EP2127781A1 - Procédé de fabrication d'une aube de turbine - Google Patents

Procédé de fabrication d'une aube de turbine Download PDF

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Publication number
EP2127781A1
EP2127781A1 EP08009847A EP08009847A EP2127781A1 EP 2127781 A1 EP2127781 A1 EP 2127781A1 EP 08009847 A EP08009847 A EP 08009847A EP 08009847 A EP08009847 A EP 08009847A EP 2127781 A1 EP2127781 A1 EP 2127781A1
Authority
EP
European Patent Office
Prior art keywords
inner structure
turbine blade
channels
interior structure
cover
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Withdrawn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
EP08009847A
Other languages
German (de)
English (en)
Inventor
Fathi Ahmad
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 EP08009847A priority Critical patent/EP2127781A1/fr
Publication of EP2127781A1 publication Critical patent/EP2127781A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D19/00—Casting in, on, or around objects which form part of the product
    • B22D19/08—Casting in, on, or around objects which form part of the product for building-up linings or coverings, e.g. of anti-frictional metal
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D19/00—Casting in, on, or around objects which form part of the product
    • B22D19/10—Repairing defective or damaged objects by metal casting procedures

Definitions

  • the invention relates to a method for producing a turbine blade. Furthermore, a turbine blade that can be produced by the method and a repair method for this turbine blade are the subject of the invention.
  • This object is achieved by first producing an inner structure of the turbine blade and then encapsulating the inner structure with a sheath to form an outer shape of the turbine blade.
  • the basic idea of the invention is thus first to manufacture the inner structure of the turbine blade in a separate step and then to cast a casing around the inner structure which has the outer shape of the turbine blade.
  • the inventive method makes it possible to produce a turbine blade with a complex internal structure in a particularly simple manner.
  • cooling ducts that have a complex geometry can be manufactured with high precision.
  • the inner structure and the envelope from different materials.
  • they may be formed of various metals and / or alloys. This makes it possible to select the materials so that they are optimally adapted to the requirements of the inner structure or to the envelope.
  • a particularly preferred embodiment provides to make the inner structure of a material with high creep resistance and the sheath of a material with high oxidation resistance.
  • Such a turbine blade has a particularly high durability and resilience.
  • materials of different crystallinity for example, one or more crystalline materials can be used.
  • the inner structure In the manufacture of the inner structure can be formed in this cooling channels. This is particularly easy because the internal structure is easily accessible.
  • the cooling fluid may be, for example, water or air.
  • the cooling fluid cools the internal structure so that it is prevented from damaging it, especially when a refractory encapsulant material is used. In this way, it is above all prevented that the internal structure softens or even melts.
  • the inner structure before encapsulating the inner structure.
  • the masking elements serve to form channels in the enclosure during the casting.
  • channels can also be formed in the enclosure with the masking elements, which channels communicate with cooling channels in the inner structure. It is also possible to form channels with a diffuser opening in the enclosure.
  • Another embodiment provides to cast the inner structure of the turbine blade.
  • the invention also relates to a turbine blade, which can be produced by the method according to the invention.
  • the invention comprises a repair method for the turbine blade.
  • the existing envelope of the turbine blade is first removed from the inner structure. Then, a new enclosure with the outer shape of the turbine blade is poured around the inner structure.
  • the Figures 1 and 2 illustrate a method of manufacturing a turbine blade according to a first embodiment of the invention. It shows FIG. 1 schematically in section an inner structure 1 of a turbine blade 2 to be produced.
  • the inner structure 1 consists of an alloy with high creep resistance and has three cooling channels 3 which extend through the inner structure 2.
  • FIG. 2 shows the turbine blade 2 in the finished state.
  • the inner structure 1 is cast in a casing 4 of an alloy with high oxidation resistance.
  • the inner structure 1 is produced from an alloy with high creep resistance. This can be done for example by machining a blank. Alternatively, the inner structure 1 may also be cast by known methods. In the manufacture of the inner structure, the cooling channels 3 are formed with.
  • the inner structure 1 is arranged in a suitable mold having the negative shape of the turbine blade 2 to be produced. Then, the inner structure 1 in the mold with a melt of the alloy for Encapsulated envelope 4, wherein simultaneously water is passed as cooling fluid through the cooling channels 3, to cool the inner structure 1. After solidification of the Umgussleg réelle last finished turbine blade 2 can be removed from the mold.
  • FIGS. 3 to 5 the production of a turbine blade 5 is shown according to a further embodiment of the method according to the invention. It shows the FIG. 3 schematically in section an inner structure 6 of the turbine blade 5, which has a cooling channel 7 and consists of a first alloy.
  • the inner structure 6 is produced in a first step, for example, by casting it from the first alloy with the aid of a suitable mold. Subsequently, the masking elements 8 are attached to the inner structure 6. Then, the inner structure 6 with the masking elements 8 is inserted into a mold having the negative shape of the turbine blade 5. The mold is filled with a melt of the second alloy, in which case simultaneously a cooling fluid such as air is passed through the cooling channel 7 in order to cool the inner structure 6. After the serving 10 is cooled, the turbine blade 5 is removed from the mold and the masking elements 8 are removed from the enclosure 10.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP08009847A 2008-05-29 2008-05-29 Procédé de fabrication d'une aube de turbine Withdrawn EP2127781A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP08009847A EP2127781A1 (fr) 2008-05-29 2008-05-29 Procédé de fabrication d'une aube de turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP08009847A EP2127781A1 (fr) 2008-05-29 2008-05-29 Procédé de fabrication d'une aube de turbine

Publications (1)

Publication Number Publication Date
EP2127781A1 true EP2127781A1 (fr) 2009-12-02

Family

ID=39768983

Family Applications (1)

Application Number Title Priority Date Filing Date
EP08009847A Withdrawn EP2127781A1 (fr) 2008-05-29 2008-05-29 Procédé de fabrication d'une aube de turbine

Country Status (1)

Country Link
EP (1) EP2127781A1 (fr)

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5296308A (en) 1992-08-10 1994-03-22 Howmet Corporation Investment casting using core with integral wall thickness control means
EP1543896A2 (fr) * 2003-12-19 2005-06-22 United Technologies Corporation Noyaux pour la coulée de précision
EP1634665A2 (fr) * 2004-09-09 2006-03-15 United Technologies Corporation Noyau composite pour la coulée de précision
EP1652603A2 (fr) * 2004-10-29 2006-05-03 United Technologies Corporation Noyaux pour la moulage de précision et procédés
EP1715139A2 (fr) * 2005-04-22 2006-10-25 United Technologies Corporation Refroidissement du bord de fuite d'une aube de turbine

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5296308A (en) 1992-08-10 1994-03-22 Howmet Corporation Investment casting using core with integral wall thickness control means
EP1543896A2 (fr) * 2003-12-19 2005-06-22 United Technologies Corporation Noyaux pour la coulée de précision
EP1634665A2 (fr) * 2004-09-09 2006-03-15 United Technologies Corporation Noyau composite pour la coulée de précision
EP1652603A2 (fr) * 2004-10-29 2006-05-03 United Technologies Corporation Noyaux pour la moulage de précision et procédés
EP1715139A2 (fr) * 2005-04-22 2006-10-25 United Technologies Corporation Refroidissement du bord de fuite d'une aube de turbine

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