EP1193006A2 - Procédé de fabrication d'une pièce coulée de précision refroidie - Google Patents

Procédé de fabrication d'une pièce coulée de précision refroidie Download PDF

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Publication number
EP1193006A2
EP1193006A2 EP01115998A EP01115998A EP1193006A2 EP 1193006 A2 EP1193006 A2 EP 1193006A2 EP 01115998 A EP01115998 A EP 01115998A EP 01115998 A EP01115998 A EP 01115998A EP 1193006 A2 EP1193006 A2 EP 1193006A2
Authority
EP
European Patent Office
Prior art keywords
casting
wax
core
cooling
mold
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
EP01115998A
Other languages
German (de)
English (en)
Other versions
EP1193006B1 (fr
EP1193006A3 (fr
Inventor
Gordon Anderson
Peter Marx
Shailendra Dr. Naik
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.)
General Electric Technology GmbH
Original Assignee
Alstom Schweiz AG
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 Alstom Schweiz AG filed Critical Alstom Schweiz AG
Publication of EP1193006A2 publication Critical patent/EP1193006A2/fr
Publication of EP1193006A3 publication Critical patent/EP1193006A3/fr
Application granted granted Critical
Publication of EP1193006B1 publication Critical patent/EP1193006B1/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
    • B22C7/00—Patterns; Manufacture thereof so far as not provided for in other classes
    • B22C7/02—Lost patterns
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/49336—Blade making
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/4998—Combined manufacture including applying or shaping of fluent material
    • Y10T29/49988—Metal casting
    • Y10T29/49989—Followed by cutting or removing material

Definitions

  • the invention relates to a method for producing a cooled Investment casting of a thermal turbomachine according to the preamble of Claim 1.
  • Castings of thermal turbomachinery are known by Casting process made.
  • Casting furnaces for such casting processes are for example from the documents EP-A1-749 790, US-3,763,926 or US-3,690,367 known.
  • the molds are generally characterized by a Wax model provided.
  • a process for making a complex Part of a gas turbine by means of a casting mold is, for example, from the Document US-5,296,308 known.
  • a core is inserted into the wax model.
  • This Core contains the structure of the cavity, which is inside the casting forms a certain cooling structure. With these castings, it must be between the Wax model and the core a wax seal can be attached to one Penetration of the slip, which forms the mold when dry, into the To prevent space.
  • the wax seal is applied to a hand Step, which is next to the core, applied.
  • Ultimately has the stage to include a cooling plate.
  • the cooling plate is on the The stage is soldered or welded and is used for impingement cooling by means of cooling holes the platform below. To avoid leakage the cooling air should be flat on the surface of the step. But this is in Contrary to the attached wax seal, which after casting a Material accumulation above the level results.
  • To the goal of a level Getting closer to the surface of the step is an additional process step such as grinding or eroding.
  • the invention is based on the object of a method for the production of a thermally stressed and cooled casting of a thermal To create turbomachine by means of a known casting process, wherein the casting of the casting with a wax model and a ceramic Core is manufactured, and the subsequent manufacturing steps are simplified and be optimized.
  • the object is achieved by a method according to the Preamble of claim 1 solved in that before producing the Mold of the casting between the wax model and the core Wax seal is only applied to a paragraph, which is located above the step to the side of the core.
  • this can be prevented even during the casting process that there are bumps on the step, which is a leak for mean the cooling air on the cooling plate.
  • the material that the Wax seal and the heel created during the casting process can ground down by a unified process step or on others, appropriately removed without unevenness form at the level. At this stage, a cooling plate can be used without further Process steps are soldered.
  • the invention relates to a method for producing a thermal loaded and cooled investment casting of a thermal turbo machine.
  • This can be, for example, a guide or Blade or around other cooled rotor or stator segments one Act gas turbine or a compressor.
  • the castings are generally known from the prior art Manufactures casting furnaces. With such a casting furnace can be complex trained and high thermal and mechanical loads removable components are manufactured. Depending on the process conditions it is possible to solidify the casting body in a directed manner. There is the Possibility of using it as a single crystal (SX) or polycrystalline Stem crystals which have a preferred direction ("directionally solidified "(DS). It is particularly important that the directional solidification takes place under conditions in which between a cooled portion of a molten raw material receiving Mold and the still molten starting material a strong one Heat exchange takes place. A zone can then freeze in a directed manner Form materials with a solidification front, which with permanent withdrawal of heat with the formation of the directly solidified casting body by the Mold moves.
  • the device consists of a vacuum chamber, which is a contains upper heating chamber and a lower cooling chamber. Both chambers are separated by a baffle.
  • the vacuum chamber holds a mold, which is filled with a melt.
  • thermal and mechanically resilient parts as in the case of guide and rotor blades from Gas turbines, for example, will be a superalloy based on Nickel used.
  • the baffles In the middle of the baffles there is an opening through which slowly removes the mold from the heating chamber during the process is moved into the cooling chamber so that the casting is from the bottom up directed frozen. The downward movement is done by a drive rod, on which the mold is stored. The bottom of the mold is executed water-cooled. Below the baffles are means to produce and leading a gas flow. These funds provide through the Gas flow next to the lower cooling chamber for additional cooling and thereby for a larger temperature gradient at the Solidification front.
  • FIG. 1 shows a wax model 10 of a casting 1, for example one to be poured turbine blade.
  • the turbine blade has a platform 2, an airfoil 3 and a blade tip 2.
  • This wax model 10 is then converted into a liquid, ceramic material, which is also a slip is called immersed. This forms around the wax model 10 later casting mold of the casting 1.
  • the ceramic Material dried so that the mold with which the casting 1 is produced, arises.
  • the wax is removed by an appropriate heat treatment, i.e. burned out.
  • the mold is also fired, i.e. in this way it contains its firmness.
  • the casting 1 is so created mold by a known, closer above Cast iron described described manufactured in a known manner. Later that ceramic mold and the core removed in a suitable manner, so for Example using an acid or a base.
  • the turbine blade of Figure 1 has a cavity in which during the Operation of the turbomachine cooling air is initiated. This cooling air can Leave the finished turbine blade again through cooling holes 5.
  • a ceramic core 6 during the production process of the casting mold, which reflects the internal geometry of the cavity.
  • the turbine 2 is additionally platform 2 by impingement cooling cooled.
  • the cast component is at a level 7 which is located next to the ceramic core 6 and on the edge of the platform 2, a cooling plate 11, in which there are cooling holes 12, soldered or welded. This cooling plate 11 is described in more detail in FIG. 3.
  • This wax seal 8 has the goal of unwanted penetration of slip to prevent in the interior of the ceramic core 6.
  • FIG. 2 shows a section along the line II - II of Figure 1 through the Stage 7, the wax seal 8 and through the ceramic core 6.
  • the wax seal 8 is only on a shoulder 9 attached, which above level 7 towards the ceramic core 6 located.
  • stage 7 and the Wax seal 8 additional, also cast material on the Turbine blade. As can be seen in FIG. 3, this has a certain one Height s, and can be independent of level 7 or regardless of the Machined surface of level 7, i.e. be sanded. This unified process step can also be done by erosion.
  • the Stage 7, to which the cooling plate 11 is soldered remains in spite of this additional editing process is unaffected, which in any case is a smooth Level 7 surface guaranteed.
  • the cooling air 13 penetrates through the Cooling holes 12 and can cool the platform 2 by impingement cooling.
  • the Smooth surface of level 7 is so important, because even a small one Unevenness in the cooling performance of this impingement cooling due to leakage losses Reduce.
  • Another advantage is that through the existing Paragraph 9 the liquid solder, which is distributed over the whole stage 7, is prevented from flowing into the cavity of the casting 1. Since the Operation of the casting 1 is also an insert in the cavity, it is important that no solder sticks to this insert and thus the proper functioning is impaired.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Molds, Cores, And Manufacturing Methods Thereof (AREA)
EP01115998A 2000-08-07 2001-06-30 Procédé de fabrication d'une pièce coulée de précision refroidie Expired - Lifetime EP1193006B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10038453 2000-08-07
DE10038453A DE10038453A1 (de) 2000-08-07 2000-08-07 Verfahren zur Herstellung eines gekühlten Feingussteils

Publications (3)

Publication Number Publication Date
EP1193006A2 true EP1193006A2 (fr) 2002-04-03
EP1193006A3 EP1193006A3 (fr) 2003-05-21
EP1193006B1 EP1193006B1 (fr) 2005-08-31

Family

ID=7651569

Family Applications (1)

Application Number Title Priority Date Filing Date
EP01115998A Expired - Lifetime EP1193006B1 (fr) 2000-08-07 2001-06-30 Procédé de fabrication d'une pièce coulée de précision refroidie

Country Status (3)

Country Link
US (1) US6435256B1 (fr)
EP (1) EP1193006B1 (fr)
DE (2) DE10038453A1 (fr)

Families Citing this family (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7752384B2 (en) * 2002-11-08 2010-07-06 Crossroads Systems, Inc. System and method for controlling access to media libraries
DE10255346A1 (de) * 2002-11-28 2004-06-09 Alstom Technology Ltd Verfahren zum Herstellen einer Turbinenschaufel
GB0413027D0 (en) * 2004-06-11 2004-07-14 Rolls Royce Plc A wax recovery method
US20080257517A1 (en) * 2005-12-16 2008-10-23 General Electric Company Mold assembly for use in a liquid metal cooled directional solidification furnace
US9403208B2 (en) 2010-12-30 2016-08-02 United Technologies Corporation Method and casting core for forming a landing for welding a baffle inserted in an airfoil
FR3035604B1 (fr) * 2015-04-30 2023-01-13 Snecma Procede de fabrication de modele pour fonderie a modele perdu
US10717130B2 (en) 2017-02-22 2020-07-21 General Electric Company Method of manufacturing turbine airfoil and tip component thereof
US11154956B2 (en) 2017-02-22 2021-10-26 General Electric Company Method of repairing turbine component using ultra-thin plate
US20180238173A1 (en) * 2017-02-22 2018-08-23 General Electric Company Method of manufacturing turbine airfoil and tip component thereof
US10610933B2 (en) * 2017-02-22 2020-04-07 General Electric Company Method of manufacturing turbine airfoil with open tip casting and tip component thereof
US10702958B2 (en) 2017-02-22 2020-07-07 General Electric Company Method of manufacturing turbine airfoil and tip component thereof using ceramic core with witness feature
US10625342B2 (en) 2017-02-22 2020-04-21 General Electric Company Method of repairing turbine component
US20190309629A1 (en) * 2018-04-05 2019-10-10 United Technologies Corporation Turbine blades and vanes for gas turbine engine
US10830354B2 (en) 2018-05-18 2020-11-10 General Electric Company Protection system with gasket for ceramic core processing operation and related method
CN112008039B (zh) * 2020-08-26 2024-06-04 合肥天鹅制冷科技有限公司 一种用于蜡模成型后的液冷装置

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3177537A (en) * 1962-12-27 1965-04-13 Prec Metalsmiths Inc Methods and apparatus for forming investment molds and mold produced thereby
US3648760A (en) * 1970-04-27 1972-03-14 Abraham J Cooper Precision investment casting apparatus
DE3234658A1 (de) * 1981-10-23 1983-05-05 Howmet Turbine Components Corp., 06830 Greenwich, Conn. Verfahren zur bildung einer rissfreien verbindung zwischen thermoplastischen festen koerpern
US5489194A (en) * 1990-09-14 1996-02-06 Hitachi, Ltd. Gas turbine, gas turbine blade used therefor and manufacturing method for gas turbine blade
DE3813287C2 (de) * 1987-06-03 1996-09-19 Rolls Royce Plc Verfahren zur Herstellung eines Metallgegenstandes
DE19726111C1 (de) * 1997-06-20 1998-11-12 Mtu Muenchen Gmbh Verfahren zur gießtechnischen Herstellung einer Turbomaschinenschaufel

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3494709A (en) * 1965-05-27 1970-02-10 United Aircraft Corp Single crystal metallic part
US3690367A (en) * 1968-07-05 1972-09-12 Anadite Inc Apparatus for the restructuring of metals
US3763926A (en) * 1971-09-15 1973-10-09 United Aircraft Corp Apparatus for casting of directionally solidified articles
US5296308A (en) * 1992-08-10 1994-03-22 Howmet Corporation Investment casting using core with integral wall thickness control means
FR2714858B1 (fr) * 1994-01-12 1996-02-09 Snecma Procédé de fabrication d'un moule carapace en matériau céramique pour fonderie à modèle perdu.
DE19539770A1 (de) * 1995-06-20 1997-01-02 Abb Research Ltd Verfahren zur Herstellung eines gerichtet erstarrten Gießkörpers und Vorrichtung zur Durchführung dieses Verfahrens
EP0894558A1 (fr) * 1997-07-29 1999-02-03 Siemens Aktiengesellschaft Aube de turbine et procédé de fabrication d'un aube de turbine

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3177537A (en) * 1962-12-27 1965-04-13 Prec Metalsmiths Inc Methods and apparatus for forming investment molds and mold produced thereby
US3648760A (en) * 1970-04-27 1972-03-14 Abraham J Cooper Precision investment casting apparatus
DE3234658A1 (de) * 1981-10-23 1983-05-05 Howmet Turbine Components Corp., 06830 Greenwich, Conn. Verfahren zur bildung einer rissfreien verbindung zwischen thermoplastischen festen koerpern
DE3813287C2 (de) * 1987-06-03 1996-09-19 Rolls Royce Plc Verfahren zur Herstellung eines Metallgegenstandes
US5489194A (en) * 1990-09-14 1996-02-06 Hitachi, Ltd. Gas turbine, gas turbine blade used therefor and manufacturing method for gas turbine blade
DE19726111C1 (de) * 1997-06-20 1998-11-12 Mtu Muenchen Gmbh Verfahren zur gießtechnischen Herstellung einer Turbomaschinenschaufel

Also Published As

Publication number Publication date
US20020029863A1 (en) 2002-03-14
DE50107262D1 (de) 2005-10-06
EP1193006B1 (fr) 2005-08-31
DE10038453A1 (de) 2002-02-21
US6435256B1 (en) 2002-08-20
EP1193006A3 (fr) 2003-05-21

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