM Technology Ltd Méthode d'ajustement de la taille des trous de refroidissement d'un composant d'une turbine à gaz
US6511790B2 (en) * 2000-08-25 2003-01-28 Fuji Photo Film Co., Ltd. Alkaline liquid developer for lithographic printing plate and method for preparing lithographic printing plate
US6383717B1 (en) * 2000-10-11 2002-05-07 Kodak Polychrome Graphics, Llc Aqueous developer for negative working lithographic printing plates
US7204019B2 (en) * 2001-08-23 2007-04-17 United Technologies Corporation Method for repairing an apertured gas turbine component
US6902865B2 (en) * 2002-07-22 2005-06-07 Gary Ganghui Teng Non-alkaline aqueous development of thermosensitive lithographic printing plates
US6803167B2 (en) * 2002-12-04 2004-10-12 Kodak Polychrome Graphics, Llc Preparation of lithographic printing plates
US7045269B2 (en) * 2003-03-10 2006-05-16 Eastman Kodak Company Method for forming images using negative working imageable elements
US7229744B2 (en) * 2003-03-21 2007-06-12 Eastman Kodak Company Method for preparing lithographic printing plates
US6844141B1 (en) * 2003-07-23 2005-01-18 Kodak Polychrome Graphics Llc Method for developing multilayer imageable elements
US7279255B2 (en) * 2006-02-07 2007-10-09 Eastman Kodak Company Negative-working radiation-sensitive compositions and imageable materials
US7175949B1 (en) * 2006-02-17 2007-02-13 Eastman Kodak Company Radiation-sensitive compositions and imageable materials

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2006106061A1 *

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