EP1013360A1 - Verfahren zur Herstellung dünner keramischer Kerne für die Giesserei - Google Patents

Verfahren zur Herstellung dünner keramischer Kerne für die Giesserei Download PDF

Info

Publication number
EP1013360A1
EP1013360A1 EP99402794A EP99402794A EP1013360A1 EP 1013360 A1 EP1013360 A1 EP 1013360A1 EP 99402794 A EP99402794 A EP 99402794A EP 99402794 A EP99402794 A EP 99402794A EP 1013360 A1 EP1013360 A1 EP 1013360A1
Authority
EP
European Patent Office
Prior art keywords
ceramic
manufacturing
core
strip
thin
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
EP99402794A
Other languages
English (en)
French (fr)
Other versions
EP1013360B1 (de
Inventor
Thierry Jean Emile Chartier
Vincent Louis Christian David
Mischael Francois Louis Derrien
Eric Jean Eberschveiller
Franck Edmond Maurice Truelle
Isabelle Marie Monique Valente
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.)
Safran Aircraft Engines SAS
Original Assignee
Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
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 Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA filed Critical Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA
Publication of EP1013360A1 publication Critical patent/EP1013360A1/de
Application granted granted Critical
Publication of EP1013360B1 publication Critical patent/EP1013360B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • 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
    • 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
    • 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
    • B22C1/20—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 of organic agents
    • B22C1/22—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 of organic agents of resins or rosins

Definitions

  • the present invention relates to a method for manufacturing thin ceramic cores for precision foundry and its application to the production of turbine blades.
  • foundry cores ceramics
  • foundry cores ceramics
  • aeronautical applications and by example, obtaining turbine blades in the foundry for turbojets.
  • Improvement of foundry processes evolving from the equiax foundry to the foundry by directed or monocrystalline solidification, further increased these kernel requirements, the use and complexity are imposed by the search for high performance for parts to be obtained, as is the case for example for hollow blades with internal cooling.
  • These fields of application are related to the precision foundry, in particular to the process known under the lost wax foundry designation. In all cases the use of the nucleus intervenes for the manufacture of hollow parts.
  • compositions intended for the preparation of such nuclei are given by FR-A 2,371,257 and mainly contain fused silica, flour zircon and cristobalite which is a form of silica crystallized, a silicone resin being used as binder and additional elements in small quantities such that lubricant and catalyst being added.
  • FR-A 2,371,257 mainly contain fused silica, flour zircon and cristobalite which is a form of silica crystallized, a silicone resin being used as binder and additional elements in small quantities such that lubricant and catalyst being added.
  • FR-A 2,371,257 examples of known compositions intended for the preparation of such nuclei are given by FR-A 2,371,257 and mainly contain fused silica, flour zircon and cristobalite which is a form of silica crystallized, a silicone resin being used as binder and additional elements in small quantities such that lubricant and catalyst being added. The process of preparation
  • the cores used to cast the parts and blades are made of ceramic with a generally porous structure: these cores are made from a mixture consisting of a refractory fraction (in the form of particles) and an organic fraction more or less complex.
  • a refractory fraction in the form of particles
  • an organic fraction more or less complex is described by EP-A 0 328 452.
  • the shaping of the foundry cores in particular from thermoplastic pastes, can be done by molding using for example a press injection. This shaping is followed by a debinding operation during which the organic fraction of the nucleus is eliminated by various known means such as sublimation or thermal degradation, depending on the materials used.
  • a porous structure results.
  • a heat treatment for baking the core to consolidate the porous structure is then applied to the refractory fraction.
  • This treatment introduces a dimensional modification, in the form of a withdrawal which is often non-isotropic in the volume of the nucleus, compared to the initial form. At this stage, it may be necessary to strengthen the core so that it is not damaged in the next cycle of use. It is known in this case in particular to carry out an impregnation by means of an organic resin.
  • one or more thin cores as well obtained are assembled either together or on a core thick central.
  • the core assembly obtained can then be used in foundry at lost wax according to current operations known per se wax injection, clustering, quenching and casting of metal parts to be obtained such as blades turbine.
  • the preparation is rotated at low speed, of the order of 1 to 2 revolutions per minute during minus 48 hours.
  • the solution obtained is spread on a support 1 forming the casting bench.
  • a shoe 2 provided a strip 3 makes it possible to obtain a strip 4 of thickness constant.
  • the strip is preheated in the mold at 100 ° C for 30 minutes.
  • the form mold used is preferably metallic.
  • the strip is then pressed in the next step (f).
  • a 40MPa pressure is applied for 3 minutes, the tape remaining in the mold.
  • the part obtained can then, at the stage (g) next, be placed in a ceramic preform and undergo a standard cooking cycle including, in the example of realization whose compositions have been indicated previously maintained at 1250 ° C for 4 hours.
  • the thin core obtained is then impregnated with an organic resin or polymer.
  • the core thus obtained has sufficient mechanical strength to allow its use in its application in foundry where it will be subjected to pressure forces especially during the injection of wax in the known process in itself a lost wax foundry.
  • Figure 2 shows a thin core 5 used for the manufacture of a blade of turbine 6.
  • the thin core obtained and in order to ensure the geometries of required foundry piece can then be assembled with other thin nuclei or on a thick central nucleus obtained for example according to a conventional method of manufacture of foundry cores.
  • various techniques can be used.
  • the thin core can be assembled by gluing, in using, for example, a ceramic glue based on silica colloidal and a mullite mineral filler in mass proportions of 30 to 70 for example.
  • a relationship mechanical by mortise-tenon system can also allow assembly.
  • the link can be ensured by a quartz tube passing through the cores and the tube is held in its cavity by glue ceramic.
  • the multi-core obtained after assembly can then be used as a standard foundry core and undergo the foundry cycle operations: wax injection, setting bunch, hardened, pouring of the part to be obtained, cooling, elimination of the nucleus.
  • One of the advantages of using conformal thin cores to the invention is to facilitate the operations of setting cooling point of the cavity parts obtained such than turbine blades. Indeed, the modifications are facilitated because the cores obtained are machinable.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Materials Engineering (AREA)
  • Molds, Cores, And Manufacturing Methods Thereof (AREA)
  • Mold Materials And Core Materials (AREA)
EP99402794A 1998-11-12 1999-11-10 Verfahren zur Herstellung dünner keramischer Kerne für die Giesserei Expired - Lifetime EP1013360B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR9814168A FR2785836B1 (fr) 1998-11-12 1998-11-12 Procede de fabrication de noyaux ceramiques minces pour fonderie
FR9814168 1998-11-12

Publications (2)

Publication Number Publication Date
EP1013360A1 true EP1013360A1 (de) 2000-06-28
EP1013360B1 EP1013360B1 (de) 2004-01-21

Family

ID=9532605

Family Applications (1)

Application Number Title Priority Date Filing Date
EP99402794A Expired - Lifetime EP1013360B1 (de) 1998-11-12 1999-11-10 Verfahren zur Herstellung dünner keramischer Kerne für die Giesserei

Country Status (4)

Country Link
US (1) US6286582B1 (de)
EP (1) EP1013360B1 (de)
DE (1) DE69914299T2 (de)
FR (1) FR2785836B1 (de)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2373747A (en) * 2001-03-27 2002-10-02 Howmet Res Corp Impregnating a fired, porous ceramic core with a polymer

Families Citing this family (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7343960B1 (en) 1998-11-20 2008-03-18 Rolls-Royce Corporation Method and apparatus for production of a cast component
US6932145B2 (en) 1998-11-20 2005-08-23 Rolls-Royce Corporation Method and apparatus for production of a cast component
US20040159985A1 (en) * 2003-02-18 2004-08-19 Altoonian Mark A. Method for making ceramic setter
FR2875425B1 (fr) * 2004-09-21 2007-03-30 Snecma Moteurs Sa Procede de fabrication d'une aube de turbomachine, assemblage de noyaux pour la mise en oeuvre du procede.
FR2878458B1 (fr) 2004-11-26 2008-07-11 Snecma Moteurs Sa Procede de fabrication de noyaux ceramiques de fonderie pour aubes de turbomachines, outil pour la mise en oeuvre du procede
US7093645B2 (en) 2004-12-20 2006-08-22 Howmet Research Corporation Ceramic casting core and method
WO2007040236A1 (ja) * 2005-10-06 2007-04-12 Mitsubishi Electric Corporation ターボファン、空気調和機
US20070221359A1 (en) * 2006-03-21 2007-09-27 United Technologies Corporation Methods and materials for attaching casting cores
FR2914871B1 (fr) 2007-04-11 2009-07-10 Snecma Sa Outillage pour la fabrication de noyaux ceramiques de fonderie pour aubes de turbomachines
CN102079653B (zh) * 2010-12-06 2013-05-08 北京航空航天大学 航空发动机叶片用硅基陶瓷型芯的制备方法
FR3022810B1 (fr) 2014-06-30 2019-09-20 Safran Aircraft Engines Procede de fabrication d'un noyau pour le moulage d'une aube
CN104384452A (zh) * 2014-10-24 2015-03-04 沈阳黎明航空发动机(集团)有限责任公司 一种薄壁硅基陶瓷型芯制备工艺
US10507515B2 (en) 2014-12-15 2019-12-17 United Technologies Corporation Ceramic core for component casting
DE102015111418A1 (de) 2015-07-14 2017-01-19 Nemak, S.A.B. De C.V. Verfahren zum Herstellen eines Gießkerns und Gießkern
US20190060982A1 (en) 2017-08-29 2019-02-28 General Electric Company Carbon fibers in ceramic cores for investment casting
KR20200045095A (ko) 2018-10-22 2020-05-04 한국기계연구원 세라믹 판의 제조 방법 및 이를 제조하기 위한 성형부재
CN110439627B (zh) * 2019-08-30 2022-02-11 中国航发动力股份有限公司 一种叶片的气膜孔及尾劈缝孔防护方法
FR3113255B1 (fr) 2020-08-06 2022-10-07 Safran Protection contre l’oxydation ou la corrosion d’une pièce creuse en superalliage
FR3113254B1 (fr) 2020-08-06 2022-11-25 Safran Protection contre l’oxydation ou la corrosion d’une pièce creuse en superalliage

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2241921A (en) * 1990-03-17 1991-09-18 Toshiba Ceramics Co Moulding a refractory nozzle for the casting of molten metal
EP0648560A1 (de) * 1993-10-13 1995-04-19 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Verfahren zur Herstellung keramischer Kerne für die Giesserei
US5711833A (en) * 1995-07-25 1998-01-27 Thermicedge Corporation Process for the production of thin walled ceramic structures

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4093017A (en) * 1975-12-29 1978-06-06 Sherwood Refractories, Inc. Cores for investment casting process
US4190450A (en) 1976-11-17 1980-02-26 Howmet Turbine Components Corporation Ceramic cores for manufacturing hollow metal castings
US4532974A (en) * 1981-07-03 1985-08-06 Rolls-Royce Limited Component casting
FR2626794B1 (fr) 1988-02-10 1993-07-02 Snecma Pate thermoplastique pour la preparation de noyaux de fonderie et procede de preparation desdits noyaux
US4989664A (en) * 1988-07-07 1991-02-05 United Technologies Corporation Core molding composition
US5273104A (en) * 1991-09-20 1993-12-28 United Technologies Corporation Process for making cores used in investment casting
US5394932A (en) * 1992-01-17 1995-03-07 Howmet Corporation Multiple part cores for investment casting

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2241921A (en) * 1990-03-17 1991-09-18 Toshiba Ceramics Co Moulding a refractory nozzle for the casting of molten metal
EP0648560A1 (de) * 1993-10-13 1995-04-19 Societe Nationale D'etude Et De Construction De Moteurs D'aviation "Snecma" Verfahren zur Herstellung keramischer Kerne für die Giesserei
US5711833A (en) * 1995-07-25 1998-01-27 Thermicedge Corporation Process for the production of thin walled ceramic structures

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2373747A (en) * 2001-03-27 2002-10-02 Howmet Res Corp Impregnating a fired, porous ceramic core with a polymer
GB2373747B (en) * 2001-03-27 2005-02-23 Howmet Res Corp Impregnated ceramic core and method of making

Also Published As

Publication number Publication date
FR2785836B1 (fr) 2000-12-15
FR2785836A1 (fr) 2000-05-19
DE69914299D1 (de) 2004-02-26
US6286582B1 (en) 2001-09-11
DE69914299T2 (de) 2004-11-25
EP1013360B1 (de) 2004-01-21

Similar Documents

Publication Publication Date Title
EP1013360B1 (de) Verfahren zur Herstellung dünner keramischer Kerne für die Giesserei
JP6097307B2 (ja) 可動ブレード用セラミックコアの製造方法、セラミックコアおよび可動ブレード
JP2005028455A (ja) インベストメント鋳造法並びにそれに用いるコア及びダイ
EP3630399B1 (de) Verbessertes herstellungsverfahren eines bauteils mit einer dualen mikrostruktur
EP0328452B1 (de) Verfahren zur Herstellung von keramischen Gusskernen
EP0648560B1 (de) Verfahren zur Herstellung keramischer Kerne für die Giesserei
FR3069179A1 (fr) Procede de fabrication de pieces de forme complexe par moulage par injection de poudres metalliques.
CA2759647C (fr) Procede de fabrication d'un ensemble comprenant une pluralite d'aubes montees dans une plateforme
EP4370260A1 (de) Verbesserter formkern zur herstellung eines hohlen omc-teils
EP4010135A1 (de) Verfahren zur herstellung eines metallteils
JPH0627482B2 (ja) ラジアル型セラミックタービンローターの製法
FR3125237A1 (fr) Noyau de fonderie amélioré pour la fabrication de pièce aéronautique métallique creuse
JP2016514054A (ja) セラミックコアの補修方法
WO2016071619A1 (fr) Procédé pour fabriquer une pale de turbine en céramique.
WO2016001564A1 (fr) Procédé de fabrication d'un noyau pour le moulage d'une aube
EP0478413B1 (de) Verfahren zur Herstellung einer Geissform aus einem Schaumstoff und keramischem Kitt
EP0112146B1 (de) Keramischer Rotor und Verfahren zur Herstellung
JP2019076954A (ja) インベストメント鋳造用セラミックコア内の炭素繊維
FR3098740A1 (fr) Procede de fabrication d’une piece metallique
FR3125446A1 (fr) Procédé de réalisation d’une préparation réfractaire pour la fabrication d’un moule en céramique, préparation obtenue par ce procédé, procédé de fabrication d’un moule en céramique et moule pour aube de turbomachine obtenu par ce procédé
EP3980207B1 (de) Verfahren zur herstellung eines turbomaschinenteils durch mim-formen
EP3487649B1 (de) Verfahren zur herstellung einer schalenform
FR3098747A1 (fr) Procede de fabrication d’une piece metallique
CA2960059C (fr) Procede de production d'un noyau ceramique
EP4382226B1 (de) Verfahren zur herstellung eines werkzeugs mit eutektischem material

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 19991119

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): DE FR GB

AX Request for extension of the european patent

Free format text: AL;LT;LV;MK;RO;SI

AKX Designation fees paid

Free format text: DE FR GB

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

GRAH Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOS IGRA

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: SNECMA MOTEURS

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REF Corresponds to:

Ref document number: 69914299

Country of ref document: DE

Date of ref document: 20040226

Kind code of ref document: P

GBT Gb: translation of ep patent filed (gb section 77(6)(a)/1977)

Effective date: 20040317

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

26N No opposition filed

Effective date: 20041022

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 17

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 18

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 19

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

Owner name: SAFRAN AIRCRAFT ENGINES

Effective date: 20170717

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 20

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: DE

Payment date: 20181023

Year of fee payment: 20

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: FR

Payment date: 20181024

Year of fee payment: 20

Ref country code: GB

Payment date: 20181024

Year of fee payment: 20

REG Reference to a national code

Ref country code: DE

Ref legal event code: R071

Ref document number: 69914299

Country of ref document: DE

REG Reference to a national code

Ref country code: GB

Ref legal event code: PE20

Expiry date: 20191109

PG25 Lapsed in a contracting state [announced via postgrant information from national office to epo]

Ref country code: GB

Free format text: LAPSE BECAUSE OF EXPIRATION OF PROTECTION

Effective date: 20191109