EP2712943A2 - Cast iron with niobium and component - Google Patents
Cast iron with niobium and component Download PDFInfo
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- EP2712943A2 EP2712943A2 EP13181651.4A EP13181651A EP2712943A2 EP 2712943 A2 EP2712943 A2 EP 2712943A2 EP 13181651 A EP13181651 A EP 13181651A EP 2712943 A2 EP2712943 A2 EP 2712943A2
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- European Patent Office
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- weight
- alloy according
- silicon
- niobium
- cobalt
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- 239000010955 niobium Substances 0.000 title claims abstract description 25
- 229910052758 niobium Inorganic materials 0.000 title claims abstract description 16
- GUCVJGMIXFAOAE-UHFFFAOYSA-N niobium atom Chemical compound [Nb] GUCVJGMIXFAOAE-UHFFFAOYSA-N 0.000 title claims abstract description 16
- 229910001018 Cast iron Inorganic materials 0.000 title description 3
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 35
- 239000000956 alloy Substances 0.000 claims abstract description 35
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims abstract description 22
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims abstract description 21
- 229910052710 silicon Inorganic materials 0.000 claims abstract description 21
- 229910017052 cobalt Inorganic materials 0.000 claims abstract description 19
- 239000010941 cobalt Substances 0.000 claims abstract description 19
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 claims abstract description 19
- 239000010703 silicon Substances 0.000 claims abstract description 18
- XUIMIQQOPSSXEZ-UHFFFAOYSA-N Silicon Chemical compound [Si] XUIMIQQOPSSXEZ-UHFFFAOYSA-N 0.000 claims abstract description 17
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims abstract description 13
- 229910052799 carbon Inorganic materials 0.000 claims abstract description 13
- ZOKXTWBITQBERF-UHFFFAOYSA-N Molybdenum Chemical compound [Mo] ZOKXTWBITQBERF-UHFFFAOYSA-N 0.000 claims abstract description 12
- 239000011651 chromium Substances 0.000 claims abstract description 12
- 229910052750 molybdenum Inorganic materials 0.000 claims abstract description 12
- 239000011733 molybdenum Substances 0.000 claims abstract description 12
- 239000011777 magnesium Substances 0.000 claims abstract description 10
- 229910052742 iron Inorganic materials 0.000 claims abstract description 9
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 claims abstract description 8
- 229910052759 nickel Inorganic materials 0.000 claims abstract description 8
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 claims abstract description 7
- 229910052749 magnesium Inorganic materials 0.000 claims abstract description 7
- 229910052804 chromium Inorganic materials 0.000 claims abstract description 6
- OAICVXFJPJFONN-UHFFFAOYSA-N Phosphorus Chemical compound [P] OAICVXFJPJFONN-UHFFFAOYSA-N 0.000 claims abstract description 5
- NINIDFKCEFEMDL-UHFFFAOYSA-N Sulfur Chemical compound [S] NINIDFKCEFEMDL-UHFFFAOYSA-N 0.000 claims abstract description 5
- 229910052787 antimony Inorganic materials 0.000 claims abstract description 5
- WATWJIUSRGPENY-UHFFFAOYSA-N antimony atom Chemical compound [Sb] WATWJIUSRGPENY-UHFFFAOYSA-N 0.000 claims abstract description 5
- 229910052717 sulfur Inorganic materials 0.000 claims abstract description 5
- 239000011593 sulfur Substances 0.000 claims abstract description 5
- 239000011572 manganese Substances 0.000 claims description 5
- 229910052698 phosphorus Inorganic materials 0.000 claims description 5
- 239000011574 phosphorus Substances 0.000 claims description 3
- PWHULOQIROXLJO-UHFFFAOYSA-N Manganese Chemical compound [Mn] PWHULOQIROXLJO-UHFFFAOYSA-N 0.000 claims description 2
- 229910052748 manganese Inorganic materials 0.000 claims description 2
- BHEPBYXIRTUNPN-UHFFFAOYSA-N hydridophosphorus(.) (triplet) Chemical compound [PH] BHEPBYXIRTUNPN-UHFFFAOYSA-N 0.000 claims 1
- 239000012535 impurity Substances 0.000 claims 1
- WPBNNNQJVZRUHP-UHFFFAOYSA-L manganese(2+);methyl n-[[2-(methoxycarbonylcarbamothioylamino)phenyl]carbamothioyl]carbamate;n-[2-(sulfidocarbothioylamino)ethyl]carbamodithioate Chemical compound [Mn+2].[S-]C(=S)NCCNC([S-])=S.COC(=O)NC(=S)NC1=CC=CC=C1NC(=S)NC(=O)OC WPBNNNQJVZRUHP-UHFFFAOYSA-L 0.000 abstract 2
- 238000002485 combustion reaction Methods 0.000 description 6
- 238000001816 cooling Methods 0.000 description 4
- 229910002804 graphite Inorganic materials 0.000 description 3
- 239000010439 graphite Substances 0.000 description 3
- 239000000203 mixture Substances 0.000 description 3
- 238000005275 alloying Methods 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 2
- 238000000576 coating method Methods 0.000 description 2
- 239000002826 coolant Substances 0.000 description 2
- 239000010949 copper Substances 0.000 description 2
- 229910000601 superalloy Inorganic materials 0.000 description 2
- 239000012720 thermal barrier coating Substances 0.000 description 2
- 239000010936 titanium Substances 0.000 description 2
- YPFNIPKMNMDDDB-UHFFFAOYSA-K 2-[2-[bis(carboxylatomethyl)amino]ethyl-(2-hydroxyethyl)amino]acetate;iron(3+) Chemical compound [Fe+3].OCCN(CC([O-])=O)CCN(CC([O-])=O)CC([O-])=O YPFNIPKMNMDDDB-UHFFFAOYSA-K 0.000 description 1
- 229910052684 Cerium Inorganic materials 0.000 description 1
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 description 1
- 229910001141 Ductile iron Inorganic materials 0.000 description 1
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 239000008186 active pharmaceutical agent Substances 0.000 description 1
- BRPQOXSCLDDYGP-UHFFFAOYSA-N calcium oxide Chemical compound [O-2].[Ca+2] BRPQOXSCLDDYGP-UHFFFAOYSA-N 0.000 description 1
- 239000000292 calcium oxide Substances 0.000 description 1
- ODINCKMPIJJUCX-UHFFFAOYSA-N calcium oxide Inorganic materials [Ca]=O ODINCKMPIJJUCX-UHFFFAOYSA-N 0.000 description 1
- GWXLDORMOJMVQZ-UHFFFAOYSA-N cerium Chemical compound [Ce] GWXLDORMOJMVQZ-UHFFFAOYSA-N 0.000 description 1
- 229910052802 copper Inorganic materials 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000001419 dependent effect Effects 0.000 description 1
- 238000005566 electron beam evaporation Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 229910052735 hafnium Inorganic materials 0.000 description 1
- VBJZVLUMGGDVMO-UHFFFAOYSA-N hafnium atom Chemical compound [Hf] VBJZVLUMGGDVMO-UHFFFAOYSA-N 0.000 description 1
- 239000000395 magnesium oxide Substances 0.000 description 1
- CPLXHLVBOLITMK-UHFFFAOYSA-N magnesium oxide Inorganic materials [Mg]=O CPLXHLVBOLITMK-UHFFFAOYSA-N 0.000 description 1
- AXZKOIWUVFPNLO-UHFFFAOYSA-N magnesium;oxygen(2-) Chemical compound [O-2].[Mg+2] AXZKOIWUVFPNLO-UHFFFAOYSA-N 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 150000001247 metal acetylides Chemical class 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 238000001556 precipitation Methods 0.000 description 1
- 229910052761 rare earth metal Inorganic materials 0.000 description 1
- 150000002910 rare earth metals Chemical class 0.000 description 1
- 229910052706 scandium Inorganic materials 0.000 description 1
- SIXSYDAISGFNSX-UHFFFAOYSA-N scandium atom Chemical compound [Sc] SIXSYDAISGFNSX-UHFFFAOYSA-N 0.000 description 1
- 239000006104 solid solution Substances 0.000 description 1
- 238000003860 storage Methods 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
- 230000035882 stress Effects 0.000 description 1
- 239000000758 substrate Substances 0.000 description 1
- 229910052715 tantalum Inorganic materials 0.000 description 1
- GUVRBAGPIYLISA-UHFFFAOYSA-N tantalum atom Chemical compound [Ta] GUVRBAGPIYLISA-UHFFFAOYSA-N 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
- LEONUFNNVUYDNQ-UHFFFAOYSA-N vanadium atom Chemical compound [V] LEONUFNNVUYDNQ-UHFFFAOYSA-N 0.000 description 1
- 229910052727 yttrium Inorganic materials 0.000 description 1
- VWQVUPCCIRVNHF-UHFFFAOYSA-N yttrium atom Chemical compound [Y] VWQVUPCCIRVNHF-UHFFFAOYSA-N 0.000 description 1
- RUDFQVOCFDJEEF-UHFFFAOYSA-N yttrium(III) oxide Inorganic materials [O-2].[O-2].[O-2].[Y+3].[Y+3] RUDFQVOCFDJEEF-UHFFFAOYSA-N 0.000 description 1
Images
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
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C37/00—Cast-iron alloys
- C22C37/06—Cast-iron alloys containing chromium
- C22C37/08—Cast-iron alloys containing chromium with nickel
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/10—Metals, alloys or intermetallic compounds
- F05D2300/11—Iron
- F05D2300/111—Cast iron
Definitions
- the invention relates to a cast iron with niobium according to claim 1 and a component according to claim 19.
- GJS alloys nodular cast iron
- Molybdenum also shows a very high tendency to increase.
- the object is achieved by an alloy according to claim 1 and a component according to claim 20.
- the invention is that cobalt and / or niobium can partially replace molybdenum.
- the application limits, which have the previous GJS alloy can be overcome.
- the iron-based alloy according to the invention has high elongations for the range of application in the temperature range of 450 ° C - 550 ° C and has the following composition (in wt .-%): Silicon (Si) 2.0% - 4.5%, especially 2.3% - 3.9% Carbon (C) 2.9% - 4.0%, in particular 3.2% - 3.7%, Niobium (Nb) 0.05% -0.7%, in particular 0.05% -0.6%, very particular 0.1% to 0.7%, Molybdenum (Mo) 0.3% - 1.5%, in particular 0.4% - 1.0% very particular optional 0.5% Cobalt (Co) 0.1% - 2.0%, in particular 0.1% - 1.0%, Manganese (Mn) ⁇ 0.3%, in particular 0.15-0.30%, Nickel (Ni) ⁇ 0.5%, in particular ⁇ 0.3%, Magnesium (Mg) ⁇ 0.07%, in particular at least 0.03%, very particular 0.03% - 0.06% Phosphorus (P) ⁇
- the proportion of silicon, cobalt, niobium and molybdenum is ⁇ 7.5% by weight, in particular ⁇ 6.5% by weight.
- Niobium improves creep strength with consistently high LCF strength and good toughness.
- Niobium causes a higher heat resistance due to the precipitation of finely distributed Nb carbides, whereby the application limits are shifted to high temperatures.
- Cobalt causes solid-solution strengthening, which positively affects the properties of the alloy at high temperatures and low stresses.
- the hot strength (Rp0,2 and Rm in the elevated temperature range) and the creep strength are positively influenced.
- the proportion of cobalt in the alloy is between 0.5 wt% to 1.5 wt%.
- magnesium By magnesium, the spherical formation of the graphite is obtained and magnesium is preferably present at least 0.03 wt .-%, a maximum of 0.07 wt .-%.
- chromium (Cr) with at least 0.01% by weight, but not more than 0.05% by weight, which increases the oxidation resistance.
- the alloy can have further elements.
- the component with the alloy shows an optimal ferritic microstructure with nodular graphite.
- the table shows exemplary (by weight) iron-based alloys of the invention having improved mechanical properties.
- main alloying elements are: C Si Not a word Nb Co 9 3.56 2.50 0.50 0.10 0.00 10 3.56 2.50 1.00 0.10 0.00 11 3.56 2.50 0.50 0.50 0.00 12 3.56 2.50 1.00 0.50 0.00 13 3.56 2.50 0.50 0.10 1.00 14 3.56 2.50 1.00 0.10 1.00 15 3.56 2.50 0.50 0.50 1.00 16 3.56 2.50 1.00 0.50 1.00 17 3.56 2.50 1.00 0.50 1.00 18 3.04 4.00 0.50 0.10 0.00 19 3.04 4.00 1.00 0.10 0.00 20 3.04 4.00 0.50 0.50 0.00 21 3.04 4.00 1.00 0.50 0.00 22 3.04 4.00 0.50 0.10 1.00 23 3.04 4.00 1.00 0.10 1.00 24 3.04 4.00 0.50 0.50 1.00 25 3.04 4.00 1.00 0.50 1.00 26 3.04 4.00 1.00 0.50 1.00 27 3.30 3.25 0.50 0.10 0.50 28 3.30 3.25 0.50 0.10 1.00 29 3.30 3.25 0.50 0.50 0.50 30 3.30 3.25
- the alloy contains no vanadium (V) and / or titanium (Ti) and / or tantalum (Ta) and / or copper (Cu).
- FIG. 1 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, for example, in Pot type executed.
- 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.
- the medium-pressure turbine part 303 has a central 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 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 in the region of the Bearing 318 are firmly connected.
- Each turbine shaft 309a, 309b has a cooling line 372 formed as a central bore 372a along the axis of rotation 306.
- the cooling line 372 is connected to the steam outlet 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. 2 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.
- 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
- 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. There, for example, form four successive turbine stages 112, the turbine 108th
- 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.
- 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.
- substrates of the components may have a directional structure, i. they are monocrystalline (SX structure) or have only longitudinal grains (DS structure).
- 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.
- Such superalloys are for example from EP 1 204 776 B1 .
- EP 1 306 454 .
- 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 are known from the EP 0 486 489 B1 .
- MCrAlX may still be present a thermal barrier coating, and consists for example of ZrO 2 , Y 2O3 -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 casing 138 of the turbine 108 and a vane head opposite the vane root.
- the vane head faces the rotor 103 and fixed to a mounting ring 140 of the stator 143.
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Refinement Of Pig-Iron, Manufacture Of Cast Iron, And Steel Manufacture Other Than In Revolving Furnaces (AREA)
- Heat Treatment Of Sheet Steel (AREA)
Abstract
Description
Die Erfindung betrifft ein Gusseisen mit Niob gemäß Anspruch 1 und ein Bauteil gemäß Anspruch 19.The invention relates to a cast iron with niobium according to claim 1 and a component according to claim 19.
Die bekannten und im Einsatz befindlichen Gusseisenlegierungen (sogenannte GJS Legierungen: Gusseisen mit Kugelgraphit) verwenden hauptsächlich Silizium und Molybdän zur Steigerung der Kriechfestigkeit, Zunderbeständigkeit und LCF-Verhalten. Dabei führen diese Elemente mit der Zeit aber zu einem deutlichen Abfall der Zähigkeit.The known and used cast iron alloys (so-called GJS alloys: nodular cast iron) mainly use silicon and molybdenum to increase creep resistance, scale resistance and LCF behavior. However, these elements lead to a significant drop in toughness over time.
Molybdän zeigt darüber hinaus eine sehr große Steigerungsneigung.Molybdenum also shows a very high tendency to increase.
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.
Die Aufgabe wird gelöst durch eine Legierung gemäß Anspruch 1 und ein Bauteil gemäß Anspruch 20.The object is achieved by an alloy according to claim 1 and a component according to claim 20.
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 und/oder Niob Molybdän teilweise ersetzen kann. Somit können die Anwendungsgrenzen, die die bisherige GJS-Legierung aufweisen, überwunden werden.The invention is that cobalt and / or niobium can partially replace molybdenum. Thus, the application limits, which have the previous GJS alloy can be overcome.
Die erfindungsgemäße eisenbasierte Legierung weist hohe Dehnungen für den Anwendungsbereich in dem Temperaturbereich von 450°C - 550°C auf und hat folgende Zusammensetzung (in Gew.-%) :
Vorteilhafterweise gilt, dass der Anteil von Silizium, Kobalt, Niob und Molybdän ≤ 7,5 Gew.-%, insbesondere ≤ 6,5 Gew.-% beträgt.Advantageously, the proportion of silicon, cobalt, niobium and molybdenum is ≦ 7.5% by weight, in particular ≦ 6.5% by weight.
Schon geringe Anteile von Kobalt und/oder Niob und Molybdän verbessern die mechanischen Kennwerte.Even small amounts of cobalt and / or niobium and molybdenum improve the mechanical properties.
Niob verbessert die Zeitstandfestigkeit bei gleichbleibend hoher LCF-Festigkeit und guter Zähigkeit.Niobium improves creep strength with consistently high LCF strength and good toughness.
Niob bewirkt durch die Ausscheidung fein verteilter Nb-Karbide eine höhere Warmfestigkeit, wodurch die Anwendungsgrenzen zu hohen Temperaturen verschoben werden.Niobium causes a higher heat resistance due to the precipitation of finely distributed Nb carbides, whereby the application limits are shifted to high temperatures.
Kobalt bewirkt eine Mischkristall-Verfestigung, welche die Eigenschaften der Legierung bei hohen Temperaturen und geringen Spannungen positiv beeinflusst.Cobalt causes solid-solution strengthening, which positively affects the properties of the alloy at high temperatures and low stresses.
Durch Zulegierung von Molybdän (vorzugsweise 0,4% - 1,0%) wird die Warmfestigkeit (Rp0,2 und Rm im erhöhten Temperaturbereich) und das Zeitstandverhalten (Kriechfestigkeit) positiv beeinflusst.By alloying molybdenum (preferably 0.4% - 1.0%), the hot strength (Rp0,2 and Rm in the elevated temperature range) and the creep strength are positively influenced.
Vorzugsweise liegt der Anteil von Kobalt in der Legierung zwischen 0,5 Gew.-% bis 1,5 Gew.-%.Preferably, the proportion of cobalt in the alloy is between 0.5 wt% to 1.5 wt%.
Vorteilhafte mechanische Werte werden für die Legierung jeweils erreicht, wenn der Kobalt-Gehalt bei 0,1 Gew.-% bis 1,0 Gew.-% Kobalt liegt.Advantageous mechanical values are achieved for the alloy in each case if the cobalt content is from 0.1% by weight to 1.0% by weight of cobalt.
Durch Magnesium wird die kugelige Ausbildung des Graphits erwirkt und Magnesium ist vorzugsweise mit mindestens 0,03 Gew.-% vorhanden, maximal 0,07 Gew.-%.By magnesium, the spherical formation of the graphite is obtained and magnesium is preferably present at least 0.03 wt .-%, a maximum of 0.07 wt .-%.
Je nach Anwendung ist vorzugsweise Chrom (Cr) mit mindestens 0,01 Gew.-%, aber maximal 0,05 Gew.-% vorhanden, das die Oxidationsbeständigkeit erhöht.Depending on the application, preference is given to chromium (Cr) with at least 0.01% by weight, but not more than 0.05% by weight, which increases the oxidation resistance.
Die Legierung kann weitere Elemente aufweisen.The alloy can have further elements.
Gegebenenfalls sind in der Legierung geringe Mindest-Beimengen von
Weiterhin ist vorzugsweise kein Chrom (Cr) in der Legierung vorhanden.Furthermore, preferably no chromium (Cr) is present in the alloy.
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 eine Dampfturbine, -
Figur 2 eine Gasturbine.
-
FIG. 1 a steam turbine, -
FIG. 2 a gas turbine.
Das Bauteil mit der Legierung zeigt ein optimales ferritisches Gefüge mit Kugelgraphit.The component with the alloy shows an optimal ferritic microstructure with nodular graphite.
Die Tabelle zeigt beispielhafte erfindungsgemäße eisenbasierte Legierungen (in Gew.-%), die verbesserte mechanische Eigenschaften aufweisen.
Weitere Beispiele für die Hauptlegierungselemente sind:
Vorzugsweise enthält die Legierung kein Vanadium (V) und/oder Titan (Ti) und/oder Tantal (Ta) und/oder Kupfer (Cu).Preferably, the alloy contains no vanadium (V) and / or titanium (Ti) and / or tantalum (Ta) and / or copper (Cu).
Das Verhältnis von C und Si sollte eine naheutektische Zusammensetzung ergeben, also einem Kohlenstoffäquivalent CE zwischen 4.1% und 4.4% entsprechen
In
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
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
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
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
Die
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.The
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.Along the
Die Ringbrennkammer 110 kommuniziert mit einem beispielsweise ringförmigen Heißgaskanal 111. Dort bilden beispielsweise vier hintereinander geschaltete Turbinenstufen 112 die Turbine 108.The
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
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.The
An dem Rotor 103 angekoppelt ist ein Generator oder eine Arbeitsmaschine (nicht dargestellt).Coupled to the
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
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.The components exposed to the hot working
Um den dort herrschenden Temperaturen standzuhalten, können diese mittels eines Kühlmittels gekühlt werden.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).Likewise, substrates of the components may have a directional structure, i. they are monocrystalline (SX structure) or have only longitudinal grains (DS structure).
Als Material für die Bauteile, insbesondere für die Turbinenschaufel 120, 130 und Bauteile der Brennkammer 110 werden beispielsweise eisen-, nickel- oder kobaltbasierte Superlegierungen verwendet.As the material for the components, in particular for the
Solche Superlegierungen sind beispielsweise aus der
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
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 2O3 -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
Claims (17)
die 0,05 Gew.-% - 0,2 Gew.-% Niob (Nb) enthält, insbesondere 0,1 Gew.-% Niob.Alloy according to claim 1,
containing 0.05 wt .-% - 0.2 wt .-% of niobium (Nb), in particular 0.1 wt .-% of niobium.
die 0,4 Gew.-% - 0,6 Gew.-% Niob (Nb) enthält, insbesondere 0,5 Gew.-%.Alloy according to claim 1,
containing 0.4 wt .-% - 0.6 wt .-% of niobium (Nb), in particular 0.5 wt .-%.
enthaltend 0,4 Gew.-% bis 0,6 Gew.-% Kobalt (Co), insbesondere 0,5 Gew.-% Kobalt (Co).Alloy according to one or more of claims 1, 2 or 3,
containing from 0.4% by weight to 0.6% by weight of cobalt (Co), in particular 0.5% by weight of cobalt (Co).
enthaltend 0,9 Gew.-% bis 1,1 Gew.-% Kobalt (Co), insbesondere 1,0 Gew.-% Kobalt (Co).Alloy according to one or more of claims 1, 2 or 3,
containing 0.9 wt .-% to 1.1 wt .-% cobalt (Co), in particular 1.0 wt .-% cobalt (Co).
deren Anteil an Silizium (Si), Kobalt (Co), Molybdän (Mo) und Niob (Nb) kleiner 6,5 Gew.-% beträgt,
insbesondere kleiner 6,0 Gew.-%,
ganz insbesondere mindestens 3,5 Gew.-% beträgt.Alloy according to one or more of the preceding claims,
their content of silicon (Si), cobalt (Co), molybdenum (Mo) and niobium (Nb) is less than 6.5% by weight,
in particular less than 6.0% by weight,
more preferably at least 3.5 wt .-% is.
deren Anteil an Molybdän (Mo) und Niob (Nb) 1,5 Gew.-% nicht übersteigt,
insbesondere mindestens 0,6 Gew.-% beträgt.Alloy according to one or more of the preceding claims,
their content of molybdenum (Mo) and niobium (Nb) does not exceed 1.5% by weight,
in particular at least 0.6 wt .-% is.
die 2,0 Gew.-% - 3,0 Gew.-% Silizium (Si) enthält, insbesondere 2,3 Gew.-% - 2,7 Gew.-% Silizium (Si),
ganz insbesondere 2,5 Gew.-% Silizium (Si).Alloy according to one or more of the preceding claims 1 to 7,
containing 2.0 wt .-% - 3.0 wt .-% silicon (Si), in particular 2.3 wt .-% - 2.7 wt .-% silicon (Si),
in particular 2.5% by weight of silicon (Si).
die 3,0 Gew.-% - 4,5 Gew.-% Silizium (Si) enthält. insbesondere 3,3 Gew.-% - 3,5 Gew.-% Silizium (Si) enthält.Alloy according to one or more of the preceding claims 1 to 7,
containing 3.0 wt .-% - 4.5 wt .-% silicon (Si). in particular 3.3 wt .-% - contains 3.5 wt .-% silicon (Si).
die 3,15 Gew.-% - 3,40 Gew.-% Silizium (Si) enthält. insbesondere 3,25 Gew.-% Silizium enthält.Alloy according to one or more of the preceding claims 1 to 7,
which contains 3.15% by weight - 3.40% by weight of silicon (Si). in particular 3.25% by weight of silicon.
die 3,9 Gew.-% - 4,1 Gew.-% Silizium (Si) enthält. insbesondere 4,0 Gew.-% Silizium (Si) enthält.Alloy according to one or more of the preceding claims 1 to 7,
containing 3.9 wt .-% - 4.1 wt .-% silicon (Si). in particular 4.0 wt .-% silicon (Si) contains.
die kein Nickel (Ni) und/oder kein Chrom (Cr) außer als mögliche Verunreinigung und/oder kein Kobalt (Co) enthält.Alloy according to one or more of the preceding claims,
which does not contain nickel (Ni) and / or chromium (Cr) except as a possible impurity and / or cobalt (Co).
die mindestens 0,01 Gew.-% Nickel (Ni) enthält, insbesondere mindestens 0,05 Gew.-%.Alloy according to one or more of the preceding claims,
containing at least 0.01 wt .-% nickel (Ni), in particular at least 0.05 wt .-%.
die 3,2 Gew.-% bis 3,4 Gew.-% Kohlenstoff (C), insbesondere 3,3 Gew.-% Kohlenstoff enthält.Alloy according to one or more of the preceding claims,
containing 3.2 wt .-% to 3.4 wt .-% carbon (C), in particular 3.3 wt .-% carbon.
die 3,4 Gew.-% bis 3,7 Gew.-% Kohlenstoff (C), insbesondere 3,55 Gew.-% Kohlenstoff enthält.Alloy according to one or more of the preceding claims 1 to 13,
containing 3.4 wt .-% to 3.7 wt .-% carbon (C), in particular 3.55 wt .-% carbon.
die für Kohlenstoff (C), Silizium (Si) und Phospor (P) ein CE-Äquivalent von 4,1% bis 4,4% aufweist,
wobei
which has a CE equivalent of 4.1% to 4.4% for carbon (C), silicon (Si) and phosphorous (P),
in which
insbesondere bestehend aus einer Legierung nach einem oder mehreren der Ansprüche 1 bis 16,
das insbesondere ein Gehäuseteil,
insbesondere einer Dampfturbine (300, 303) oder einer Gasturbine (100) ist.component
in particular consisting of an alloy according to one or more of claims 1 to 16,
in particular a housing part,
in particular a steam turbine (300, 303) or a gas turbine (100).
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102012217892.9A DE102012217892A1 (en) | 2012-10-01 | 2012-10-01 | Cast iron with niobium and component |
Publications (2)
Publication Number | Publication Date |
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EP2712943A2 true EP2712943A2 (en) | 2014-04-02 |
EP2712943A3 EP2712943A3 (en) | 2016-11-09 |
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EP13181651.4A Withdrawn EP2712943A3 (en) | 2012-10-01 | 2013-08-26 | Cast iron with niobium and component |
Country Status (5)
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US (1) | US20140093416A1 (en) |
EP (1) | EP2712943A3 (en) |
CN (1) | CN103710614A (en) |
DE (1) | DE102012217892A1 (en) |
RU (1) | RU2639194C2 (en) |
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CN104342594A (en) * | 2014-12-02 | 2015-02-11 | 江苏金洋机械有限公司 | Alloy for preparing iron cushion plate for high-iron buckle |
JP6466727B2 (en) * | 2015-02-06 | 2019-02-06 | 日産自動車株式会社 | Spheroidal graphite cast iron and automotive engine exhaust system parts |
US10662510B2 (en) * | 2016-04-29 | 2020-05-26 | General Electric Company | Ductile iron composition and process of forming a ductile iron component |
US11618937B2 (en) * | 2019-10-18 | 2023-04-04 | GM Global Technology Operations LLC | High-modulus, high-strength nodular iron and crankshaft |
CN111074145B (en) * | 2019-12-05 | 2021-06-01 | 江苏吉鑫风能科技股份有限公司 | Low-temperature-toughness ultra-thick large-end-face ferritic nodular iron casting and preparation method thereof |
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- 2012-10-01 DE DE102012217892.9A patent/DE102012217892A1/en not_active Withdrawn
-
2013
- 2013-08-26 EP EP13181651.4A patent/EP2712943A3/en not_active Withdrawn
- 2013-09-23 US US14/033,613 patent/US20140093416A1/en not_active Abandoned
- 2013-09-30 CN CN201310461826.3A patent/CN103710614A/en active Pending
- 2013-09-30 RU RU2013143927A patent/RU2639194C2/en not_active IP Right Cessation
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EP0486489B1 (en) | 1989-08-10 | 1994-11-02 | Siemens Aktiengesellschaft | High-temperature-resistant, corrosion-resistant coating, in particular for components of gas turbines |
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Also Published As
Publication number | Publication date |
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CN103710614A (en) | 2014-04-09 |
US20140093416A1 (en) | 2014-04-03 |
DE102012217892A1 (en) | 2014-05-15 |
EP2712943A3 (en) | 2016-11-09 |
RU2639194C2 (en) | 2017-12-20 |
RU2013143927A (en) | 2015-04-10 |
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