EP1398098A1 - Procédé pour la fabrication d'aubes de turbine avec des canaux de refroidissement - Google Patents

Procédé pour la fabrication d'aubes de turbine avec des canaux de refroidissement Download PDF

Info

Publication number
EP1398098A1
EP1398098A1 EP03015950A EP03015950A EP1398098A1 EP 1398098 A1 EP1398098 A1 EP 1398098A1 EP 03015950 A EP03015950 A EP 03015950A EP 03015950 A EP03015950 A EP 03015950A EP 1398098 A1 EP1398098 A1 EP 1398098A1
Authority
EP
European Patent Office
Prior art keywords
core
pin
shell
wax
turbine blade
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
EP03015950A
Other languages
German (de)
English (en)
Other versions
EP1398098B1 (fr
Inventor
Wilfried Dr. Schneiders
Jörn Dr. Grossmann
Theodor Schmitte
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.)
Doncasters Precision Castings Bochum GmbH
Original Assignee
Doncasters Precision Castings Bochum GmbH
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 Doncasters Precision Castings Bochum GmbH filed Critical Doncasters Precision Castings Bochum GmbH
Publication of EP1398098A1 publication Critical patent/EP1398098A1/fr
Application granted granted Critical
Publication of EP1398098B1 publication Critical patent/EP1398098B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • 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
    • B22C21/00—Flasks; Accessories therefor
    • B22C21/12—Accessories
    • B22C21/14—Accessories for reinforcing or securing moulding materials or cores, e.g. gaggers, chaplets, pins, bars

Definitions

  • the invention relates to a method for producing turbine blades cooling channels arranged therein, a ceramic core being produced, which is overmolded with a wax, over which overmolded with wax Core by repeated dipping and sanding a ceramic molded shell is generated, which is burned after removing the wax, the space created by removing the wax to form the turbine blade is poured out with molten metal while doing so Movements of the core in the mold shell by itself starting from the core positioning aids extending into the molded shell are prevented, and after the metal has hardened, the mold shell and the core removed as well as the metallic turbine blade mechanically is processed.
  • the object of the invention is a method of the initially described Specify genus in which movements of the core during the casting can be reliably prevented and impairments of the material properties or surfaces of the turbine blade are excluded.
  • a pin in the positioning aid free face of the core is embedded, which protrudes over the face and is also embedded in the molded shell, and that the protruding end of the Pin is removed during mechanical processing. That leaves them Material properties, the wall thicknesses and the surfaces of all functionally important Areas of the turbine blade from the arrangement of the pin unaffected.
  • the pin can be inserted into the ceramic without additional effort Embed core. Its about that from the so-called crown bottom of the turbine blade protruding end can be easily removed. That under the End of the pin located at the crown bottom does not need to be removed, because it doesn't bother. It is understood that the dimensions of the pin are so be chosen that on the one hand a firm embedding in the core material is possible and that, on the other hand, the pin has sufficient stability when Cast has.
  • the pin should preferably consist of a nickel-based alloy, in particular made of NiCr 82. Such an alloy is essentially resistant to oxidation and has sufficient mechanical strength in the High temperature range above 1,400 ° C. But others can too materials known per se can be used for the pen, e.g. Platinum, Precious metal alloys based on palladium or tungsten, or if necessary, pins made of ceramic materials.
  • a pen is used, its material when firing the molded shell oxidized, then a version is recommended in which the pin with a Abutment for the metal of the turbine blade is provided. It can in the simplest case, it is a circumferential groove.
  • the pen should be like this be embedded in the core that the circumferential groove in the area of later crown bottom.
  • the core shown schematically in Figures 1 and 2 consists of a ceramic material. Its lower section 2 in FIGS. 1 and 2 is set up for connection to a bracket, not shown. from lower section go out two upper sections 3, 4, which are essentially extend parallel to each other. At least the upper section 4 has Profiling 5 on the formation of the cooling channels in the turbine blade serve.
  • the core 1 is manufactured, the upper end faces 6 Pins 7 embedded, which protrude above the upper end faces 6.
  • the pencils consist of a nickel-based alloy in the embodiment shown, namely from NiCr 82.
  • the core prepared in this way is extrusion-coated with a wax layer 8 (FIG. 3).
  • This wax layer 8 defines a space that will later form the Turbine blade is poured out with molten metal.
  • the above the core 1 protruding end 10 of the pin 7 or pins 7 is also over the wax layer 8 and has a in the area of the wax layer 8 Circumferential groove 11.
  • the space released by the wax layer 8 can be melted Metal 12 are poured out, which after cooling and Harden the turbine blade forms.
  • the molten metal 12 also flows into the circumferential groove 11 of the pin or pins 7, so that a positive connection is produced, which is at least necessary if the pen material is burned when the Shaped shell 9 tends to surface oxidation ( Figure 6).
  • the core 1 and the Removed molded shell 9 ( Figure 7) and the resulting turbine blade 13 can be machined.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Molds, Cores, And Manufacturing Methods Thereof (AREA)
  • Casting Devices For Molds (AREA)
EP03015950A 2002-08-08 2003-07-14 Procédé pour la fabrication d'aubes de turbine avec des canaux de refroidissement Expired - Lifetime EP1398098B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10236339 2002-08-08
DE10236339A DE10236339B3 (de) 2002-08-08 2002-08-08 Verfahren zum Herstellen von Turbinenschaufeln mit darin angeordneten Kühlkanälen

Publications (2)

Publication Number Publication Date
EP1398098A1 true EP1398098A1 (fr) 2004-03-17
EP1398098B1 EP1398098B1 (fr) 2006-09-13

Family

ID=30469580

Family Applications (1)

Application Number Title Priority Date Filing Date
EP03015950A Expired - Lifetime EP1398098B1 (fr) 2002-08-08 2003-07-14 Procédé pour la fabrication d'aubes de turbine avec des canaux de refroidissement

Country Status (5)

Country Link
US (1) US6896036B2 (fr)
EP (1) EP1398098B1 (fr)
JP (1) JP2004076731A (fr)
DE (2) DE10236339B3 (fr)
ES (1) ES2272858T3 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
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CN106734941A (zh) * 2017-01-22 2017-05-31 江苏永瀚特种合金技术有限公司 一种能更改熔模精密铸造中芯头自由端稳定性的方法

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US7134475B2 (en) * 2004-10-29 2006-11-14 United Technologies Corporation Investment casting cores and methods
US20070240845A1 (en) * 2006-04-18 2007-10-18 Graham Stephen D Investment cast article and method of production thereof
US7302989B1 (en) 2006-06-06 2007-12-04 Siemens Power Generation, Inc. Modular mold system with ceramic inserts
US7610946B2 (en) * 2007-01-05 2009-11-03 Honeywell International Inc. Cooled turbine blade cast tip recess
DE102007012321A1 (de) * 2007-03-09 2008-09-11 Rolls-Royce Deutschland Ltd & Co Kg Verfahren zum Feingießen von metallischen Bauteilen mit dünnen Durchgangskanälen
US8066052B2 (en) * 2007-06-07 2011-11-29 United Technologies Corporation Cooled wall thickness control
US20110146075A1 (en) * 2009-12-18 2011-06-23 Brian Thomas Hazel Methods for making a turbine blade
US20110150666A1 (en) * 2009-12-18 2011-06-23 Brian Thomas Hazel Turbine blade
US8647064B2 (en) 2010-08-09 2014-02-11 General Electric Company Bucket assembly cooling apparatus and method for forming the bucket assembly
US8851846B2 (en) 2010-09-30 2014-10-07 General Electric Company Apparatus and methods for cooling platform regions of turbine rotor blades
US9835035B2 (en) 2013-03-12 2017-12-05 Howmet Corporation Cast-in cooling features especially for turbine airfoils
US9713838B2 (en) * 2013-05-14 2017-07-25 General Electric Company Static core tie rods
DE102014207791A1 (de) * 2014-04-25 2015-10-29 Siemens Aktiengesellschaft Verfahren zum Feingießen von metallischen Bauteilen
GB201411332D0 (en) 2014-06-26 2014-08-13 Rolls Royce Plc Core positioning
US9828915B2 (en) 2015-06-15 2017-11-28 General Electric Company Hot gas path component having near wall cooling features
US9970302B2 (en) 2015-06-15 2018-05-15 General Electric Company Hot gas path component trailing edge having near wall cooling features
US9938899B2 (en) 2015-06-15 2018-04-10 General Electric Company Hot gas path component having cast-in features for near wall cooling
US9897006B2 (en) 2015-06-15 2018-02-20 General Electric Company Hot gas path component cooling system having a particle collection chamber
JP6613803B2 (ja) 2015-10-22 2019-12-04 三菱日立パワーシステムズ株式会社 翼、これを備えているガスタービン、及び翼の製造方法
US10099284B2 (en) 2015-12-17 2018-10-16 General Electric Company Method and assembly for forming components having a catalyzed internal passage defined therein
US10137499B2 (en) 2015-12-17 2018-11-27 General Electric Company Method and assembly for forming components having an internal passage defined therein
US9987677B2 (en) 2015-12-17 2018-06-05 General Electric Company Method and assembly for forming components having internal passages using a jacketed core
US10099276B2 (en) 2015-12-17 2018-10-16 General Electric Company Method and assembly for forming components having an internal passage defined therein
US9968991B2 (en) 2015-12-17 2018-05-15 General Electric Company Method and assembly for forming components having internal passages using a lattice structure
US10099283B2 (en) 2015-12-17 2018-10-16 General Electric Company Method and assembly for forming components having an internal passage defined therein
US9579714B1 (en) 2015-12-17 2017-02-28 General Electric Company Method and assembly for forming components having internal passages using a lattice structure
US10046389B2 (en) 2015-12-17 2018-08-14 General Electric Company Method and assembly for forming components having internal passages using a jacketed core
US10150158B2 (en) 2015-12-17 2018-12-11 General Electric Company Method and assembly for forming components having internal passages using a jacketed core
US10118217B2 (en) 2015-12-17 2018-11-06 General Electric Company Method and assembly for forming components having internal passages using a jacketed core
US10335853B2 (en) 2016-04-27 2019-07-02 General Electric Company Method and assembly for forming components using a jacketed core
US10286450B2 (en) 2016-04-27 2019-05-14 General Electric Company Method and assembly for forming components using a jacketed core
FR3100143B1 (fr) * 2019-08-30 2021-11-12 Safran Procédé amélioré de fabrication d’un noyau céramique pour la fabrication d’aubes de turbomachine
KR102549163B1 (ko) * 2021-08-13 2023-06-28 윤병관 왁스rp용 3d프린팅이 이용된 가스터빈용 블레이드 제작방법

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US4596281A (en) * 1982-09-02 1986-06-24 Trw Inc. Mold core and method of forming internal passages in an airfoil
GB2202772A (en) * 1987-03-25 1988-10-05 Ae Plc Improvements in or relating to supporting cores during investment casting
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US6349759B1 (en) * 1999-04-05 2002-02-26 Pcc Airfoils, Inc. Apparatus and method for casting a metal article

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JPH1052736A (ja) * 1996-08-09 1998-02-24 Honda Motor Co Ltd ロストワックス法による中空鋳物の製造方法
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US4596281A (en) * 1982-09-02 1986-06-24 Trw Inc. Mold core and method of forming internal passages in an airfoil
GB2202772A (en) * 1987-03-25 1988-10-05 Ae Plc Improvements in or relating to supporting cores during investment casting
DE3813287A1 (de) * 1987-06-03 1988-12-15 Rolls Royce Plc Verfahren zur herstellung eines metallgegenstandes
US6349759B1 (en) * 1999-04-05 2002-02-26 Pcc Airfoils, Inc. Apparatus and method for casting a metal article

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106734941A (zh) * 2017-01-22 2017-05-31 江苏永瀚特种合金技术有限公司 一种能更改熔模精密铸造中芯头自由端稳定性的方法

Also Published As

Publication number Publication date
US6896036B2 (en) 2005-05-24
EP1398098B1 (fr) 2006-09-13
DE10236339B3 (de) 2004-02-19
JP2004076731A (ja) 2004-03-11
US20040055736A1 (en) 2004-03-25
DE50305016D1 (de) 2006-10-26
ES2272858T3 (es) 2007-05-01

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