EP1674174A1 - Procédé de fabrication d'un moule de fonderie - Google Patents

Procédé de fabrication d'un moule de fonderie Download PDF

Info

Publication number
EP1674174A1
EP1674174A1 EP04030823A EP04030823A EP1674174A1 EP 1674174 A1 EP1674174 A1 EP 1674174A1 EP 04030823 A EP04030823 A EP 04030823A EP 04030823 A EP04030823 A EP 04030823A EP 1674174 A1 EP1674174 A1 EP 1674174A1
Authority
EP
European Patent Office
Prior art keywords
wall
mold
model
component
produced
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
EP04030823A
Other languages
German (de)
English (en)
Other versions
EP1674174B1 (fr
Inventor
Thomas Beck
Georg Dr. Bostanjoglo
Uwe Dr. Paul
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.)
Siemens AG
Original Assignee
Siemens 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 Siemens AG filed Critical Siemens AG
Priority to EP08000499A priority Critical patent/EP1920858B1/fr
Priority to DE502004008983T priority patent/DE502004008983D1/de
Priority to DE502004009738T priority patent/DE502004009738D1/de
Priority to EP04030823A priority patent/EP1674174B1/fr
Priority to US11/318,835 priority patent/US20060162893A1/en
Publication of EP1674174A1 publication Critical patent/EP1674174A1/fr
Application granted granted Critical
Publication of EP1674174B1 publication Critical patent/EP1674174B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

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
    • 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
    • B22C9/10—Cores; Manufacture or installation of cores
    • B22C9/108—Installation of cores

Definitions

  • the invention relates to a method for producing a casting mold according to claim 1.
  • Formed as a hollow body components with complex shaped geometries and complex through-holes in the region of an outer wall of the component can be prepared in various ways.
  • a casting mold is produced from a wax model of the component, which at least in part represents the negative of the component to be produced, in that the wax model is covered with ceramic or a sand mold.
  • the object is achieved by a method for producing a casting mold according to claim 1.
  • a mold which has corresponding projections, which at least partially represent the negative of a hole.
  • FIG. 1 shows a component 1 which, for example, has a cavity 31 at least in part of its volume and can be produced with the casting mold 16 (FIGS. 2, 3, 4, 5).
  • the component 1 has at least one component wall 4, 4 ', in particular outer component walls 4, 4'.
  • at least one hole 13, in this case a through hole 13, is formed in the wall 4.
  • the hole 13 may also be a blind hole.
  • the component 1 may be metallic or ceramic, for example.
  • it is a turbine component 1 of a gas turbine 100 (FIG. 15) or steam turbine and is, for example, a turbine blade 120, 130 (FIGS. 15, 17) or a heat shield element 155 (FIG. 16), which is made, for example, of an iron, nickel or cobalt-based superalloy.
  • through holes 13 are provided, for example, as cooling air holes 13 to cool the component 1 by film cooling.
  • the through hole 13 has, for example, a round or oval-shaped hole part 7, which widened from the cavity 31 to the outer surface 11 of the wall 4 to a diffuser 10, so that there the hole 13 deviates from the shape of the hole part 7.
  • the mold 16 for such components 1 with complex shapes of a through hole 13, 7 + 10 can be made easier and faster with the method according to the invention.
  • the wall of the component 1 is, for example, 2 to 6 mm, in particular 3 to 4 mm thick.
  • the hole part 7 has a diameter of 0.3 to 1.2 mm, in particular 0.6 to 0.8 mm.
  • the diffuser 10 is formed on the outer surface 11, for example, trapezoidal and has dimensions of 1.5 to 5mm x 1.5 to 5mm and goes to a depth of 1 to 1.5mm in the component wall 4, 4 'into it.
  • Figure 2 shows schematically a part of the mold 16, which consists of an inner wall 25, in particular of a core 25 and an outer wall 28.
  • the core 25 forms, for example, a part of the cavity 31 of the component 1.
  • At least one projection 19, 34, 37 is formed of molding material.
  • the projection 19, 34, 37 extends at least over part of the space between an inner surface 20 the inner wall 25 and an inner surface 21 of the outer wall 28th
  • the continuous projection 19 extends continuously from the inner surface 20 of the inner wall to the inner surface 21 of the outer wall.
  • the continuous projection 19 has been formed by casting ceramic of a through hole 13 in a wax model 43 (FIG. 7) of the component 1 (FIGS. 9-15).
  • the continuous projection 19 in the gap 26 prevents filling with material 22 during casting, so that after removal of the mold 16 with its inner wall 25 and its outer wall 28 and the continuous projection 19, a through hole 13 results.
  • FIG. 3 shows a further embodiment of a casting mold 16, which is produced by the method according to the invention.
  • the inner projection 34, 37 'does not extend continuously from an inner surface 20 of the inner wall 25 to an inner surface 21 of the outer wall 28.
  • the inner projection 34 is formed only on the inner surface 20 of the inner wall 25 and extends to a certain distance d to the inner surface 21 of the outer wall 28th During casting, when filling the cavity 26 with material 22, therefore, the passage opening 13 is not completely formed. In the area between the inner projection 34 and the inner surface 21 of the outer wall 28, material 22 is present after the casting of the component 1. However, the area is correspondingly thin, in particular membrane-like, so that it can be easily removed in a very short time. It can also be said that at the end of the casting process, the passage opening 13 of the component 1 to be produced is still somewhat closed. This is useful, for example, if subsequently at least one coating is applied to the outer outer surface 11 of the component 1.
  • the inner projection 34 can also have a support connection 40 (indicated by dashed lines) in order to support the inner projection 34, which projects freely into the intermediate space 26, against the outer wall 28.
  • the support connection 40 is formed smaller in cross section than the cross section of the inner projection 34, 37 ', which is opposite to the outer wall 28. The support connection 40 thus represents only a part of the through hole 13 to be produced.
  • the inner projection 34 may have at its end an advantageous portion 37 'which corresponds in part to the outer projection 37 ( Figure 4) and does not contact the wall 21 but optionally has the support connection 40.
  • the complex shape of the diffuser 10 previously had to be elaborately incorporated into the molded component. This is omitted here for the most part, since only a relatively small upper portion of the diffuser 10 is to be reworked by removing material. Since, in particular, the production of the areas lying deeper in the wall 4 means considerable expenditure, for example in laser guidance, this casting mold 16 has considerable advantages.
  • FIG. 4 shows a further embodiment of a formed mold 16 which was produced by the method according to the invention.
  • the outer protrusion 37 is formed only on the inner surface 21 of the outer wall 28.
  • the outer projection 37 represents the negative 37 of the diffuser 10 of the through-opening 13 to be produced.
  • the diffuser 10 has a more complex geometry than a simple symmetrical hole and would therefore be very complicated to produce with subsequent incorporation.
  • a simply formed hole part 7 (Fig. 1) are incorporated from the diffuser region 10 in the component 1 in the wall 4. This can be done by laser processing or radio wire erosion as well as other methods.
  • a corresponding support connection 40 between the projection 37 and the inner wall 25 may be present (indicated by dashed lines).
  • FIG. 5 shows a further embodiment of a formed mold 16, which was produced by the method according to the invention.
  • an inner projection 34 is also formed on the inner surface 20 of the inner wall 25.
  • the inner projection 34 forms a further part of this passage opening 13, namely the area of the hole part 7.
  • the outer projection 37 represents the area of the diffuser 10 of the component 1 to be produced.
  • FIG. 6 shows the top view of an outer wall 28 of a formed mold 16 produced by the method according to the invention.
  • the reference numeral 34 indicates the area from which the hole part 7 will be formed.
  • the reference numeral 37 designates the region of the projection 19, which represents the diffuser region 10 of the through-hole 13 to be produced.
  • FIGS. 7 to 14 show how a casting mold 16 according to FIGS. 2 to 6 is to be produced according to the invention.
  • FIG. 7 shows the inner wall 25 or the core 25 of the casting mold 16, on which a model 43, in particular made of wax, is present, which corresponds in its geometry and thickness to the component 1 to be produced.
  • the inner wall 25 represents the core 25, for example.
  • the model 43 for example, like the component 1 to be produced with the casting mold 16, is a hollow component.
  • the wax model 43 is internally filled with a ceramic 25 (FIG. 7) and externally covered with an outer wall 28 (FIG. 8), in which case the model, in particular a wax model 43, is removed (eg. B. by melting), so that a mold 16 (Fig. 2, 3, 4) is formed.
  • material for example, liquid metal is poured into the mold 16, the component 1 is formed.
  • At least one depression 46 according to FIGS. 9 to 12 is introduced into this model 43.
  • This depression 46 is not the cavity of the model 43, but starts, for example, from the surface 58 of the model 43.
  • the recess 46 extends, for example, all the way through the model 43, that is to say to the inner wall 25 ( Figure 9), or is formed as a blind hole ( Figure 10) which does not extend to the inner wall 25, i. extends only over part of the wall thickness of the model 43.
  • the recess 46 can be inserted into the model 43 when the inner wall 25 or the core 25 already with the model 43 are merged ( Figure 9) or before this occurs ( Figure 12).
  • the recess 46 can be made in various ways, for example by drilling, milling or laser machining.
  • this recess 46 may have an oblique hole or oblique "hole” 49, as shown in Figure 11, 12.
  • an inner wall 25 or outer wall 28 having an oblique projection can not be produced by molding a ceramic into a corresponding mold and releasing the mold by peeling or loosening.
  • the through recess 46 (FIGS. 9, 12) is completely filled with material 52, which for example corresponds to the ceramic of the inner wall 25 or the outer wall 28 (FIG. 13).
  • material 52 for example corresponds to the ceramic of the inner wall 25 or the outer wall 28 (FIG. 13).
  • This can be done together with the introduction or application of the material for the core 25 or for the outer wall 28.
  • a sand mold is often used, which is applied to the surface 58 of the model 43, thereby filling the recesses 46 in the desired manner.
  • the recess 46 can be filled separately with material 52 before applying the outer wall 28.
  • the material 52 is introduced, for example in the form of a slurry and cured, for example, when the outer wall 28 rests, so that the material 52 is in communication with the inner wall 25 or the outer wall 28. If, in turn, the outer wall 28 is added to the arrangement according to FIG. 13 and the model 43 is removed, then a casting mold 16 according to FIG. 2 forms.
  • the continuous recess 46 that extends to the inner wall 25 may be only partially filled with the ceramic 52 leaving a void space 55 within the recess 46 ( Figure 14).
  • the core 25 is already present in the model 43, for example.
  • the void space 55 remains, and when the model 43 is removed, a mold as shown in FIG. 3 is formed.
  • the void 55 is filled with a wax that is removable along with the model 43.
  • the recess 46 may extend only partially in the model 43 ( Figures 10, 11) and is completely filled, for example, with a ceramic material 52 ( Figure 15) before the outer wall 28 is applied to the model 43 or applied the outer wall 28, so that the mold 16 is formed after removal of the model 43 of Figure 4.
  • FIG. 16 shows by way of example a gas turbine 100 in a longitudinal partial section.
  • the gas turbine 100 has inside a rotatably mounted about a rotation axis 102 rotor 103, which is also referred to as a turbine runner.
  • a compressor 105 for example a toroidal combustion chamber 110, in particular annular combustion chamber 106, with a plurality of coaxially arranged burners 107, a turbine 108 and the exhaust housing 109.
  • the annular combustion chamber 106 communicates with an annular annular hot gas channel 111, for example.
  • Each turbine stage 112 is formed from two blade rings.
  • a series 125 formed of rotor blades 120 follows.
  • the vanes 130 are attached to the stator 143, whereas the blades 120 of a row 125 are mounted on the rotor 103 by means of a turbine disk 133. Coupled to the rotor 103 is a generator or work machine (not shown).
  • air 105 is sucked in and compressed by the compressor 105 through the intake housing 104.
  • the compressed air provided at the turbine-side end of the compressor 105 is supplied to the burners 107 where it is mixed with a fuel.
  • the mixture is then burned to form the working fluid 113 in the combustion chamber 110.
  • the working medium 113 flows along the hot gas channel 111 past the guide vanes 130 and the rotor blades 120.
  • the working medium 113 expands in a pulse-transmitting manner, so that the rotor blades 120 drive the rotor 103 and drive the machine coupled to it.
  • the components exposed to the hot working medium 113 are subject to thermal loads during operation of the gas turbine 100.
  • the guide vanes 130 and rotor blades 120 of the first turbine stage 112, viewed in the direction of flow of the working medium 113, are subjected to the greatest thermal stress in addition to the heat shield bricks lining the annular combustion chamber 106. In order to withstand the temperatures prevailing there, they are cooled by means of a coolant.
  • the turbine blade 120, 130 is still air-cooled and has film cooling holes 13 which are produced with the mold 16 of the invention (FIGS. 2-6) in the cast and / or directionally solidified turbine blade 120, 130.
  • the guide blade 130 has a guide blade foot facing the inner housing 138 of the turbine 108 (not shown here). and a vane head opposite the vane root.
  • the vane head faces the rotor 103 and fixed to a mounting ring 140 of the stator 143.
  • FIG. 17 shows, by way of example, a combustion chamber 110 of a gas turbine 100.
  • the combustion chamber 110 is configured, for example, as a so-called annular combustion chamber, in which a plurality of burners 102 arranged around the turbine shaft 103 in the circumferential direction open into a common combustion chamber space.
  • the combustion chamber 110 is configured in its entirety as an annular structure, which is positioned around the turbine shaft 103 around.
  • the combustion chamber 110 is designed for a comparatively high temperature of the working medium M of about 1000 ° C to 1600 ° C.
  • the combustion chamber wall 153 is provided on its side facing the working medium M side with an inner lining formed from heat shield elements 155.
  • Each heat shield element 155 is equipped on the working medium side with a particularly heat-resistant protective layer or made of high-temperature-resistant material. Due to the high temperatures in the interior of the combustion chamber 110, a cooling system is additionally provided for the heat shield elements 155 or for their holding elements. Often the heat shield elements 155 have film cooling holes 13 or passages for fuel into the combustion chamber 110 created in the heat shield element 155 with the mold 16.
  • FIG. 18 shows a perspective view of a moving blade 120 or guide blade 130 of a turbomachine that extends along a longitudinal axis 121.
  • the turbomachine may be a gas turbine of an aircraft or a power plant for power generation, a steam turbine or a compressor.
  • the blade 120, 130 has along the longitudinal axis 121 consecutively a fastening region 400, a blade platform 403 adjoining thereto and an airfoil 406. As a guide blade 130, the blade 130 may have at its blade tip 415 another platform (not shown).
  • a blade root 183 is formed, which serves for attachment of the blades 120, 130 to a shaft or a disc (not shown).
  • the blade root 183 is designed, for example, as a hammer head. Other designs as Christmas tree or Schwalbenschwanzfuß are possible.
  • the blade 120, 130 has a leading edge 409 and a trailing edge 412 for a medium flowing past the airfoil 406.
  • blade 120, 130 for example, solid metallic materials are used in all regions 400, 403, 406 of the blade 120, 130.
  • the blade 120, 130 can in this case be produced by a casting process by means of the casting mold 16, also by means of directed solidification, by a forging process, by a milling process or combinations thereof.
  • directionally solidified microstructures which means both single crystals that have no grain boundaries or at most small angle grain boundaries, and stem crystal structures that have probably longitudinal grain boundaries but no transverse grain boundaries. These second-mentioned crystalline structures are also known as directionally solidified structures. Such methods are known from US Pat. No. 6,024,792 and EP 0 892 090 A1.
  • Refurbishment means that components 120, 130 may have to be freed of protective layers after use (eg by sandblasting). This is followed by removal of the corrosion and / or oxidation layers or products. Optionally, even cracks in the component 120, 130 are repaired. Thereafter, a recoating occurs of the component 120, 130 and a renewed use of the component 120, 130.
  • the blade 120, 130 may be hollow or solid. If the blade 120, 130 is to be cooled, it is hollow and may still film cooling holes 418 (indicated by dashed lines) on. As a protection against corrosion, the blade 120, 130, for example, corresponding mostly metallic coatings (MCrA1X) and as protection against heat mostly a ceramic coating.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP04030823A 2004-12-27 2004-12-27 Procédé de fabrication d'un moule de fonderie Not-in-force EP1674174B1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP08000499A EP1920858B1 (fr) 2004-12-27 2004-12-27 Procédé de fabrication d'un moule
DE502004008983T DE502004008983D1 (de) 2004-12-27 2004-12-27 Verfahren zur Herstellung einer Gussform
DE502004009738T DE502004009738D1 (de) 2004-12-27 2004-12-27 Verfahren zur Herstellung einer Gussform
EP04030823A EP1674174B1 (fr) 2004-12-27 2004-12-27 Procédé de fabrication d'un moule de fonderie
US11/318,835 US20060162893A1 (en) 2004-12-27 2005-12-27 Method for the production of a casting mold

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP04030823A EP1674174B1 (fr) 2004-12-27 2004-12-27 Procédé de fabrication d'un moule de fonderie

Related Child Applications (1)

Application Number Title Priority Date Filing Date
EP08000499A Division EP1920858B1 (fr) 2004-12-27 2004-12-27 Procédé de fabrication d'un moule

Publications (2)

Publication Number Publication Date
EP1674174A1 true EP1674174A1 (fr) 2006-06-28
EP1674174B1 EP1674174B1 (fr) 2009-02-11

Family

ID=35094534

Family Applications (2)

Application Number Title Priority Date Filing Date
EP04030823A Not-in-force EP1674174B1 (fr) 2004-12-27 2004-12-27 Procédé de fabrication d'un moule de fonderie
EP08000499A Not-in-force EP1920858B1 (fr) 2004-12-27 2004-12-27 Procédé de fabrication d'un moule

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP08000499A Not-in-force EP1920858B1 (fr) 2004-12-27 2004-12-27 Procédé de fabrication d'un moule

Country Status (3)

Country Link
US (1) US20060162893A1 (fr)
EP (2) EP1674174B1 (fr)
DE (2) DE502004009738D1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2841710B1 (fr) 2012-04-24 2018-10-31 United Technologies Corporation C ur de moteur à turbine à gaz créant une partie de profil aérodynamique extérieure
EP1876325B2 (fr) † 2006-07-05 2023-01-25 Raytheon Technologies Corporation Système de référence externe et de positionnement des trous de refroidissement par film utilisant des trous de localisation d'un noyau

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2014113184A1 (fr) * 2013-01-18 2014-07-24 General Electric Company Procédé permettant de former des orifices de refroidissement coulés dans un composant d'aéronef
EP3111055A2 (fr) * 2014-02-25 2017-01-04 Siemens Aktiengesellschaft Revêtement de pièce de turbine formant une barrière thermique présentant des propriétés de matériau variables en fonction de la profondeur
WO2016133987A2 (fr) 2015-02-18 2016-08-25 Siemens Aktiengesellschaft Formation de passages de refroidissement dans des pièces coulées en superalliage d'une turbine à combustion
DE102019201085A1 (de) * 2019-01-29 2020-07-30 Siemens Aktiengesellschaft Herstellungsverfahren für ein Bauteil mit integrierten Kanälen

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0559251A1 (fr) * 1992-02-18 1993-09-08 General Motors Corporation Procédé pour la production des structure coulées, à paroi mince avec une résistance à chaud élevée

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4487246A (en) * 1982-04-12 1984-12-11 Howmet Turbine Components Corporation System for locating cores in casting molds
US5810552A (en) * 1992-02-18 1998-09-22 Allison Engine Company, Inc. Single-cast, high-temperature, thin wall structures having a high thermal conductivity member connecting the walls and methods of making the same
EP0861927A1 (fr) 1997-02-24 1998-09-02 Sulzer Innotec Ag Procédé de fabrication de structures monocristallines
EP0892090B1 (fr) 1997-02-24 2008-04-23 Sulzer Innotec Ag Procédé de fabrication de structure monocristallines
US6329015B1 (en) 2000-05-23 2001-12-11 General Electric Company Method for forming shaped holes
US6637500B2 (en) * 2001-10-24 2003-10-28 United Technologies Corporation Cores for use in precision investment casting
GB0226559D0 (en) * 2002-11-14 2002-12-18 Rolls Royce Plc Investment moulding process and apparatus
US6929054B2 (en) * 2003-12-19 2005-08-16 United Technologies Corporation Investment casting cores

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0559251A1 (fr) * 1992-02-18 1993-09-08 General Motors Corporation Procédé pour la production des structure coulées, à paroi mince avec une résistance à chaud élevée

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1876325B2 (fr) † 2006-07-05 2023-01-25 Raytheon Technologies Corporation Système de référence externe et de positionnement des trous de refroidissement par film utilisant des trous de localisation d'un noyau
EP2841710B1 (fr) 2012-04-24 2018-10-31 United Technologies Corporation C ur de moteur à turbine à gaz créant une partie de profil aérodynamique extérieure

Also Published As

Publication number Publication date
EP1920858B1 (fr) 2009-07-08
DE502004008983D1 (de) 2009-03-26
US20060162893A1 (en) 2006-07-27
EP1674174B1 (fr) 2009-02-11
EP1920858A1 (fr) 2008-05-14
DE502004009738D1 (de) 2009-08-20

Similar Documents

Publication Publication Date Title
EP1529580B1 (fr) Moule de fonderie
EP1869290B1 (fr) Composant a trou de refroidissement par film fluide
EP1819905A1 (fr) Système de couches, utilisation et procédé pour la fabrication d'un système multicouche
EP2101938B1 (fr) Procédé de fabrication d'un modèle pour la reproduction par la technique de la coulée fine d'un composant qui présente au moins un espace creux
EP2143520A1 (fr) Méthode de fabrication d'un trou
EP1857218A1 (fr) Procédé de réparation d'élément et un élement
WO2006056524A1 (fr) Procede pour fabriquer un modele perdu et noyau place a l'interieur
EP1645653A1 (fr) Revêtement protecteur
EP1835045A1 (fr) Procédé d'obtention d'une pièce revêtue
EP2213759A1 (fr) Procédé de revêtement d'un composant à trous de refroidissement par film et composant
EP1674174B1 (fr) Procédé de fabrication d'un moule de fonderie
EP1814690A1 (fr) Composant comprenant une cavite remplie de matiere
EP2230041A2 (fr) Procédé de fabrication d'un trou
WO2006069822A1 (fr) Procede de creation d'un trou
EP1686240A1 (fr) Composant avec une portion applatie dans un trou
EP1820939A1 (fr) Procédé et dispositiv pour le revêtement des aubes de turbine
EP1772531A1 (fr) Procédé et appareil de revêtement intérieur.
EP1655091A1 (fr) Méthode pour l'usinage par électrochimie d'une pièce et pièce de travail ayant un passage.
EP1808251B1 (fr) Procédé de dressage d'un électrode d'érosion et d'usinage par électro-érosion
EP1658913A1 (fr) Procédé et pièce de coulée
EP1930115A1 (fr) Fil, son utilisation et procédé de soudage
WO2010118960A1 (fr) Procédé de fabrication d'un moule négatif pour la coulée d'une aube de turbine et moule pour la fabrication d'un modèle à la cire d'aube de turbine
EP2602352A1 (fr) Composant à trous de refroidissement par film
WO2012065851A1 (fr) Procédé raccourci pour le forage d'un trou
EP1772533A1 (fr) Appareil pour revêter des surfaces interieures, retort et methode pour l'application du tel revêtement

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: 20060508

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU MC NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR LV MK YU

AKX Designation fees paid

Designated state(s): CH DE GB IT LI

17Q First examination report despatched

Effective date: 20071221

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): CH DE GB IT LI

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: CH

Ref legal event code: EP

REF Corresponds to:

Ref document number: 502004008983

Country of ref document: DE

Date of ref document: 20090326

Kind code of ref document: P

REG Reference to a national code

Ref country code: CH

Ref legal event code: NV

Representative=s name: SIEMENS SCHWEIZ AG

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: 20091112

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

Ref country code: IT

Free format text: LAPSE BECAUSE OF FAILURE TO SUBMIT A TRANSLATION OF THE DESCRIPTION OR TO PAY THE FEE WITHIN THE PRESCRIBED TIME-LIMIT

Effective date: 20090211

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

Ref country code: GB

Payment date: 20101209

Year of fee payment: 7

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

Ref country code: CH

Payment date: 20110308

Year of fee payment: 7

Ref country code: DE

Payment date: 20110221

Year of fee payment: 7

REG Reference to a national code

Ref country code: CH

Ref legal event code: PL

GBPC Gb: european patent ceased through non-payment of renewal fee

Effective date: 20111227

REG Reference to a national code

Ref country code: DE

Ref legal event code: R119

Ref document number: 502004008983

Country of ref document: DE

Effective date: 20120703

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

Ref country code: CH

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20111231

Ref country code: DE

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20120703

Ref country code: LI

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20111231

Ref country code: GB

Free format text: LAPSE BECAUSE OF NON-PAYMENT OF DUE FEES

Effective date: 20111227