EP1831420A1 - Procede pour reparer des aubes de turbine - Google Patents

Procede pour reparer des aubes de turbine

Info

Publication number
EP1831420A1
EP1831420A1 EP05817688A EP05817688A EP1831420A1 EP 1831420 A1 EP1831420 A1 EP 1831420A1 EP 05817688 A EP05817688 A EP 05817688A EP 05817688 A EP05817688 A EP 05817688A EP 1831420 A1 EP1831420 A1 EP 1831420A1
Authority
EP
European Patent Office
Prior art keywords
ptal coating
repaired
turbine
coating
ptal
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.)
Ceased
Application number
EP05817688A
Other languages
German (de)
English (en)
Inventor
Thomas Cosack
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines GmbH
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 MTU Aero Engines GmbH filed Critical MTU Aero Engines GmbH
Publication of EP1831420A1 publication Critical patent/EP1831420A1/fr
Ceased 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
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C10/00—Solid state diffusion of only metal elements or silicon into metallic material surfaces
    • C23C10/02—Pretreatment of the material to be coated
    • 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
    • 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
    • F05D2300/10—Metals, alloys or intermetallic compounds
    • F05D2300/14—Noble metals, i.e. Ag, Au, platinum group metals
    • F05D2300/143—Platinum group metals, i.e. Os, Ir, Pt, Ru, Rh, Pd
    • 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

Definitions

  • the invention relates to a method for repairing turbine blades of a gas turbine.
  • Blades and vanes of a turbine are coated on their surfaces for providing a hot gas corrosion protection layer or also for providing a thermal insulation layer with a PtAl coating or a platinum-aluminum coating. During operation, wear of this PtAl coating occurs, so the PtAl coating must be repaired or replaced from time to time.
  • the procedure for repairing turbine blades in the region of their PtAl coating is such that the turbine blade is completely stripped off, so that after stripping, only the base material of the turbine blade is present.
  • a new PtAl coating is built up by setting and alitating the turbine blade.
  • the complete stripping of the turbine blades is complicated and expensive.
  • the construction of a completely new PtAl coating is also complicated and expensive.
  • the present invention is based on the problem to provide a novel method for repairing turbine blades of a gas turbine.
  • the method comprises at least the following steps: a) provision of a turbine blade which has, at least in sections, a PtAl coating to be repaired; b) cleaning the turbine blade at least in the area of the PtAl coating to be repaired; c) Alitating the turbine blade exclusively at least in the area of the cleaned PtAl coating.
  • the present invention it is proposed for the first time to repair a PtAl coating of a turbine blade by merely alitating after cleaning the PtAl coating to be repaired is made.
  • the invention is based on the finding that, after cleaning and, if appropriate, slight removal of a turbine blade to be repaired, residual coatings with a sufficient platinum content are present on the surface, so that a mere Alitieren again a PtAl coating with good hot gas corrosion protection properties and oxidation protection properties can be provided.
  • Fig. 1 a highly schematic view of a turbine blade to be repaired.
  • FIG. 1 shows a turbine blade 10 of a gas turbine aircraft engine which has an airfoil 11 and a blade root 12.
  • the turbine blades 10 carry a PtAl coating 13 in the region of their airfoil 11 to provide hot gas corrosion protection.
  • the PtAl coating may wear, necessitating renewal or repair of the PtAl coating 13.
  • the procedure according to the invention is such that the turbine blade 10 is cleaned at least in the region of the PtAl coating to be repaired.
  • a near-surface and relatively thin layer of the PtAl coating to be repaired is removed from the PtAl coating 13 to be repaired.
  • a layer in the order of a maximum of 10 .mu.m, preferably of at most 5 .mu.m, is removed from the PtAl coating to be repaired.
  • This cleaning and / or removal is carried out by mechanical means, preferably by high-pressure water jets. Alternatively, the cleaning and / or removal can also be done chemically. After cleaning and, if appropriate, removal, the repair or renewal of the PtAl coating takes place in that the turbine blade 10 is alitiert at least in the region of the purified PtAl coating. The residual coating remaining after cleaning and, if necessary, removal has sufficient platinum whose potential can be used to build up a renewed PtAl coating. By merely alitating, ie by supplying pure aluminum, it is therefore possible to produce a PtAl coating with full usability.
  • Alitating the purified PtAl coating can be accomplished in the usual way by powder packing, gas phase aliquoting, or aliquoting by a slip method.
  • turbine blades in the area of their PtAl coating can be repaired in a particularly simple, rapid and cost-effective manner.
  • For the purposes of the invention is dispensed with a costly stripping or removal of the complete PtAl coating.
  • no re-application of expensive platinum is required with the method according to the invention.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • Materials Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne un procédé servant à réparer les aubes d'une turbine à gaz et comprenant les étapes suivantes : a) mise à disposition d'une aube de turbine présentant au moins par segments un revêtement PtAl à réparer ; b) nettoyage de l'aube de turbine au moins dans la zone du revêtement PtAl à réparer ; c) calorisation simple de l'aube de turbine au moins dans la zone du revêtement PtAl nettoyé.
EP05817688A 2004-12-11 2005-12-07 Procede pour reparer des aubes de turbine Ceased EP1831420A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102004059762A DE102004059762A1 (de) 2004-12-11 2004-12-11 Verfahren zur Reparatur von Turbinenschaufeln
PCT/DE2005/002204 WO2006063561A1 (fr) 2004-12-11 2005-12-07 Procede pour reparer des aubes de turbine

Publications (1)

Publication Number Publication Date
EP1831420A1 true EP1831420A1 (fr) 2007-09-12

Family

ID=35842689

Family Applications (1)

Application Number Title Priority Date Filing Date
EP05817688A Ceased EP1831420A1 (fr) 2004-12-11 2005-12-07 Procede pour reparer des aubes de turbine

Country Status (5)

Country Link
US (1) US20090232975A1 (fr)
EP (1) EP1831420A1 (fr)
JP (1) JP2008523291A (fr)
DE (1) DE102004059762A1 (fr)
WO (1) WO2006063561A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102014200119A1 (de) * 2014-01-08 2015-07-09 Siemens Aktiengesellschaft Verfahren zum Reinigen von Oberflächen eines Brenners

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20130160609A1 (en) * 2011-12-22 2013-06-27 General Electric Company Method for recovering platinum from aviation engine components

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3544348A (en) * 1968-10-25 1970-12-01 United Aircraft Corp Overhaul process for aluminide coated gas turbine engine components
US6494960B1 (en) * 1998-04-27 2002-12-17 General Electric Company Method for removing an aluminide coating from a substrate
US6203847B1 (en) * 1998-12-22 2001-03-20 General Electric Company Coating of a discrete selective surface of an article
US6174380B1 (en) * 1998-12-22 2001-01-16 General Electric Company Method of removing hot corrosion products from a diffusion aluminide coating
US6158957A (en) * 1998-12-23 2000-12-12 United Technologies Corporation Thermal barrier removal process
US6485780B1 (en) * 1999-08-23 2002-11-26 General Electric Company Method for applying coatings on substrates
US6355116B1 (en) * 2000-03-24 2002-03-12 General Electric Company Method for renewing diffusion coatings on superalloy substrates
US6863738B2 (en) * 2001-01-29 2005-03-08 General Electric Company Method for removing oxides and coatings from a substrate
US6875292B2 (en) * 2001-12-20 2005-04-05 General Electric Company Process for rejuvenating a diffusion aluminide coating
EP1411149A1 (fr) * 2002-10-18 2004-04-21 Siemens Aktiengesellschaft Procédé pour l'enlèvement d'un revêtement d'un composant

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2006063561A1 *

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102014200119A1 (de) * 2014-01-08 2015-07-09 Siemens Aktiengesellschaft Verfahren zum Reinigen von Oberflächen eines Brenners

Also Published As

Publication number Publication date
WO2006063561A1 (fr) 2006-06-22
DE102004059762A1 (de) 2006-06-14
US20090232975A1 (en) 2009-09-17
JP2008523291A (ja) 2008-07-03

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