EP2274141B1 - Procede pour ebavurer un noyau de fonderie en matiere ceramique et utilisation d'un dispositif pour la mise en oeuvre d'un tel procede - Google Patents

Procede pour ebavurer un noyau de fonderie en matiere ceramique et utilisation d'un dispositif pour la mise en oeuvre d'un tel procede Download PDF

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Publication number
EP2274141B1
EP2274141B1 EP09732323.2A EP09732323A EP2274141B1 EP 2274141 B1 EP2274141 B1 EP 2274141B1 EP 09732323 A EP09732323 A EP 09732323A EP 2274141 B1 EP2274141 B1 EP 2274141B1
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EP
European Patent Office
Prior art keywords
tool
deburring
ceramic
surface portion
cutting
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
EP09732323.2A
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German (de)
English (en)
French (fr)
Other versions
EP2274141A1 (fr
Inventor
Christian Defrocourt
Serge Prigent
Daniel Quach
Patrick Wehrer
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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Publication date
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Publication of EP2274141A1 publication Critical patent/EP2274141A1/fr
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Publication of EP2274141B1 publication Critical patent/EP2274141B1/fr
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B28—WORKING CEMENT, CLAY, OR STONE
    • B28B—SHAPING CLAY OR OTHER CERAMIC COMPOSITIONS; SHAPING SLAG; SHAPING MIXTURES CONTAINING CEMENTITIOUS MATERIAL, e.g. PLASTER
    • B28B11/00—Apparatus or processes for treating or working the shaped or preshaped articles
    • B28B11/18—Apparatus or processes for treating or working the shaped or preshaped articles for removing burr
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B24—GRINDING; POLISHING
    • B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
    • B24B19/00—Single-purpose machines or devices for particular grinding operations not covered by any other main group
    • B24B19/14—Single-purpose machines or devices for particular grinding operations not covered by any other main group for grinding turbine blades, propeller blades or the like
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B24—GRINDING; POLISHING
    • B24B—MACHINES, DEVICES, OR PROCESSES FOR GRINDING OR POLISHING; DRESSING OR CONDITIONING OF ABRADING SURFACES; FEEDING OF GRINDING, POLISHING, OR LAPPING AGENTS
    • B24B9/00—Machines or devices designed for grinding edges or bevels on work or for removing burrs; Accessories therefor
    • B24B9/02—Machines or devices designed for grinding edges or bevels on work or for removing burrs; Accessories therefor characterised by a special design with respect to properties of materials specific to articles to be ground
    • B24B9/06—Machines or devices designed for grinding edges or bevels on work or for removing burrs; Accessories therefor characterised by a special design with respect to properties of materials specific to articles to be ground of non-metallic inorganic material, e.g. stone, ceramics, porcelain

Definitions

  • the present invention relates to the finishing of parts obtained by injection of a ceramic paste into a mold formed of the assembly of at least two parts, along a joint plane.
  • the invention relates more particularly to the elimination of burrs in the area of the joint plane of the two parts.
  • the invention relates to ceramic cores used in the manufacture of hollow turbine engine blades by the lost wax foundry technique.
  • foundry cores of a type called “ceramic” is particularly known in certain applications that require the achievement of a set of characteristics and stringent quality criteria such as resistance to high temperatures, lack of reactivity , dimensional stability and good mechanical characteristics.
  • these applications having such requirements there are known aeronautical applications and for example the foundry turbine blades for turbojet engines.
  • the refinement of foundry processes from the foundry known as equiaxed to the foundry by directed solidification or monocrystalline has further increased these requirements for cores whose use and complexity are imposed by the search for high performance for parts to obtain, as is the case for example for hollow vanes with internal cooling.
  • the complex crystalline structure sought in the dawn is not compatible with the burrs on the core. These can become detached during casting and pollute the room by creating inclusions and / or geometric defects. A burr that stays in place creates a crack in the room and therefore a breakaway. The cores must therefore be deburred.
  • Manual deburring has the risk of generating high levels of rejects with defects such as: crack initiation, kernel breakage during handling, lack of repeatability, kernel spalling resulting in inclusions in metal parts.
  • Article SP3inc "Machining guides for diabetes cutting tools" December 31, 2000 , xp002537150 discloses diamond cutting tools for machining parts made of ceramic material before firing.
  • JP2000052329-A1 discloses a method of deburring uncooked ceramics according to the preamble of claim 1.
  • the invention by deburring before firing the foundry core, it avoids the problem of dimensional variation of the core and opens the possibility of carrying out this operation by means of a controller. Automation ensures a better repeatability of deburring from one core to another. This results in a better deburring quality and a reduction in room breakage. Better kernel quality also reduces crack initiation. The result is a reduction in manufacturing cycles, which reduces costs.
  • an angle-propeller milling tool of between 20 and 70 ° and a hemispherical end is used. In this way, the cut material is dragged away from the cutting area, reducing the risk of jamming.
  • the cooling is provided by diffusion of a fluid towards the surface portion to be deburred. This is for example air.
  • the method is particularly suitable for deburring ceramic cores of turbomachine blades. It makes it possible in particular to reduce the creep primers of the cast products.
  • a finisher of ceramic cores of casting parts comprising a support for said core, a mandrel forming a tool-holder rotatable about its axis and at least one nozzle of injection of cooling fluid.
  • the figure 1 represents an example of a piece consisting of a core element for a hollow turbine engine blade.
  • the envelope of this element 10 has the shape of the internal cavity of the hollow blade once it has been melted.
  • the element 10 comprises an upper portion 10A which will constitute the designated bath part of the blade. This part is separated from the central body 10B by a space which will constitute the transverse upper wall of the hollow blade.
  • This central portion 10B is extended downwardly by the foot 10D which is used for gripping and fixing the core in the shell mold in which the molten metal is cast.
  • the central portion is hollowed out with longitudinal openings 10B 'which will constitute the internal partitions defining the circuit of the cooling fluid to inside the dawn cavity.
  • Part 10B is extended laterally on one side by a portion of the trailing edge 10C which is thinner and has openings 10C 'which will constitute partitions between them channels which open along the trailing edge of the blade for the evacuation of the cooling fluid.
  • the core is intended after casting of the metal and its cooling to be removed to release the circulation cavity of the cooling air of the blade.
  • This piece is obtained by injection of a ceramic paste using a press.
  • the paste is obtained by mixing a binder, an organic polymer, and particles of ceramic materials.
  • the mixture is injected by means of injection presses, such as screw injection presses, into a metal injection mold.
  • This mold is formed of an assembly of at least two elements with cavity which are brought into contact with each other along a junction surface which is commonly referred to as joint plane.
  • joint plane a junction surface which is commonly referred to as joint plane.
  • the paste gradually spreads from the inlet to the volume formed by the fingerprints. However material passes and infiltrates between the surfaces of the joint plane. When demolding, this excess material forms the burrs.
  • We have shown on the figure 2 the appearance of the core of the figure 1 at the outlet of the injection mold.
  • the areas corresponding to the joint planes of the mold parts are extended by a burr. For example, we see the B1 burr along the edge of the core. Another burr B2 is visible along the inner edges of the recesses 10C 'in the area of the trailing edge 10C. A burr B3 is also seen along the edges of the recesses 10B 'in the zone 10B.
  • the rest of the process of manufacturing the core consists, after the injection, to unmold the core, bake it in a furnace at high temperature, then to ensure its finishing and dimensional control.
  • finishing is to remove B1, B2, B3. They can be removed either just after the injection of the mixture, it is a deburring before cooking or after cooking it is then a deburring core in the cooked state.
  • the material is removed before firing, on the part after injection of the polymer-ceramic mixture in order to eliminate said problems related to the deformation of the part during and after firing.
  • the method of the invention defines core cutting parameters taking into account the intrinsic properties of the material thereof.
  • polyethylene glycol for example, has properties that can change in the vicinity of room temperature, in particular it tends to soften. This causes, when attacking the material forming the burr with a conventional milling, stuffing material. This material jam eventually prevents the removal of the burr.
  • a helical bur is used, that is to say with a longitudinal cutting edge in the form of a helix.
  • the inclination of the helix is defined by a helix angle ⁇ of between 20 and 70 degrees preferably between 35 and 65 degrees.
  • the diameter of the cutter suitable for this operation given the narrow spaces formed by the recesses is between 0.5 and 1 mm.
  • the end of the cutter is preferably hemispherical.
  • the material constituting the flash is maintained at a temperature below the glass transition temperature.
  • One way is to provide nozzles that expel cool air towards the end of the moving cutter.
  • the temperature is maintained between 16 and 26 ° C.
  • the tool is rotated on itself along the burr to be eliminated.
  • the cutting and feed speeds are adapted to the profile. For example they differ between the contour and the pocket of the core or the grooves at the exit of the trailing edge.
  • the illustrative cutting speed is between 5 and 25 m per minute and the feed rate is between 400 and 1800 mm per minute.
  • the piece 10 is fixed on a support 300 so as to make its contour accessible to a cutter 100 itself mounted on a mandrel 200 forming a tool holder.
  • the air injection nozzle 400 or any other suitable cooling fluid is directed on the surface of the portion of the workpiece to be deburred.
  • the figure 5 shows a deburring device.
  • the mandrel 200 is secured to a rotating support 210 which itself can be mounted on a milling machine, not shown, with three axes for example.
  • a fixed plate 220 serves to support the nozzle 400 via a bracket 410 adjustable in position. The plate may have several nozzles as needed.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Ceramic Engineering (AREA)
  • Structural Engineering (AREA)
  • Inorganic Chemistry (AREA)
  • Molds, Cores, And Manufacturing Methods Thereof (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Milling Processes (AREA)
  • Devices For Post-Treatments, Processing, Supply, Discharge, And Other Processes (AREA)
EP09732323.2A 2008-04-18 2009-04-17 Procede pour ebavurer un noyau de fonderie en matiere ceramique et utilisation d'un dispositif pour la mise en oeuvre d'un tel procede Active EP2274141B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0802179A FR2930188B1 (fr) 2008-04-18 2008-04-18 Procede pour ebavurer une piece en matiere ceramique.
PCT/EP2009/054591 WO2009127721A1 (fr) 2008-04-18 2009-04-17 Procede pour ebavurer un noyau de fonderie en matiere ceramique

Publications (2)

Publication Number Publication Date
EP2274141A1 EP2274141A1 (fr) 2011-01-19
EP2274141B1 true EP2274141B1 (fr) 2015-06-03

Family

ID=40243939

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09732323.2A Active EP2274141B1 (fr) 2008-04-18 2009-04-17 Procede pour ebavurer un noyau de fonderie en matiere ceramique et utilisation d'un dispositif pour la mise en oeuvre d'un tel procede

Country Status (9)

Country Link
US (1) US8490673B2 (zh)
EP (1) EP2274141B1 (zh)
JP (1) JP5416762B2 (zh)
CN (1) CN102056717B (zh)
BR (1) BRPI0910569B1 (zh)
CA (1) CA2721449C (zh)
FR (1) FR2930188B1 (zh)
RU (1) RU2501639C2 (zh)
WO (1) WO2009127721A1 (zh)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2977510B1 (fr) * 2011-07-08 2019-08-16 Safran Aircraft Engines Noyau de fonderie, procede de fabrication d'une aube de turbine utilisant un tel noyau.
DE102013013268A1 (de) 2013-08-08 2015-02-12 Technische Hochschule Mittelhessen Verfahren zur Verwertung von Zuckerrübenschnitzel und anderer cellulosehaltiger Biomasse durch Doppelcarbonisierung
CN104550760B (zh) * 2014-12-31 2016-07-06 北京钢研高纳科技股份有限公司 一种可溶芯修补方法
CN105234350B (zh) * 2015-11-17 2017-05-03 沈阳明禾石英制品有限责任公司 一种厚大且尺寸突变陶瓷型芯及其制备方法
FR3046736B1 (fr) * 2016-01-15 2021-04-23 Safran Noyau refractaire comprenant un corps principal et une coque
CN106514876B (zh) * 2016-09-27 2018-03-09 淮阴工学院 氧化锆陶瓷的切削方法
FR3059259B1 (fr) * 2016-11-29 2019-05-10 Jy'nove Procede de fabrication d'un noyau ceramique de fonderie
ES2862748T5 (es) 2017-10-10 2024-05-07 Continental Reifen Deutschland Gmbh Mezcla de caucho reticulable con azufre, vulcanizado de la mezcla de caucho y neumáticos para vehículo
US10814454B2 (en) 2018-05-24 2020-10-27 General Electric Company Tool guide for tie bar removal from casting cores

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5996912A (ja) * 1982-11-26 1984-06-04 株式会社東芝 セラミツク製品の製造法
JPS62268607A (ja) * 1986-05-19 1987-11-21 株式会社東芝 セラミツクスの機械加工方法およびその装置
FR2626794B1 (fr) * 1988-02-10 1993-07-02 Snecma Pate thermoplastique pour la preparation de noyaux de fonderie et procede de preparation desdits noyaux
SU1634506A1 (ru) * 1988-04-18 1991-03-15 Винницкий политехнический институт Устройство дл зачистки керамических изделий
US5465780A (en) * 1993-11-23 1995-11-14 Alliedsignal Inc. Laser machining of ceramic cores
JPH07256544A (ja) * 1994-03-23 1995-10-09 Ngk Insulators Ltd セラミックス製ロータのバリ取り方法及びバリ取り装置
JP3406415B2 (ja) * 1994-10-19 2003-05-12 日本碍子株式会社 セラミック素材及びこれを利用したセラミック製品の製造方法
JP2003205495A (ja) * 2002-01-11 2003-07-22 Murata Mfg Co Ltd グリーンシートの積層装置
JP4202665B2 (ja) * 2002-03-27 2008-12-24 日本特殊陶業株式会社 焼成済セラミック成形体の製造方法、及びセラミックヒータの製造方法
US7101263B2 (en) * 2002-11-06 2006-09-05 United Technologies Corporation Flank superabrasive machining
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
JP4736578B2 (ja) * 2005-07-11 2011-07-27 Ｔｄｋ株式会社 グリーンシート積層体切断装置
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
CN102056717B (zh) 2012-10-24
FR2930188A1 (fr) 2009-10-23
JP2011516318A (ja) 2011-05-26
FR2930188B1 (fr) 2013-09-20
CA2721449A1 (fr) 2009-10-22
WO2009127721A1 (fr) 2009-10-22
BRPI0910569A2 (pt) 2015-09-22
CN102056717A (zh) 2011-05-11
RU2010146980A (ru) 2012-05-27
BRPI0910569B1 (pt) 2019-02-26
JP5416762B2 (ja) 2014-02-12
US20110049748A1 (en) 2011-03-03
US8490673B2 (en) 2013-07-23
EP2274141A1 (fr) 2011-01-19
RU2501639C2 (ru) 2013-12-20
CA2721449C (fr) 2016-08-16

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