EP1219728A1 - Procédé de décapage d'un aube de turbine - Google Patents

Procédé de décapage d'un aube de turbine Download PDF

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Publication number
EP1219728A1
EP1219728A1 EP00128573A EP00128573A EP1219728A1 EP 1219728 A1 EP1219728 A1 EP 1219728A1 EP 00128573 A EP00128573 A EP 00128573A EP 00128573 A EP00128573 A EP 00128573A EP 1219728 A1 EP1219728 A1 EP 1219728A1
Authority
EP
European Patent Office
Prior art keywords
corrosion protection
protection layer
layer
layer thickness
base body
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Withdrawn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
EP00128573A
Other languages
German (de)
English (en)
Inventor
Andre Dr. Jeutter
Helge Reymann
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.)
Siemens AG
Original Assignee
Siemens 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 Siemens AG filed Critical Siemens AG
Priority to EP00128573A priority Critical patent/EP1219728A1/fr
Priority to CA002366179A priority patent/CA2366179A1/fr
Priority to JP2001394716A priority patent/JP2002212762A/ja
Priority to US10/033,036 priority patent/US6660102B2/en
Publication of EP1219728A1 publication Critical patent/EP1219728A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • 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
    • C23G—CLEANING OR DE-GREASING OF METALLIC MATERIAL BY CHEMICAL METHODS OTHER THAN ELECTROLYSIS
    • C23G5/00—Cleaning or de-greasing metallic material by other methods; Apparatus for cleaning or de-greasing metallic material with organic solvents
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B08—CLEANING
    • B08B—CLEANING IN GENERAL; PREVENTION OF FOULING IN GENERAL
    • B08B3/00—Cleaning by methods involving the use or presence of liquid or steam
    • B08B3/02—Cleaning by the force of jets or sprays
    • 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
    • C23F—NON-MECHANICAL REMOVAL OF METALLIC MATERIAL FROM SURFACE; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL; MULTI-STEP PROCESSES FOR SURFACE TREATMENT OF METALLIC MATERIAL INVOLVING AT LEAST ONE PROCESS PROVIDED FOR IN CLASS C23 AND AT LEAST ONE PROCESS COVERED BY SUBCLASS C21D OR C22F OR CLASS C25
    • C23F1/00—Etching metallic material by chemical means
    • C23F1/10—Etching compositions
    • C23F1/14—Aqueous compositions
    • C23F1/16—Acidic compositions
    • C23F1/28—Acidic compositions for etching iron group metals

Definitions

  • the invention relates to a method for stripping a provided with a corrosion protection layer base body Turbine blade.
  • Turbine blades in particular gas turbine blades, are often to protect against corrosion and oxidation with a Provide corrosion protection layer.
  • a protective layer mostly consists of a material from the group MCrAlX, whereby M stands for iron, cobalt or nickel, Cr for chrome, Al for Aluminum and X is selected from the group yttrium, Scandium, Lantan and Rare Earth.
  • M stands for iron, cobalt or nickel
  • Cr for chrome
  • Al for Aluminum
  • X is selected from the group yttrium, Scandium, Lantan and Rare Earth.
  • Such a protective layer is particularly high temperatures often applied to a base body of the turbine blade, that of a nickel or cobalt base superalloy consists.
  • a ceramic thermal barrier coating applied.
  • the coating is used over time by oxidation and Corrosion starts, it can also cause erosion and mechanical damage come. To the turbine blades after a certain Not having to completely replace the operating time, it is usually worth restoring the protective coating. This "refurbishment" first requires careful stripping of the turbine blade from the old one Corrosion protection layer.
  • WO 93/03201 shows such a stripping process.
  • an old corrosion protection layer in particular Corrosion products are stored through cleaning and then applying an aluminide layer. With the subsequent removal of this aluminide layer is the corrosion protection layer together with the corrosion products removed.
  • This process is very effective, but comparatively complex and expensive.
  • the invention has for its object an effective and Inexpensive method for stripping a turbine blade to be indicated by a corrosion protection layer.
  • this object is achieved by the specification a method for stripping one with a corrosion protection layer provided basic body of a turbine blade, in which a first one, which is external with respect to the base body Outer part of the corrosion protection layer by a water jet is abrasively removed and then a second, before removing the outer part between the outer part and the inner part of the corrosion protection layer lying on the base body is chemically removed.
  • Figure 1 shows a gas turbine blade 1.
  • the gas turbine blade 1 has a base body 3 made of a nickel or Cobalt base superalloy.
  • the gas turbine blade 1 is directed along a blade axis 2.
  • the blade axis 2 follows an airfoil 5, a platform area 7 and a mounting area 9.
  • On the surface of the sheet area 5 and also towards the sheet area 5 The surface of the platform area 7 is a corrosion protection layer 11 applied. This consists of an MCrAlY alloy.
  • the corrosion protection layer 11 has a reference of the base body 3 on the outer part 13. Between the outer part 13 and the base body 3 is an inner part 15 the corrosion protection layer 11 is arranged.
  • the distinction between outer part 13 and inner part 15 does not necessarily mean a chemical or crystallographic diversity of these areas.
  • the outer part 13 is rather in The stripping process is defined by the fact that Water jet 23 removed from a water jet device 21 becomes.
  • This stripping by means of a water jet speeds up the entire decoating process the gas turbine blade 1 from the corrosion protection layer 11 considerably.
  • the corrosion protection layer 11 will not removed by the water jet 23 down to the base body 3. Rather, the inner part 15 remains on the base body 3 received. This ensures that the water jet 23 does not hit the base body 3 in a damaging manner or aerodynamically on its surface changed.
  • the inner part 15 is removed chemically. This happens especially with hydrochloric acid.
  • the removal by means of of the water jet 23 does not necessarily lead to one Residual coating with the inner part 15 with a homogeneous Layer thickness.
  • the layer thickness can vary locally.
  • FIG 2 is a longitudinal section through a section of the Gas turbine blade 1 shown.
  • the corrosion protection layer 11 On the base body 3 is the corrosion protection layer 11 is arranged.
  • the outer part 13 the corrosion protection layer 11 is already partially from the water jet 23 removed.
  • the corrosion protection layer 11 has a total layer thickness D1.
  • the outer part 13 of the anti-corrosion layer 11 has an outer part layer thickness D2.
  • the inner part 15 of the corrosion protection layer 11 has one Inner part layer thickness D3.
  • the outer part layer thickness D2 is greater than 70% of the total layer thickness D1, but smaller than 95% of the total layer thickness D1. This will, on the one hand the removal of a large part of the corrosion protection layer 11 achieved by means of the water jet 23 and thus inexpensively. On the other hand, it is avoided that the water jet 23 hits the base body 3.
  • FIG 3 shows schematically the chemical removal in one Hydrochloric acid bath 31.
  • the inner part becomes through the hydrochloric acid bath 31 15 of the corrosion protection layer 11 substantially removed.
  • layer areas can locally 33 of the corrosion protection layer 11 remain.
  • Such Layer areas 33 are removed by a suitable method, e.g. thermographic, determined. Assign such layer areas 33 still have a residual layer thickness R, which is still comparatively is thick, one can again by means of the water jet 23 abrasive removal down to a minimum layer thickness M.
  • the layer regions 33 are then subjected to an acid treatment again subjected. If necessary, this procedure repeated several times.
  • the turbine blade is 1 in practically completely decoated efficiently. On such a thing stripped turbine blade 1 can now a new corrosion protection layer 11 are applied.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • General Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • ing And Chemical Polishing (AREA)
EP00128573A 2000-12-27 2000-12-27 Procédé de décapage d'un aube de turbine Withdrawn EP1219728A1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
EP00128573A EP1219728A1 (fr) 2000-12-27 2000-12-27 Procédé de décapage d'un aube de turbine
CA002366179A CA2366179A1 (fr) 2000-12-27 2001-12-24 Technique pour retirer le revetement d'une aube de turbine
JP2001394716A JP2002212762A (ja) 2000-12-27 2001-12-26 タービン翼の除層方法
US10/033,036 US6660102B2 (en) 2000-12-27 2001-12-27 Method of decoating a turbine blade

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP00128573A EP1219728A1 (fr) 2000-12-27 2000-12-27 Procédé de décapage d'un aube de turbine

Publications (1)

Publication Number Publication Date
EP1219728A1 true EP1219728A1 (fr) 2002-07-03

Family

ID=8170837

Family Applications (1)

Application Number Title Priority Date Filing Date
EP00128573A Withdrawn EP1219728A1 (fr) 2000-12-27 2000-12-27 Procédé de décapage d'un aube de turbine

Country Status (4)

Country Link
US (1) US6660102B2 (fr)
EP (1) EP1219728A1 (fr)
JP (1) JP2002212762A (fr)
CA (1) CA2366179A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102004049825A1 (de) * 2004-10-13 2006-04-20 Mtu Aero Engines Gmbh Verfahren zum Entschichten von Bauteilen
FR3103126A1 (fr) * 2019-11-20 2021-05-21 Safran Aircraft Engines Dispositif et procédé améliorés d’usinage de pièce aéronautique

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6955308B2 (en) * 2003-06-23 2005-10-18 General Electric Company Process of selectively removing layers of a thermal barrier coating system
US9102014B2 (en) 2010-06-17 2015-08-11 Siemens Energy, Inc. Method of servicing an airfoil assembly for use in a gas turbine engine
US8859479B2 (en) 2011-08-26 2014-10-14 United Technologies Corporation Chemical stripping composition and method
US9758877B2 (en) * 2013-03-01 2017-09-12 General Electric Company Compositions and methods for inhibiting corrosion in gas turbine air compressors
US20150165569A1 (en) * 2013-12-18 2015-06-18 Petya M. Georgieva Repair of turbine engine components using waterjet ablation process
EP3312152B1 (fr) * 2016-10-21 2021-03-10 Rolls-Royce Corporation Enlèvement de revêtements de substrats céramiques ou composites à matrice céramique
CN115122243B (zh) * 2022-07-25 2024-04-30 西门子能源燃气轮机部件(江苏)有限公司 涂层厚度可控的涂层厚度去除方法

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5167721A (en) * 1989-11-27 1992-12-01 United Technologies Corporation Liquid jet removal of plasma sprayed and sintered
EP1013797A1 (fr) * 1998-12-22 2000-06-28 General Electric Company Procédé d'enlèvement de produits de corrosion à haute température d'un revêtement d'une aluminure par diffusion

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4339282A (en) * 1981-06-03 1982-07-13 United Technologies Corporation Method and composition for removing aluminide coatings from nickel superalloys

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5167721A (en) * 1989-11-27 1992-12-01 United Technologies Corporation Liquid jet removal of plasma sprayed and sintered
EP1013797A1 (fr) * 1998-12-22 2000-06-28 General Electric Company Procédé d'enlèvement de produits de corrosion à haute température d'un revêtement d'une aluminure par diffusion

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102004049825A1 (de) * 2004-10-13 2006-04-20 Mtu Aero Engines Gmbh Verfahren zum Entschichten von Bauteilen
DE102004049825B4 (de) * 2004-10-13 2006-11-09 Mtu Aero Engines Gmbh Verfahren zum Entschichten von beschichteten Bauteilen
FR3103126A1 (fr) * 2019-11-20 2021-05-21 Safran Aircraft Engines Dispositif et procédé améliorés d’usinage de pièce aéronautique

Also Published As

Publication number Publication date
US6660102B2 (en) 2003-12-09
US20020148488A1 (en) 2002-10-17
CA2366179A1 (fr) 2002-06-27
JP2002212762A (ja) 2002-07-31

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