EP2241391A1 - Procédé de fabrication d'un moule négatif destiné à couler une aube de turbine et moule de fabrication d'un modèle en cire d'une aube de turbine - Google Patents

Procédé de fabrication d'un moule négatif destiné à couler une aube de turbine et moule de fabrication d'un modèle en cire d'une aube de turbine Download PDF

Info

Publication number
EP2241391A1
EP2241391A1 EP09005327A EP09005327A EP2241391A1 EP 2241391 A1 EP2241391 A1 EP 2241391A1 EP 09005327 A EP09005327 A EP 09005327A EP 09005327 A EP09005327 A EP 09005327A EP 2241391 A1 EP2241391 A1 EP 2241391A1
Authority
EP
European Patent Office
Prior art keywords
wax model
blade
platform
turbine blade
spacer
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.)
Withdrawn
Application number
EP09005327A
Other languages
German (de)
English (en)
Inventor
Fathi Ahmad
Winfried Dr. Esser
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
Siemens Corp
Original Assignee
Siemens AG
Siemens Corp
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, Siemens Corp filed Critical Siemens AG
Priority to EP09005327A priority Critical patent/EP2241391A1/fr
Priority to US13/263,871 priority patent/US20120031579A1/en
Priority to PCT/EP2010/054327 priority patent/WO2010118960A1/fr
Priority to EP10713890A priority patent/EP2419229A1/fr
Publication of EP2241391A1 publication Critical patent/EP2241391A1/fr
Withdrawn legal-status Critical Current

Links

Images

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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D23/00—Casting processes not provided for in groups B22D1/00 - B22D21/00

Definitions

  • the present invention relates to a method for producing a negative mold for the casting of a turbine blade, in which a wax model of the turbine blade is produced and the negative mold is created on the basis of the wax model.
  • the invention relates to an auxiliary device used in the method and to a mold for producing a wax model of a turbine blade.
  • a method for the production of a turbine blade by casting in which a wax model of the blade is produced, wherein the blade root is produced by filling in a mold having the blade contour. Subsequently, a mold shell for the casting of the turbine blade is produced, wherein the mold remains on the blade root. After a melting out of the wax model, the inner contour of the mold defines the outer contour of the turbine blade to be cast. In other words, the mold represents a part of the casting mold for the casting of the turbine blade.
  • the mold is to achieve an improvement in the surface accuracy for the shaping of the blade root in the context of this method, so that a complex reworking of the blade root after casting of the turbine blade not necessary is.
  • the mold is either made of a heat-resistant, sufficiently oxidation-resistant alloy material so as to be reusable, or it is made as a disposable mold made of a low alloy steel.
  • the first object is achieved by a method for producing a negative mold for casting a turbine blade according to claim 1, the second object by a method for manufacturing a turbine blade according to claim 8 and the third object by a spacer for a wax mold according to claim 9.
  • the dependent claims contain advantageous embodiments of the invention.
  • the turbine blade to be cast has a blade platform and a fastening element for securing the blade to a blade holder, wherein at least one surface of the fastening element is spaced from a platform surface of the blade platform.
  • a wax model of the turbine blade to be produced is produced and, using the wax model, a negative mold of the turbine blade is created after the wax model has hardened. After completion of the negative mold, the wax model is melted out.
  • the invention is based on the finding that deviations in the shape of, in particular, the fastening elements of turbine blades due to deformations of the wax model during curing and / or storage until the production of the negative mold and / or a transport arise.
  • These deformations can be particularly serious in the area of the blade suspension, which is generally formed by hook-shaped elements which are spaced from the blade platform.
  • these hooks are particularly critical in terms of sizing the distance between the hooks and the bucket platform. Namely, this distance defines the position of the platform in the hot gas path of the turbine.
  • the particularly critical distance between the hook and the blade platform can be kept very constant, so that a reworking of a cast turbine blade is usually no longer necessary. Since the spacer is removed from the wax model prior to making the female mold, it does not need to be made of a material that will survive the casting process of casting the turbine blade. Compared to the aforementioned mold, therefore, a much less heat-resistant material and thus a less expensive material can be used.
  • the spacer is already arranged during hardening of the wax model between the platform surface of the blade platform and the at least one opposite surface of the fastening element, but remains until immediately before the production of the negative mold in the wax model. In this way, the distance between the blade platform and the fastener influencing deformations of the Wax model from the production to its use are avoided continuously.
  • the at least one spacer completely fills the space between the platform surface of the blade platform and the at least one opposite surface of the fastening element.
  • the spacer may rest against at least one further surface of the fastening element.
  • a spacer may also be used which has a receptacle adapted to the shape of the fastening element for receiving at least part of the fastening element. In this way, the fastener can be secured against deformation in all relevant directions.
  • the spacer may also be part of a mold for making the wax model of the turbine blade.
  • the spacer used may in particular be made of metal or ceramic. If the spacer is made of metal, for example, steel or aluminum in question, with aluminum brings advantages because of its low weight.
  • a turbine blade having a paddle platform and a fastener for attaching the paddle to a paddle mount is made wherein at least one surface of the fastener is spaced from a platform surface of the paddle platform.
  • the turbine blade is cast by means of a negative mold of the turbine blade.
  • the method according to the invention for producing a turbine blade makes it possible to produce the turbine blade with surfaces and dimensions that are easily controllable in the particularly relevant areas of the suspension, without the use of a mold being necessary for this purpose.
  • a turbine blade wax mold spacer having a blade platform and a fastener for securing the blade to a blade support, at least one surface of the fastener being spaced from a platform surface of the blade platform.
  • the spacer according to the invention has a receptacle adapted to the shape of the fastening element for receiving at least part of the fastening element.
  • Such a spacer can advantageously be used in the context of the method according to the invention for producing a negative mold for the production of a turbine blade. It may in particular be made of metal, for example of steel or aluminum. Also, a ceramic production is possible.
  • a mold for making a wax model of a turbine blade comprising a removable or separable part which, upon removal of the wax model from the mold, remains on the wax model and forms a spacer according to the invention.
  • FIG. 1 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 with a shaft 101, which is also referred to as a turbine runner.
  • an intake housing 104 a compressor 105, for example, a toroidal combustion chamber 110, in particular annular combustion chamber, with a plurality of coaxially arranged burners 107, a turbine 108 and the exhaust housing 109th
  • a compressor 105 for example, a toroidal combustion chamber 110, in particular annular combustion chamber, with a plurality of coaxially arranged burners 107, a turbine 108 and the exhaust housing 109th
  • the annular combustion chamber 110 communicates with an annular annular hot gas channel 111, for example.
  • annular annular hot gas channel 111 for example.
  • turbine stages 112 connected in series form the turbine 108.
  • Each turbine stage 112 is formed, for example, from two blade rings. As seen in the flow direction of a working medium 113 follows in the hot gas channel 111 a Leitschaufelsch 115 a 125 formed from blades 120 series.
  • the guide vanes 130 are fastened to an inner housing 138 of a stator 143, whereas the moving blades 120 of a row 125 are attached to the rotor 103 by means of a turbine disk 133, for example.
  • 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 flow direction of the working medium 113, are subjected to the greatest thermal stress in addition to the heat shield elements lining the annular combustion chamber 110.
  • substrates of the components may have a directional structure, i. they are monocrystalline (SX structure) or have only longitudinal grains (DS structure).
  • iron-, nickel- or cobalt-based superalloys are used as the material for the components, in particular for the turbine blade 120, 130 and components of the combustion chamber 110.
  • Such superalloys are for example from EP 1 204 776 B1 .
  • EP 1 306 454 .
  • the blades 120, 130 may be anti-corrosion coatings (MCrAlX; M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni), X is an active element and is yttrium (Y) and / or silicon , Scandium (Sc) and / or at least one element of the rare earth or hafnium).
  • M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni)
  • X is an active element and is yttrium (Y) and / or silicon , Scandium (Sc) and / or at least one element of the rare earth or hafnium).
  • Such alloys are known from the EP 0 486 489 B1 .
  • EP 0 412 397 B1 or EP 1 306 454 A1 are known from the EP 0 486 489 B1 .
  • MCrAlX may still be present a thermal barrier coating, and consists for example of ZrO 2 , Y 2 O 3 -ZrO 2 , ie it is not, partially or completely stabilized by yttria and / or calcium oxide and / or magnesium oxide.
  • Electron beam evaporation produces stalk-shaped grains in the thermal barrier coating.
  • the vane 130 has a guide vane foot (not shown here) facing the inner housing 138 of the turbine 108 and a vane head opposite the vane foot.
  • the vane head faces the rotor 103 and fixed to a mounting ring 140 of the stator 143.
  • FIG. 2 shows a perspective view of a blade 120 or guide vane 130 of a turbomachine, which 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 adjacent thereto and an airfoil 406 and a blade tip 415.
  • 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.
  • Such superalloys are for example from EP 1 204 776 B1 .
  • EP 1 306 454 .
  • the blade 120, 130 can be made by a casting process, also by directional solidification, by a forging process, by a milling process or combinations thereof.
  • Workpieces with a monocrystalline structure or structures are used as components for machines which are exposed to high mechanical, thermal and / or chemical stresses during operation.
  • Such monocrystalline workpieces takes place e.g. by directed solidification from the melt.
  • These are casting processes in which the liquid metallic alloy is transformed into a monocrystalline structure, i. to the single-crystal workpiece, or directionally solidified.
  • dendritic crystals are aligned along the heat flow and form either a columnar grain structure (columnar, i.e., grains that run the full length of the workpiece and here, in common usage, are referred to as directionally solidified) or a monocrystalline structure, i. the whole workpiece consists of a single crystal.
  • a columnar grain structure columnar, i.e., grains that run the full length of the workpiece and here, in common usage, are referred to as directionally solidified
  • a monocrystalline structure i. the whole workpiece consists of a single crystal.
  • 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.
  • the blades 120, 130 may have coatings against corrosion or oxidation, e.g. M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni), X is an active element and stands for yttrium (Y) and / or silicon and / or at least one element of the rare ones Earth, or hafnium (Hf)).
  • M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni)
  • X is an active element and stands for yttrium (Y) and / or silicon and / or at least one element of the rare ones Earth, or hafnium (Hf)).
  • Such alloys are known from the EP 0 486 489 B1 . EP 0 786 017 B1 . EP 0 412 397 B1 or EP 1 306 454 A1 which are to be part of this disclosure with regard to the chemical composition of the alloy.
  • the density is preferably 95% of the theoretical density.
  • the layer composition comprises Co-30Ni-28Cr-8Al-0.6Y-0.7Si or Co-28Ni-24Cr-10Al-0.6Y.
  • nickel-based protective layers such as Ni-10Cr-12Al-0.6Y-3Re or Ni-12Co-21Cr-11Al-0.4Y-2Re or Ni-25Co-17Cr-10Al-0.4Y-1 are also preferably used , 5RE.
  • thermal barrier coating which is preferably the outermost layer, and consists for example of ZrO 2 , Y 2 O 3 -ZrO 2 , ie it is not, partially or completely stabilized by yttria and / or calcium oxide and / or magnesium oxide.
  • the thermal barrier coating covers the entire MCrAlX layer.
  • Electron beam evaporation produces stalk-shaped grains in the thermal barrier coating.
  • the thermal barrier coating may have porous, micro- or macro-cracked grains for better thermal shock resistance.
  • the thermal barrier coating is therefore preferably more porous than the MCrAlX layer.
  • Refurbishment means that components 120, 130 may need to be deprotected after use (e.g., 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. This is followed by a re-coating 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.
  • the FIG. 3 shows a combustion chamber 110 of a gas turbine.
  • the combustion chamber 110 is designed, for example, as a so-called annular combustion chamber, in which a plurality of burners 107 arranged around a rotation axis 102 in the circumferential direction open into a common combustion chamber space 154, which generate flames 156.
  • the combustion chamber 110 is configured in its entirety as an annular structure, which is positioned around the axis of rotation 102 around.
  • the combustion chamber 110 is designed for a comparatively high temperature of the working medium M of about 1000 ° C to 1600 ° C. Even with these, for the materials unfavorable operating parameters, the combustion chamber wall 153 is provided on its side facing the working medium M with an inner lining formed from heat shield elements 155.
  • Each heat shield element 155 made of an alloy is equipped on the working medium side with a particularly heat-resistant protective layer (MCrAlX layer and / or ceramic coating) or is made of high-temperature-resistant material (solid ceramic blocks).
  • M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni), X is an active element and stands for yttrium (Y) and / or silicon and / or at least one element of the rare earths, or hafnium (Hf).
  • MCrAlX means: M is at least one element of the group iron (Fe), cobalt (Co), nickel (Ni), X is an active element and stands for yttrium (Y) and / or silicon and / or at least one element of the rare earths, or hafnium (Hf).
  • Such alloys are known from the EP 0 486 489 B1 .
  • EP 0 412 397 B1 or EP 1 306 454 A1 are known from the EP 0 486 489 B1 .
  • EP 0 412 397 B1 or EP 1 306 454 A1 is known from the EP 0 486 489 B1 .
  • MCrAlX may still be present, for example, a ceramic thermal barrier coating and consists for example of ZrO 2 Y 2 O 3 -ZrO 2 , ie it is not, partially or completely stabilized by yttria and / or calcium oxide and / or magnesium oxide.
  • Electron beam evaporation produces stalk-shaped grains in the thermal barrier coating.
  • thermal barrier coating may have porous, micro- or macro-cracked grains for better thermal shock resistance.
  • Refurbishment means that heat shield elements 155 may have to be freed of protective layers after their use (eg by sandblasting). This is followed by removal of the corrosion and / or oxidation layers or products. If necessary, cracks in the heat shield element 155 are also repaired. This is followed by a recoating of the heat shield elements 155 and a renewed use of the heat shield elements 155.
  • the heat shield elements 155 are then, for example, hollow and possibly still have cooling holes (not shown) which open into the combustion chamber space 154.
  • FIG. 4 shows in a highly schematic representation of the suspension of a guide vane 1 on a retaining ring 3, which extends in the circumferential direction of the turbine at least a portion of the circumference.
  • the holding element 3 has holding projections 5, on which the turbine blade 1 is fastened.
  • the turbine blade 1 has an airfoil 9 and at least one blade platform 11 arranged at the radially outer end of the airfoil 9. A corresponding blade platform can also be arranged at the radially inner end of the airfoil 9 (in FIG FIG. 4 not shown).
  • the blade platform 11 has a radially inner platform surface 13, which forms part of the wall of the flow path for the hot combustion gases in the gas turbine.
  • retaining hooks 7 are formed, with which the turbine blade can be suspended from the retaining projections 5 of the support member 3. Corresponding retaining hooks may also be present on the radially inner platform.
  • the distance d between the radially outer platform surface 15 and a hook surface 17 opposite this platform surface determines, in conjunction with the position of the holding projections 5 of the holding element 3, the positioning of the radially inner platform surface 13 in the hot gas path of the gas trubline and is thus suitable for forming a fluidically optimized hot gas path of FIG great importance.
  • a defined distance d between the radially outer platform surface and the hook surface 7 is of great importance.
  • a casting mold for a wax model of the turbine blade 9 to be produced is created. Since no particularly high temperatures occur when casting the wax model, the material for the wax mold can be optimized in terms of machinability, so that the contour of the wax model can be generated precisely as a negative mold. A once manufactured mold for the wax model can also be reused, so that not necessarily included in any method for producing a negative model for a turbine blade, the step of producing a mold for a wax model. Only when a turbine blade with a new geometry is to be produced for the first time, a casting mold for the corresponding wax model has to be newly produced.
  • the wax model of the turbine blade is poured in step 21.
  • spacer elements are inserted into the region of the retaining hooks 7.
  • Such a spacer element 219 is schematically in FIG. 6 shown.
  • the figure shows a section of a wax model 201 of the turbine blade 1 FIG. 4 ,
  • the wax model includes a model vane blade 209, a model platform 211 having a radially inner model platform surface 213, and a radially outer model platform surface 215.
  • Extending from the model platform 211 is a model holding hook 207, which has a model hook surface 217 facing and spaced from the outer model platform surface 215.
  • spacer elements 219 are inserted into the space between the radially outer model platform surface 215 and the opposed model hook surface 217.
  • the spacer 219 is made of a dimensionally stable material, such as metal or ceramic.
  • metallic materials such as steel or aluminum, can be produced with precise dimensions, so that the thickness of the spacer can be adapted very closely to the distance d to be maintained between the radially outer model platform surface 215 and the opposing model hook surface 217.
  • the spacer 219 is inserted into the space between the radially outer platform surface 215 and the opposing model hook surface 217, the distance between these two surfaces is against a change due to deformations in the wax model during further curing and / or during transport and / or secured the bearing of the wax model.
  • the spacer 219 also has a thickened portion 221, which serves as an edge, which lies opposite the end face 223 of the model hook 207. In this way, a displacement of the end face 223 by deformation in particular of the model hook 207 can be reliably counteracted.
  • the spacer 219 in the present embodiment after removal of the wax model from the mold may also be formed so that it forms part of the mold during the casting process, which can then be taken together with the wax model from the mold or separated from the mold. Due to the fact that in this alternative embodiment of the method the spacer is already in its position during casting, the wax model in the region of the model hook 207 is also secured against deformations which could occur when removing the model from the mold.
  • the spacer 229 advantageously remains in the wax model 201 of the turbine blade 1 until, based on the wax model 201, a negative mold for the turbine blade 1 is created.
  • the negative mold is formed, for example, by means of a ceramic material around the wax model (step 27).
  • the wax is melted out of the negative mold, so that the resulting cavity for casting the turbine blade in step 29 is used.
  • the female mold is removed and the process for producing the turbine blade is completed.
  • the present invention provides a simple means of counteracting deformation of the wax model used during a casting process to manufacture a turbine blade. This can provide improvements in maintaining a precise geometry of the wax model, thereby reducing the number of faulty cast turbine blades that are to be reworked or, in the worst case, scrap.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP09005327A 2009-04-14 2009-04-14 Procédé de fabrication d'un moule négatif destiné à couler une aube de turbine et moule de fabrication d'un modèle en cire d'une aube de turbine Withdrawn EP2241391A1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
EP09005327A EP2241391A1 (fr) 2009-04-14 2009-04-14 Procédé de fabrication d'un moule négatif destiné à couler une aube de turbine et moule de fabrication d'un modèle en cire d'une aube de turbine
US13/263,871 US20120031579A1 (en) 2009-04-14 2010-03-31 Method for producing a negative mold for casting a turbine blade and mold for producing a wax model of a gas turbine
PCT/EP2010/054327 WO2010118960A1 (fr) 2009-04-14 2010-03-31 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
EP10713890A EP2419229A1 (fr) 2009-04-14 2010-03-31 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

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP09005327A EP2241391A1 (fr) 2009-04-14 2009-04-14 Procédé de fabrication d'un moule négatif destiné à couler une aube de turbine et moule de fabrication d'un modèle en cire d'une aube de turbine

Publications (1)

Publication Number Publication Date
EP2241391A1 true EP2241391A1 (fr) 2010-10-20

Family

ID=40652719

Family Applications (2)

Application Number Title Priority Date Filing Date
EP09005327A Withdrawn EP2241391A1 (fr) 2009-04-14 2009-04-14 Procédé de fabrication d'un moule négatif destiné à couler une aube de turbine et moule de fabrication d'un modèle en cire d'une aube de turbine
EP10713890A Withdrawn EP2419229A1 (fr) 2009-04-14 2010-03-31 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

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP10713890A Withdrawn EP2419229A1 (fr) 2009-04-14 2010-03-31 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

Country Status (3)

Country Link
US (1) US20120031579A1 (fr)
EP (2) EP2241391A1 (fr)
WO (1) WO2010118960A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150028080A1 (en) * 2012-02-06 2015-01-29 Siemens Aktiengesellschaft Method for the cohesive connection of two components using integrally formed portions for manipulating said components
CN117000947A (zh) * 2023-09-21 2023-11-07 河北钢研德凯科技有限公司 涡轮转子蜡模拼接工装

Citations (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2053757A (en) * 1979-07-19 1981-02-11 Rolls Royce Lost wax patterns
US4464094A (en) * 1979-05-04 1984-08-07 Trw Inc. Turbine engine component and method of making the same
US4641702A (en) * 1985-03-28 1987-02-10 Mercury Machine Company Method and mold for molding investment casting patterns of irregular shape
EP0486489B1 (fr) 1989-08-10 1994-11-02 Siemens Aktiengesellschaft Revetement anticorrosion resistant aux temperatures elevees, notamment pour elements de turbines a gaz
EP0412397B1 (fr) 1989-08-10 1998-03-25 Siemens Aktiengesellschaft Revêtement protecteur contenant du rhénium possédant une résistance plus grande à la corrosion et l'oxydation
DE19726111C1 (de) 1997-06-20 1998-11-12 Mtu Muenchen Gmbh Verfahren zur gießtechnischen Herstellung einer Turbomaschinenschaufel
EP0892090A1 (fr) 1997-02-24 1999-01-20 Sulzer Innotec Ag Procédé de fabrication de structure smonocristallines
EP0786017B1 (fr) 1994-10-14 1999-03-24 Siemens Aktiengesellschaft Couche de protection de pieces contre la corrosion, l'oxydation et les contraintes thermiques excessives, et son procede de production
WO1999067435A1 (fr) 1998-06-23 1999-12-29 Siemens Aktiengesellschaft Alliage a solidification directionnelle a resistance transversale a la rupture amelioree
US6024792A (en) 1997-02-24 2000-02-15 Sulzer Innotec Ag Method for producing monocrystalline structures
WO2000044949A1 (fr) 1999-01-28 2000-08-03 Siemens Aktiengesellschaft Superalliage a base de nickel presentant une bonne usinabilite
EP1216770A2 (fr) * 2000-12-22 2002-06-26 ALSTOM Power N.V. Procédé et dispositif pour la coulée d'une partie d'un moule servant à la fabrication d'une aube de turbine
EP1306454A1 (fr) 2001-10-24 2003-05-02 Siemens Aktiengesellschaft Revêtement protecteur contenant du rhénium pour la protection d'un élément contre l'oxydation et la corrosion aux températures élevées
EP1319729A1 (fr) 2001-12-13 2003-06-18 Siemens Aktiengesellschaft Pièce résistante à des températures élevées réalisé en superalliage polycristallin ou monocristallin à base de nickel
EP1204776B1 (fr) 1999-07-29 2004-06-02 Siemens Aktiengesellschaft Piece resistant a des temperatures elevees et son procede de production

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3204303A (en) * 1963-06-20 1965-09-07 Thompson Ramo Wooldridge Inc Precision investment casting

Patent Citations (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4464094A (en) * 1979-05-04 1984-08-07 Trw Inc. Turbine engine component and method of making the same
GB2053757A (en) * 1979-07-19 1981-02-11 Rolls Royce Lost wax patterns
US4641702A (en) * 1985-03-28 1987-02-10 Mercury Machine Company Method and mold for molding investment casting patterns of irregular shape
EP0486489B1 (fr) 1989-08-10 1994-11-02 Siemens Aktiengesellschaft Revetement anticorrosion resistant aux temperatures elevees, notamment pour elements de turbines a gaz
EP0412397B1 (fr) 1989-08-10 1998-03-25 Siemens Aktiengesellschaft Revêtement protecteur contenant du rhénium possédant une résistance plus grande à la corrosion et l'oxydation
EP0786017B1 (fr) 1994-10-14 1999-03-24 Siemens Aktiengesellschaft Couche de protection de pieces contre la corrosion, l'oxydation et les contraintes thermiques excessives, et son procede de production
EP0892090A1 (fr) 1997-02-24 1999-01-20 Sulzer Innotec Ag Procédé de fabrication de structure smonocristallines
US6024792A (en) 1997-02-24 2000-02-15 Sulzer Innotec Ag Method for producing monocrystalline structures
DE19726111C1 (de) 1997-06-20 1998-11-12 Mtu Muenchen Gmbh Verfahren zur gießtechnischen Herstellung einer Turbomaschinenschaufel
WO1999067435A1 (fr) 1998-06-23 1999-12-29 Siemens Aktiengesellschaft Alliage a solidification directionnelle a resistance transversale a la rupture amelioree
WO2000044949A1 (fr) 1999-01-28 2000-08-03 Siemens Aktiengesellschaft Superalliage a base de nickel presentant une bonne usinabilite
EP1204776B1 (fr) 1999-07-29 2004-06-02 Siemens Aktiengesellschaft Piece resistant a des temperatures elevees et son procede de production
EP1216770A2 (fr) * 2000-12-22 2002-06-26 ALSTOM Power N.V. Procédé et dispositif pour la coulée d'une partie d'un moule servant à la fabrication d'une aube de turbine
EP1306454A1 (fr) 2001-10-24 2003-05-02 Siemens Aktiengesellschaft Revêtement protecteur contenant du rhénium pour la protection d'un élément contre l'oxydation et la corrosion aux températures élevées
EP1319729A1 (fr) 2001-12-13 2003-06-18 Siemens Aktiengesellschaft Pièce résistante à des températures élevées réalisé en superalliage polycristallin ou monocristallin à base de nickel

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150028080A1 (en) * 2012-02-06 2015-01-29 Siemens Aktiengesellschaft Method for the cohesive connection of two components using integrally formed portions for manipulating said components
CN117000947A (zh) * 2023-09-21 2023-11-07 河北钢研德凯科技有限公司 涡轮转子蜡模拼接工装

Also Published As

Publication number Publication date
EP2419229A1 (fr) 2012-02-22
WO2010118960A1 (fr) 2010-10-21
US20120031579A1 (en) 2012-02-09

Similar Documents

Publication Publication Date Title
DE102009016260A1 (de) Verfahren beim Schweißen und Bauteil
WO2009144077A1 (fr) Procédé pour souder en fonction d’une orientation préférentielle du substrat
EP2547488B1 (fr) Procédé de reconditionnement d'une aube de turbine avec au moins une plate-forme
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
EP2373824A1 (fr) Procédé pour recouvrir un composant pourvu de trous de refroidissement pelliculaire et composant
EP2884048A1 (fr) Revêtement d'isolation thermique d'une aube de turbine
EP2379252A1 (fr) Composant à structure différenciée et procédé de fabrication
WO2009087189A2 (fr) Brasage de trous, procédé de revêtement et baguettes de brasure
EP2088224A1 (fr) Procédé de fabrication d'une couche rugueuse et système de couche
EP2226149A1 (fr) Procédé de soudure en deux étapes
EP2224039A1 (fr) Revêtement doté d'un procédé de revêtement thermique et non thermique
EP1661640A1 (fr) Fabrication d'un modèle perdu et noyaux incorporé dans le modèle
EP2241391A1 (fr) Procédé de fabrication d'un moule négatif destiné à couler une aube de turbine et moule de fabrication d'un modèle en cire d'une aube de turbine
WO2009053154A1 (fr) Procédé pour éliminer une couche métallique au moyen du procédé fic au cours d'une étape intermédiaire
WO2018114766A1 (fr) Procédé d'assemblage de segments de composants à gaz chaud par brasage et composant à gaz chaud correspondant
EP1797985A1 (fr) Procédé et dispositif de soudage
EP2463043A1 (fr) Pièce de formage coulée en céramique dotée de différents facteurs de rétrécissement et procédé de coulée
EP2463044A1 (fr) Noyau de fonderie en céramique modulaire et procédé de coulée
EP2452775A1 (fr) Procédé de forage raccourci d'un trou
DE102013226217A1 (de) Reparatur von Gasturbinenkomponenten unter Verwendung von Ausschussteilen
EP2441537A1 (fr) Outil à noyau doté de crayons variables et procédé de fabrication d'un noyau
WO2008086912A1 (fr) Électrode d'érosion à structure modulaire et son utilisation
EP1930115A1 (fr) Fil, son utilisation et procédé de soudage
EP2450123A1 (fr) Procédé de fabrication d'un outil pour la fabrication de noyaux
EP2450122A1 (fr) Optimisation d'un outil por la fabrication de noyaux, procédé de fabrication d'un outil pour la fabrication de noyaux et un outil pour la fabrication de noyaux

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

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 HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA RS

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20110421