POWDER MADE OF A COBALT-CHROMIUM ALLOY

Abstract

A titanium-free cobalt-chromium alloy for a powder, contains (in wt.%) C 0.40 -1.50%, Cr 24.0 - 32.0%, W 3.0 - 8.0%, Mo 0.1 - 5.0%, where 4.0 < W + Mo < 9.5 is satisfied by the content of W and Mo in wt.%, Nb max. 0.5%, Ta max. 0.5 %, where Nb + Ta < 0.8 is satisfied by the content of Nb and Ta in wt.%, Ni 0.005 - 25.0%, Fe 0.005 -15.0%, where Ni + Fe > 3.0 is satisfied by the content of Ni and Fe in wt.%, Mn 0.005 -5.0%, Al max. 0.5%, N 0.0005 - 0.15%, Si < 0.3%, Cu max. 0.4%, O 0.0001 - 0.1%, P max. 0.015%, B max. 0.015%, S max. 0.015%, residual Co, and impurities resulting from the production process, in particular Zr max. 0.03% and Ti max. 0.025%.

Claims

1. A titanium-free cobalt-chromium alloy for powder, comprising (in wt-%) C 0.40 - 1.50% Cr 24.0 - 32.0% W 3.0 - 8.0% Mo 0.1 - 5.0%, wherein 4.0 ≤ W + Mo ≤ 9.5, with the contents of W and Mo in wt-%, is satisfied Nb max. 0.5% Ta max. 0.5%, wherein Nb + Ta ≤ 0.8, with the contents of Nb and Ta in wt-%, is satisfied Ni 0.005 - 25.0% Fe 0.005 - 15.0%, wherein Ni + Fe > 3.0, with the contents of Ni and Fe in wt-%, is satisfied Mn 0.005 - 5.0% Al max. 0.5% N 0.0005 - 0.15% Si < 0.3% Cu max. 0.4% O 0.0001 -0.1% P max. 0.015% B max. 0.015% S max. 0.015% Co the rest and manufacturing-related impurities, especially Zr max. 0.03% Ti max. 0.025%.

2. The alloy according to claim 1, in which the following relationships must be satisfied, especially after a heat treatment: 10.0 volume-% ≤ M.sub.23C.sub.6 ≤40.0 volume-% and M.sub.7C.sub.3 ≤ 10.0 volume-%.

3. The alloy according to claim 1, with a C content (in wt-%) of 0.4 to 1.4%.

4. The alloy according to claim 1, with a Cr content (in wt-%) of 25.0 to 31.0%.

5. The alloy according to claim 1, with a Mo content (in wt-%) of 0.1 to 4.0%, especially 0.1 to 3.0%.

6. The alloy according to claim 1, with a W content (in wt-%) of 0.5 - 6.5%.

7. The alloy according to claim 1, with a W content (in wt-%) of 3.5 to 8.0%, wherein 4.2 ≤ W + Mo ≤ 9.5, with the contents of W and Mo in wt-%, must be satisfied, wherein the preferred range 4.5 ≤ W + Mo ≤ 9.0% is satisfied.

8. The alloy according to claim 1, with a Ta content (in wt-%) of max. 0.5%, wherein Nb + Ta ≤ 0.6, with the contents of Nb and Ta in wt-%, must be satisfied, wherein the preferred range Nb + Ta ≤ 0.5% is satisfied.

9. The alloy according to claim 1, with a Ni content (in wt-%) of 0.005 to 24.0%, especially 0.005 to 21.0%.

10. The alloy according to claim 1, with an Fe content (in wt-%) of 0.05 to 15.0%.

11. The alloy according to claim 1, with a Mn content (in wt-%) of 0.005 to 4.5%.

12. The alloy according to claim 1, with a N content (in wt-%) of 0.001 to 0.12%, especially of 0.001 to 0.10%.

13. The alloy according to claim 1, with a Si content (in wt-%) of max. 0.25%, especially of max. 0.20%.

14. The alloy according to claim 1, with an O content (in wt-%) of 0.001 to 0.1%, especially of 0.002 to 0.08%.

15. The alloy according to claim 1, with a Cu content (in wt-%) of max. 0.3%, with a B content (in wt-%) of max. 0.012%, with a S content (in wt-%) of max. 0.010%, with a Pb content (in wt-%) of max. 0.005%, with a Zn content (in wt-%) of max. 0.005%, with a Sn content (in wt-%) of max. 0.005%, with a Bi content (in wt-%) of max. 0.005%, with a V content (in wt-%) of max. 0.005%, with an Y content (in wt-%) of max. 0.005%, with a Hf content (in wt-%) of max. 0.015% and with a La content (in wt-%) of max. 0.005%.

16. A method for manufacture of a powder from the alloy according to claim 1, wherein the alloy is smelted in a vacuum induction smelting furnace and atomized in a closed atomization system, wherein the melt is fed through a nozzle to a supplied gas stream having a specified gas flow rate and the solidified powder particles are collected in a gas-tightly sealed container.

17. A use of the alloy according to claim 1 as powder for generative fabrication methods and/or in combination with a HIP method, for the HIP methods as well as for the build-up welding and/or coating.

18. A use of the alloy according to claim 1 as component part and/or as coating under tribological, corrosive and oxidizing conditions or combinations of such conditions.

19. A use of the method according to claim 16 for generation of a powder for generative fabrication methods and/or in combination with a HIP method, for the HIP methods as well as for the build-up welding and/or coating.

20. The use of the method according to claim 16 for generation of a component part and/or a coating under tribological, corrosive and oxidizing conditions or combinations of such conditions.

Description

[0117] In the following, a method is presented for manufacture of a powder from a cobalt-chromium alloy according to the invention, in that an alloy is smelted in a vacuum induction smelting furnace, a closed atomization system is adjusted with a supplied gas, the melt is fed through a nozzle to a gas stream having a specified gas flow rate, the solidified powder particles are collected in a gas-tightly sealed container.

[0118] The powder according to the invention is preferably produced in a vacuum inert-gas atomization system (VIGA). In this system, the alloy is smelted in a VIM furnace and the molten melt is held for 20 minutes to 2 hours for homogenization. The melt is passed into a casting gate, which leads to a gas stream, in which the molten metal is atomized to metal particles under high pressure of 5 to 100 bar with inert gas. The melt is heated in the melting crucible at 5 to 400° C. above the melting point. The metal flow rate during atomization is 0.5 to 80 kg /min and the gas flow rate is 2 to 150 m.sup.3/min. Due to the rapid cooling, the metal particles solidify in the form of balls (spherical particles). The inert gas used for the atomization may if necessary contain 0.01 to 100% nitrogen. The gas phase is then separated from the powder in a cyclone, after which the powder is packaged. In the process, the particles have a particle size of 5 .Math.m to 250 .Math.m, gas inclusions of 0.0 to 4% pore area (pores < 1 .Math.m) relative to the total area of evaluated objects, a bulk density of 2 up to the density of the alloy of approximately 8.5 g/cm.sup.3 and are packaged air-tightly under a shield gas atmosphere containing argon.

[0119] The range of values for the particle size of the powder lies between 5 and 250 .Math.m, wherein preferred ranges lie between 5 and 150 .Math.m or 10 and 150 .Math.m. The preferred ranges are obtained by separation of too-fine and too-coarse particles by means of sieving and sifting processes. These processes take place under shield gas atmosphere and may be carried out one or more times.

[0120] The inert gas for powder manufacture may optionally be argon or a mixture of argon with 0.01 to < 100% nitrogen. Possible restrictions of the nitrogen content may be: [0121] 0.01 to 80% [0122] 0.01 to 50% [0123] 0.01 to 30% [0124] 0.01 to 20% [0125] 0.01 to 10% [0126] 0.01 to 10% [0127] 0.1 to 5% [0128] 0.5 to 10% [0129] 1 to 5% [0130] 2 to 3%

[0131] Alternatively, the inert gas may optionally be helium.

[0132] The inert gas should preferably have a purity of at least 99.996 vol-%. In particular, the nitrogen content should have from 0.0 to 10 ppmv, the oxygen content from 0.0 to 4 ppmv and an H.sub.2O content of ≤ 5 ppmv.

[0133] In particular, the inert gas may preferably have a purity of at least 99.999 vol-%. In particular, the nitrogen content should have from 0.0 to 5 ppmv, the oxygen content from 0.0 to 2 ppmv and an H.sub.2O content of ≤ 3 ppmv. The dew point in the system lies in the range of -10 to -120° C. Preferably, it lies in the range of -30 to -100° C.

[0134] The pressure during the powder atomization may preferably be 10 to 80 bar.

[0135] The component parts and components or layers on component parts and components manufactured by means of additive fabrication are built up from layer thicknesses of 5 to 500 .Math.m and have a textured microstructure directly after the manufacture, with grains elongated in build-up direction having a mean grain size of 2 .Math.m to 1000 .Math.m. The preferred range lies between 5 .Math.m and 500 .Math.m. A component-part fabrication may take place if necessary with heating of the building-up space and/or with in situ heat treatment by laser control.

[0136] Moreover, the powder described above may be used if necessary for the manufacture of the component parts by means of HIP or conventional sintering and extrusion pressing processes. Furthermore, a method combination of additive fabrication and subsequent HIP treatment is possible. In the process, the post-processing steps described below for the generative fabrication are possibly to be used for HIP component parts.

[0137] Likewise, the alloy according to the invention may be used if necessary for the build-up welding on metallic components of any type. In this way the high wear resistance, hardness with very good corrosion and oxidation resistance are achieved in combination with crack-free or almost crack-free microstructure and improved ductility in comparison with Stellite no. 6.

[0138] Moreover, the alloy according to the invention may be suitable for binder jetting methods. In this method, component parts are built up in layers, although, in comparison with laser-melting methods, an organic binder, which ensures cohesion of the powder particles, is introduced locally. After hardening of the binder, the so-called green part is freed from the non-bonded powder, after which the binder is removed and the part is sintered.

[0139] The methods and additional apparatuses for pre-heating and post-heating may be of advantage for the alloy according to the invention. EBM methods - electron beam melting - may be considered as an example. The powder bed is selectively melted in layers by the electron beam. The process takes place under high vacuum. Therefore this process is suitable in particular for hard materials, which have lower ductility, and/or for reactive materials. The pre-heating and/or post-heating may likewise be implemented in laser-based methods. The component parts and components or layers on component parts and components manufactured by means of additive fabrication and other methods described above may be subjected optionally to a homogenization, stress-relief, solution and/or precipitation-hardening annealing. The heat treatments may be subjected if necessary under vacuum or shield gas, such as, for example, argon or hydrogen, followed by a cooling in the furnace, if necessary under shield gas, in air, in the agitated annealing atmosphere or in the water bath.

[0140] The component parts may be annealed if necessary at temperatures between 400° C. and 1250° C. for 1 hour to 300 hours under vacuum, air or shield gas for the homogenization or for the stress relaxation. Thereafter the component parts may be solution, stress-relief or precipitation-hardening annealed if necessary at temperatures between 400° C. and 1050° C. for 0.5 hour to 30 hours under vacuum, air or shield gas.

[0141] Thereafter the surface may optionally be cleaned or machined by pickling, abrasive blasting, grinding, turning, scalping, milling. Optionally, such a machining may even be carried out partly or completely already before the annealing.

[0142] After an annealing, the component parts and components or layers on component parts and components manufactured by means of additive fabrication and other methods described above have a mean grain size of 2 .Math.m to 2000 .Math.m. The preferred range lies between 20 .Math.m and 500 .Math.m.

[0143] The term “additive/generative fabrication” may be subdivided into rapid prototyping, rapid tooling, rapid manufacturing or the like, depending on application level.

[0144] In general, a distinction is made here among: [0145] 3D printing with powders [0146] Selective laser sintering [0147] Selective laser melting [0148] Electron beam melting [0149] Binder jetting [0150] Laser build-up welding [0151] High-speed laser build-up welding [0152] Ultra-high-speed laser build-up welding [0153] Selective electron-beam welding or the like.

[0154] The abbreviations used here are defined as follows: [0155] VIM Vacuum Induction Melting [0156] VIGA Vacuum Induction Melting and Inert Gas Atomization

[0157] The cobalt-chromium alloy according to the invention should preferably be used in areas in which tribological, corrosive and/or oxidative conditions prevail, such as, for example, diverters, valves, especially valve seats, brake disks, especially the wearing surfaces of brakes, rollers, rods and/or replacement for galvanic hard-chromium coatings, in the oil, gas and automobile industry as well as turbine engineering. Beyond that, it is also suitable for the chemical process industry and packaging industry.

[0158] The claimed limits for the alloy according to the invention can therefore be justified individually as follows: wear resistance and hardness increase with increasing carbide content. Carbon is primarily responsible for the carbide formation.

[0159] A minimum content of 0.40% C is necessary in order to obtain an adequately good wear resistance and high hardness. At higher C contents, the processability and weldability deteriorate. The upper limit is therefore set at 1.50%.

[0160] For a good oxidation and corrosion resistance as well as for carbide formation, it is necessary to have an adequate proportion of Cr, at least 24.0%, in the alloy. At higher Cr contents, the undesired phases may be formed and thus reduce the processability of the alloy. The upper limit is therefore set at 32.0%.

[0161] The volume percentage of carbides increases with increasing W content. Moreover, the strength of the alloy is increased by solution hardening. A minimum content of 3.0% is necessary, in order to achieve an adequate proportion of carbides. At higher W contents, M.sub.7C.sub.3 carbides, which increase the cracking tendency of the alloy in any welding processes, are increasingly formed. Moreover, higher contents very greatly increase the costs. The upper limit is therefore set at 8.0% W.

[0162] At adequately high W content, an Mo content of at least 0.1% further increases the stability of desired M.sub.23C.sub.6 carbides. At higher Mo contents, the processability deteriorates. The upper limit is therefore set at 5.0%.

[0163] For a good processability due to adequately high carbide volume percentage, it is necessary that the sum Mo be greater than 4.0%. If the sum W + Mo is greater than 9.5%, the costs of the alloy are increased very greatly.

[0164] The low cracking tendency during the compaction process is achieved not only by balanced concentrations of C, Cr, Mo, W but also by a reduction of the formation of metastable M.sub.7C.sub.3 carbides, which dissolve under temperature influence, as well as coarse MC carbides, which are brittle due to the absence of glide planes and act as crack-initiation sites. Moreover, it is important to keep volume percentages of M.sub.6C, sigma and Laves phases as low as possible, in order to ensure the processability of the component parts. Thus CoCr6 in the base composition (see Tables 1 and 2) has approximately 15 volume-% of M.sub.7C.sub.6 carbides, which is primarily segregated and from approximately 1100° C. begin to transform to M.sub.23C.sub.6. The dissolution of M.sub.7C.sub.6 blocky carbides and the segregation of M.sub.23C.sub.6 carbides is complete at approximately 980° C. This phase transformation leads to additional stresses in the material due to the volume changes and crack formation. Therefore the contents of the following elements, which support the formation of above-mentioned phases, are intentionally greatly limited in the alloy according to the invention.

[0165] Moreover, Zr (impurity) segregates very strongly during the solidification process and increases the cracking tendency. The content of Zr is therefore specified as max. 0.03%. The Hf content is limited to max. 0.015% and the Ti content (impurity) to max. 0.025%. The sum of Zr, Hf and Ti is limited to ≤0.04%.

[0166] Just as Zr, Hf and Ti, Nb and Ta among other ingredients stabilize MC carbides. Therefore the contents of Nb and Ta are respectively limited to ≤0.5%, wherein the sum of Nb and Ta is limited to ≤0.8%.

[0167] At adequately high Ni content, the ductility of the alloy is increased. Moreover, the fcc structure is stabilized. At too-high content, the strength of the alloy is reduced due to the large increase in stacking fault energy. The Ni content is therefore limited to 25.0%.

[0168] The content of Fe is limited to max. 15.0%, since at higher contents the strength in Co-base alloys is reduced. In general, Fe has an effect similar to that of Ni. At high contents, however, a reduction of the strength and increase of the ductility may lead to formation of the undesired phases such as Laves and sigma in the alloy. Too-low Fe contents cause increased manufacturing costs for the material. The iron content should therefore be higher than 0.005%.

[0169] Manganese is limited to 5.0%, since this element at higher contents may increase the cracking tendency during the welding process. Too-low Mn contents may not ensure the desulfurization effect in the alloy. The manganese content should therefore be higher than 0.005%.

[0170] Even very low proportions of aluminum effectively bind oxygen in the melt. At too-high contents, the weldability due to aluminum may again negatively influence the reactivity. The Al content is therefore limited to 0.5%.

[0171] Nitrogen is limited to 0.15%, so that the nitride formation is reduced, in order to limit the cracking tendency during the compaction process. Too-low N contents causes increased costs during the manufacture of the alloy. The nitrogen content should therefore be higher than 0.0005%.

[0172] Silicon is limited to lower than 0.3%, since this element increases the cracking tendency during the compaction process very strongly on the basis of its segregation behavior. The limitation of the Si content permits the increased C content.

[0173] Copper is limited to 0.4%, since this element reduces the oxidation resistance.

[0174] The oxygen content should be lower than 0.1%, since this element impairs the mechanical properties of the compacted component parts and/or coatings of the alloy according to the invention. Too-low O contents cause increased manufacturing costs for the powder. The oxygen content should therefore be higher than 0.0001%.

[0175] The content of P should be kept as low as possible, since this surface-active element very greatly increases the cracking tendency due to the formation of low-melting eutectics during welding processes. Therefore max. 0.015% is specified.

[0176] The content of boron should be kept as low as possible, since this surface-active element very greatly increases the cracking tendency during welding processes. Therefore max. 0.015% is specified.

[0177] The contents of sulfur should be kept as low as possible, since this surface-active element forms the low-melting eutectics during any welding processes and enormously supports the cracking tendency. Therefore max. 0.015% S is specified.

[0178] Pb is limited to max. 0.005%, since this element reduces the processability. The same is true for Zn, Sn, Bi, V, Y and La.

[0179] The volume of M.sub.23C.sub.6 carbides is limited to maximum 40 volume-%, since at higher volume the ductility of the material is greatly lowered. Too-low volume percentage of M.sub.23C.sub.6 carbides reduces the wear resistance of the material. Therefore min. 10 volume-% M.sub.23C.sub.6 is required.

[0180] At the same time, the volume of M.sub.7C.sub.3 carbides is limited to max. 10 volume-%, since higher phase proportions strongly favor the crack formation.

[0181] By means of thermodynamic simulations (JMatPro and ThermoCalc) with the TTNi8 database, an extensive experimental matrix with variation of the chemical compositions was calculated. Exemplary alloys are presented in Tables 1 and 2. In this way, it is possible to explain the relationships between chemical composition and the phase formation. Since thermodynamic simulations without possible diffusion processes during the solidification were used for these calculations, the following residual elements, Cu, P, S, Pb, Zn, Sn, Bi, V, Y, La, which may arrive from raw materials or from the industrial production, were not taken into consideration in the calculations. The upper limits were applied on the basis of the combination of technical experience and economic aspects. In the tables, the alloys CoCr6 and MP75 are indicated as typical compositions. This alloy CoCr6 was taken as the basis for the development according to the invention. CoCr6 in basic version exhibits a complex carbide structure.

[0182] The objective of the development according to the invention was to adapt the compositions on the basis of different C contents such that M.sub.23C.sub.6 carbides are formed between 10.0 volume-% and 40.0 volume-%, in order to ensure high hardness and the wear resistance, and the formation of M.sub.7C.sub.3 carbides is limited to max. 10.0 volume-%. On the basis of their unfavorable morphology, the formation of MC and M.sub.6C carbides should be reduced as much as possible (respectively to 2 volume-%) or should be suppressed. Moreover, the alloys should not contain any Laves and sigma phase if at all possible. This is achieved by adaptation of the combination of C, W, Mo, Nb, Ta, Zr, Hf and Ti.

[0183] The low contents of Nb and Ta, as in the alloys B-42, B-43 as well as in B-44, already stabilize the MC carbides. The elements Zr, Hf and Ti with lower contents achieve similar effect (alloys B-45, B-46 and B-49). Further alloys in the tables show examples within the claimed composition ranges. An adapted combination of C, W and Mo is necessary in order to achieved a high volume of M.sub.23C.sub.6 carbides, without the presence of high volume of metastable M.sub.7C.sub.3 carbides in the microstructure of the alloy (alloys B-2, B-3, B-5, B-7, B-8, B-11 , B-12, B-13, B-14, B-15, B-53, B-55, B-65, B-72). With the increase of the C content (B-70, B-71 , B-72), Cr as well as W and Mo content should likewise be increased. This makes it possible to obtain only the M.sub.23C.sub.6 carbides, even at 1.5 wt-% C (B-72) (see Table 2).

TABLE-US-00001 Chemical composition of exemplary alloys (E: according to the invention, N: not according to the invention, T: prior art) all values in wt-%: [Andere = Other; Rest = the rest; commas should be read as periods] CoCr6 MP75 B-2 B-3 B-5 B-7 B-8 B-11 B-12 B-13 B-14 B-15 B-21 B-24 T T E E E E E E E E E E N N C 1.1 0.22 0.6 0.6 0.7 0.6 0.6 0.75 0.6 0.9 0.8 0.4 0.4 0.8 Cr 28.0 28.5 29.0 28.0 29.0 29.0 29.0 29.0 29.0 29.0 29.0 29.0 28.0 32.0 W 4.5 0.01 6.0 5.0 5.0 5.0 5.0 5.0 5.0 5.0 5.0 5.0 4.5 4.5 Mo – 6.0 0.5 1.0 1.0 0.1 0.5 1.0 1.0 1.0 1.0 1.0 0.1 0.1 Fe 1.0 0.2 0.5 0.5 0.5 0.5 0.5 0.5 0.5 0.005 0.05 0.5 2.0 2.0 Nl 1.0 0.25 9.4 9.9 9.8 14.0 14.0 9.7 9.7 9.7 6.0 10.0 1.0 2.0 Mn 0.5 0.5 0.005 0.005 0.005 0.005 0.005 0.005 0.005 0.005 5.0 0.005 1.0 1.0 Al – 0.05 0.005 0.005 0.005 0.005 0.005 0.005 0.005 0.005 0.1 0.005 0.1 0.1 Si 1.0 0.7 0.05 0.05 0.05 0.05 0.05 0.05 0.05 0.05 0.1 0.05 1.0 1.0 Ti – 0.01 0.002 0.002 0.002 0.002 0.002 0.002 0.002 0.002 0.002 0.002 0.002 0.002 0.002 Nb – – 0.01 0.01 0.01 0.01 0.01 0.01 0.01 0.01 0.01 0.01 0.01 0.01 N – – 0.01 0.01 0.01 0.01 0.01 0.01 0.01 0.01 0.01 0.01 0.01 0.01 B – – 0.0005 0.001 0.001 0.001 0.001 0.002 0.001 0.008 0.001 0.002 0.001 0.001 Zr – – 0.0005 0.001 0.001 0.002 0.0005 0.005 0.005 0.005 0.005 0.0005 0.005 0.002 O – – 0.015 0.015 0.015 0.015 0.015 0.015 0.015 0.015 0.015 0.015 0.015 0.015 Andere – – – – – – – – – – – – – – Co Rest Rest Rest Rest Rest Rest Rest Rest Rest Rest Rest Rest Rest Rest B-29 B-31 B-33 B-34 B-42 B-43 B-44 B-45 B-46 B-49 B-53 B-55 B-59 N N N N E N E E N N E E N C 0.8 0.8 0.8 0.5 0.8 0.8 0.8 0.8 0.8 0.8 0.8 0.8 0.8 Cr 24.0 29.0 29.0 29.0 29.0 29.0 29.0 29.0 29.0 29.0 29.0 29.0 29.0 W 3.0 8.0 4.5 4.5 5.0 5.0 5.0 5.0 5.0 5.0 5.0 5.0 5.0 Mo 0.1 0.1 5.0 5.0 1.0 1.0 1.0 1.0 1.0 1.0 1.0 1.0 1.0 Fe 2.0 2.0 2.0 2.0 2.0 2.0 2.0 2.0 2.0 2.0 0.1 5.0 8.0 Nl 2.0 2.0 2.0 2.0 10.0 10.0 10.0 10.0 10.0 10.0 19.0 5.0 10.0 Mn 1.0 1.0 1.0 1.0 0.3 0.3 0.3 0.3 0.3 0.3 0.3 0.3 0.3 Al 0.1 0.1 0.1 0.1 0.1 0.1 0.1 0.5 0.1 0.5 0.1 0.1 0.1 Si 1.0 1.0 1.0 1.0 0.29 0.29 0.29 0.29 0.3 0.3 0.3 0.3 0.3 Ti 0.002 0.002 0.01 0.002 0.002 0.002 0.002 0.0025 0.1 0.025 0.002 0.002 0.002 Nb 0.01 0.01 0.01 0.01 0.5 1.0 0.5 0.01 0.01 0.01 0.01 0.01 0.01 N 0.01 0.01 0.01 0.01 0.01 0.01 0.01 0.03 0.03 0.01 0.01 0.01 0.01 B 0.001 0.002 0.001 0.003 0.002 0.002 0.002 0.002 0.002 0.001 0.002 0.001 0.001 Zr 0.001 0.001 0.004 0.003 0.001 0.001 0.001 0.001 0.03 0.03 0.005 0.003 0.002 O 0.015 0.015 0.015 0.015 0.015 0.015 0.015 0.015 0.015 0.015 0.015 0.015 0.015 Andere – – – – Ta 0.5 Ta 1.0 Ta 0.3 Hf 0.01 Hf 0.1 Hf 0.1 – – – Co Rest Rest Rest Rest Rest Rest Rest Rest Rest Rest B-63 B-65 B-69 B-70 B-71 B-72 E N N N N E C 0.9 1.5 1.5 1.5 1.5 1.5 Cr 29.0 29.0 26.0 32.0 32.0 32.0 W 5.0 5.0 4.5 5.0 6.0 7.0 Mo 1.0 1.0 0.5 1.0 1.0 2.0 Fe 0.5 0.5 2.0 0.5 0.5 0.5 Ni 9.5 9.5 5.0 10.0 10.0 10.0 Mn 0.3 0.3 1.0 0.1 0.1 1.0 Al 0.5 0.005 0.005 0.005 0.005 0.005 Si 0.1 0.1 0.1 0.1 0.1 0.1 Ti 0.002 0.002 0.002 0.002 0.002 0.002 Nb 0.01 0.01 0.01 0.01 0.01 0.01 N 0.01 0.01 0.01 0.01 0.01 0.01 B 0.001 0.001 0.001 0.002 0.003 0.001 Zr 0.005 0.005 0.005 0.003 0.0005 0.0005 O 0.015 0.015 0.015 0.015 0.015 0.015 Andere - - - - - - Co Rest Rest Rest Rest Rest Rest

TABLE-US-00002 Phase stability ranges: [Max. Volumen = Max. volume; Stabilitätsbereich = Stability range; Ja/nein = Yes/No; Primar = Primary; ja = yes; nein = no] M.sub.23C.sub.6 M.sub.7C.sub.3 M.sub.8C MC Sigma Laves-Ph. SolvusT-c.sup.∧C Max Voluman, % Stabilitäts-bereish,.sup.∧C Max. Volumen. % Ja/nein Ja/nein Ja/nein Ja/nein Basis CoCr6 T 1100 23 Primär-980 15 ja ja nein nein MP75 T Primär 4.7 nein nein nein nein ja nein B-2 E Primär 14 nein nein nein nein nein nein B-3 E Primär 14 nein nein nein nein nein nein B-5 E Primär 17 nein nein nein nein nein nein B-7 E 1240 14 Primär-1150 10 nein nein nein nein B-8 E Primär 13 nein nein nein nein nein nein B-11 E Primär 18 nein nein nein nein nein nein B-12 E Primär 18 nein nein nein nein nein nein B-13 E Primär 20 Primär-1250 4 nein nein nein nein B-14 E Primär 18 nein nein nein nein nein nein B-15 E Primär 10 nein nein nein nein nein nein B-21 N 1 260 9 Primär-1230 5 ja nein nein ja B-24 N Primär 18 Primär-1270 3 ja nein nein ja B-29 N 990 18 Primär-860 12 ja ja nein nein B-31 N Primär 18 Primär-1250 4 ja nein nein ja B-33 N Primär 18 nein nein nein nein ja ja B-34 N Primär 13 nein nein nein nein ja ja B-42 E Primär 16 nein nein nein ja nein nein B-43 N Primär 14 nein nein nein ja nein nein B-44 E Primär 16 nein nein nein ja nein nein B-45 E Primär 17 nein nein nein ja nein nein B-46 N Primär 17 nein nein nein ja nein nein B-49 N Primär 18 nein nein nein ja nein nein B-53 E Primär 18 Primär-1250 4 nein nein nein nein B-55 E Primär 18 nein nein nein nein nein nein B-59 N Primär 18 nein nein nein nein ja nein B-63 E Primär 20 Primär-1240 4 ja ja nein nein B-65 N Primär 34 Primär-990 18 nein nein nein nein B-69 N 1160 35 Primär-720 20 nein nein nein nein B-70 N Primär 34 Primär-1140 16 nein nein nein nein B-71 N Primär 34 Primär-1160 12 nein nein nein nein B-72 E Primär 35 nein nein nein nein nein nein

[0184] In Table 3, first exemplary atomized chemical compositions are presented (akin to B-12 and B-13 with different Ni contents). It is possible, by means of laser-based additive fabrication, to generate component parts having different process parameters without macro-cracks (see FIG. 1).

[0185] FIG. 1 shows a material body, built up by means of laser-based additive fabrication, having different process parameters {light-exposure strategies) without macro-cracks.

[0186] As predicted in the thermodynamic calculations, no primary M.sub.7C.sub.3 carbides as well as eutectic solidification were detected. The carbide precipitation of M.sub.23C.sub.6 is induced by means of heat treatment. Advantages of this are that carbide size and distribution may be controlled by a heat treatment.

TABLE-US-00003 First exemplary atomized chemical compositions. n.a. = not analyzed. Andere = Others; Rest = the rest P10331 P10332 P10333 P10376 P10377 E E E E E C 0.78 0.77 0.80 0.82 0.80 Cr 28.82 28.97 28.62 28.34 27.64 W 4.01 4.07 4.28 4.19 4.22 Mo 1.48 1.43 1.45 1.56 1.44 Fe 0.05 0.04 0.05 0.08 0.08 Ni 10.06 9.91 9.92 18.68 20.11 Mn 0.001 0.001 0.012 n.a. n.a. Al 0.015 0.013 0.015 n.a n.a Si 0.01 0.01 0.03 0.02 0.02 Ti 0.001 0.001 0.001 n.a. n.a. Nb 0.001 0.002 0.001 0.01 0.01 N 0.002 0.002 0.002 0.002 0.002 B 0.0005 0.0005 0.0005 0.001 0.001 Zr 0.001 0.001 0.001 O 0.010 0.011 0.011 0.008 0.009 Andere n.a. n.a. n.a. n.a. n.a. Co Rest Rest Rest Rest Rest