EP1970142A1 - Procédé de soudure fine de composants métalliques dotés de canaux de passage fins - Google Patents

Procédé de soudure fine de composants métalliques dotés de canaux de passage fins Download PDF

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Publication number
EP1970142A1
EP1970142A1 EP08150863A EP08150863A EP1970142A1 EP 1970142 A1 EP1970142 A1 EP 1970142A1 EP 08150863 A EP08150863 A EP 08150863A EP 08150863 A EP08150863 A EP 08150863A EP 1970142 A1 EP1970142 A1 EP 1970142A1
Authority
EP
European Patent Office
Prior art keywords
wax
mold
ceramic
casting
ceramic core
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
EP08150863A
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German (de)
English (en)
Other versions
EP1970142B1 (fr
Inventor
Richard Whitton
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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 Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP1970142A1 publication Critical patent/EP1970142A1/fr
Application granted granted Critical
Publication of EP1970142B1 publication Critical patent/EP1970142B1/fr
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • 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
    • B22C9/10—Cores; Manufacture or installation of cores
    • B22C9/108—Installation of cores

Definitions

  • the invention relates to a method for investment casting of metal components with very thin through channels by the lost wax process, in particular of turbine blades, formed in between the mold shells with ceramic core positioned therein by injecting a wax mass, a wax model and after removing the shell molds on the outer surface of the wax model in a dipping and Besandungslui a ceramic mold is produced, which is fired after the melting of the wax and then poured with a molten metal and the mold and the core then destroyed and removed.
  • a non-meltable mold (wax mold, mold shell) is first produced from a master model in which a wax model consisting of a fusible material, in particular a special wax, is produced in a casting process.
  • the wax models provided with a casting system are assembled into model screws and then coated with a refractory material in a multiple immersion and Besandungslui.
  • the wax model is then melted out and then the remaining mold of refractory material is fired into a ceramic casting mold.
  • the liquid metal is poured to produce the desired components. After solidification of the metal, the ceramic molds are destroyed.
  • a ceramic core is overmolded with wax and then formed around the wax layer by repeated dipping in a ceramic binder and dressing a ceramic casting mold which is fired after removal of the wax.
  • the free space left by the melting of the wax between the core and the shell mold is poured out with molten metal to form the turbine blade. Movements of the core during pouring can be prevented by metallic positioning aids mounted in the ceramic core. After pouring and solidifying the metal, the ceramic core and the ceramic casting shell are destroyed and removed. Subsequently, the casting is machined and the positioning aids are removed again.
  • cooling channels profilings are formed on the ceramic core.
  • the invention has for its object to provide a precision casting on the basis of lost wax for the production of turbine blades with through channels, which also allows the production of very thin through-channels within the casting process.
  • the ceramic core pins positioned in the mold provided for the formation of the wax model may be molded to a ceramic core arranged to form a cavity in the respective component in the wax pattern mold.
  • the stiffening layer can be made of wax or similar thermoplastic materials which melt together with the wax model material.
  • the stiffening layer is reinforced by fibers to increase the strength and rigidity of the stiffening layer.
  • cooling ducts of small diameter and in different, for example conical and / or curved, form are required to improve the efficiency of the engine.
  • Turbine vane 1 which is only partially illustrated, starts from a cavity 3 formed in the blade root 2 as a passage channel 4 with a very small diameter acting as a microturbine nozzle for the passage of cooling air. Together with the investment casting of the turbine blade by the lost wax process, the cavity 3 and also the through-channel 4 are produced.
  • Fig. 2 the ceramic core 5 for forming the cavity 3 and the integrally formed thin ceramic core pin 6 for forming the equally thin through-channel 4 is shown, which - according to the lost wax process - for the production of the ceramic mold first in an existing solid shell molded wax mold (not shown) with a is enclosed in this pressed wax mass 7.
  • the brittle ceramic core pin 6 can break easily due to its small diameter when applying or injecting the wax mass 7, this is coated with a fusible stiffening layer 8 before pressing the wax mass 7 and therefore can not be destroyed or damaged during this process step.
  • the injected wax mass 7 and the fusible stiffening layer 8 are melted and the ceramic casting mold is fired.
  • the ceramic casting mold is then poured out with a molten metal alloy intended for the turbine blade. In the subsequent process step, the ceramic casting mold and the ceramic core 5 and the ceramic core pin 6 are destroyed and removed.
  • the fusible stiffening layer can also be made of wax or a fiber-reinforced wax or other thermoplastic material that can be easily melted out during the lost-wax casting from the ceramic casting mold.
  • the invention is not limited to the previously explained application. It can always be used in casting by the lost wax casting turbine blades or other components where thin channels can no longer be produced during casting with a correspondingly thin ceramic core and otherwise separate production of thin through-channels is too expensive, for example, in a support structure in the area of the guide vanes of a turbine stage to form a very narrow pre-swirl nozzle or to form very thin channels in the turbine blade tips.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Molds, Cores, And Manufacturing Methods Thereof (AREA)
EP08150863A 2007-03-09 2008-01-31 Procédé de soudure fine de composants métalliques dotés de canaux de passage fins Expired - Fee Related EP1970142B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102007012321A DE102007012321A1 (de) 2007-03-09 2007-03-09 Verfahren zum Feingießen von metallischen Bauteilen mit dünnen Durchgangskanälen

Publications (2)

Publication Number Publication Date
EP1970142A1 true EP1970142A1 (fr) 2008-09-17
EP1970142B1 EP1970142B1 (fr) 2011-09-28

Family

ID=39325914

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08150863A Expired - Fee Related EP1970142B1 (fr) 2007-03-09 2008-01-31 Procédé de soudure fine de composants métalliques dotés de canaux de passage fins

Country Status (3)

Country Link
US (1) US8096343B2 (fr)
EP (1) EP1970142B1 (fr)
DE (1) DE102007012321A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103706760A (zh) * 2014-01-06 2014-04-09 安徽厚林精密金属科技有限公司 一种绞肉机顶盖的精密铸造方法
CN113441688A (zh) * 2021-06-30 2021-09-28 共享装备股份有限公司 一种芯撑及使用方法

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2362822A2 (fr) 2008-09-26 2011-09-07 Mikro Systems Inc. Systèmes, dispositifs et/ou procédés pour fabriquer des moulages par coulée
US9056795B2 (en) * 2009-08-09 2015-06-16 Rolls-Royce Corporation Support for a fired article
US8813824B2 (en) * 2011-12-06 2014-08-26 Mikro Systems, Inc. Systems, devices, and/or methods for producing holes
CN103056302A (zh) * 2011-12-13 2013-04-24 丹阳市精密合金厂有限公司 航空发动机机匣类环形铸件空心支板成型用陶瓷型芯
CN103056303A (zh) * 2011-12-13 2013-04-24 丹阳市精密合金厂有限公司 一种支板成型用陶瓷型芯
CN102601306A (zh) * 2012-03-31 2012-07-25 四川德力铁道科技有限公司 一种适用于蜡模精铸工艺的模料模组的热水脱蜡方法
DE102013016868A1 (de) 2013-10-11 2015-04-16 Flc Flowcastings Gmbh Feingussverfahren hohler Bauteile
US10507515B2 (en) 2014-12-15 2019-12-17 United Technologies Corporation Ceramic core for component casting
CN107790644A (zh) * 2017-11-09 2018-03-13 东方电气集团东方汽轮机有限公司 一种防止空心叶片蜡模变形的方法
US11179769B2 (en) 2019-02-08 2021-11-23 Raytheon Technologies Corporation Investment casting pin and method of using same
CN112077261B (zh) * 2019-06-13 2021-10-08 中国航发商用航空发动机有限责任公司 一种多孔铸件的制备工艺
US11642720B2 (en) 2019-10-16 2023-05-09 Raytheon Technologies Corporation Integral core bumpers
US11326470B2 (en) * 2019-12-20 2022-05-10 General Electric Company Ceramic matrix composite component including counterflow channels and method of producing

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GB2150874A (en) * 1983-12-07 1985-07-10 Rolls Royce Investment casting
US5641014A (en) * 1992-02-18 1997-06-24 Allison Engine Company Method and apparatus for producing cast structures
EP0873803A1 (fr) * 1997-04-25 1998-10-28 Mitsubishi Steel MFG. CO., LTD. Procédé de production d'un modèle en cire
JP2000246392A (ja) * 1999-03-02 2000-09-12 Hitachi Metals Ltd セラミック中子を有するワックス模型の成型方法
US20040055736A1 (en) 2002-08-08 2004-03-25 Doncasters Precision Castings-Bochum Gmbh Method of making turbine blades having cooling channels
US20050274478A1 (en) * 2004-06-14 2005-12-15 Verner Carl R Investment casting

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GB2150874A (en) * 1983-12-07 1985-07-10 Rolls Royce Investment casting
US5641014A (en) * 1992-02-18 1997-06-24 Allison Engine Company Method and apparatus for producing cast structures
EP0873803A1 (fr) * 1997-04-25 1998-10-28 Mitsubishi Steel MFG. CO., LTD. Procédé de production d'un modèle en cire
JP2000246392A (ja) * 1999-03-02 2000-09-12 Hitachi Metals Ltd セラミック中子を有するワックス模型の成型方法
US20040055736A1 (en) 2002-08-08 2004-03-25 Doncasters Precision Castings-Bochum Gmbh Method of making turbine blades having cooling channels
US20050274478A1 (en) * 2004-06-14 2005-12-15 Verner Carl R Investment casting

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103706760A (zh) * 2014-01-06 2014-04-09 安徽厚林精密金属科技有限公司 一种绞肉机顶盖的精密铸造方法
CN103706760B (zh) * 2014-01-06 2016-06-22 安徽厚林精密金属科技有限公司 一种绞肉机顶盖的精密铸造方法
CN113441688A (zh) * 2021-06-30 2021-09-28 共享装备股份有限公司 一种芯撑及使用方法
CN113441688B (zh) * 2021-06-30 2022-07-08 共享装备股份有限公司 一种芯撑及使用方法

Also Published As

Publication number Publication date
EP1970142B1 (fr) 2011-09-28
US8096343B2 (en) 2012-01-17
DE102007012321A1 (de) 2008-09-11
US20080216983A1 (en) 2008-09-11

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