EP1593445B1 - Procédé de fabrication d'un élément coulé creux avec un revêtement intérieur - Google Patents

Procédé de fabrication d'un élément coulé creux avec un revêtement intérieur Download PDF

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Publication number
EP1593445B1
EP1593445B1 EP04010492A EP04010492A EP1593445B1 EP 1593445 B1 EP1593445 B1 EP 1593445B1 EP 04010492 A EP04010492 A EP 04010492A EP 04010492 A EP04010492 A EP 04010492A EP 1593445 B1 EP1593445 B1 EP 1593445B1
Authority
EP
European Patent Office
Prior art keywords
coating
casting
component
cavity
hollow
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.)
Expired - Lifetime
Application number
EP04010492A
Other languages
German (de)
English (en)
Other versions
EP1593445A1 (fr
Inventor
Knut Halberstadt
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 DE502004004360T priority Critical patent/DE502004004360D1/de
Priority to EP04010492A priority patent/EP1593445B1/fr
Priority to CNB2005100689161A priority patent/CN1318160C/zh
Priority to US11/117,195 priority patent/US20050241797A1/en
Publication of EP1593445A1 publication Critical patent/EP1593445A1/fr
Application granted granted Critical
Publication of EP1593445B1 publication Critical patent/EP1593445B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C1/00—Compositions of refractory mould or core materials; Grain structures thereof; Chemical or physical features in the formation or manufacture of moulds
    • B22C1/16—Compositions of refractory mould or core materials; Grain structures thereof; Chemical or physical features in the formation or manufacture of moulds characterised by the use of binding agents; Mixtures of binding agents
    • B22C1/165—Compositions of refractory mould or core materials; Grain structures thereof; Chemical or physical features in the formation or manufacture of moulds characterised by the use of binding agents; Mixtures of binding agents in the manufacture of multilayered shell moulds
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C7/00—Patterns; Manufacture thereof so far as not provided for in other classes
    • B22C7/02—Lost patterns
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/02—Sand moulds or like moulds for shaped castings
    • B22C9/04—Use of lost patterns
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/12—Treating moulds or cores, e.g. drying, hardening
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D27/00—Treating the metal in the mould while it is molten or ductile ; Pressure or vacuum casting
    • B22D27/15—Treating the metal in the mould while it is molten or ductile ; Pressure or vacuum casting by using vacuum
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D29/00—Removing castings from moulds, not restricted to casting processes covered by a single main group; Removing cores; Handling ingots
    • B22D29/001—Removing cores
    • B22D29/002—Removing cores by leaching, washing or dissolving
    • 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
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
    • F05B2230/00—Manufacture
    • F05B2230/90—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
    • F05D2230/00—Manufacture
    • F05D2230/90—Coating; Surface treatment

Definitions

  • the present invention relates to a method for producing a hollow cast component, in particular a hollow cast turbine blade, with internal coating on the walls of at least one cavity.
  • Thermally highly stressed components can be provided on their outside with a coating to protect them in a thermally stressful environment against corrosion and / or oxidation.
  • MCrAlY coatings are suitable as protection against oxidation and / or corrosion.
  • an MCrAlY coating is to be understood as meaning a coating of a metallic alloy which comprises chromium (Cr) and aluminum (Al) and in which Y stands for yttrium or a rare earth element and M for iron ( Fe), cobalt (Co) or nickel (Ni).
  • Turbine blades are exposed to high temperatures during operation and usually have cavities through which cooling fluid is passed. Under certain operating conditions, these cavities may experience temperatures that require protection of the interior walls against oxidation and / or corrosion.
  • Another object of the present invention is to provide an improved hollow molded turbine component.
  • the first object is achieved by a method according to claim 1 and the second object by a hollow-cast turbine component according to claim 7.
  • the component is cast from a base material.
  • a mold is used which comprises at least one casting core for defining the at least one cavity.
  • the coating material for the internal coating of the component prior to casting of the component on at least one casting core applied. After casting, the casting core is then removed again from the cavity.
  • the inner coating is first produced, and then the component is cast around it.
  • an inner coating in particular with an MCrAlY inner coating
  • the material of the casting core is chosen such that it can be removed from the cavity of the finished component, without the coating material is removed with.
  • Particularly suitable materials for the casting core are those materials which can be removed from the cavity by means of chemical processes which do not attack the coating material and the base material of the component.
  • materials for casting cores for casting turbine components such as turbine blades, ceramic materials are therefore particularly suitable.
  • the casting temperature during casting of the component is chosen in particular such that it lies below the melting temperature of the coating material in order to prevent melting of the coating material during the casting process, and thus mixing with the base material of the component.
  • the application of the coating material to the casting core can be carried out, for example, by means of high-energy spraying processes, such as, for example, the high-speed flame tips (English: High-speed flame spraying) Velocity Oxygen Fuel Spraying, HVOF for short) or plasma spraying (APS for short).
  • high-energy spraying processes such as, for example, the high-speed flame tips (English: High-speed flame spraying) Velocity Oxygen Fuel Spraying, HVOF for short) or plasma spraying (APS for short).
  • a hollow-cast turbine blade according to the invention has at least one cavity and an inner coating present in the cavity, in particular an MCrAlY coating.
  • this hollow-cast turbine component Due to the internal coating of the hollow-cast turbine component, this hollow-cast turbine component according to the prior art has an improved oxidation and corrosion property. It can therefore be exposed to higher temperatures.
  • FIG. 1 shows a hollow-cast turbine component in a schematic representation.
  • FIGS. 2-7 show in a highly schematic representation various stages of production of the hollow-cast turbine blade.
  • FIG. 1 schematically shows a hollow-cast turbine blade 1 in a sectional view.
  • the turbine blade 1 comprises a blade body 2, in which in the present embodiment, four cavities 3, 5, 7, 9 are formed, which are used, for example, for passing cooling air.
  • the blade body 2 has an outer surface 12 which is provided with an MCrAlY coating for protection against oxidation and / or corrosion.
  • the blade body 2 has inner surfaces 4, 6, 8, 10, which delimit the cavities 3, 5, 7, 9 and form the inner walls of the cavities.
  • the inner surfaces 4, 6, 8, 10 are also provided with an MCrAlY coating 14, 16, 18, 20 to protect them against oxidation and / or corrosion.
  • the method for producing the turbine blade 1 described with reference to FIG. 1 will be explained below with reference to FIGS. 2 to 7. However, the method can also be used for internal coating of other hollow cast components.
  • a ceramic casting core 22 is molded and sintered for the mold for making the turbine blade Fig. 2).
  • an MCrAlY coating 14 is applied to the ceramic core 22.
  • a high-energy spraying method such as high-speed flame tips (HVOF) or plasma spraying (APS), can be used for this purpose.
  • the thickness with which the MCrAlY coating 14 is applied to the casting core depends on the thickness with which the inner walls of the turbine blade are to be coated.
  • a wax pattern 24 of the turbine blade is molded onto the casting core 22 ( Figure 4). Subsequently, the outer shell 26 of the mold is applied to the wax model 24. Thereafter, the wax is burned out and the casting shell 26 is sintered to complete the casting mold 28 ( Figure 5).
  • Turbine blade casting typically occurs at effusion temperatures below 1500 ° C.
  • the melting point of the MCrAlY coating 14 is typically above 1600 ° C. A melting of the coating 14 during the casting process and thus a mixing of the coating material with the base material of the turbine blade 1 therefore does not take place.
  • the casting temperatures must be below the melting temperature of the coating material, if a melting of the coating and mixing with the base material to be avoided.
  • the casting shell 26 is cut off and the blade 1 is cleaned (FIG. 6).
  • the casting core 22 is leached, i. the ceramic casting core 22 is removed from the solidified turbine blade 1 by means of an alkali. Since the MCrAlY coating 14, like the blade material, is resistant to the leaches used, the MCrAlY coating 14 remains on the inside of the turbine blade 1 during leaching of the ceramic casting core 22 ( Figure 7). In the following, the turbine blade produced in this way can be mechanically processed in the usual way and coated on the outside.
  • the described method is not only suitable for the inner coating of turbine blades, but in principle also for the inner coating of other hollow-cast components. It is also possible to use the process for applying coatings other than MCrAlY coatings. Also, the casting core does not necessarily need to be made of a ceramic material. It only has to be ensured that the casting core can be removed without removing the coating applied to the inside of the workpiece.
  • the tools for making the casting cores or the wax models must be corrected by the thickness of the protective layer in order to ensure the specified wall thicknesses of the hollow-cast component.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Molds, Cores, And Manufacturing Methods Thereof (AREA)

Claims (7)

  1. Procédé de production d'un élément (1) coulé creux, notamment d'un élément de turbine coulé creux, ayant un revêtement (14, 16, 18, 20) intérieur dans au moins une cavité (3, 5, 7, 9), dans lequel
    - on coule l'élément (1) en une matière de base,
    - lors de la coulée, on utilise une lingotière de coulée qui comprend au moins un noyau (22) de coulée pour définir au moins une cavité (3, 5, 7, 9) et,
    - on enlève de la cavité (3, 5, 7) le noyau (2) de coulée après la coulée,
    caractérisée,
    en ce que avant la coulée, on dépose la matière de revêtement pour le revêtement (14, 16, 18, 20) intérieur de l'élément (1) sur au moins un noyau (22) de coulée.
  2. Procédé de production d'un élément selon la revendication (1),
    caractérisé,
    en ce que l'on utilise comme matière pour le noyau (22) de coulée, une matière qui peut être éliminée de la cavité (3, 5, 7, 9) au moyen d'un procédé chimique qui n'attaque pas la matière de revêtement et la matière de base de l'élément (1) .
  3. Procédé de production d'un élément selon la revendication 1 ou 2,
    caractérisé,
    en ce que l'on utilise un matériau céramique comme matière pour le noyau (22) de coulée.
  4. Procédé de production d'un élément selon la revendication 1 à 3,
    caractérisé,
    en ce que la température de coulée est inférieure au point de fusion de la matière de revêtement.
  5. Procédé de production d'un élément selon la revendication 1 à 4,
    caractérisé,
    en ce que le revêtement (14, 16, 18, 20) intérieur ait un revêtement en McrAly.
  6. Procédé de production d'un élément selon la revendication 5,
    caractérisé,
    en ce que pour le dépôt de la matière de revêtement sur le noyau (22) de coulée, on utilise un procédé de projection à grande énergie.
  7. Elément (1) de turbine coulé creux ayant au mois, en vue en coupe, une cavité(3, 5, 7) fermée et un revêtement (14, 16, 18) intérieur en McrAly présent dans la cavité (3, 5, 7) fermée.
EP04010492A 2004-05-03 2004-05-03 Procédé de fabrication d'un élément coulé creux avec un revêtement intérieur Expired - Lifetime EP1593445B1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
DE502004004360T DE502004004360D1 (de) 2004-05-03 2004-05-03 Verfahren zum Herstellen eines hohlgegossenen Bauteils mit Innenbeschichtung
EP04010492A EP1593445B1 (fr) 2004-05-03 2004-05-03 Procédé de fabrication d'un élément coulé creux avec un revêtement intérieur
CNB2005100689161A CN1318160C (zh) 2004-05-03 2005-04-27 用于制造带有内涂层的空心铸件的方法及透平机构件
US11/117,195 US20050241797A1 (en) 2004-05-03 2005-04-28 Method for producing a hollow cast component having an inner coating

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP04010492A EP1593445B1 (fr) 2004-05-03 2004-05-03 Procédé de fabrication d'un élément coulé creux avec un revêtement intérieur

Publications (2)

Publication Number Publication Date
EP1593445A1 EP1593445A1 (fr) 2005-11-09
EP1593445B1 true EP1593445B1 (fr) 2007-07-18

Family

ID=34924837

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04010492A Expired - Lifetime EP1593445B1 (fr) 2004-05-03 2004-05-03 Procédé de fabrication d'un élément coulé creux avec un revêtement intérieur

Country Status (4)

Country Link
US (1) US20050241797A1 (fr)
EP (1) EP1593445B1 (fr)
CN (1) CN1318160C (fr)
DE (1) DE502004004360D1 (fr)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7998604B2 (en) * 2007-11-28 2011-08-16 United Technologies Corporation Article having composite layer
US20110171394A1 (en) * 2008-08-26 2011-07-14 Allen David B Method of making a combustion turbine component using thermally sprayed transient liquid phase forming layer
EP2329901A1 (fr) * 2009-12-03 2011-06-08 Siemens Aktiengesellschaft Moule en fonte doté de noyaux de fonderie internes stabilisés, procédé de fonte et pièce moulée
CN102581217A (zh) * 2012-02-20 2012-07-18 含山县全兴内燃机配件有限公司 一种用于内燃机工作内腔的复合铸渗层的制备方法
US8720526B1 (en) * 2012-11-13 2014-05-13 Siemens Energy, Inc. Process for forming a long gas turbine engine blade having a main wall with a thin portion near a tip
US20140183782A1 (en) * 2013-01-03 2014-07-03 General Electric Company Mold assembly for forming a cast component and method of manufacturing a mold assembly
US9975173B2 (en) 2013-06-03 2018-05-22 United Technologies Corporation Castings and manufacture methods
US20150183026A1 (en) * 2013-12-27 2015-07-02 United Technologies Corporation Investment mold having metallic donor element
FR3071867B1 (fr) * 2017-10-02 2020-07-31 Safran Aircraft Engines Aube composite a matrice ceramique et procede de fabrication d'une telle aube
US20200164431A1 (en) * 2018-11-28 2020-05-28 GM Global Technology Operations LLC Methods for manufacturing cast components with integral thermal barrier coatings

Family Cites Families (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4332843A (en) * 1981-03-23 1982-06-01 General Electric Company Metallic internal coating method
US4532974A (en) * 1981-07-03 1985-08-06 Rolls-Royce Limited Component casting
DE3365469D1 (en) * 1982-11-03 1986-09-25 Secr Defence Brit Casting of metal articles
ATE116171T1 (de) * 1990-09-25 1995-01-15 Allied Signal Inc Herstellung von komplexen hohlräumen in gussstücken.
DE4035790C1 (fr) * 1990-11-10 1991-05-08 Mtu Muenchen Gmbh
US6241000B1 (en) * 1995-06-07 2001-06-05 Howmet Research Corporation Method for removing cores from castings
US6029736A (en) * 1997-08-29 2000-02-29 Howmet Research Corporation Reinforced quartz cores for directional solidification casting processes
DE19856901C2 (de) * 1998-12-10 2003-01-16 Mtu Aero Engines Gmbh Verfahren zum Beschichten von Hohlkörpern
US7055574B2 (en) * 2004-07-27 2006-06-06 Honeywell International Inc. Method of producing metal article having internal passage coated with a ceramic coating

Also Published As

Publication number Publication date
EP1593445A1 (fr) 2005-11-09
CN1318160C (zh) 2007-05-30
DE502004004360D1 (de) 2007-08-30
US20050241797A1 (en) 2005-11-03
CN1693006A (zh) 2005-11-09

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