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 PDFInfo
- 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
Links
Images
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)
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)
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 |
Families Citing this family (33)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
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 |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
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 |
Family Cites Families (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US1563480A (en) * | 1924-01-26 | 1925-12-01 | Fanner Mfg Co | Chaplet |
US3596703A (en) * | 1968-10-01 | 1971-08-03 | Trw Inc | Method of preventing core shift in casting articles |
GB8800686D0 (en) * | 1988-01-13 | 1988-02-10 | Rolls Royce Plc | Method of supporting core in mould |
US5296308A (en) * | 1992-08-10 | 1994-03-22 | Howmet Corporation | Investment casting using core with integral wall thickness control means |
US5623985A (en) * | 1996-03-13 | 1997-04-29 | Pcc Airfoils, Inc. | Apparatus and method for molding an article |
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 |
DE19926817A1 (de) * | 1999-06-12 | 2000-12-14 | Abb Research Ltd | Turbinenbauteil |
US6364001B1 (en) * | 2000-08-15 | 2002-04-02 | Pcc Airfoils, Inc. | Method of casting an article |
GB2368549B (en) * | 2000-11-02 | 2004-04-28 | Rolls Royce Plc | Apparatus for performing foundary work |
-
2002
- 2002-08-08 DE DE10236339A patent/DE10236339B3/de not_active Expired - Fee Related
-
2003
- 2003-07-14 ES ES03015950T patent/ES2272858T3/es not_active Expired - Lifetime
- 2003-07-14 DE DE50305016T patent/DE50305016D1/de not_active Expired - Lifetime
- 2003-07-14 EP EP03015950A patent/EP1398098B1/fr not_active Expired - Lifetime
- 2003-08-06 JP JP2003206348A patent/JP2004076731A/ja active Pending
- 2003-08-07 US US10/636,483 patent/US6896036B2/en not_active Expired - Fee Related
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
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)
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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