EP1974068A1 - Fonte contenant du cobalt et élément constitutif - Google Patents

Fonte contenant du cobalt et élément constitutif

Info

Publication number
EP1974068A1
EP1974068A1 EP07703621A EP07703621A EP1974068A1 EP 1974068 A1 EP1974068 A1 EP 1974068A1 EP 07703621 A EP07703621 A EP 07703621A EP 07703621 A EP07703621 A EP 07703621A EP 1974068 A1 EP1974068 A1 EP 1974068A1
Authority
EP
European Patent Office
Prior art keywords
cobalt
alloy
alloy according
silicon
turbine
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
EP07703621A
Other languages
German (de)
English (en)
Other versions
EP1974068B1 (fr
Inventor
Stefan Janssen
Shilun Sheng
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 EP07703621.8A priority Critical patent/EP1974068B1/fr
Publication of EP1974068A1 publication Critical patent/EP1974068A1/fr
Application granted granted Critical
Publication of EP1974068B1 publication Critical patent/EP1974068B1/fr
Not-in-force legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C37/00—Cast-iron alloys
    • C22C37/10—Cast-iron alloys containing aluminium or silicon
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C37/00—Cast-iron alloys
    • C22C37/04—Cast-iron alloys containing spheroidal graphite

Definitions

  • the invention relates to a cast iron with cobalt according to claim 1 and a component according to claim 30.
  • the known and used cast iron alloys (so-called GJS ductile iron alloys) mainly use silicon and molybdenum to increase creep resistance, scale resistance and creep rupture strength.
  • GJS ductile iron alloys mainly use silicon and molybdenum to increase creep resistance, scale resistance and creep rupture strength.
  • these elements lead to a significant drop in toughness over time.
  • molybdenum shows a very large segregation tendency.
  • the object is achieved by an alloy according to claim 1 and a component according to claim 30.
  • the invention is that cobalt can partially or completely replace the molybdenum.
  • the alloy according to the invention has high elongations for the range of application in the temperature range from 450 ° C.-550 ° C. and has the following composition (in% by weight): Silicon 2.0% - 4.5%
  • Molybdenum ⁇ 1.5%, in particular ⁇ 1.0%, manganese ⁇ 0.5%, in particular ⁇ 0.25%,
  • Nickel ⁇ 0.5%, in particular ⁇ 0.3%, remainder iron.
  • the proportion of silicon, cobalt and molybdenum is ⁇ 7.5 wt%.
  • the proportion of cobalt in the alloy is between 0.5wt% to 1.5wt% cobalt.
  • the alloy can have further elements.
  • the alloy consists of iron, silicon, cobalt and carbon.
  • the alloy consists of iron, silicon, cobalt, carbon and manganese. Further advantages result from an alloy consisting of iron, silicon, cobalt, carbon and optional admixtures of molybdenum, manganese and / or nickel.
  • unwanted impurities of maximum 0.007wt% of sulfur 0.008wt% of magnesium 0.049wt% are present in the alloy.
  • Figure 1 is a microsection
  • Figure 2 shows mechanical characteristics
  • Figure 3 is a steam turbine
  • Figure 4 is a gas turbine.
  • Figure 1 shows an almost optimal ferritic microstructure ( ⁇ be etched) with spheroidal graphite of an alloy with about 2 wt% Cobalt:
  • Figure 2 shows the influence of cobalt on the mechanical properties of the alloy, which are shown in the following table (in wt%).
  • the elongation at break R p o2 increases from 271N / mm 2 to 284N / mm ⁇ 2:
  • the tensile strength Rm increases from 403N / mm 2 to 412N / mm .2 z
  • the elongation at break A5 increases from 15.5% to 21.9%.
  • the fracture rate Z increases from 13.8% to 29.5% Even small amounts of cobalt (0.5wt% to l, 0wt% or l, 0wt% to l, 5wt%) improve the mechanical properties.
  • FIG. 3 shows 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 312 and an outer housing 315 surrounding it.
  • the high-pressure turbine part 300 is designed, for example, in Topfbauart.
  • the medium-pressure turbine part 303 is designed, for example, 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.
  • the high-pressure turbine section 300 has a shaft seal 345.
  • the turbine shaft 309 is sealed from the outer housing 315 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 blading 357. This high-pressure blading 357, together with the associated blades, not shown, represents a first blading region 360.
  • the medium-pressure turbine part 303 has a central steam inflow region 333. Assigned to the steam inflow region 333, the turbine shaft 309 has a radially symmetrical one
  • the turbine shaft 309 has a second blading area 366 with the medium-pressure rotor blades 354 in the medium-pressure turbine section 303.
  • 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 low-pressure turbine section, not shown, which is connected downstream of the flow.
  • the turbine shaft 309 is composed for example of two partial turbine shafts 309a and 309b, which are fixedly connected to one another in the region of the bearing 318.
  • Each turbine shaft 309a, 309b has a cooling duct 372 formed as a central bore 372a along the axis of rotation 306.
  • the cooling duct 372 is connected to the steam outlet region 351 via an inflow duct 375 having a radial bore 375a.
  • the coolant line 372 is connected to a cavity, not shown, below the shaft shield.
  • the supply lines 375 are designed as a radial bore 375a, as a result of which "cold" steam can flow into the central bore 372a from the high-pressure turbine section 300.
  • the current flowing through the cooling line steam has a much lower temperature than the in the Dampfeinstrom Siemens 333 incoming between superheated steam, so that an effective cooling the first rotor blade rows 342 of the medium-pressure turbine section 303 and the jacket surface 330 in the region of these rotor blade rows 342 are ensured.
  • FIG. 4 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.
  • a compressor 105 for example, a torus-like
  • 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 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 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. Coupled to the rotor 103 is a generator or work machine (not shown).
  • substrates of the components may have a directional structure, i. they are monocrystalline (SX structure) or have only longitudinal grains (DS structure).
  • SX structure monocrystalline
  • DS structure longitudinal grains
  • 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.
  • superalloys are known, for example, from EP 1 204 776 B1, EP 1 306 454, EP 1 319 729 A1, WO 99/67435 or WO 00/44949; These documents are part of the disclosure regarding the chemical composition of the alloys.
  • blades 120, 130 may be anti-corrosion coatings (MCrAlX; M is at least one member of the group
  • Iron (Fe), cobalt (Co), nickel (Ni), X is an active element and stands for yttrium (Y) and / or silicon, scandium (Sc) and / or at least one element of rare earth 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 should be part of this disclosure with regard to the chemical composition.
  • a thermal barrier coating On the MCrAlX may still be present a thermal barrier coating, and consists for example of ZrÜ2, Y2Ü3-Zr ⁇ 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), produce stalk-shaped grains in the thermal barrier coating.
  • EB-PVD electron beam evaporation
  • 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.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Des alliages de fonte connus sont limités dans leurs applications par rapport à la température. L'utilisation de cobalt permet de mettre au point un ensemble ferritique optimal de manière à repousser les limites d'applications à des températures élevées au moyen d'un alliage comprenant 2,0 - 4,5 % en poids de silicium, 0,5 - 5 % en poids de cobalt, 2,5 - 4 % en poids de carbone, = 1% en poids de molybdène, = 0,25 % en poids de manganèse, = 0,3 % en poids de nickel, le reste étant du fer, et la part de silicium, de cobalt et de molybdène étant inférieure à 7,5 % en poids.
EP07703621.8A 2006-01-16 2007-01-03 Fonte contenant du cobalt et élément constitutif Not-in-force EP1974068B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP07703621.8A EP1974068B1 (fr) 2006-01-16 2007-01-03 Fonte contenant du cobalt et élément constitutif

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP06000851A EP1808504A1 (fr) 2006-01-16 2006-01-16 Fonte de fer avec cobalt et son utilisation dans une turbine à vapeur
EP07703621.8A EP1974068B1 (fr) 2006-01-16 2007-01-03 Fonte contenant du cobalt et élément constitutif
PCT/EP2007/050057 WO2007082788A1 (fr) 2006-01-16 2007-01-03 Fonte contenant du cobalt et élément constitutif

Publications (2)

Publication Number Publication Date
EP1974068A1 true EP1974068A1 (fr) 2008-10-01
EP1974068B1 EP1974068B1 (fr) 2013-07-24

Family

ID=36384290

Family Applications (2)

Application Number Title Priority Date Filing Date
EP06000851A Withdrawn EP1808504A1 (fr) 2006-01-16 2006-01-16 Fonte de fer avec cobalt et son utilisation dans une turbine à vapeur
EP07703621.8A Not-in-force EP1974068B1 (fr) 2006-01-16 2007-01-03 Fonte contenant du cobalt et élément constitutif

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP06000851A Withdrawn EP1808504A1 (fr) 2006-01-16 2006-01-16 Fonte de fer avec cobalt et son utilisation dans une turbine à vapeur

Country Status (4)

Country Link
US (1) US20100178192A1 (fr)
EP (2) EP1808504A1 (fr)
CN (1) CN101400812A (fr)
WO (1) WO2007082788A1 (fr)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102008051042A1 (de) * 2008-10-09 2010-04-15 Siemens Aktiengesellschaft Gusseisen mit Kobalt und Bauteil
US20100322813A1 (en) * 2009-06-23 2010-12-23 General Electric Company SiMo DUCTILE IRON CASTINGS IN GAS TURBINE APPLICATIONS
EP2511394B1 (fr) * 2011-04-15 2015-05-27 Siemens Aktiengesellschaft Fonte dotée de niobium et composant
DE102011051446A1 (de) 2011-06-29 2013-01-03 Siempelkamp Giesserei Gmbh Gusseisen mit Kugelgraphit, insbesondere für Hochtemperaturanwendungen
CN103146990B (zh) * 2013-03-29 2016-07-06 天津新伟祥工业有限公司 汽车涡轮壳体用高硅钼铬球铁材质及其制备方法
CN105714181A (zh) * 2016-02-26 2016-06-29 铜陵安东铸钢有限责任公司 一种含钴球墨铸铁及其制备方法
WO2018093894A1 (fr) * 2016-11-18 2018-05-24 Michigan Technological University Alliages de fer ductile et matériaux comprenant une couche mince d'un alliage de fer ductile

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3740212A (en) * 1971-03-31 1973-06-19 Int Nickel Co Oxidation resistant austenitic ductile nickel chromium iron
JPH0613738B2 (ja) * 1984-07-31 1994-02-23 株式会社クボタ 延性に富んだ高強度ダクタイル鋳鉄管の製造方法
FR2681878B1 (fr) * 1991-09-26 1993-12-31 Centre Tech Ind Fonderie Fonte a graphite spherouidal resistant a la chaleur.

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2007082788A1 *

Also Published As

Publication number Publication date
EP1974068B1 (fr) 2013-07-24
CN101400812A (zh) 2009-04-01
WO2007082788A1 (fr) 2007-07-26
EP1808504A1 (fr) 2007-07-18
US20100178192A1 (en) 2010-07-15

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