EP1593445A1 - 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
EP1593445A1
EP1593445A1 EP04010492A EP04010492A EP1593445A1 EP 1593445 A1 EP1593445 A1 EP 1593445A1 EP 04010492 A EP04010492 A EP 04010492A EP 04010492 A EP04010492 A EP 04010492A EP 1593445 A1 EP1593445 A1 EP 1593445A1
Authority
EP
European Patent Office
Prior art keywords
coating
casting
cast
component
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.)
Granted
Application number
EP04010492A
Other languages
German (de)
English (en)
Other versions
EP1593445B1 (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 EP04010492A priority Critical patent/EP1593445B1/fr
Priority to DE502004004360T priority patent/DE502004004360D1/de
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
Not-in-force 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 Production of a hollow-cast component, in particular a hollow cast turbine blade, with internal coating to the Walls of at least one cavity.
  • Thermally highly stressed components can on their outside be provided with a coating to keep them in thermal stressful environment against corrosion and / or oxidation too protect.
  • MCrAlY coatings suitable. Under an MCrAlY coating is intended in the context of the present Description a coating of a metallic Alloy to understand the chromium (Cr) and aluminum (Al), and in the Y for yttrium or an element of rare earths and M for iron (Fe), cobalt (Co) or nickel (Ni) stand.
  • Turbine blades are high in operation Exposed to temperatures and generally have cavities on, is passed through the cooling fluid. For certain Operating conditions can be in these cavities temperatures occur, providing protection of the interior walls against oxidation and / or require corrosion.
  • Another object of the present invention is therein, an improved hollow-cast turbine component for To make available.
  • the first object is achieved by a method according to claim 1 and the second task by a hollowed out Turbine component solved according to claim 7.
  • the component of a base material cast When casting finds a mold using which at least one casting core for defining the at least one Includes cavity.
  • the inner coating first the inner coating and then cast the component around it.
  • an internal coating especially with a MCrAlY inner coating provided become.
  • the material of the casting core is selected in this case is that it is from the cavity of the finished component remove without the coating material with Will get removed.
  • materials for the casting core are particularly suitable such materials, which are made by chemical processes, which the coating material and the base material of Do not attack the component, remove it from the cavity.
  • materials for the casting core are particularly suitable such materials, which are made by chemical processes, which the coating material and the base material of Do not attack the component, remove it from the cavity.
  • materials for the casting core are suitable therefore especially ceramic materials.
  • the casting temperature is Cast of the component in particular chosen so that they below the melting temperature of the coating material lies to melt the coating material during the casting process, and thus a mixture with the Prevent base material of the component.
  • the application of the coating material on the casting core For example, by means of high-energy spraying such as the high velocity flame tips (High Velocity Oxygen Fuel Spraying, short: HVOF) or Plasma spraying (short: APS) take place.
  • high-energy spraying such as the high velocity flame tips (High Velocity Oxygen Fuel Spraying, short: HVOF) or Plasma spraying (short: APS) take place.
  • a hollow-molded turbine blade according to the invention has at least one cavity and one in the cavity Inner coating, in particular a MCrAlY coating on.
  • Fig. 1 shows a hollow-cast turbine component in one schematic representation.
  • Figures 2-7 show in a highly schematic Depicting various stages of manufacture of the hollow cast turbine blade.
  • FIG 1 is schematically a hollow cast Turbine blade 1 shown in a sectional view.
  • the Turbine blade 1 comprises a blade body 2, in which in the present embodiment, four cavities 3, 5, 7, 9th are formed, the example.
  • the blade body 2 has an outer surface 12 to be used to protect against oxidation and / or corrosion a MCrAlY coating is provided.
  • the Blade body 2 inner surfaces 4, 6, 8, 10 on which the Cavities 3, 5, 7, 9 limit and the inner walls of the Form cavities.
  • the inner surfaces 4, 6, 8, 10 are also provided with a MCrAlY coating 14, 16, 18, 20 to also to protect them against oxidation and / or corrosion.
  • an MCrAlY coating 14 applied to the ceramic cast core 22 This can, for example, a high-energy Spray methods, such as high-speed flame tips (HVOF) or plasma spraying (APS).
  • HVOF high-speed flame tips
  • APS plasma spraying
  • the thickness, with the MCrAlY coating 14 applied to the casting core depends on the thickness, with which the inner walls the turbine blade to be coated.
  • the casting shell 26 becomes knocked off and the blade 1 cleaned (Fig. 6).
  • the casting core 22 is leached, i. of the ceramic casting core 22 is removed by means of an alkali from the solidified turbine blade 1 removed. Because the MCrAlY coating 14 as well as the blade material against the leaches resistant, the MCrAlY coating remains 14 during leaching of the ceramic casting core 22 on the inside of the turbine blade 1 (Fig. 7). in the Below, the turbine blade thus produced in usually mechanically processed and coated outside become.
  • the described method is not only suitable for Internal coating of turbine blades, but basically also for internal coating of other hollow cast components. It is also possible to use the method of applying others Use coatings as MCrAlY coatings. Also
  • the casting core does not necessarily need one ceramic material to be produced. It just has to Be sure that the casting core is removed can, without affecting the inside of the workpiece applied coating is removed with.
EP04010492A 2004-05-03 2004-05-03 Procédé de fabrication d'un élément coulé creux avec un revêtement intérieur Not-in-force EP1593445B1 (fr)

Priority Applications (4)

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
DE502004004360T DE502004004360D1 (de) 2004-05-03 2004-05-03 Verfahren zum Herstellen eines hohlgegossenen Bauteils mit Innenbeschichtung
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 true EP1593445A1 (fr) 2005-11-09
EP1593445B1 EP1593445B1 (fr) 2007-07-18

Family

ID=34924837

Family Applications (1)

Application Number Title Priority Date Filing Date
EP04010492A Not-in-force 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)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2011067000A1 (fr) * 2009-12-03 2011-06-09 Siemens Aktiengesellschaft Moule avec noyau intérieur stabilisé, procédé de coulée et pièce coulée
FR3071867A1 (fr) * 2017-10-02 2019-04-05 Safran Aircraft Engines Aube composite a matrice ceramique et procede de fabrication d'une telle aube

Families Citing this family (8)

* 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
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
US20200164431A1 (en) * 2018-11-28 2020-05-28 GM Global Technology Operations LLC Methods for manufacturing cast components with integral thermal barrier coatings

Citations (3)

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Publication number Priority date Publication date Assignee Title
US4332843A (en) * 1981-03-23 1982-06-01 General Electric Company Metallic internal coating method
US5215785A (en) * 1990-11-10 1993-06-01 Mtu Motoren- Und Turbinen- Union Muenchen Gmbh Method for the powder pack coating of hollow bodies
DE19856901A1 (de) * 1998-12-10 2000-06-15 Mtu Muenchen Gmbh Verfahren zum Beschichten von Hohlkörpern

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US4532974A (en) * 1981-07-03 1985-08-06 Rolls-Royce Limited Component casting
EP0108528B1 (en) * 1982-11-03 1986-08-20 The Secretary Of State For Defence In Her Britannic Majesty's Government Of The United Kingdom Of Great Britain And Casting of metal articles
JPH06501205A (ja) * 1990-09-25 1994-02-10 ロバート　ボッシュ　テクノロジイ　コーポレイション 鋳造物または半固体物体の内部に複雑なキャビティーを形成する方法
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
US7055574B2 (en) * 2004-07-27 2006-06-06 Honeywell International Inc. Method of producing metal article having internal passage coated with a ceramic coating

Patent Citations (3)

* 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
US5215785A (en) * 1990-11-10 1993-06-01 Mtu Motoren- Und Turbinen- Union Muenchen Gmbh Method for the powder pack coating of hollow bodies
DE19856901A1 (de) * 1998-12-10 2000-06-15 Mtu Muenchen Gmbh Verfahren zum Beschichten von Hohlkörpern

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
"COATINGS BEAT GAS-TURBINE HEAT", 2 November 2000, MACHINE DESIGN, PENTON,INC. CLEVELAND, US, PAGE(S) 110,112,114, ISSN: 0024-9114, XP001199224 *
MUBOYADZHYAN S A ET AL: "CONDENSATION AND CONDENSATION-DIFFUSION COATINGS FOR TURBINE BLADESMADE OF HIGH-TEMPERATURE ALLOYS WITH A DIRECTED CRYSTAL STRUCTURE", METAL SCIENCE AND HEAT TREATMENT, CONSULTANTS BUREAU. NEW YORK, US, vol. 38, no. 3/4, 1 March 1996 (1996-03-01), pages 159 - 162, XP000698923, ISSN: 0026-0673 *

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2011067000A1 (fr) * 2009-12-03 2011-06-09 Siemens Aktiengesellschaft Moule avec noyau intérieur stabilisé, procédé de coulée et pièce coulée
FR3071867A1 (fr) * 2017-10-02 2019-04-05 Safran Aircraft Engines Aube composite a matrice ceramique et procede de fabrication d'une telle aube

Also Published As

Publication number Publication date
CN1693006A (zh) 2005-11-09
EP1593445B1 (fr) 2007-07-18
CN1318160C (zh) 2007-05-30
DE502004004360D1 (de) 2007-08-30
US20050241797A1 (en) 2005-11-03

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