EP1974068B1 - Cast iron comprising cobalt and component - Google Patents

Cast iron comprising cobalt and component Download PDF

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Publication number
EP1974068B1
EP1974068B1 EP07703621.8A EP07703621A EP1974068B1 EP 1974068 B1 EP1974068 B1 EP 1974068B1 EP 07703621 A EP07703621 A EP 07703621A EP 1974068 B1 EP1974068 B1 EP 1974068B1
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EP
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Prior art keywords
cast iron
nodular cast
cobalt
iron according
turbine
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EP07703621.8A
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German (de)
French (fr)
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EP1974068A1 (en
Inventor
Stefan Janssen
Shilun Sheng
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Siemens AG
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Siemens AG
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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 a cast iron with cobalt according to claim 1 and a component according to claim 32.
  • 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 also shows a very large tendency to segregation.
  • JP 61 041 721 discloses a spheroidal iron with 0.2-1.06.
  • the object is achieved by an alloy according to claim 1 and a component according to claim 32.
  • 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 to 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 ⁇ 0.25%, nickel ⁇ 0.5%, in particular ⁇ 0.3%, Rest 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 cobalt content is 0.5wt%, 1.0wt% cobalt, 1.5wt% cobalt and 2.0wt% 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.
  • undesirable impurities in the alloy are maximum phosphorus 0,007wt% sulfur 0,008wt% magnesium 0,049wt% available.
  • FIG. 1 shows a nearly optimal ferritic microstructure (etched) with spheroidal graphite from an alloy with about 2wt% cobalt: carbon 3,67wt% silicon 2,41wt% manganese 0,029wt% cobalt 1,94wt% iron Rest.
  • FIG. 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 p02 increases from 271N / mm 2 to 284N / mm 2
  • the tensile strength Rm increases from 403N / mm 2 to 412N / mm 2 .
  • the elongation at break A5 increases from 15.5% to 21.9%.
  • the fracture rate Z increases from 13.8% to 29.5%.
  • FIG. 3 a steam turbine 300, 303 is shown 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 enclosing this.
  • 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 blade 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.
  • the turbine shaft 309 has a radially symmetric 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 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 downstream low-pressure turbine, not shown.
  • 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 sub-turbine shaft 309a, 309b has a cooling line 372 designed as a central bore 372a along the axis of rotation 306.
  • the cooling line 372 is connected to the vapor exit region 351 via an inflow line 375 having a radial bore 375a.
  • 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 375a, allowing "cold" steam from the high pressure turbine section 300 to flow into the central bore 372a.
  • the vapor passes through the storage area 321 into the medium-pressure turbine section 303 and there to the mantle surface 330 of the turbine shaft 309 in the steam inflow area 333.
  • the steam flowing through the cooling line has a significantly lower temperature as the reheated steam flowing into the Dampfeinström Siemens 333, so that an effective cooling of the first blade rows 342 of the medium-pressure turbine section 303 and the mantle surface 330 is ensured in the region of these blade rows 342.
  • 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 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 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).
  • 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. 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 longitudinal grains
  • iron-, nickel- or cobalt-based superalloys are used as the material for the components.
  • superalloys are for example from EP 1 204 776 B1 .
  • EP 1 306 454 are used as the material for the components.
  • 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 which should be part of this disclosure in terms of chemical composition.
  • MCrAlX may still be present a thermal barrier coating, and consists for example of ZrO 2 , Y 2 O 3 -ZrO 2 , that is, 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.

Description

Die Erfindung betrifft ein Gusseisen mit Kobalt gemäß Anspruch 1 und ein Bauteil gemäß Anspruch 32.The invention relates to a cast iron with cobalt according to claim 1 and a component according to claim 32.

Die bekannten und im Einsatz befindlichen Gusseisenlegierungen (so genannte GJS Sphärogusslegierungen) verwenden hauptsächlich Silizium und Molybdän zur Steigerung der Kriechfestigkeit, Zunderbeständigkeit und Zeitstandfestigkeit. Dabei führen diese Elemente mit der Zeit aber zu einem deutlichen Abfall der Zähigkeit. ,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. However, these elements lead to a significant drop in toughness over time. .

Molybdän zeigt darüber hinaus eine sehr große Seigerungsneigung.Molybdenum also shows a very large tendency to segregation.

Es ist daher Aufgabe der Erfindung eine Legierung und ein Bauteil anzugeben, die die oben genannten Nachteile überwinden und bessere mechanische Festigkeiten über die Einsatzdauer aufweisen.It is therefore an object of the invention to provide an alloy and a component which overcome the above-mentioned disadvantages and have better mechanical strength over the period of use.

JP 61 041 721 offenbart einer Sphäragusseisen mit 0.2-1.06. JP 61 041 721 discloses a spheroidal iron with 0.2-1.06.

Die Aufgabe wird gelöst durch eine Legierung gemäß Anspruch 1 und ein Bauteil gemäß Anspruch 32.The object is achieved by an alloy according to claim 1 and a component according to claim 32.

In den Unteransprüchen sind weitere vorteilhafte Maßnahmen aufgelistet, die beliebig miteinander in vorteilhafter Art und Weise miteinander verknüpft werden.In the dependent claims further advantageous measures are listed, which are arbitrarily linked with each other in an advantageous manner.

Die Erfindung besteht darin, dass Kobalt das Molybdän teilweise oder ganz ersetzen kann. Somit können die Anwendungsgrenzen, die die bisherige GJS-Legierung aufweisen, überwunden werden. Die erfindungsgemäße Legierung weist hohe Dehnungen für den Anwendungsbereich in dem Temperaturbereich von 450°C - 550°C auf und hat folgende Zusammensetzung (in wt%): Silizium 2,0% - 4,5% Kobalt 0,5% - 5% Kohlenstoff 2,0% - 4,5%, insbesondere 2,5% - 4%, Molybdän ≤ 1,5%, insbesondere ≤ 1,0%, Mangan ≤ 0,25%, Nickel ≤ 0,5%, insbesondere ≤ 0,3%, Rest Eisen.The invention is that cobalt can partially or completely replace the molybdenum. Thus, the application limits, which have the previous GJS alloy can be overcome. The alloy according to the invention has high elongations for the range of application in the temperature range from 450 ° C to 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 ≤ 0.25%, nickel ≤ 0.5%, in particular ≤ 0.3%, Rest iron.

Vorteilhafterweise gilt, dass der Anteil von Silizium, Kobalt und Molybdän ≤ 7,5wt% ist.
Vorzugsweise liegt der Anteil von Kobalt in der Legierung zwischen 0,5wt% bis 1,5wt% Kobalt.
Vorteilhafte mechanische Werte werden für die Legierung jeweils erreicht, wenn der Kobalt-Gehalt bei 0,5wt%, bei 1,0wt% Kobalt, bei 1,5wt% Kobalt sowie 2,0wt% Kobalt liegt.Advantageously, the proportion of silicon, cobalt and molybdenum is ≦ 7.5 wt%.
Preferably, the proportion of cobalt in the alloy is between 0.5wt% to 1.5wt% cobalt.
Favorable mechanical values are achieved for the alloy when the cobalt content is 0.5wt%, 1.0wt% cobalt, 1.5wt% cobalt and 2.0wt% cobalt.

Die Legierung kann weitere Elemente aufweisen. Vorzugsweise besteht die Legierung jedoch aus Eisen, Silizium, Kobalt und Kohlenstoff.
Besondere Vorteile werden auch erzielt, wenn die Legierung aus Eisen, Silizium, Kobalt, Kohlenstoff und Mangan besteht. Weitere Vorteile ergeben sich mit einer Legierung, die aus Eisen, Silizium, Kobalt, Kohlenstoff sowie optionalen Beimengungen aus Molybdän, Mangan und/oder Nickel besteht.The alloy can have further elements. Preferably, however, the alloy consists of iron, silicon, cobalt and carbon.
Particular advantages are also achieved if 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.

Gegebenenfalls sind in der Legierung unerwünschte Verunreinigungen von maximal Phosphor 0,007wt% Schwefel 0,008wt% Magnesium 0,049wt% vorhanden.Optionally, undesirable impurities in the alloy are maximum phosphorus 0,007wt% sulfur 0,008wt% magnesium 0,049wt% available.

Weiterhin ist vorzugsweise kein Chrom (Cr) in der Legierung bis auf die üblichen Verunreinigungen vorhanden.
Ebenso vorzugsweise ist kein Magnesium (Mg) in der Legierung bis auf die üblichen Verunreinigungen vorhanden.Furthermore, preferably no chromium (Cr) is present in the alloy except for the usual impurities.
Also preferably, no magnesium (Mg) is present in the alloy except for the usual impurities.

Ausführungsbeispiele der Erfindung werden anhand folgender Figuren näher erläutert.Embodiments of the invention will be explained in more detail with reference to the following figures.

Es zeigen:

Figur 1
ein Schliffbild,
Figur 2
mechanische Kennwerte,
Figur 3
eine Dampfturbine,
Figur 4
eine Gasturbine.
Show it:
FIG. 1
a micrograph,
FIG. 2
mechanical characteristics,
FIG. 3
a steam turbine,
FIG. 4
a gas turbine.

Figur 1 zeigt ein fast optimales ferritisches Gefüge (angeätzt) mit Kugelgraphit aus einer Legierung mit etwa 2wt% Kobalt: Kohlenstoff 3,67wt% Silizium 2,41wt% Mangan 0,029wt% Kobalt 1,94wt% Eisen Rest. FIG. 1 shows a nearly optimal ferritic microstructure (etched) with spheroidal graphite from an alloy with about 2wt% cobalt: carbon 3,67wt% silicon 2,41wt% manganese 0,029wt% cobalt 1,94wt% iron Rest.

Figur 2 zeigt den Einfluss von Kobalt auf die.mechanischen Eigenschaften der Legierung, die in der folgenden Tabelle (Angaben in wt%) aufgezeigt sind. Kobalt 0 0,54 1,04 1, 94 Kohlenstoff 3, 63 3,61 3, 68 3,67 Silizium 2,45 2,44 2,47 2,41 Mangan 0,067 0,036 0,03 0,029 Phosphor 0,007 0,006 0,007 0,007 Schwefel 0,009 0,006 0,008 0,008 Magnesium 0,044 0,04 0,05 0,049 FIG. 2 shows the influence of cobalt on the mechanical properties of the alloy, which are shown in the following table (in wt%). cobalt 0 0.54 1.04 1, 94 carbon 3, 63 3.61 3, 68 3.67 silicon 2.45 2.44 2.47 2.41 manganese 0.067 0,036 0.03 0,029 phosphorus 0,007 0,006 0,007 0,007 sulfur 0.009 0,006 0,008 0,008 magnesium 0,044 0.04 0.05 0,049

Die Bruchdehnung Rp02 steigt von 271N/mm2 auf 284N/mm2
Die Zugfestigkeit Rm steigt von 403N/mm2 auf 412N/mm2.
Die Bruchdehnung A5 steigt von 15,5% auf 21,9%.
Ebenso steigt die Brucheinschnürung Z von 13,8% auf 29,5%.The elongation at break R p02 increases from 271N / mm 2 to 284N / mm 2
The tensile strength Rm increases from 403N / mm 2 to 412N / mm 2 .
The elongation at break A5 increases from 15.5% to 21.9%.
Likewise, the fracture rate Z increases from 13.8% to 29.5%.

Schon geringe Anteile von Kobalt (0,5wt% bis 1,0wt% oder 1,0wt% bis 1,5wt%) verbessern die mechanischen Kennwerte.Even small amounts of cobalt (0.5wt% to 1.0wt% or 1.0wt% to 1.5wt%) improve the mechanical properties.

In Figur 3 ist eine Dampfturbine 300, 303 mit einer sich entlang einer Rotationsachse 306 erstreckenden Turbinenwelle 309 dargestellt.In FIG. 3 a steam turbine 300, 303 is shown with a turbine shaft 309 extending along a rotation axis 306.

Die Dampfturbine weist eine Hochdruck-Teilturbine 300 und eine Mitteldruck-Teilturbine 303 mit jeweils einem Innengehäuse 312 und einem dieses umschließenden Außengehäuses 315 auf. Die Hochdruck-Teilturbine 300 ist beispielsweise in Topfbauart ausgeführt. Die Mitteldruck-Teilturbine 303 ist beispielsweise zweiflutig ausgeführt. Es ist ebenfalls möglich, dass die Mitteldruck-Teilturbine 303 einflutig ausgeführt ist.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 enclosing this. 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.

Entlang der Rotationsachse 306 ist zwischen der Hochdruck-Teilturbine 300 und der Mitteldruck-Teilturbine 303 ein Lager 318 angeordnet, wobei die Turbinenwelle 309 in dem Lager 318 einen Lagerbereich 321 aufweist. Die Turbinenwelle 309 ist auf einem weiteren Lager 324 neben der Hochdruck-Teilturbine 300 aufgelagert. Im Bereich dieses Lagers 324 weist die Hochdruck-Teilturbine 300 eine Wellendichtung 345 auf. Die Turbinenwelle 309 ist gegenüber dem Außengehäuse 315 der Mitteldruck-Teilturbine 303 durch zwei weitere Wellendichtungen 345 abgedichtet. Zwischen einem Hochdruck-Dampfeinströmbereich 348 und einem Dampfaustrittsbereich 351 weist die Turbinenwelle 309 in der Hochdruck-Teilturbine 300 die Hochdruck-Laufbeschaufelung 357 auf. Diese Hochdruck-Laufbeschaufelung 357 stellt mit den zugehörigen, nicht näher dargestellten Laufschaufeln einen ersten Beschaufelungsbereich 360 dar.Along the axis of rotation 306, 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 from the outer housing 315 of the medium-pressure turbine section 303 by two further shaft seals 345. Between a high-pressure steam inflow region 348 and a steam outlet region 351, the turbine shaft 309 in the high-pressure turbine section 300 has the high-pressure impeller blade 357. This high-pressure blading 357, together with the associated blades, not shown, represents a first blading region 360.

Die Mitteldruck-Teilturbine 303 weist einen zentralen Dampfeinströmbereich 333 auf. Dem Dampfeinströmbereich 333 zugeordnet weist die Turbinenwelle 309 eine radialsymmetrische Wellenabschirmung 363, eine Abdeckplatte, einerseits zur Teilung des Dampfstromes in die beiden Fluten der Mitteldruck-Teilturbine 303 sowie zur Verhinderung eines direkten Kontaktes des heißen Dampfes mit der Turbinenwelle 309 auf. Die Turbinenwelle 309 weist in der Mitteldruck-Teilturbine 303 einen zweiten Beschaufelungsbereich 366 mit den Mitteldruck-Laufschaufeln 354 auf. Der durch den zweiten Beschaufelungsbereich 366 strömende heiße Dampf strömt aus der Mitteldruck-Teilturbine 303 aus einem Abströmstutzen 369 zu einer strömungstechnisch nachgeschalteten, nicht dargestellten Niederdruck-Teilturbine.The medium-pressure turbine part 303 has a central steam inflow region 333. Associated with the steam inflow region 333, the turbine shaft 309 has a radially symmetric 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 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 downstream low-pressure turbine, not shown.

Die Turbinenwelle 309 ist beispielsweise aus zwei Teilturbinenwellen 309a und 309b zusammengesetzt, die im Bereich des Lagers 318 fest miteinander verbunden sind. Jede Teilturbinenwelle 309a, 309b weist eine als zentrale Bohrung 372a entlang der Rotationsachse 306 ausgebildete Kühlleitung 372 auf: Die Kühlleitung 372 ist mit dem Dampfaustrittsbereich 351 über eine eine radiale Bohrung 375a aufweisende Zuströmleitung 375 verbunden. In der Mitteldruck-Teilturbine 303 ist die Kühlmittelleitung 372 mit einem nicht näher dargestellten Hohlraum unterhalb der Wellenabschirmung verbunden. Die Zustromleitungen 375 sind als radiale Bohrung 375a ausgeführt, wodurch "kalter" Dampf aus der Hochdruck-Teilturbine 300 in die zentrale Bohrung 372a einströmen kann. Über die insbesondere auch als radial gerichtete Bohrung 375a ausgebildete Abströmleitung 372 gelangt der Dampf durch den Lagerbereich 321 hindurch in die Mitteldruck-Teilturbine 303 und dort an die Manteloberfläche 330 der Turbinenwelle 309 im Dampfeinströmbereich 333. Der durch die Kühlleitung strömende Dampf hat eine deutlich niedrigere Temperatur als der in den Dampfeinströmbereich 333 einströmende zwischenüberhitzte Dampf, so dass eine wirksame Kühlung der ersten Laufschaufelreihen 342 der Mitteldruck-Teilturbine 303 sowie der Manteloberfläche 330 im Bereich dieser Laufschaufelreihen 342 gewährleistet ist.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 sub-turbine shaft 309a, 309b has a cooling line 372 designed as a central bore 372a along the axis of rotation 306. The cooling line 372 is connected to the vapor exit region 351 via an inflow line 375 having a radial bore 375a. In the medium-pressure turbine part 303, 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 375a, allowing "cold" steam from the high pressure turbine section 300 to flow into the central bore 372a. Via the discharge line 372, which is also designed in particular as a radially directed bore 375a, the vapor passes through the storage area 321 into the medium-pressure turbine section 303 and there to the mantle surface 330 of the turbine shaft 309 in the steam inflow area 333. The steam flowing through the cooling line has a significantly lower temperature as the reheated steam flowing into the Dampfeinströmbereich 333, so that an effective cooling of the first blade rows 342 of the medium-pressure turbine section 303 and the mantle surface 330 is ensured in the region of these blade rows 342.

Die Figur 4 zeigt beispielhaft eine Gasturbine 100 in einem Längsteilschnitt.The FIG. 4 shows by way of example a gas turbine 100 in a longitudinal partial section.

Die Gasturbine 100 weist im Inneren einen um eine Rotationsachse 102 drehgelagerten Rotor 103 mit einer Welle 101 auf, der auch als Turbinenläufer bezeichnet wird.
Entlang des Rotors 103 folgen aufeinander ein Ansauggehäuse 104, ein Verdichter 105, eine beispielsweise torusartige Brennkammer 110, insbesondere Ringbrennkammer, mit mehreren koaxial angeordneten Brennern 107, eine Turbine 108 und das Abgasgehäuse 109.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.
Along the rotor 103 follow one another 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

Die Ringbrennkammer 110 kommuniziert mit einem beispielsweise ringförmigen Heißgaskanal 111. Dort bilden beispielsweise vier hintereinander geschaltete Turbinenstufen 112 die Turbine 108.The annular combustion chamber 110 communicates with an annular annular hot gas channel 111, for example. There, for example, four turbine stages 112 connected in series form the turbine 108.

Jede Turbinenstufe 112 ist beispielsweise aus zwei Schaufelringen gebildet. In Strömungsrichtung eines Arbeitsmediums 113 gesehen folgt im Heißgaskanal 111 einer Leitschaufelreihe 115 eine aus Laufschaufeln 120 gebildete Reihe 125.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.

Die Leitschaufeln 130 sind dabei an einem Innengehäuse 138 eines Stators 143 befestigt, wohingegen die Laufschaufeln 120 einer Reihe 125 beispielsweise mittels einer Turbinenscheibe 133 am Rotor 103 angebracht sind.
An dem Rotor 103 angekoppelt ist ein Generator oder eine Arbeitsmaschine (nicht dargestellt).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).

Während des Betriebes der Gasturbine 100 wird vom Verdichter 105 durch das Ansauggehäuse 104 Luft 135 angesaugt und verdichtet. Die am turbinenseitigen Ende des Verdichters 105 bereitgestellte verdichtete Luft wird zu den Brennern 107 geführt und dort mit einem Brennmittel vermischt. Das Gemisch wird dann unter Bildung des Arbeitsmediums 113 in der Brennkammer 110 verbrannt. Von dort aus strömt das Arbeitsmedium 113 entlang des Heißgaskanals 111 vorbei an den Leitschaufeln 130 und den Laufschaufeln 120. An den Laufschaufeln 120 entspannt sich das Arbeitsmedium 113 impulsübertragend, so dass die Laufschaufeln 120 den Rotor 103 antreiben und dieser die an ihn angekoppelte Arbeitsmaschine.During operation of the gas turbine 100, 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. From there, the working medium 113 flows along the hot gas channel 111 past the guide vanes 130 and the rotor blades 120. On 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.

Die dem heißen Arbeitsmedium 113 ausgesetzten Bauteile unterliegen während des Betriebes der Gasturbine 100 thermischen Belastungen. Die Leitschaufeln 130 und Laufschaufeln 120 der in Strömungsrichtung des Arbeitsmediums 113 gesehen ersten Turbinenstufe 112 werden neben den die Ringbrennkammer 110 auskleidenden Hitzeschildelementen am meisten thermisch belastet.
Um den dort herrschenden Temperaturen standzuhalten, können diese mittels eines Kühlmittels gekühlt werden.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.
To withstand the prevailing temperatures, they can be cooled by means of a coolant.

Ebenso können Substrate der Bauteile eine gerichtete Struktur aufweisen, d.h. sie sind einkristallin (SX-Struktur) oder weisen nur längsgerichtete Körner auf (DS-Struktur).
Als Material für die Bauteile, insbesondere für die Turbinenschaufel 120, 130 und Bauteile der Brennkammer 110 werden beispielsweise eisen-, nickel- oder kobaltbasierte Superlegierungen verwendet.
Solche Superlegierungen sind beispielsweise aus der EP 1 204 776 B1 , EP 1 306 454 , EP 1 319 729 A1 , WO 99/67435 oder WO 00/44949 bekannt; diese Schriften sind bzgl. der chemischen Zusammensetzung der Legierungen Teil der Offenbarung.Likewise, substrates of the components can have a directional structure, ie they are monocrystalline (SX structure) or have only longitudinal grains (DS structure).
As the material for the components, in particular for the turbine blade 120, 130 and components of the combustion chamber 110, for example, iron-, nickel- or cobalt-based superalloys are used.
Such superalloys are for example from EP 1 204 776 B1 . EP 1 306 454 . EP 1 319 729 A1 . WO 99/67435 or WO 00/44949 known; These documents are part of the disclosure regarding the chemical composition of the alloys.

Ebenso können die Schaufeln 120, 130 Beschichtungen gegen Korrosion (MCrAlX; M ist zumindest ein Element der Gruppe Eisen (Fe), Kobalt (Co), Nickel (Ni), X ist ein Aktivelement und steht für Yttrium (Y) und/oder Silizium, Scandium (Sc) und/oder zumindest ein Element der Seltenen Erden bzw. Hafnium). Solche Legierungen sind bekannt aus der EP 0 486 489 B1 , EP 0 786 017 B1 , EP 0 412 397 B1 oder EP 1 306 454 A1 , die bzgl. der chemischen Zusammensetzung Teil dieser Offenbarung sein sollen.Also, 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). 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 should be part of this disclosure in terms of chemical composition.

Auf der MCrAlX kann noch eine Wärmedämmschicht vorhanden sein, und besteht beispielsweise aus ZrO2, Y2O3-ZrO2, d.h. sie ist nicht, teilweise oder vollständig stabilisiert durch Yttriumoxid und/oder Kalziumoxid und/oder Magnesiumoxid.On the MCrAlX may still be present a thermal barrier coating, and consists for example of ZrO 2 , Y 2 O 3 -ZrO 2 , that is, it is not, partially or completely stabilized by yttria and / or calcium oxide and / or magnesium oxide.

Durch geeignete Beschichtungsverfahren wie z.B. Elektronenstrahlverdampfen (EB-PVD) werden stängelförmige Körner in der Wärmedämmschicht erzeugt.By suitable coating methods, e.g. Electron beam evaporation (EB-PVD) produces stalk-shaped grains in the thermal barrier coating.

Die Leitschaufel 130 weist einen dem Innengehäuse 138 der Turbine 108 zugewandten Leitschaufelfuß (hier nicht dargestellt) und einen dem Leitschaufelfuß gegenüberliegenden Leitschaufelkopf auf. Der Leitschaufelkopf ist dem Rotor 103 zugewandt und an einem Befestigungsring 140 des Stators 143 festgelegt.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.

Claims (35)

  1. Nodular cast iron containing (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 ≤ 0.25%, nickel ≤ 0.5%, in particular ≤0.3%,
    remainder iron.
  2. Nodular cast iron according to Claim 1,
    wherein the proportion of silicon, cobalt and molybdenum is less than 7.5 wt%.
  3. Nodular cast iron according to Claim 1 or 2,
    containing from 0.5 wt% to 2.0 wt% cobalt.
  4. Nodular cast iron according to Claim 1 or 2,
    containing from 0.5 wt% to 1.5 wt% cobalt.
  5. Nodular cast iron according to Claim 1 or 2,
    containing from 0.5 wt% to 1.0 wt% cobalt.
  6. Nodular cast iron according to Claim 1 or 2,
    containing from 1.0 wt% to 2.0 wt% cobalt.
  7. Nodular cast iron according to Claim 1 or 2,
    containing from 1.0 wt% to 1.5 wt% cobalt.
  8. Nodular cast iron according to Claim 1 or 2,
    containing from 1.5 wt% to 2.0 wt% cobalt.
  9. Nodular cast iron according to Claim 1 or 2,
    containing 0.5 wt% cobalt.
  10. Nodular cast iron according to Claim 1 or 2,
    containing 1 wt% cobalt.
  11. Nodular cast iron according to Claim 1 or 2,
    containing 1.5 wt% cobalt.
  12. Nodular cast iron according to Claim 1 or 2,
    containing 2.0 wt% cobalt.
  13. Nodular cast iron according to one or more of the preceding claims,
    which contains molybdenum.
  14. Nodular cast iron according to one or more of the preceding Claims 1 to 12,
    which contains no molybdenum.
  15. Nodular cast iron according to one or more of the preceding claims,
    which contains manganese.
  16. Nodular cast iron according to Claim 15,
    which has a manganese content ≤ 0.07 wt%.
  17. Nodular cast iron according to Claim 15,
    which has a manganese content ≤ 0.03 wt%.
  18. Nodular cast iron according to one or more of the preceding Claims 1 to 14,
    which contains no manganese.
  19. Nodular cast iron according to one or more of the preceding claims,
    which contains nickel.
  20. Nodular cast iron according to one or more of the preceding Claims 1 to 18,
    which contains no nickel.
  21. Nodular cast iron according to one or more of the preceding claims,
    which contains 2.0 wt% - 3.0 wt% silicon.
  22. Nodular cast iron according to Claim 21,
    which contains 2.5 wt% silicon.
  23. Nodular cast iron according to one or more of the preceding claims,
    which contains from 3.5 wt% to 4.0 wt% carbon,
    in particular 3.7 wt% carbon.
  24. Nodular cast iron according to one or more of the preceding claims,
    which contains at most 0.07 wt% phosphorus.
  25. Nodular cast iron according to one or more of the preceding claims,
    which contains at most 0.008 wt% sulfur (S).
  26. Nodular cast iron according to one or more of the preceding claims,
    which contains at most 0.05 wt% magnesium.
  27. Nodular cast iron according to one or more of the preceding claims,
    which contains no chromium (Cr).
  28. Nodular cast iron according to one or more of the preceding claims,
    which contains no magnesium (Mg).
  29. Nodular cast iron according to one or more of the preceding claims,
    consisting of
    iron, silicon, cobalt and carbon.
  30. Nodular cast iron according to one or more of the preceding Claims 1 to 28,
    consisting of
    iron, silicon, cobalt, carbon and manganese.
  31. Nodular cast iron according to one or more of the preceding Claims 1 to 28,
    consisting of
    iron, silicon, cobalt, carbon and optionally manganese, molybdenum and/or nickel.
  32. Component,
    consisting of a nodular cast iron according to one or more of Claims 1 to 31.
  33. Component according to Claim 32,
    which is a housing part.
  34. Component according to Claim 32 or 33,
    which is a component of a steam turbine (300, 303) or a gas turbine (100).
  35. Component according to Claim 32, 33 or 34,
    which comprises a substrate which is iron- or steel-based.
EP07703621.8A 2006-01-16 2007-01-03 Cast iron comprising cobalt and component Not-in-force EP1974068B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP07703621.8A EP1974068B1 (en) 2006-01-16 2007-01-03 Cast iron comprising cobalt and component

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
EP06000851A EP1808504A1 (en) 2006-01-16 2006-01-16 Cast iron containing cobalt for use in steam turbines
PCT/EP2007/050057 WO2007082788A1 (en) 2006-01-16 2007-01-03 Cast iron comprising cobalt and component
EP07703621.8A EP1974068B1 (en) 2006-01-16 2007-01-03 Cast iron comprising cobalt and component

Publications (2)

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

Family

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Family Applications (2)

Application Number Title Priority Date Filing Date
EP06000851A Withdrawn EP1808504A1 (en) 2006-01-16 2006-01-16 Cast iron containing cobalt for use in steam turbines
EP07703621.8A Not-in-force EP1974068B1 (en) 2006-01-16 2007-01-03 Cast iron comprising cobalt and component

Family Applications Before (1)

Application Number Title Priority Date Filing Date
EP06000851A Withdrawn EP1808504A1 (en) 2006-01-16 2006-01-16 Cast iron containing cobalt for use in steam turbines

Country Status (4)

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

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102008051042A1 (en) * 2008-10-09 2010-04-15 Siemens Aktiengesellschaft Cast iron with cobalt and component
US20100322813A1 (en) * 2009-06-23 2010-12-23 General Electric Company SiMo DUCTILE IRON CASTINGS IN GAS TURBINE APPLICATIONS
EP2511394B1 (en) * 2011-04-15 2015-05-27 Siemens Aktiengesellschaft Cast iron with niobium and component
DE102011051446A1 (en) 2011-06-29 2013-01-03 Siempelkamp Giesserei Gmbh Ductile iron, especially for high temperature applications
CN103146990B (en) * 2013-03-29 2016-07-06 天津新伟祥工业有限公司 Vehicle turbine housing high silicon molybdenum chromium magnesium iron material and preparation method thereof
CN105714181A (en) * 2016-02-26 2016-06-29 铜陵安东铸钢有限责任公司 Cobalt-containing nodular cast iron and preparing method thereof
WO2018093894A1 (en) * 2016-11-18 2018-05-24 Michigan Technological University Ductile iron alloys and materials including a thin-wall layer of a ductile iron alloy

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 (en) * 1984-07-31 1994-02-23 株式会社クボタ Manufacturing method of ductile high-strength ductile cast iron pipe
FR2681878B1 (en) * 1991-09-26 1993-12-31 Centre Tech Ind Fonderie HEAT RESISTANT SPHEROUIDAL GRAPHITE CAST IRON.

Also Published As

Publication number Publication date
EP1974068A1 (en) 2008-10-01
CN101400812A (en) 2009-04-01
WO2007082788A1 (en) 2007-07-26
EP1808504A1 (en) 2007-07-18
US20100178192A1 (en) 2010-07-15

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