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CN1693006A - Method for producing hollow castings with internal coating - Google Patents

Method for producing hollow castings with internal coating Download PDF

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Publication number
CN1693006A
CN1693006A CNA2005100689161A CN200510068916A CN1693006A CN 1693006 A CN1693006 A CN 1693006A CN A2005100689161 A CNA2005100689161 A CN A2005100689161A CN 200510068916 A CN200510068916 A CN 200510068916A CN 1693006 A CN1693006 A CN 1693006A
Authority
CN
China
Prior art keywords
casting
coating
cavity
casting core
mcraly
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
CNA2005100689161A
Other languages
Chinese (zh)
Other versions
CN1318160C (en
Inventor
克努特·哈伯斯塔特
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 Corp
Original Assignee
Siemens Corp
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 Corp filed Critical Siemens Corp
Publication of CN1693006A publication Critical patent/CN1693006A/en
Application granted granted Critical
Publication of CN1318160C publication Critical patent/CN1318160C/en
Anticipated expiration legal-status Critical
Expired - Fee Related 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

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

Abstract

In the method according to the invention for producing a hollow cast component having an inner coating in at least one cavity, the component is cast from a base material. A casting mold, which comprises at least one mold insert for defining at least one cavity is used for the casting. In the method according to the invention, the coating material for the inner coating of the component is applied to at least one mold insert before the component is cast. The mold insert is then removed from the cavity after the casting.

Description

Be used to make the method that has internally coated hollow casting
Technical field
The present invention relates to a kind of member that is used to make a slush casting, especially the method for the turbine member of a slush casting has undercoating on the inwall of at least one cavity of this hollow casting.
Background technology
The member that bears high heat load can have a coating in its outside, is corroded and/or oxidation in the thermic load zone to avoid it.Especially be fit to adopt the MCrAlY coating for this reason.A kind of MCrAlY coating is appreciated that in the scope of this specification becoming is a kind of metal alloy coating, and it comprises chromium (Cr) and aluminium (Al), and Y wherein represents yttrium or a kind of rare earth element, and M represents iron (Fe), cobalt (Co) or nickel (Ni).
But under certain condition of work, the inwall of the hollow casting of working in the high heat load zone also can bear very high temperature, therefore is necessary also to prevent that this inwall is corroded and/or oxidation, so that this member can reach predetermined service life really.
A kind of is turbine member, especially turbine blade about this example that bears the slush casting member of high heat load.Turbine blade will bear high temperature and have some usually when work has cooling fluid to be guided the cavity that flows through therein.Under certain condition of work, the temperature in these cavitys causes preventing that inwall is subjected to oxidation and/or corrosion.
Up to now, the inwall of hollow casting has obtained protection more or less by Diffusional aluminizing.Yet along with the rising of temperature, this aluminized coating but reaches its limit, and therefore anticorrosion in fact no longer validly.
Utilize traditional method may in the quite complicated cavity of the part of hollow casting or in the inner chamber, for example apply especially effectively MCrAlY coating in the cavity of turbine blade hardly.Spraying coating process is applied to the inner-wall spraying coating to hollow casting unsatisfactorily.
Summary of the invention
Therefore, the technical problem to be solved in the present invention is to provide a kind of method, utilizes this method apply a undercoating especially can for the complicated inner cavity of hollow casting, especially the MCrAlY undercoating.
Another technical problem that the present invention will solve is to provide a kind of turbine member of improved slush casting.
Above-mentioned first technical problem is by a kind of member that is used to make a slush casting, especially the method for the turbine member of a slush casting solves, have undercoating at least one cavity of this hollow casting, wherein, this member is formed by a kind of host material casting, when casting, adopt one to comprise that at least one is used for the mold of the casting core of definite described at least one cavity, according to method of the present invention, the internally coated coating material that is used for this member is applied at least one casting core before this member of casting, and after casting is finished this casting core is removed from described cavity.
Above-mentioned second technical problem solves by a kind of turbine member of slush casting, and according to the present invention, this turbine member has at least one cavity and the undercoating in this cavity.
Therefore, be at first to make undercoating according to the present invention, cast out described member around this undercoating then.According to this method, also can give member for example the complicated especially cavity or the inner chamber of the gas turbine blades of slush casting coat a undercoating, a MCrAlY undercoating especially.At this, can select the casting core material therefor, make and remove the cavity of the member that it can make from casting, and can not cause coating material together to be removed simultaneously.
Especially be fit to adopt a kind of like this material as the material that is used for described casting core, that is, this material can be removed from described cavity by the chemical method of coating material that can not corrode described member and host material.For example can make the casting core of ceramic material.Such ceramic core can be removed from the cavity of described turbine member by a kind of appropriate MCrAlY undercoating that can not corrode described turbine member and the alkali lye of host material.As being used to cast for example therefore especially suitable ceramic material that adopts of material of the casting core of turbine blade of turbine member.
In manufacture method of the present invention, the casting temperature in the time of can be especially with cast construction is chosen to be lower than the fusion temperature of described coating material.Therefore thereby avoid coating material that fusing takes place in casting process and mix with the host material of member.
Can be for example by a kind of high energy spraying method, HVOF (English: High VelocityOxygen Fuel Spraying for example; Abbreviation HVOF) or plasma spray coating (abbreviation APS) described coating material is coated on the described casting core.
Turbine blade according to a kind of slush casting of the present invention has at least one cavity and the undercoating in this cavity, especially MCrAlY undercoating.
Based on this undercoating, have better anti-oxidant and anticorrosion properties according to the turbine member of slush casting of the present invention than turbine member of the prior art, and therefore can bear higher temperature.
Description of drawings
By the accompanying drawing illustrated embodiment some other advantage of the present invention and details are described in detail below.
Fig. 1 is the diagrammatic depiction of the turbine member of a slush casting;
Fig. 2 to 7 is respectively the schematic diagram of extremely simplifying in each stage of the turbine member of making slush casting shown in Figure 1.
The specific embodiment
Fig. 1 is the sectional schematic diagram of the turbine blade 1 of a slush casting.This turbine blade 1 comprises a blade body 2.In the illustrated embodiment, in this blade body 2, be configured with four cavitys 3,5,7,9.These cavitys for example cooling but air flow through usefulness.This blade body 2 has an outer surface 12.This outer surface has a MCrAlY coating for preventing oxidized and/or corroding.In addition, described blade body 2 also has some inner surfaces 4,6,8,10.These inner surfaces limit some cavitys 3,5,7,9 and constitute the inwall of these cavitys.These inner surfaces 4,6,8,10 have a MCrAlY coating 14,16,18,20 equally, are corroded and/or oxidation avoiding.
Be described by Fig. 2 to 7 pair of method that is used to make turbine blade 1 shown in Figure 1 below.Yet this method also can be used for applying undercoating to the member of other slush castings.
As the first step, at first be to carry out sintering (referring to Fig. 2) for the casting core 22 of moulding one pottery that is used to cast this turbine blade and to it.Next step (referring to Fig. 3) coats a MCrAlY coating 14 on this ceramic casting core 22.For example can adopt a high energy spraying process, for example HVOF (HVOF) or plasma spray coating (APS) for this reason.This MCrAlY coating 14 depends on the undercoating thickness that should have on this turbine blade inwall at the coating thickness on the casting core at this.
On finishing, after the coating, on this casting core 22, inject a wax simulation 24 (referring to Fig. 4) of this turbine blade to casting core.Outside casting shell 26 with mold is installed on this wax simulation 24 subsequently.Make the wax after-flame burn up and make casting shell 26 sintering afterwards, so that finish the manufacturing (referring to Fig. 5) of mold 28.
After the manufacturing of finishing mold 28, this turbine blade 1 of casting in a vacuum.The casting of this turbine blade 1 is typically carried out 1500 ℃ of following temperature.The fusing point of described MCrAlY coating 14 then typically is higher than 1600 ℃.Therefore, the fusing of coating 14 and and then can not taking place mixing of this coating material and turbine blade 1 host material can not take place in casting process.Even if when adopting other to be different from the coating of MCrAlY coating, only want to avoid mixing of this coating fusing and this coating material and host material, cast temperature just must be lower than the fusion temperature of this coating material.
After casting finishes, will cast shell 26 and dismantle and clean this blade 1 (referring to Fig. 6).At last described casting core 22 is carried out alkali lye and embathe, that is to say by a kind of alkali lye the casting core 22 of described pottery is removed from the turbine blade 1 that has solidified.Because the same ability alkali lye with blade material of described MCrAlY coating 14, this MCrAlY coating 14 is just stayed after the casting core 22 of described pottery is clean by alkali lye on the inboard of turbine blade 1 (referring to Fig. 7).Next just can carry out machined and outside coating to this turbine blade of casting according to common mode.
Said method is not only applicable to coat undercoating to turbine blade, and is suitable in principle coating undercoating to other slush casting member yet.Equally also can apply the coating that other are different from the MCrAlY coating with this method.Casting core also not necessarily must be made with a kind of ceramic material.Only need guarantee that casting core can be removed the coating that is coated in simultaneously on the workpiece inboard and can together not be removed thereupon and get final product.
Being used to make aspect the instrument of casting core or wax simulation, note the thickness of such protective finish of instrument correction must be had specific wall thickness with the member of guaranteeing this slush casting.

Claims (8)

1.一种用于制造一空心铸造的构件(1)，尤其是一空心铸造的透平机构件的方法，该空心铸件的至少一个空腔(3，5，7，9)内带有内涂层(14，16，18，20)，其中，该构件(1)由一种基质材料铸造而成，在铸造时采用一个包括至少一个用于确定所述至少一个空腔(3，5，7，9)的铸造型芯(22)的铸模，并且在浇铸完成之后将该铸造型芯(22)从所述空腔(3，5，7，9)中去除，其特征在于，用于该构件(1)的内涂层(14，16，18，20)的涂层材料在浇铸前被涂敷在至少一个铸造型芯(22)上。1. A method for producing a hollow cast component (1), in particular a hollow cast turbine component, in which at least one cavity (3, 5, 7, 9) has an internal Coating (14, 16, 18, 20), wherein the component (1) is cast from a matrix material using a coating comprising at least one cavity (3, 5, 7, 9) of the casting core (22), and after the casting is completed, the casting core (22) is removed from the cavity (3, 5, 7, 9), characterized in that for The coating material of the inner coating (14, 16, 18, 20) of the component (1) is applied to at least one casting core (22) before casting. 2.如权利要求1所述的方法，其特征在于，作为用于所述铸造型芯(22)的材料采用这样一种材料，即，该材料借助一种不会侵蚀所述构件(1)的涂层材料和基质材料的化学方法可从所述空腔(3，5，7，9)中去除。2. The method according to claim 1, characterized in that as material for the casting core (22) a material is used which is The coating material and matrix material can be chemically removed from the cavities (3, 5, 7, 9). 3.如权利要求1或2所述的方法，其特征在于，作为用于所述铸造型芯(22)的材料采用一种陶瓷材料。3. The method as claimed in claim 1 or 2, characterized in that a ceramic material is used as material for the casting core (22). 4.如权利要求1至3之一所述的方法，其特征在于，铸造温度低于所述涂层材料的熔化温度。4. The method as claimed in one of claims 1 to 3, characterized in that the casting temperature is below the melting temperature of the coating material. 5.如权利要求1至4之一所述的方法，其特征在于，所述内涂层(14，16，18，20)是一种MCrAlY材料涂层。5. The method as claimed in one of claims 1 to 4, characterized in that the inner coating (14, 16, 18, 20) is a coating of MCrAlY material. 6.如权利要求5所述的方法，其特征在于，采用一种高能喷涂方法来将所述涂层材料涂覆在所述铸造型芯(22)上。6. The method according to claim 5, characterized in that a high-energy spraying method is used to apply the coating material to the casting core (22). 7.一种空心铸造的透平机构件，它具有至少一个空腔(3，5，7，9)和在该空腔(3，5，7，9)中的一内涂层(14，16，18，20)。7. A hollow cast turbine component having at least one cavity (3, 5, 7, 9) and an inner coating (14, 9) in the cavity (3, 5, 7, 9) 16, 18, 20). 8.如权利要求7所述的空心铸造的透平机构件，其特征在于，该透平机构件具有一由MCrAlY材料制成的内涂层(14，16，18，20)。8. The hollow cast turbine component according to claim 7, characterized in that it has an inner coating (14, 16, 18, 20) made of MCrAlY material.
CNB2005100689161A 2004-05-03 2005-04-27 Method for producing hollow casting with internal coating and turbine component Expired - Fee Related CN1318160C (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP04010492.9 2004-05-03
EP04010492A EP1593445B1 (en) 2004-05-03 2004-05-03 Process of making a hollow member having an internal coating

Publications (2)

Publication Number Publication Date
CN1693006A true CN1693006A (en) 2005-11-09
CN1318160C CN1318160C (en) 2007-05-30

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CNB2005100689161A Expired - Fee Related CN1318160C (en) 2004-05-03 2005-04-27 Method for producing hollow casting with internal coating and turbine component

Country Status (4)

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US (1) US20050241797A1 (en)
EP (1) EP1593445B1 (en)
CN (1) CN1318160C (en)
DE (1) DE502004004360D1 (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102581217A (en) * 2012-02-20 2012-07-18 含山县全兴内燃机配件有限公司 Preparation method of composite casting-infiltration layer used for working inner cavities of internal-combustion engine
CN111230048A (en) * 2018-11-28 2020-06-05 通用汽车环球科技运作有限责任公司 Method for manufacturing a cast component with an integrated thermal barrier coating

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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 (en) * 2009-12-03 2011-06-08 Siemens Aktiengesellschaft Mould with stabilised internal casting core, casting method and casting part
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 (en) * 2017-10-02 2020-07-31 Safran Aircraft Engines COMPOSITE AUBE WITH CERAMIC MATRIX AND PROCESS FOR MANUFACTURING SUCH A BLADE
FR3113254B1 (en) * 2020-08-06 2022-11-25 Safran Protection against oxidation or corrosion of a hollow superalloy part

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CN102581217A (en) * 2012-02-20 2012-07-18 含山县全兴内燃机配件有限公司 Preparation method of composite casting-infiltration layer used for working inner cavities of internal-combustion engine
CN111230048A (en) * 2018-11-28 2020-06-05 通用汽车环球科技运作有限责任公司 Method for manufacturing a cast component with an integrated thermal barrier coating

Also Published As

Publication number Publication date
DE502004004360D1 (en) 2007-08-30
US20050241797A1 (en) 2005-11-03
EP1593445A1 (en) 2005-11-09
CN1318160C (en) 2007-05-30
EP1593445B1 (en) 2007-07-18

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Granted publication date: 20070530

Termination date: 20140427