EP1980343B1 - Fertigungsverfahren von keramischen Kernen zum Gießen von Laufradschaufeln für Strömungsmaschinen - Google Patents

Fertigungsverfahren von keramischen Kernen zum Gießen von Laufradschaufeln für Strömungsmaschinen Download PDF

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Publication number
EP1980343B1
EP1980343B1 EP08103504.0A EP08103504A EP1980343B1 EP 1980343 B1 EP1980343 B1 EP 1980343B1 EP 08103504 A EP08103504 A EP 08103504A EP 1980343 B1 EP1980343 B1 EP 1980343B1
Authority
EP
European Patent Office
Prior art keywords
core
trailing edge
blade
dies
thicker
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.)
Active
Application number
EP08103504.0A
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English (en)
French (fr)
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EP1980343A1 (de
Inventor
Yvon Louesdon
Serge Prigent
Jean-Louis Verger
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
SNECMA SAS
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Filing date
Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of EP1980343A1 publication Critical patent/EP1980343A1/de
Application granted granted Critical
Publication of EP1980343B1 publication Critical patent/EP1980343B1/de
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Anticipated expiration legal-status Critical

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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
    • B22C9/105—Salt cores
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22C—FOUNDRY MOULDING
    • B22C13/00—Moulding machines for making moulds or cores of particular shapes
    • B22C13/12—Moulding machines for making moulds or cores of particular shapes for cores
    • B22C13/16—Moulding machines for making moulds or cores of particular shapes for cores by pressing through a die

Definitions

  • the ceramic material has abrasive properties and the shear stresses generated by the new, more severe filling conditions are the cause of premature wear of the fine areas of the tools resulting in an increase in the number of production stops and maintenance costs. tooling.
  • the demolding operation can cause deformation of the core when the paste has infiltrated into the mechanisms of the core box.
  • these conditions for filling and demolding the core in the core box are at the origin of cracks and burrs type indications which cause the disposal of large quantities of cores after their ejection and control. Defects can also be revealed only after the debinding and baking heat treatment.
  • such a turbine blade 1 comprises an intrados face IN an extrados face EX, a leading edge BA and a trailing edge BF.
  • the dawn includes several internal cavities, here 7: 1A to 1G.
  • the cavities are separated from each other by partitions: 1AB, 1BC, etc.
  • the trailing edge comprises an opening 1 H or a plurality of openings on its long fed from the last cavity 1 G by GH channels 1 'parallel to each other for the exhaust of the cooling fluid in the gas stream.
  • the cooling fluid consists of air taken from the compressor.
  • This core 10 When making this type of blade by casting a molten metal in a carapace mold, it must incorporate therein a core which occupies the voids of the cavities to be formed in the blade.
  • This core 10 shown schematically on the figure 2 is of complex geometry. It comprises a portion corresponding to the cavities of the blade 10A, a portion 10B corresponding to the cavities of the root of the blade and a portion 10C forming a gripping handle during manufacture.
  • a part 10D corresponding to what is designated by bathtub in the jargon of the domain. This part is here separated from the part 10A by a transverse recess. This recess forms the bottom wall of the bathtub after casting.
  • the thin zone generally extends a few millimeters from the edge of the core corresponding to the trailing edge.
  • the figure 3 represents an injection box, forming a core mold, in the open position. It comprises a lower plate 310 and an upper plate 320 respectively fixed to the lower and upper matrices of the injection molding machine, not shown.
  • This type of box comprises two indentations one said lower 330 the other upper 340.
  • the paste mixture of polymer and ceramic
  • Each imprint includes on its inner wall relief elements forming the decorations to reserve the recessed portions of the core.
  • the section of a conventional mold for turbine blade core 10 is shown in section. It comprises impressions 330 and 340 with decorations 370 for the cavities intended to protect the partitions of the finished blade.
  • the curvature of the nucleus along its rope is important.
  • the direction of the kernel portion located at the trailing edge forms an angle of the order of 45 to 60 degrees with the direction of the thicker portion located on the leading edge side. This curvature does not make fingerprints without moving parts because we can not avoid the parts against the remains.
  • a modified mold is made, that is to say a mold or some areas that were movable in the matrix become fixed.
  • Such a mold comprises figure 5 , a lower cavity 530 and an upper cavity 540 between the two plates 560 and 580 of the injection molding machine.
  • the core 10 is injected into the space between the two cavities.
  • Sets 510 enter the core to reserve the partitions cavities.
  • Ejectors 570 are formed in the lower recess 530 under the trailing edge portion 10A1.
  • the axis of the decorations 510 is oriented in the main opening direction of the tool indicated by the arrows F'1 and F'2.
  • the decors 510 of the trailing edge are demolded by mechanical ejectors 570 sliding along the axis of the arrows, here vertical. These are metal rods that are actuated from outside the mold. They are located in the lower part 530 of the mold.
  • the mold preferably has no hinge contrary to the prior art but can be fixed to the upper plates 580 and lower 560 of the injection press as shown in FIG. figure 5 .
  • the two indentations 530 and 540 are placed in the press along their joint plane P;
  • the core is extracted with the help of ejectors 570 which print upward pressure on the part 10A1 of the core.
  • a sufficient number of ejectors are determined and distributed so as to ensure a low pressure at their point of contact with the core. This distribution of the total pressure in several low pressures makes it possible to avoid any buckling of the core during its ejection.
  • the ejectors maintain a direction as parallel as possible to the demolding axis.
  • the ejectors are distributed over the entire core 62 and that in the figure they are seven in number: two ejectors 63 of the bath 62b, an ejector 64 of the core body 62a, an ejector 65 of the connection zone foot / core body, two 62c core foot ejectors 62c, and a 62d injection core ejector 67.
  • the ejectors 63 to 67 print a bottom-up motion to the ceramic core 62 and lift it from the imprint.
  • the core is heated to a temperature sufficient to degrade the organic components it contains.
  • the other steps consist in heating the core to the sintering temperature of the ceramic particles that compose it. If additional consolidation is necessary, impregnation with an organic resin

Claims (2)

  1. Verfahren zur Herstellung eines Formkerns für eine Turbomaschinenschaufel mit einer Vorderkante und einer Hinterkante, aufweisend eine dünne Zone mit einer Dicke von weniger als 0,5 mm, die der Hinterkante der Schaufel entspricht, und einem Abschnitt, der dicker als die dünne Zone ist, umfassend die Formung eines Gemischs, das eine Belastung aus keramischen Partikeln und ein organisches Bindemittel enthält, in einem Werkzeug, die Herauslösung aus dem Werkzeug, die Entbinderung und eine thermische Behandlung zur Verfestigung des Kerns, dadurch gekennzeichnet, dass
    - das Werkzeug einen ersten und einen zweiten Formhohlraum (530, 540) des Kerns umfasst, die relativ zueinander in einer Richtung (F'1, F'2) beweglich sind zwischen einer Gießposition und einer Entformungsposition, wobei die Formhohlräume des Kerns Folgendes aufweisen:
    bewegliche Teilstücke für den dicken Abschnitt,
    Dekore (510), deren Achse in der Richtung (F'1, F'2) ausgerichtet ist, mechanische Auswerfer (570), die auf dem einen oder dem anderen der Formhohlräume vorgesehen sind und in der Richtung (F'1, F'2) verschiebbar sind, derart, dass der Abschnitt, welcher der Hinterkante der Schaufel entspricht, in der Öffnungsrichtung (F'1, F'2) entformt wird,
    wobei die zwei Formhohlräume für das Gießen ohne bewegliches Teilstück der dünnen Zone, die der Hinterkante entspricht, ausgebildet sind, wobei mindestens einer der zwei Formhohlräume, in der Zone, die der Hinterkante entspricht, so ausgebildet ist, dass Abschnitte des Kerns mit Überdicke erhalten werden, was das Befüllen der Spritzgussform lokal vereinfacht,
    - in dem Werkzeug ein Kernrohling mit dem Abschnitt mit Überdicke geformt wird und
    - der Abschnitt mit Überdicke spanend bearbeitet wird, nachdem der Rohling aus der Form herausgelöst wurde, und zwar vor oder nach dem Vorgang der thermischen Behandlung, um die Zone zu erhalten, die der Hinterkante der Schaufel entspricht.
  2. Verfahren nach Anspruch 1, wobei der Abschnitt mit Überdicke mindestens einem Kanal zum Ablassen der Kühlluft der dünnen Zone der Schaufel entspricht.
EP08103504.0A 2007-04-11 2008-04-11 Fertigungsverfahren von keramischen Kernen zum Gießen von Laufradschaufeln für Strömungsmaschinen Active EP1980343B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0702640A FR2914871B1 (fr) 2007-04-11 2007-04-11 Outillage pour la fabrication de noyaux ceramiques de fonderie pour aubes de turbomachines

Publications (2)

Publication Number Publication Date
EP1980343A1 EP1980343A1 (de) 2008-10-15
EP1980343B1 true EP1980343B1 (de) 2013-08-21

Family

ID=38667301

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08103504.0A Active EP1980343B1 (de) 2007-04-11 2008-04-11 Fertigungsverfahren von keramischen Kernen zum Gießen von Laufradschaufeln für Strömungsmaschinen

Country Status (7)

Country Link
US (1) US7931459B2 (de)
EP (1) EP1980343B1 (de)
JP (1) JP5450976B2 (de)
CA (1) CA2629053C (de)
FR (1) FR2914871B1 (de)
IL (1) IL190667A (de)
RU (1) RU2461439C2 (de)

Families Citing this family (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2959947B1 (fr) * 2010-05-11 2014-03-14 Snecma Outillage d'injection d'une piece
FR2965740B1 (fr) * 2010-10-06 2013-04-12 Snecma Moule de fabrication de pieces par injection de cire
FR2966067B1 (fr) * 2010-10-19 2017-12-08 Snecma Moule d'injection pour modele en cire d'une aube de turbine a support du noyau isostatique
KR101220875B1 (ko) 2010-11-01 2013-01-11 대우조선해양 주식회사 고정피치 프로펠러 조형 장치 및 방법
FR2978069B1 (fr) * 2011-07-22 2013-09-13 Snecma Moule pour piece de turbomachine d'aeronef comprenant un dispositif ameliore de support d'inserts destines a etre integres a la piece
FR2984880B1 (fr) * 2011-12-23 2014-11-21 Snecma Procede de fabrication d'un noyau ceramique pour aube mobile, noyau ceramique, aube mobile
FR2990367B1 (fr) 2012-05-11 2014-05-16 Snecma Outillage de fabrication d'un noyau de fonderie pour une aube de turbomachine
FR2995305B1 (fr) * 2012-09-10 2014-09-05 Snecma Procede de fabrication ameliore d'un noyau en ceramique destine a la fabrication d'une aube de module de turbomachine
CN103331413B (zh) * 2013-06-09 2015-06-10 沈阳黎明航空发动机(集团)有限责任公司 一种调节片自动出模模具
CN103537652B (zh) * 2013-10-14 2015-08-12 西安航空动力股份有限公司 一种防止高压涡轮导向叶片变形的精铸方法
CN104384449B (zh) * 2014-10-29 2016-07-20 西安航空动力股份有限公司 一种控制精铸涡轮叶片晶粒度的方法
FR3034128B1 (fr) * 2015-03-23 2017-04-14 Snecma Noyau ceramique pour aube de turbine multi-cavites
GB2544577B (en) * 2015-07-06 2019-05-15 Safran Aircraft Engines Tooling for use during heat treatment to support a preform made of powder
US10052683B2 (en) * 2015-12-21 2018-08-21 General Electric Company Center plenum support for a multiwall turbine airfoil casting
FR3048374B1 (fr) * 2016-03-01 2018-04-06 Snecma Noyau pour le moulage d'une aube ayant des cavites superposees et comprenant un conduit de depoussierage traversant une cavite de part en part
CN105750491B (zh) * 2016-04-25 2017-11-14 株洲中航动力精密铸造有限公司 空心叶片的蜡模成型模具及空心叶片的壁厚控制方法
FR3080051B1 (fr) 2018-04-13 2022-04-08 Safran Noyau pour la fonderie d'une piece aeronautique
CN114273624B (zh) * 2021-11-30 2024-03-15 共享装备股份有限公司 一种铸造砂箱合箱检测量具及其应用
CN117444154B (zh) * 2023-12-21 2024-03-08 平遥县北三狼腾胜铸造有限公司 一种覆膜砂铸造装置

Family Cites Families (14)

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Publication number Priority date Publication date Assignee Title
US4190450A (en) 1976-11-17 1980-02-26 Howmet Turbine Components Corporation Ceramic cores for manufacturing hollow metal castings
JPS5445314A (en) * 1977-09-16 1979-04-10 Kubota Ltd Method of making centerless ceramic core
JPS59109304A (ja) * 1982-12-15 1984-06-25 日本碍子株式会社 ラジアル型セラミツクタ−ビンロ−タの製造法
JPS59224306A (ja) * 1983-05-13 1984-12-17 日本碍子株式会社 セラミツク部品の製造法
FR2626794B1 (fr) 1988-02-10 1993-07-02 Snecma Pate thermoplastique pour la preparation de noyaux de fonderie et procede de preparation desdits noyaux
US5014763A (en) * 1988-11-30 1991-05-14 Howmet Corporation Method of making ceramic cores
JPH0623644U (ja) * 1992-08-25 1994-03-29 アイシン高丘株式会社 中子成形用金型
JPH0760974A (ja) * 1993-08-30 1995-03-07 Brother Ind Ltd インク噴射装置の製造方法
RU2094163C1 (ru) * 1995-12-28 1997-10-27 Всероссийский научно-исследовательский институт авиационных материалов Составной керамический стержень
FR2785836B1 (fr) 1998-11-12 2000-12-15 Snecma Procede de fabrication de noyaux ceramiques minces pour fonderie
US20030015308A1 (en) * 2001-07-23 2003-01-23 Fosaaen Ken E. Core and pattern manufacture for investment casting
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
US7569172B2 (en) * 2005-06-23 2009-08-04 United Technologies Corporation Method for forming turbine blade with angled internal ribs
FR2900850B1 (fr) 2006-05-10 2009-02-06 Snecma Sa Procede de fabrication de noyaux ceramiques de fonderie pour aubes de turbomachine

Also Published As

Publication number Publication date
RU2461439C2 (ru) 2012-09-20
US20080251979A1 (en) 2008-10-16
JP2008260065A (ja) 2008-10-30
IL190667A (en) 2013-04-30
US7931459B2 (en) 2011-04-26
CA2629053A1 (fr) 2008-10-11
IL190667A0 (en) 2008-12-29
CA2629053C (fr) 2016-08-23
FR2914871A1 (fr) 2008-10-17
EP1980343A1 (de) 2008-10-15
FR2914871B1 (fr) 2009-07-10
RU2008114147A (ru) 2009-10-20
JP5450976B2 (ja) 2014-03-26

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