EP1155760B1 - Procédé de fabrication d'une pièce moulée à charge thermique élevée - Google Patents

Procédé de fabrication d'une pièce moulée à charge thermique élevée Download PDF

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Publication number
EP1155760B1
EP1155760B1 EP01109115A EP01109115A EP1155760B1 EP 1155760 B1 EP1155760 B1 EP 1155760B1 EP 01109115 A EP01109115 A EP 01109115A EP 01109115 A EP01109115 A EP 01109115A EP 1155760 B1 EP1155760 B1 EP 1155760B1
Authority
EP
European Patent Office
Prior art keywords
casting
cooling
polymer foam
process according
protective layer
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.)
Expired - Lifetime
Application number
EP01109115A
Other languages
German (de)
English (en)
Other versions
EP1155760A1 (fr
Inventor
Dr. Alexander Beek
Dr.Peter Ernst
Reinhard Fried
Hans-Joachim Rösler
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 Technology 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 Technology AG filed Critical Alstom Technology AG
Priority to EP05111586A priority Critical patent/EP1645347B1/fr
Publication of EP1155760A1 publication Critical patent/EP1155760A1/fr
Application granted granted Critical
Publication of EP1155760B1 publication Critical patent/EP1155760B1/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
    • B22C7/00—Patterns; Manufacture thereof so far as not provided for in other classes
    • B22C7/02—Lost patterns
    • B22C7/023—Patterns made from expanded plastic materials
    • 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
    • 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
    • B22C9/00—Moulds or cores; Moulding processes
    • B22C9/02—Sand moulds or like moulds for shaped castings
    • B22C9/04—Use of lost patterns
    • B22C9/043—Removing the consumable pattern
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/182—Transpiration cooling
    • F01D5/183—Blade walls being porous
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/186—Film cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/21—Manufacture essentially without removing material by casting
    • F05D2230/211—Manufacture essentially without removing material by casting by precision casting, e.g. microfusing or investment casting
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/606—Directionally-solidified crystalline structures
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/611—Coating
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/612—Foam

Definitions

  • the invention relates to a method for producing a thermally loaded casting of a thermal turbomachine according to the preamble of claim 1.
  • thermal turbomachines charged with hot gas for example turbine blades of gas turbines
  • cooling air bores or with cooling structures in order to be able to increase the temperature of the hot gas on the one hand and to extend the service life of the affected parts on the other hand.
  • the inside or a double-walled cooling system, for example, of a turbine blade with cooling air is cooled by dissipating the heat to the outside.
  • the outside of the blade is cooled by a film, which forms on the surface of the turbine blade. The aim is to make film cooling as effective as possible while at the same time reducing the amount of cooling air.
  • metal felts in turbine blades are known. This is apparent, for example, from the documents DE-C2-32 03 869 or from DE-C2-32 35 230.
  • This application of a metal felt has the task of providing an (internal) cooling system.
  • this metal felt can serve as protection against abrasion by external mechanical loads, in particular when it has been arranged on the outside of the turbine blade and coated with a ceramic protective layer.
  • a turbine blade with similar properties is also known from European publication EP-B1-132667.
  • the invention is based on the object to provide a method for producing a thermally loaded casting of a thermal turbomachine with an integrated cooling structure, which increases the efficiency of the turbomachine.
  • the cooling structure should consist of the same material as the casting and, if possible, can be produced in one step during the casting process.
  • the object is achieved by a method according to the preamble of claim 1 in that a wax model of the part to be cooled is provided, at least one polymer foam is provided, which is stapled to the wax model or introduced into a cavity of the wax model containing at least one polymer foam and the wax model in a ceramic material be immersed, wherein the ceramic material accumulates around the wax model and also fills the polymer foam with the ceramic material, the ceramic material is dried, so that a mold is formed, the wax and the at least one polymer foam are removed by a heat treatment, the Casting with the mold is made by a known casting process and the ceramic material is removed.
  • an externally whitening, open-pored cooling structure can be coated with a ceramic protective layer in front of the casting additional, external abrasion and to protect it from the surrounding hot gases. Due to the open-pored structure of the metal foam, the ceramic protective layer adheres very well to it and the possibility of chipping due to the extreme operating conditions is reduced. In addition, the cooling under the ceramic protective layer is still ensured, provided that the cooling structure is not completely penetrated by the ceramic protective layer.
  • a polymer foam with a variable pore size can be used so as to strengthen or reduce cooling of certain areas of the cooling system compared to other areas.
  • the thermally loaded casting may be a nozzle or bucket, a heat release segment, a platform of the nozzle or bucket, or a combustor wall of a gas turbine, or a bucket of a compressor.
  • the invention relates to a method for producing a thermally loaded casting of a thermal turbomachine.
  • these may be, for example, a guide or moving blade of a gas turbine or a compressor, a heat recovery segment of a gas turbine, the wall of a combustion chamber or a similar, highly thermally loaded casting.
  • castings are manufactured using casting furnaces generally known in the art. Such a casting furnace can be used to produce complex components that can be exposed to high thermal and mechanical stresses. Depending on the process conditions, it is possible to produce the casting body directionally solidified. In this case, it is possible to form it as single crystal ("single crystal", SX) or polycrystalline as columnar crystals which have a preferred direction ("directionally solidified", DS). Of particular importance is that directed solidification occurs under conditions where there is a strong heat exchange between a cooled part of a molten raw material receiving mold and the still molten raw material. It may then form a zone of directionally solidified material with a solidification front, which migrates with continuous removal of heat to form the directly solidified Giess stressess by the mold.
  • SX single crystal
  • DS directionally solidified
  • the device consists of a vacuum chamber containing an upper heating chamber and a lower cooling chamber. Both chambers are separated by a baffle.
  • the vacuum chamber receives a mold, which is filled with a melt.
  • a superalloy based on nickel is used.
  • In the middle of the baffle there is an opening through which the mold is slowly moved from the heating chamber into the cooling chamber during the process so that the casting solidifies from the bottom upwards. The downward movement is done by a drive rod on which the mold is mounted.
  • the bottom of the mold is water cooled.
  • Below the baffle means for generating and guiding a gas flow are present. These means provide by the gas flow next to the lower cooling chamber for additional cooling and thus for a larger temperature gradient at the solidification front.
  • the turbine blade 1 of Figure 1 has a cavity 6, from which cooling air 18 is passed through inner cooling holes 8,8b in the double-walled cooling system 7 during operation of the turbomachine.
  • the arrows indicate the flow direction of the cooling air 18.
  • the cooling air 18 then flows both inside the turbine blade in the height and to the trailing edge 3 of the turbine blade 1. It can the cooling system 7 at the trailing edge 3, to outer cooling holes 8,8 a or to larger cooling holes 8,8 c, both at the front 2, on the pressure side 4 or on the suction side 5 may be present, leave again.
  • Film cooling is established at the outer cooling holes 8, 8a, while the walls inside the cooling system 7 are cooled by convection.
  • axial ribs 10 may also be present within the cooling system 8, in which case no metal foam 9 is present and in which the cooling air 18 can flow unhindered.
  • FIG. 3 which shows the front edge 2 from the blade root 9 to the blade tip 10 in the form of a longitudinal section through a turbine blade 1 according to the invention, reveals the flow direction of the cooling air 18.
  • the cooling air 18 enters the cooling system 7 through internal cooling openings 8, 8b from the cavity 6 on.
  • the cooling air 18 then flows through the pores of the metal foam 9, which is located within the cooling system 7.
  • the aim of the invention is now to produce such, filled with open-cell metal foam 9 cooling systems 7 already during the casting process with cast iron furnace, as mentioned above, integral with the entire casting.
  • a wax model of the part to be cooled is provided.
  • An open-pore polymer foam which, for example, a Polyurethane foam is stapled to the wax model of the part to be molded or introduced into a possibly existing cavity of the wax model.
  • Various wax / polymer models can also be stapled together to form an entire model.
  • the polymer foam and the wax model is then immersed in a liquid, ceramic material, which is also called slip. Not only does the wax mold form the casting's casting mold, but the ceramic material also penetrates into the pores of the polymer foam.
  • the slurry penetrates the polymer foam completely because it is an open-pore foam.
  • the ceramic material is dried, so that the mold with which the casting is produced arises.
  • the wax and also the polymer foam is removed by a suitable heat treatment, ie burned out.
  • the casting mold is fired, ie it contains its strength in this way.
  • the casting is made in a known manner with the resulting mold by a known, further described above furnace. Since the liquid alloy penetrates without difficulty during filling not only in the mold itself, but also in the pores formed by the polymer foam, which form the subsequent cooling system, the above-mentioned metal foam 9 is formed as a cooling system 7 simultaneously during the solidification of the alloy.
  • the cast part and the metal foam then consist of one part and further process steps for producing the cooling structure do not occur.
  • This type of production avoids by the casting process and the subsequent solidification also a porosity of the superalloy within the metal foam 9, since even during filling the liquid alloy evenly distributed within the open-pore mold (created by the polymer foam).
  • the ceramic casting mold can then be removed in a suitable manner, for example by using an acid or an alkali.
  • FIG. 2 schematically shows a section through a turbine blade 1 according to the invention.
  • the cooling structure 7 is present only at the front edge 2 of the turbine blade 1.
  • This cooling structure 7 was created as described above by simply adhering the polymer foam to the wax model. All other manufacturing steps are the same.
  • the cooling air 18 penetrates from the cavity 6 through the cooling holes 8,8b in the cooling structure 7 a.
  • the cooling structure 7 itself is coated with a ceramic protective layer 11 (Thermal Barrier Coating, TBC). This is done, for example, by a known from the prior art plasma spray method or an equivalent coating method.
  • TBC Thermal Barrier Coating
  • the coating of the porous cooling structure 7 with TBC can be done in various ways (by varying the parameters such as spray angle, distance, particle size, velocity, temperature, etc.).
  • the cooling structure 7 can be completely penetrated with TBC, so that the pores of the metal foam 9 are completely filled. Pores allow very good adhesion of the TBC.
  • the cooling structure 7 may also be covered with TBC only in a layer near the surface, so that there is still a layer underneath the protective layer of TBC into which cooling air 18 can penetrate. It is also conceivable that cooling holes 8 are present within the protective layer 11, through which the cooling air 18 exits to the outside. Due to the open-pore structure of the metal foam 9, the ceramic protective layer 11 adheres very well.
  • the adhesion of the ceramic protective layer 11 to the cooling structure By a coarsening to the pore size outward (where the protective layer 11 is applied), the adhesion of the ceramic protective layer 11 to the cooling structure to be improved.
  • the chipping of the TBC during operation of the casting by poor adhesion to the base material is advantageously significantly reduced or prevented.
  • the ceramic protective layer 11 itself is porous enough to allow the passage of cooling air to a sufficient extent, no external cooling holes are required. In this way, a so-called sweat cooling can be achieved, which has proven to be very effective in the cooling effect.
  • Possible cooling holes 8 within the ceramic protective layer 11 may be formed by appropriate masking prior to coating with TBC and unmasking by suitable means thereafter.
  • the masking can be done, for example, with polymer foam, which is burned out for unmasking.
  • a second way of masking the surface is to provide places within the mold that occupy that location. In this case, the ceramic mold is removed at these locations only after coating with TBC.
  • a metal foam 9 as in FIG. 2 on the outer surface and the additional coating with TBC makes sense, in particular, at the points at which abrasion by mechanical action can occur, for example at the blade tip of a turbine blade 1 or on a heat release segment, since the open-pore structure of the metal foam 9 is very flexible and not clogged by the abrasion itself. Overall, however, the abrasion is reduced by the flexibility of the metal foam 9.
  • FIGS. 4 to 8 Casting parts, as shown in FIGS. 4 to 8, can also be produced by the method according to the invention.
  • Figures 4 and 5 show a heat rejection segment 14 of a gas turbine.
  • This heat statement 1 can have a double-walled cooling structure 7 (FIG. 4) or also an externally attached metal foam 9 (FIG. 5), which, analogously to the turbine blade of FIG. 2, can be completely or partially coated with a protective layer 11 made of TBC.
  • the heat dissipation segment is traversed by cooling air 18. This is made possible by the open-pore metal foam 9.
  • the cooling air 18 penetrates through cooling holes 8 in the cooling system 7 and leaves it through this again.
  • FIGS. 6a, 6b show two variants of section VI of FIG. 5.
  • the metal foam 9 can obtain a different pore size by varying the pore size of the polymer foam during the production process.
  • FIG. 6a shows the metal foam 9 1 , 9 2 with a variable pore size. This allows a stronger or a weaker cooling einzetner areas of the casting. As already mentioned above, this is also advantageous for a better hold of the protective layer 11 on the metal foam 9.
  • the protective layer 11 may also be pierced with cooling holes 8 through which the cooling air 18 can flow to the outside.
  • the cooling system 7 consists of several layers of the metal foam 9 and intermediate plates 15.
  • the number of layers metal foam 9 / plate 15 is selected only by way of example and depends on special application. Already during production, as described above, several layers of wax / polymer foam are provided, from which subsequently the casting mold for the casting, as already described above, is manufactured. This leads during production directly to the embodiment shown in Figure 6b.
  • the cooling air 18 penetrates the metal foam 9, can flow within a "plane" and cool by convection or transpiration. Although the various planes are separated by the plates 15, there are cooling holes 8 through which the cooling air 18 can change the plane. Generally, the specific design depends Of course, this cooling system 7 from the individual case.
  • the cooling holes 8 within the plates 15 are also already produced during manufacture.
  • the embodiment also applies to the guide vane 16 shown in FIG. 7, which has two cooled platforms 17, and the likewise cooled combustion chamber wall 19 shown in FIG. 8.
  • Further exemplary embodiments, which are not illustrated with figures, are the cooled castings (FIG. Shovels, etc.) of a compressor.
  • the castings with an integrated, open-pore cooling system 7 produced by the method according to the invention are also advantageous because the pressure difference of the cooling medium between the external pressure and the internal pressure (inside the cavity 6) greatly influences the effectiveness of the cooling. This pressure difference can be very well adjusted and controlled by the appropriate choice of pores (distribution, size, etc.) of the metal foam 9.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Claims (9)

  1. Procédé de fabrication d'une pièce coulée sollicitée thermiquement (1, 14, 16, 17) d'une turbomachine thermique avec un procédé de coulée connu, la pièce coulée sollicitée thermiquement (1, 14, 16, 17) présentant une structure de refroidissement intégrée (7) et étant fabriquée avec un moule de coulée,
    caractérisé en ce que
    (a) un modèle en cire de la pièce à refroidir est fourni ;
    (b) au moins une mousse de polymère est fournie, laquelle est adhérée au modèle en cire ou est introduite dans un espace creux du modèle en cire,
    (c) l'au moins une mousse de polymère et le modèle en cire sont plongés dans un matériau céramique (barbotine), le matériau céramique se déposant autour du modèle en cire et la mousse de polymère se remplissant aussi du matériau céramique,
    (d) le matériau céramique est séché, de sorte qu'il se forme un moule de coulé,
    (e) la cire et l'au moins une mousse de polymère sont enlevées par un traitement thermique,
    (f) la pièce coulée (1, 14, 16, 17) est fabriquée avec le moule de coulée par un procédé de coulée connu et
    (g) le matériau céramique est enlevé.
  2. Procédé selon la revendication 1,
    caractérisé en ce que
    l'on revêt une structure de refroidissement (7) à pores ouverts, se trouvant sur la pièce coulée (1, 14, 16, 17), tournée vers l'extérieur, avec une couche de protection céramique (11).
  3. Procédé selon la revendication 2,
    caractérisé en ce que
    la couche de protection céramique (11) traverse complètement la structure de refroidissement (7) ou la structure de refroidissement (7) n'est revêtue que près de la surface avec la couche de protection (11).
  4. Procédé selon la revendication 3,
    caractérisé en ce que
    aux endroits de la surface de la pièce coulée (1, 14, 16, 17) auxquels des trous de refroidissement (8) doivent se produire, avant le revêtement avec une couche de protection céramique (11), on prévoit un masquage et ces endroits sont démasqués à nouveau après le revêtement.
  5. Procédé selon la revendication 1,
    caractérisé en ce que
    plusieurs couches de la mousse de polymère et de la cire sont présentes, lesquelles servent à fabriquer des structures de refroidissement à pores ouverts (7) qui sont séparées les unes des autres par des plaques (15).
  6. Procédé selon la revendication 1,
    caractérisé en ce que
    la mousse de polymère présente une taille de pores variable.
  7. Procédé selon la revendication 1,
    caractérisé en ce que
    la mousse de polymère est une mousse de polyuréthane.
  8. Procédé selon la revendication 1,
    caractérisé en ce que
    l'on utilise un procédé de coulée pour la fabrication de pièces coulées rigidifiées monocristallines ou orientées.
  9. Procédé selon la revendication 1,
    caractérisé en ce que
    le procédé est un procédé de fabrication d'une aube directrice ou mobile (1), d'un segment accumulateur de chaleur (14), d'une plate-forme (17) de l'aube directrice ou mobile (1, 16), d'une paroi de chambre de combustion (18) d'une turbine à gaz ou d'une aube directrice ou mobile (1, 16) d'un compresseur.
EP01109115A 2000-05-17 2001-04-12 Procédé de fabrication d'une pièce moulée à charge thermique élevée Expired - Lifetime EP1155760B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP05111586A EP1645347B1 (fr) 2000-05-17 2001-04-12 Procédé de fabrication d'une pièce moulée à charge thermique élevée

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10024302A DE10024302A1 (de) 2000-05-17 2000-05-17 Verfahren zur Herstellung eines thermisch belasteten Gussteils
DE10024302 2000-05-17

Related Child Applications (1)

Application Number Title Priority Date Filing Date
EP05111586A Division EP1645347B1 (fr) 2000-05-17 2001-04-12 Procédé de fabrication d'une pièce moulée à charge thermique élevée

Publications (2)

Publication Number Publication Date
EP1155760A1 EP1155760A1 (fr) 2001-11-21
EP1155760B1 true EP1155760B1 (fr) 2006-02-15

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EP05111586A Expired - Lifetime EP1645347B1 (fr) 2000-05-17 2001-04-12 Procédé de fabrication d'une pièce moulée à charge thermique élevée
EP01109115A Expired - Lifetime EP1155760B1 (fr) 2000-05-17 2001-04-12 Procédé de fabrication d'une pièce moulée à charge thermique élevée

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US (1) US6412541B2 (fr)
EP (2) EP1645347B1 (fr)
DE (3) DE10024302A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2013144022A1 (fr) 2012-03-28 2013-10-03 Alstom Technology Ltd Procédé pour retirer une céramique

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EP1475567A1 (fr) * 2003-05-08 2004-11-10 Siemens Aktiengesellschaft Structure stratifiée et procédé de fabrication de la structure stratifiée
EP1481747A3 (fr) * 2003-05-27 2007-05-02 Alstom Technology Ltd Procédé de fabrication d'une pièce chargée par chaleur et piéce
EP1496140A1 (fr) * 2003-07-09 2005-01-12 Siemens Aktiengesellschaft Structure stratifiée et procédé pour sa production
EP1533113A1 (fr) 2003-11-14 2005-05-25 Siemens Aktiengesellschaft Système stratifié pour dissipation de chaleur à haute température et méthode de fabrication
US20050111966A1 (en) * 2003-11-26 2005-05-26 Metheny Alfred P. Construction of static structures for gas turbine engines
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DE10024302A1 (de) 2001-11-22
DE50114026D1 (de) 2008-07-24
EP1155760A1 (fr) 2001-11-21
US6412541B2 (en) 2002-07-02

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