US20100178192A1 - Cast Iron Comprising Cobalt and Component - Google Patents

Cast Iron Comprising Cobalt and Component Download PDF

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Publication number
US20100178192A1
US20100178192A1 US12/087,797 US8779707A US2010178192A1 US 20100178192 A1 US20100178192 A1 US 20100178192A1 US 8779707 A US8779707 A US 8779707A US 2010178192 A1 US2010178192 A1 US 2010178192A1
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US
United States
Prior art keywords
alloy
cobalt
silicon
turbine
molybdenum
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.)
Abandoned
Application number
US12/087,797
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English (en)
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
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Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Assigned to SIEMENS AKTIENGESELLSCHAFT reassignment SIEMENS AKTIENGESELLSCHAFT ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: SHENG, SHILUN, JANSSEN, STEFAN
Publication of US20100178192A1 publication Critical patent/US20100178192A1/en
Abandoned legal-status Critical Current

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    • 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 an alloy, a cast iron comprising cobalt and a component thereof.
  • GJS spherocast alloys primarily use silicon and molybdenum to increase the creep strength, scaling resistance and endurance strength. Over time, however, these elements lead to a significant decrease in the ductility.
  • Molybdenum furthermore exhibits a very high susceptibility to segregation.
  • the invention consists in cobalt partially or fully replacing molybdenum.
  • the working limitations presented by the previous GJS alloy can therefore be overcome.
  • the alloy according to the invention has high elongations for the application field in the temperature range of 450° C.-550° C., and has the following composition (in wt %):
  • silicon 2.0%-4.5% cobalt 0.5%-5% carbon 2.0%-4.5%, in particular 2.5%-4%, 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 less than 7.5 wt %.
  • the proportion of cobalt in the alloy lies between 0.5 and 1.5 wt % cobalt.
  • the alloy may contain further elements.
  • the alloy consists of iron, silicon, cobalt and carbon.
  • the alloy consists of iron, silicon, cobalt, carbon and manganese.
  • an alloy which consists of iron, silicon, cobalt, carbon and optionally admixtures of molybdenum, manganese and/or nickel.
  • the alloy may optionally contain undesired impurities of at most
  • magnesium (Mg) there is preferably no magnesium (Mg) in the alloy except for the usual impurities.
  • FIG. 1 shows a micrograph
  • FIG. 2 shows mechanical characteristics
  • FIG. 3 shows a steam turbine
  • FIG. 4 shows a gas turbine.
  • FIG. 1 shows an almost optimal ferritic structure (etched) with spherical graphite made of an alloy with about 2 wt % cobalt:
  • FIG. 2 shows the influence of cobalt on the mechanical properties of the alloys, which are listed in the following table (data in wt %).
  • the elongation at break R p02 increases from 271 N/mm 2 to 284 N/mm 2 .
  • the tensile strength Rm increases from 403 N/mm 2 to 412 N/mm 2 .
  • the elongation at break A 5 increases from 15.5% to 21.9%.
  • the necking at fracture Z increases from 13.8% to 29.5%.
  • FIG. 3 shows a steam turbine 300 , 303 having a turbine shaft 309 extending along a rotation axis 306 .
  • the steam turbine comprises a high-pressure turbine part 300 and a medium-pressure turbine part 303 , each with an inner housing 312 and an outer housing 315 enclosing the latter.
  • the high-pressure turbine part 300 is, for example, configured in pot design.
  • the medium-pressure turbine part 303 is, for example, configured to be twin-streamed. It is likewise possible for the medium-pressure turbine part 303 to be configured to be single-streamed.
  • a bearing 318 is arranged along the rotation axis 306 between the high-pressure turbine part 300 and the medium-pressure turbine part 303 , the turbine shaft 309 comprising a bearing region 321 in the bearing 318 .
  • the turbine shaft 309 is mounted on a further bearing 324 beside the high-pressure turbine part 300 .
  • the high-pressure turbine part 300 comprises a shaft seal 345 .
  • the turbine shaft 309 is sealed relative to the outer housing 315 of the medium-pressure turbine part 303 by two further shaft seals 345 .
  • the turbine shaft 309 in the high-pressure turbine part 300 comprises the high-pressure rotor blading 357 . With the associated rotor blades (not represented in detail), this high-pressure rotor blading 357 constitutes a first blading region 360 .
  • the medium-pressure turbine part 303 comprises a central steam intake region 333 .
  • the turbine shaft 309 comprises a radially symmetric shaft shield 363 , a cover plate, on the one hand to divide the steam flow into the two streams of the medium-pressure turbine part 303 and also to prevent direct contact of the hot steam with the turbine shaft 309 .
  • the turbine shaft 309 comprises a second blading region 366 with the medium-pressure rotor blades 354 . The hot steam flowing through the second blading region 366 flows from the medium-pressure turbine part 303 out of a discharge port 369 to a low-pressure turbine part (not shown) connected downstream.
  • the turbine shaft 309 is composed for example of two turbine shaft parts 309 a and 309 b , which are connected firmly to one another in the region of the bearing 318 .
  • Each turbine shaft part 309 a and 309 b comprises a cooling line 372 formed as a central bore 372 a along the rotation axis 306 .
  • the cooling line 372 is connected to the steam outlet region 351 via a feed line 375 comprising a radial bore 375 a .
  • the coolant line 372 is connected to a cavity (not shown) below the shaft shield.
  • the feed lines 375 are configured as a radial bore 375 a , so that “cold” steam from the high-pressure turbine part 300 can flow into the central bore 372 a .
  • the discharge line 372 also formed in particular as a radially directed bore 375 a , the steam passes through the bearing region 321 into the medium-pressure turbine part 333 and there onto the lateral surface 330 of the turbine shaft 309 in the steam intake region 333 .
  • the steam flowing through the cooling line is at a much lower temperature than the temporarily superheated steam flowing into the steam intake region 333 , so as to ensure effective cooling of the first rotor blade row 342 of the medium-pressure turbine part 303 and the lateral surface 330 in the region of this rotor blade row 342 .
  • FIG. 4 shows a gas turbine 100 by way of example in a partial longitudinal section.
  • the gas turbine 100 internally comprises a rotor 103 , which will also be referred to as the turbine rotor, mounted so as to rotate about a rotation axis 102 and having a shaft 101 .
  • an intake manifold 104 there are an intake manifold 104 , a compressor 105 , an e.g. toroidal combustion chamber 110 , in particular a ring combustion chamber, having a plurality of burners 107 arranged coaxially, a turbine 108 and the exhaust manifold 109 .
  • a compressor 105 e.g. toroidal combustion chamber 110 , in particular a ring combustion chamber, having a plurality of burners 107 arranged coaxially, a turbine 108 and the exhaust manifold 109 .
  • the ring combustion chamber 110 communicates with an e.g. annular hot gas channel 111 .
  • annular hot gas channel 111 There, for example, four successively connected turbine stages 112 form the turbine 108 .
  • Each turbine stage 112 is formed for example by two blade rings. As seen in the flow direction of a working medium 113 , a guide vane row 115 is followed in the hot gas channel 111 by a row 125 formed by rotor blades 120 .
  • the guide vanes 130 are fastened on an inner housing 138 of a stator 143 while the rotor blades 120 of a row 125 are fastened on the rotor 103 , for example by means of a turbine disk 133 .
  • air 135 is taken in and compressed by the compressor 105 through the intake manifold 104 .
  • the compressed air provided at the end of the compressor 105 on the turbine side is delivered to the burners 107 and mixed there with a fuel.
  • the mixture is then burnt to form the working medium 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 by imparting momentum, so that the rotor blades 120 drive the rotor 103 and the work engine coupled to it.
  • the components exposed to the hot working medium 113 experience thermal loads. Apart from the heat shield elements lining the ring combustion chamber 110 , the guide vanes 130 and rotor blades 120 of the first turbine stage 112 , as seen in the flow direction of the working medium 113 , are heated the most.
  • Substrates of the components may likewise comprise a directional structure, i.e. they are monocrystalline (SX structure) or comprise only longitudinally directed grains (DS structure).
  • SX structure monocrystalline
  • DS structure longitudinally directed grains
  • Iron-, nickel- or cobalt-based superalloys are for example used as material for the components, in particular for the turbine blades 120 , 130 and components of the combustion chamber 110 .
  • Such 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; with respect to the chemical composition of the alloys, these documents are part of the disclosure.
  • the blades 120 , 130 may likewise have coatings against corrosion (MCrAlX; M is at least one element from 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 rare earth element, or hafnium).
  • M is at least one element from 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 rare earth element, 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, with respect to the chemical composition, are intended to be part of this disclosure.
  • thermal barrier layer which consists for example of ZrO 2 , Y 2 O 3 —ZrO 2 , i.e. it is not stabilized or is partially or fully stabilized by yttrium oxide and/or calcium oxide and/or magnesium oxide.
  • Rod-shaped grains are produced in the thermal barrier layer by suitable coating methods, for example electron beam deposition (EB-PVD).
  • EB-PVD electron beam deposition
  • the guide vane 130 comprises a guide vane root (not shown here) facing the inner housing 138 of the turbine 108 , and a guide vane head lying opposite the guide vane root.
  • the guide vane head faces the rotor 103 and is fixed on a fastening ring 140 of the stator 143 .

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  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US12/087,797 2006-01-16 2007-01-03 Cast Iron Comprising Cobalt and Component Abandoned US20100178192A1 (en)

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
EP06000851.3 2006-01-16
PCT/EP2007/050057 WO2007082788A1 (fr) 2006-01-16 2007-01-03 Fonte contenant du cobalt et élément constitutif

Publications (1)

Publication Number Publication Date
US20100178192A1 true US20100178192A1 (en) 2010-07-15

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Family Applications (1)

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US12/087,797 Abandoned US20100178192A1 (en) 2006-01-16 2007-01-03 Cast Iron Comprising Cobalt and Component

Country Status (4)

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

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20110194969A1 (en) * 2008-10-09 2011-08-11 Stefan Janssen Ductile Iron Having Cobalt
US20140030133A1 (en) * 2011-04-15 2014-01-30 Lutz Dekker Cast iron containing niobium and component
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

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100322813A1 (en) * 2009-06-23 2010-12-23 General Electric Company SiMo DUCTILE IRON CASTINGS IN GAS TURBINE APPLICATIONS
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

Citations (2)

* 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
US5236660A (en) * 1991-09-26 1993-08-17 Centre Technique Des Industries De La Fonderie Heat-resistant vermicular or spheroidal graphite cast iron

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
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

Patent Citations (2)

* 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
US5236660A (en) * 1991-09-26 1993-08-17 Centre Technique Des Industries De La Fonderie Heat-resistant vermicular or spheroidal graphite cast iron

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20110194969A1 (en) * 2008-10-09 2011-08-11 Stefan Janssen Ductile Iron Having Cobalt
US20140030133A1 (en) * 2011-04-15 2014-01-30 Lutz Dekker Cast iron containing niobium and component
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

Also Published As

Publication number Publication date
EP1974068B1 (fr) 2013-07-24
EP1808504A1 (fr) 2007-07-18
CN101400812A (zh) 2009-04-01
WO2007082788A1 (fr) 2007-07-26
EP1974068A1 (fr) 2008-10-01

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Owner name: SIEMENS AKTIENGESELLSCHAFT, GERMANY

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:JANSSEN, STEFAN;SHENG, SHILUN;SIGNING DATES FROM 20080620 TO 20080626;REEL/FRAME:021269/0738

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