EP1658913A1 - Procédé et pièce de coulée - Google Patents

Procédé et pièce de coulée Download PDF

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Publication number
EP1658913A1
EP1658913A1 EP04027556A EP04027556A EP1658913A1 EP 1658913 A1 EP1658913 A1 EP 1658913A1 EP 04027556 A EP04027556 A EP 04027556A EP 04027556 A EP04027556 A EP 04027556A EP 1658913 A1 EP1658913 A1 EP 1658913A1
Authority
EP
European Patent Office
Prior art keywords
melt
casting method
control element
component
casting
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Withdrawn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
EP04027556A
Other languages
German (de)
English (en)
Inventor
Stefan Dr. Janssen
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 EP04027556A priority Critical patent/EP1658913A1/fr
Priority to EP05815684A priority patent/EP1812186A2/fr
Priority to KR1020077013594A priority patent/KR100929451B1/ko
Priority to US11/667,575 priority patent/US7681623B2/en
Priority to PCT/EP2005/055766 priority patent/WO2006053838A2/fr
Priority to CN200580039744A priority patent/CN100591440C/zh
Publication of EP1658913A1 publication Critical patent/EP1658913A1/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Withdrawn legal-status Critical Current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
    • B22D11/00—Continuous casting of metals, i.e. casting in indefinite lengths
    • B22D11/10—Supplying or treating molten metal
    • B22D11/11—Treating the molten metal
    • B22D11/112—Treating the molten metal by accelerated cooling
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D27/00—Treating the metal in the mould while it is molten or ductile ; Pressure or vacuum casting
    • B22D27/04—Influencing the temperature of the metal, e.g. by heating or cooling the mould
    • 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

Definitions

  • the invention relates to a casting method according to claim 1 and a cast component according to claim 20.
  • Modern modeling and simulation tools for solidification of castings mean that complex casting processes can be mastered well today. A better and more targeted adjustment of structures and properties is thus possible. It is possible to set better mechanical properties with a higher reproducibility for critical component areas in the casting process.
  • the casting-related adjustment of the, for example, required homogeneous globulitic structure in the case of graphite extrusion is difficult. This is due to the poor dissipation of heat and solidification energy.
  • the mechanical values in these highly stressed component areas increase with increasing wall thickness.
  • U.S. Patent No. 5,314,000 discloses a method of controlling grain size during a casting process.
  • the object is achieved by a casting method according to claim 1 and a cast component according to claim 20.
  • FIG. 1 shows a device 1 comprising a casting mold 10 with a melt 4 and at least one, here for example two control elements 7.
  • the melt 4 is introduced.
  • the control elements 7 consist for example of the same material as the melt 7 or another fusible material.
  • the melting temperature of the control elements 7 can therefore be less than, equal to or greater than the melting temperature of the material of the melt 4.
  • the control elements 7 may therefore be metallic, ceramic or glass.
  • the temperature of the control elements 7 can be adjusted in advance before they come into contact with the melt 4. This can be done by heating or cooling as needed.
  • control elements 7 can be actively cooled, in which a coolant is passed for example through the control elements 7 or brought at one end with at least one control element 7 in contact, so that a forced cooling takes place.
  • the control elements 7 are initially not melted. In particular, but may not have, the Control elements 7, after they have come into contact with the melt 4, during the liquid phase of the melt 4 (phase in which the melt is present) or melt during the solidification of the melt 4 at least partially or completely.
  • the control elements 7 are not made of the material as the mold 10, but serve for the additional removal of heat from the melt.
  • the control elements 7 are therefore not cast cores. Your material forms after solidification an integral part of the molded component 13th
  • the control elements 7 are, in particular, a solid crystalline body and not built up (like a mold in a casting process from individual grains (sand mold), which are connected to each other for example by a binder.
  • the control element 7 is, for example, a sintered body of many grains.
  • the casting method according to the invention also does not represent a spraying method in which a material is overmolded with a molten or soft material.
  • control elements 7 may be the same or different sizes.
  • the control elements 7 have an elongated shape and are in particular symmetrical, in particular cylindrical.
  • a component 13 which is produced by the casting method can, for example, represent a component of a steam generator 300, 303 or gas turbine 100 for an aircraft or for power generation, in which case it is in particular a housing component.
  • FIG. 2a, b show schematically the operation of the casting method according to the invention.
  • FIG. 2 a shows, for example, a cuboid wall element of a component in a casting method according to the prior art.
  • the temporal dissipation of heat energy dQ / dt is shown here with Q ⁇ .
  • FIG. 2 b shows the corresponding wall element 7 in a casting method according to the invention, in which, for example, a control element 7 is present in the melt 4.
  • a control element 7 is present in the melt 4.
  • the control element 7 absorbs heat or, if the control element 7 even melts, it deprives the melt 4 of melting energy.
  • their cooling rate is increased, ie Q ⁇ is significantly increased. This prevents slower solidification in thicker areas and thick components, which often leads to graphite degeneration or porosity and voids.
  • introducing control elements 7 into the melt 4 for example, a homogeneous spherulitic graphite expression, in particular in the case of gray cast parts, is achieved.
  • FIG. 3 shows a cast component 13 according to the invention.
  • the component 13 is formed from a melt 4 and has the control elements 7, which are surrounded by the solidified melt 4 on.
  • the control elements 7 are here, for example, introduced in a thick-walled region 16 of the component 13.
  • Such thick-walled areas 16 represent, for example, the flanges of a housing part.
  • thick means a wall thickness of at least 200 mm.
  • the control elements 7 are introduced there, where later holes 19 are introduced into the flange 16, so material is removed.
  • the control elements 7 are not a part of the mold 10 and are for example metallic, but may also be ceramic or glassy.
  • FIG. 4 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 for example, has thick-walled portions 16 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.
  • blades 120, 130 for example, solid metallic materials, in particular superalloys, are used in all regions 400, 403, 406 of the blade 120, 130.
  • superalloys are known, for example, from EP 1204776 B1, EP 1306454, EP 1319729 A1, WO 99/67435 or WO 00/44949; these writings are part of the revelation.
  • 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.
  • the blades 120, 130 may be coatings against corrosion or oxidation (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 and / or at least one element of the rare earths, or hafnium (Hf)).
  • 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 and / or at least one element of the rare earths, or hafnium (Hf)).
  • Such alloys are known from EP 0 486 489 B1, EP 0 786 017 B1, EP 0 412 397 B1 or EP 1 306 454 A1, which are intended to be part of this disclosure.
  • a thermal barrier coating may be present and consists for example of ZrO 2 , Y 2 O 4 -ZrO 2 , ie it is not, partially or completely stabilized by yttria and / or calcium oxide and / or magnesium oxide.
  • suitable coating processes such as electron beam evaporation (EB-PVD), stalk-shaped grains are produced in the thermal barrier coating.
  • 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.
  • FIG. 5 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 multiplicity of burners 107 arranged around the rotation axis 102 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 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.
  • 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.
  • a particularly heat-resistant protective layer or made of high-temperature-resistant material may be solid ceramic stones or alloys with MCrAlX and / or ceramic coatings.
  • the materials of the combustion chamber wall and its coatings may be similar to the turbine blades.
  • Due to the high temperatures inside the combustion chamber 110 may also be provided for the heat shield elements 155 and for their holding elements, a cooling system.
  • the heat shield elements may have thick-walled regions 16 and therefore be produced by the process according to the invention.
  • FIG. 6 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 with, for example, thick-walled areas 16.
  • the annular combustion chamber 106 communicates with an annular annular hot gas channel 111, for example.
  • Each turbine stage 112 is formed, for example, from two blade rings. As seen in the direction of flow of a working medium 113, in the hot gas channel 111 of a row of guide vanes 115, a series 125 formed of rotor blades 120 follows.
  • the vanes 130 are in this case on an inner housing 138 (with, for example, thick-walled areas 16) of a stator 143, whereas the blades 120 of a row 125 are attached to the rotor 103, for example by means of a turbine disk 133. Coupled to the rotor 103 is a generator or work machine (not shown).
  • air 135 is sucked and compressed by the compressor 105 through the intake housing 104 (with, for example, thick-walled areas 16).
  • 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. To withstand the prevailing temperatures, they can be cooled by means of a coolant.
  • substrates of the components can have a directional structure, ie they are monocrystalline (SX structure) or have only longitudinal grains (DS structure).
  • SX structure monocrystalline
  • DS structure only longitudinal grains
  • blades 120, 130 may be anti-corrosion coatings (MCrA1X; 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 and / or at least one element of the rare earths 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 and / or at least one element of the rare earths or hafnium).
  • Such alloys are known from EP 0 486 489 B1, EP 0 786 017 B1, EP 0 412 397 B1 or EP 1 306 454 A1, which are intended to be part of this disclosure.
  • a thermal barrier coating On the MCrAlX may still be present a thermal barrier coating, and consists for example of ZrO 2 , Y 2 O 4 -ZrO 2 , that is, it is not, partially or completely stabilized by yttria and / or calcium oxide and / or magnesium oxide.
  • suitable coating processes such as electron beam evaporation (EB-PVD), stalk-shaped grains are produced 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. 7 shows by way of example a steam turbine 300, 303 with a turbine shaft 309 extending along a rotation axis 306.
  • the steam turbine has a high-pressure turbine section 300 and a medium-pressure turbine section 303, each having an inner housing 21 (with, for example, thick-walled areas 16) and an outer housing 315 enclosing this (with, for example, thick-walled areas 16).
  • the high-pressure turbine part 300 is designed, for example, in Topfbauart.
  • the medium-pressure turbine section 303 is double-flow. It is also possible for the medium-pressure turbine section 303 to be single-flow.
  • a bearing 318 is arranged between the high-pressure turbine section 300 and the medium-pressure turbine section 303, the turbine shaft 309 having a bearing region 321 in the bearing 318.
  • the turbine shaft 309 is supported on another bearing 324 adjacent to the high pressure turbine sub 300. In the area of this bearing 324, the high-pressure turbine section 300 has a shaft seal 345.
  • the turbine shaft 309 is sealed off from the outer housing 315 with, for example, thick-walled regions 16 of the medium-pressure turbine section 303 by two further shaft seals 345.
  • the turbine shaft 309 in the high-pressure turbine section 300 has the high-pressure impeller blade 354, 357.
  • the middle-pressure blast turbine 303 has a central steam inflow region 333.
  • the turbine shaft 309 Associated with the steam inflow region 333, the turbine shaft 309 has a radially symmetrical shaft shield 363, a cover plate, on the one hand for dividing the steam flow into the two flows of the medium-pressure turbine section 303 and for preventing direct contact of the hot steam with the turbine shaft 309.
  • the turbine shaft 309 has in the medium-pressure turbine section 303 a second blading area 366 with the medium-pressure blades 354, 342.
  • the hot steam flowing through the second blading area 366 flows out of the medium-pressure turbine section 303 from a discharge connection 369 to a downstream low-pressure turbine, not shown.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Powder Metallurgy (AREA)
EP04027556A 2004-11-19 2004-11-19 Procédé et pièce de coulée Withdrawn EP1658913A1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP04027556A EP1658913A1 (fr) 2004-11-19 2004-11-19 Procédé et pièce de coulée
EP05815684A EP1812186A2 (fr) 2004-11-19 2005-11-04 Procédé et pièce de coulée
KR1020077013594A KR100929451B1 (ko) 2004-11-19 2005-11-04 주조 방법 및 주물 부품
US11/667,575 US7681623B2 (en) 2004-11-19 2005-11-04 Casting process and cast component
PCT/EP2005/055766 WO2006053838A2 (fr) 2004-11-19 2005-11-04 Procede de coulee et piece coulee
CN200580039744A CN100591440C (zh) 2004-11-19 2005-11-04 铸造方法和铸件

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP04027556A EP1658913A1 (fr) 2004-11-19 2004-11-19 Procédé et pièce de coulée

Publications (1)

Publication Number Publication Date
EP1658913A1 true EP1658913A1 (fr) 2006-05-24

Family

ID=34927460

Family Applications (2)

Application Number Title Priority Date Filing Date
EP04027556A Withdrawn EP1658913A1 (fr) 2004-11-19 2004-11-19 Procédé et pièce de coulée
EP05815684A Withdrawn EP1812186A2 (fr) 2004-11-19 2005-11-04 Procédé et pièce de coulée

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP05815684A Withdrawn EP1812186A2 (fr) 2004-11-19 2005-11-04 Procédé et pièce de coulée

Country Status (5)

Country Link
US (1) US7681623B2 (fr)
EP (2) EP1658913A1 (fr)
KR (1) KR100929451B1 (fr)
CN (1) CN100591440C (fr)
WO (1) WO2006053838A2 (fr)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR20140100111A (ko) * 2013-02-05 2014-08-14 삼성테크윈 주식회사 압축 시스템
CN109877277A (zh) * 2019-03-21 2019-06-14 重庆大学 一种铸造厚壁铸件的方法

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3726331A (en) * 1971-04-28 1973-04-10 R Bunting Continuous casting process
JPS62250125A (ja) * 1986-04-23 1987-10-31 Hitachi Metals Ltd ブレ−キ部品とその製造法
US6253829B1 (en) * 1997-03-24 2001-07-03 Fujikura Ltd. Heat sink, and process and apparatus for manufacturing the same
EP1013781B1 (fr) * 1998-12-23 2004-05-06 United Technologies Corporation Procédé pour la production des objets à base de superalliage à base de nickel moulés sous pression

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US4611791A (en) * 1983-01-10 1986-09-16 Coble Gary L Diffuser system for annealing furnace with water cooled base
US4807728A (en) * 1986-03-20 1989-02-28 Hitachi Metals, Ltd. Brake member and method of manufacturing same
CH670786A5 (fr) * 1986-09-24 1989-07-14 Bbc Brown Boveri & Cie
DE58908611D1 (de) 1989-08-10 1994-12-08 Siemens Ag Hochtemperaturfeste korrosionsschutzbeschichtung, insbesondere für gasturbinenbauteile.
DE3926479A1 (de) 1989-08-10 1991-02-14 Siemens Ag Rheniumhaltige schutzbeschichtung, mit grosser korrosions- und/oder oxidationsbestaendigkeit
US5314000A (en) * 1993-05-03 1994-05-24 General Electric Company Method of controlling grain size distribution in investment casting
US5522448A (en) * 1994-09-27 1996-06-04 Aluminum Company Of America Cooling insert for casting mold and associated method
JP3370676B2 (ja) 1994-10-14 2003-01-27 シーメンス アクチエンゲゼルシヤフト 腐食・酸化及び熱的過負荷に対して部材を保護するための保護層並びにその製造方法
US5673745A (en) * 1996-06-27 1997-10-07 General Electric Company Method for forming an article extension by melting of an alloy preform in a ceramic mold
EP0892090B1 (fr) 1997-02-24 2008-04-23 Sulzer Innotec Ag Procédé de fabrication de structure monocristallines
EP0861927A1 (fr) * 1997-02-24 1998-09-02 Sulzer Innotec Ag Procédé de fabrication de structures monocristallines
US6109334A (en) * 1997-07-15 2000-08-29 North American Royalties, Inc. Method of static casting composite brake drum
EP1306454B1 (fr) 2001-10-24 2004-10-06 Siemens Aktiengesellschaft Revêtement protecteur contenant du rhénium pour la protection d'un élément contre l'oxydation et la corrosion aux températures élevées
WO1999067435A1 (fr) 1998-06-23 1999-12-29 Siemens Aktiengesellschaft Alliage a solidification directionnelle a resistance transversale a la rupture amelioree
US6800148B2 (en) * 1998-11-05 2004-10-05 Rolls-Royce Corporation Single crystal vane segment and method of manufacture
US6231692B1 (en) 1999-01-28 2001-05-15 Howmet Research Corporation Nickel base superalloy with improved machinability and method of making thereof
DE50006694D1 (de) 1999-07-29 2004-07-08 Siemens Ag Hochtemperaturbeständiges bauteil und verfahren zur herstellung des hochtemperaturbeständigen bauteils
US6908288B2 (en) * 2001-10-31 2005-06-21 General Electric Company Repair of advanced gas turbine blades
EP1319729B1 (fr) 2001-12-13 2007-04-11 Siemens Aktiengesellschaft Pièce résistante à des températures élevées réalisé en superalliage polycristallin ou monocristallin à base de nickel

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3726331A (en) * 1971-04-28 1973-04-10 R Bunting Continuous casting process
JPS62250125A (ja) * 1986-04-23 1987-10-31 Hitachi Metals Ltd ブレ−キ部品とその製造法
US6253829B1 (en) * 1997-03-24 2001-07-03 Fujikura Ltd. Heat sink, and process and apparatus for manufacturing the same
EP1013781B1 (fr) * 1998-12-23 2004-05-06 United Technologies Corporation Procédé pour la production des objets à base de superalliage à base de nickel moulés sous pression

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
PATENT ABSTRACTS OF JAPAN vol. 012, no. 132 (C - 490) 22 April 1988 (1988-04-22) *

Also Published As

Publication number Publication date
CN101060951A (zh) 2007-10-24
US20070295471A1 (en) 2007-12-27
EP1812186A2 (fr) 2007-08-01
CN100591440C (zh) 2010-02-24
WO2006053838A3 (fr) 2006-11-09
KR100929451B1 (ko) 2009-12-02
US7681623B2 (en) 2010-03-23
KR20070086287A (ko) 2007-08-27
WO2006053838A2 (fr) 2006-05-26

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