A low density Nickel base gamma prime strengthened superalloy, a component and method

Abstract

A nickel-based gamma-prime strengthened superalloy which comprises (by weight): 3.0-13.0 % cobalt, 11.5-13.5 % chromium, 1.5-2.0 % molybdenum, 1.7-2.7 % tungsten, 3.8-4.8 % aluminium, 1.7-2.7 % titanium, 3.8-5.5 % niobium, 0.005-0.20 % carbon, 0.005-0.50 % silicon, 0-2.0 % hafnium, 0-5.0 % iron, 0-0.03 % boron and 0-0.05 % zirconium, with the balance being nickel and impurities. The alloy can be used for conventional casting, directional solidification or single crystal formation of such as later stage blades in land-based gas turbines. It can also be used in additive manufacturing by laser powder bed fusion, selective electron beam processes or liquid metal deposition.

Description

The invention refers to a low density Nickel base gamma prime strengthened superalloy especially for later stage gas turbine blades. When later stage blades in a gas turbine are designed for aerodynamic efficiency and against creep, the design work is constrained by Low Cycle Fatigue (LCF) in the disc attachment due to the mass of said blades. A reduced density in the blade alloy will, everything else being equal, enable designs with better aerodynamic efficiency and / or allow for higher metal temperatures, as it eases the LCF constraint. Improved aerodynamic efficiency and / or increased allowable metal temperatures will e.g., enable an increased thermal efficiency in a combined cycle power plant resulting in reduced CO2 emissions. Later stage blades in land based gas turbines typically operate in the 873K (600°C) to 1073K (800°C) range where hot corrosion agents are particularly aggressive. In order to enable fuel flexibility, including use of corrosive biofuels, and handle air borne contaminants such as sea salt, it is thus advantageous to have a good hot corrosion resistance. Furthermore, the alloy should be produced with a clean process, especially w.r.t. Sulfur which should be kept below about 5ppm to avoid the detrimental effect of sulfur on the adherence of the CnOi layer. Furthermore, while Silicon (Si) need to be low to avoid detrimental effect on the grain boundary strength, a near absence of Silicon (Si) could result in sluggish formation of the protective CnCh layer since Silicon (Si) is beneficial for the selective oxidation of Chromium (Cr), and this could provide a window of opportunity for the influx of corrosive species into the alloy. IN792, a Nickel base gamma prime strengthened superalloy for Conventional Casting (CC) with a nominal composition, in wt%. of Ni-8.5Co-12.5Cr-1,8Mo-4W-3.4Al-4Ti-4Ta-0.08C-0.02Zr-0.015B has a good combination of creep and hot corrosion resistance, a density of 8.37 kg / dm3, and is extensively used for later stage blades and other turbine components. Molybdenum (Mo) and Tungsten (W) are used to strengthen the gamma matrix while Titanium (Ti) and Tantalum (Ta) are used to strengthen the gamma prime particles. There is a beneficial effect of Aluminum (Al), and, the detrimental effect of the heavy elements Rhenium (Re), Tungsten (W) and / or Tantalum (Ta) on the density. It should also be noted that Niobium (Nb) and Tantalum (Ta) are preferable to Titanium (Ti) for strengthening of the gamma prime phase in the sense that they provide more strengthening per at%, and do not result in as much risk for unwanted phases (UP) precipitation relative to their strengthening effect. Furthermore, Titanium (Ti) reduces the heat treatment window. Tantalum (Ta) is a strong MC former. In the in-house code, the user can chose which carbides said user expect to be present. It is therefore the aim of the invention to improve the desired properties and to reduce the density of a Nickel based superalloy. The problem is solved by a Nickel based superalloy according to claim I and a component of claim 17 and method according to claim 19. In the dependent claims further advantages are listed which can be combined with each other arbitrarily to yield further advantages. The description gives only examples of the invention. For a good oxidation and hot corrosion resistance in this temperature range, it is necessary to have a nominal composition with at least about 11.5wt% Chromium (Cr) to enable formation of an adherent and continuous layer of CnCh within the oxide layer. This will retard further oxidation, and retard the influx of corrosive elements into the alloy. Furthermore, Molybdenum (Mo) should be below about 1.5wt%, as in e.g., IN792, and Vanadium (V) be avoided, as in e.g., IN792, since these elements can react with and exacerbate the attack from corrosive agents. Hafnium (Hf) up to about 0.7wt% or up to 2.0% is included by some casting vendors to improve the casting yield. Whether Hafnium (Hf) is an advantage, and if so at what level, depends on the component geometry, and, the specific casting methodology, mold materials and rigs used by the vendor. When Hafnium (Hf) is added, the levels of one or more of the other alloy elements are reduced somewhat to ensure that this does not cause an increased propensity for precipitation of unwanted phases (UP) such as Laves or Sigma. It should be noted that Tantalum (Ta) is often added for enhanced oxidation resistance as well as for strength in Nickel base superalloys made for the high metal temperatures seen in hot stage blades, while Niobium (Nb) provides the same strengthening effect per at% but does not boost the oxidation resistance. More specifically, Tantalum (Ta) supports the formation of a protective AI2O3 layer. A replacement of Tantalum (Ta) by Niobium (Nb) is seen as beneficial in later stage blades where a reduced density is important, the metal temperatures are not on the levels seen in hot stage blades, CnCb layers provide a good protection and AI2O3 layers cannot form because the temperature is too low. A blade alloy having corrosion resistance on the IN792 level, creep resistance on at least the IN792 level, and a reduced density would enable higher performance. It is accordingly the aim of the invention to provide an alloy with IN792 level corrosion resistance, at least IN792 level creep resisance, and a reduced density. Relative to IN792, the strengthening levels in the gamma and gamma prime phase are similar, as is the risk for UP precipitation, while the gamma prime content is increased. This will increase the creep strength. At the same time the density is reduced which will improve the LCF resistance and further increase the specific creep resistance. Since the gamma prime content is increased, and thus the gamma content reduced, it is possible to reduce the Tungsten (W) content while keeping the Molybdenum (Mo) content similar, and, retain about the same level of strengthening of said gamma matrix. This reduction in Tungsten (W) will reduce the density. In the gamma prime phase, Tantalum (Ta) is fully replaced by Niobium (Nb). Furthermore, in terms of at% there is more Niobium (Nb) in the present invention than there is Tantalum (Ta) in IN792. Hence the Titanium (Ti) level can be reduced and the Aluminum (Al) level increased relative to IN792 for the same level of strengthening of the gamma prime particles. This reduces the density, mostly because Tantalum (Ta) is avoided. This combination is furthermore beneficial with respect to the risk for UP precipitation, and, increases the Heat Treatment Window (HTW). Silicon (Si) is prudently included at a low measured level while nominally set to zero in most specifications for IN792 and many other alloys. This inclusion is to avoid the risk for the reduction in oxidation and hot corrosion resistance which might occur if the production process for a component turned out to result in an unusually low level of Silicon (Si). Hafoium (Hf) values can be added as necessary, typically at levels up to about 0.7wt% for Conventional Casting (CC) and in the order of 1,4wt% to 2.0wt% for Directional Solidification (DS) like SX or columnar casting. Iron (Fe) can be judiciously used to reduce the gamma prime solvus in order to improve the processability. In yielding SX or DS microstructure with this alloy, levels of Zirconium (Zr) and Boron (B) have to be kept low. But Zirconium (Zr) and Boron (B) can preferably be introduced for yielding a CC (equiaxed) structure with this alloy, especially at least 0.005% Zirconium (Zr) and / or at least 0.005% Boron (B). The inventive Nickel based superalloy comprises (in wt%): 3.0% -13.0% Cobalt (Co) 11.5%- 13.5% Chromium (Cr), especially 12.0% - 13.0% Chromium (Cr) 1.5% - 2.0% Molybdenum (Mo) 1.7% - 2.7% Tungsten (W) 3.8% - 4.8% Aluminum (Al) especially 4.0% - 4.5% Aluminum (Al) 1.7% - 2.7% Titanium (Ti) 3.8% - 5.5% Niobium (Nb) 0.005% - 0.20% Carbon (C) up to 0.03% Boron (B) up to 0.05% Zirconium (Zr) 0.005% - 0.50% Silicon (Si) up to 2.0% Hafnium (Hf) up to 5.0 wt% Iron (Fe). Especially the rest being Nickel (Ni) and unavoidable impurities. It can be noted that the present invention is free of Rhenium (Re) and / or Ruthenium (Ru) and / or Tantalum (Ta), elements which are commonly used in modem Nickel base superalloys but which, as seen from the density formula, unfortunately significantly increase their densities. It is also low in Tungsten (W) and / or another element which increases the density. CC compositions compared to DS, SX, columnar structured need some Carbon (C), Boron (B) and Zirconium (Zr) wherein Silicon (Si) must be low. Moderate Hafnium (Hf) can be used (in wt%): 3.0- 13.0 Cobalt (Co) 12.0 - 13.5 Chromium (Cr) 1.5 - 2.0 Molybdenum (Mo) 1.7-2.7 Tungsten (W) 4.0-4.8 Aluminum (Al) 1.7 - 2.7 Titanium (Ti) 4.3 - 5.3 Niobium (Nb), 0.04-0.15 Carbon (C), 0.005 - 0.03 Boron (B) 0.005 - 0.05 Zirconium (Zr) 0.005 - 0.02 Silicon (Si) up to 0.7 Hafnium (Hf) or even more preferred (in wt%): Ni - 5Co - 12.5Cr - 1.8Mo - (2.2-2.4)W - 4.4A1 - (2.0-2.4)Ti - 4.9Nb - 0.07C - 0.01 Si -0.01 Zr. An embodiment LD1CC with a composition, in wt%, given by Ni-5Co-12.5Cr-l.8Mo-2.2W-4.4Al-2.0Ti-4.9Nb-0.07C-0.015B-0.01Zr-0.01Si has a density' of 7.98 kg / dm3, a gamma prime particle content of 56.3 mol%. All carbides are, consistent with our assumption of TaC for IN792, assumed to be NbC which is regarded as an equally strong MC former, and, present at a higher level in at% in LD1CC than Tantalum (Ta) is in IN792. The gamma prime particle content, the lattice parameters are similar to those of IN792, however and, very usefully, the density is significantly lower and the gamma prime content significantly higher. An embodiment LD2CC with a composition, in wt%, is given by Ni-5Co-12.5Cr-l.8Mo-2.4W-4.4Al-2.4Ti-4.9Nb-0.07C-0.015B-0.01Zr-0.01Si. SX compositions may have a lover amount of Niobium (Nb), Silicon (Si) can be much higher than in CC or DS compositions, low content of carbon (C) and almost no Zirconium (Zr) and Boron (B), possible, if needed moderate amount of Hafnium (Hf): (in wt%) 3.0-13.0 Cobalt (Co) 12.0 - 13.5 Chromium (Cr) 1.5 - 2.0 Molybdenum (Mo) 1.7 - 2.7 Tungsten (W) 3.8-4.8 Aluminum (Al) 1.7 - 2.7 Titanium (Ti) 4.1 -4.8 Niobium (Nb) 0.005 - 0.035 Carbon (C) 0.04 - 0.50 Silicon (Si) up to 0.7 Hafnium (Hf) or more preferred: (in wt%) Ni- 5Co - 12.5Cr - 1 8Mo - (2.2-2.4)W - (4.1 -4.4)A1 - (2.0-2.4)Ti - 4.4Nb -0.015C - (0.05 - 0.25)Si. The embodiment LD1SX, an SX version of LD1CC with a composition, in wt%, given by Ni-5Co-12.5Cr-l.8Mo-2.2W-4.4Al-2.0Ti-4.4Nb-0.015C-0.05Si has the same density, gamma prime particle content. (Niobium) Nb has been reduced relative to LD1CC to give the same concentrations of Nb in the gamma and gamma prime particles as in LD1CC, consistent with the assumption that the carbides in LD1CC are of the NbC type. The embodiment LD2SX with a composition, in wt%, given by Ni-5Co-12.5Cr-l.8Mo-2.4W-4.4Al-2.4Ti-4.4Nb-0.015C-0.05Si has a density of 8.02kg / dm3, a gamma prime particle content of 55.5 mol%. The carbides are, consistent with our assumption of TaC for IN792, assumed to be NbC. At the typical service temperature of 973K. (700°C), the gamma prime content is about 61.0mol% and there is only 1,4mol% of UP. It should also be noted that despite the high gamma prime content, the Solvus is only 1461K (1188°C) and with a Solidus of 563K (1290°C) this gives a very large HTW of 102K. This is very beneficial for many production processes. A CC alloy LD2CC corresponding to LD2SX can be obtained by increasing the Carbon (C) content to 0.07wt% and the Niobium (Nb) content to 4.9wt%, assuming the so added carbides to be NbC. It s a fact that, IN792 is, with the standard heat treatment involving a HIP / solutioning / homogenization step of 4h at about 1473K (1200°C), less than perfectly solutioned and homogenized, and, tends to retain a small amount of eutectics. This is consistent with the high Titanium (Ti) content in IN792. Hence it should be possible to allow which can be better solutioned and homogenized, and, what is required for this is a large HTW. The embodiment LD3SX with a composition, in wt%, given by Ni-5Co-12.5Cr-l.8Mo-2.4W-4.lAl-2.4Ti-4.4Nb-0.015C-0.25Si has a density of 8.01 kg / dm3, a gamma prime particle content of 58.4mol%. All carbides are, consistent with our assumption of TaC for IN792, assumed to be NbC. At the typical service temperature of 973K (700°C), the gamma prime content is about 63.3mol% and there is only 3.4mol% of UP. In our experience, this is not a high predicted UP value, alloys with this level of predicted UP tend to be stable in service if they can be well solutioned and homogenized.. It should also be noted that despite the high gamma prime content, the Solvus is only 1468K (1195°C), and, with a Solidus of 1556K (1283°C) this gives a large HTW of 88K. A CC alloy LD3CC corresponding to LD3SX can be obtained by increasing the Carbon (C) content to 0.07wt% and the Nb content to 4.9wt%, assuming the so added carbides to be NbC. Hafnium (Hf) can be added as required w.r.t. the CC production process requirements, as done today for IN792, in which case one or more of the alloy elements need to be adjusted by those skilled in the art such that e.g., the propensity for UP precipitation does not increase. Iron can be added to reduce the Solvus to well below 1473K (1200°C). This could e.g., ensure that Hot Isostatic Pressing (HIP) can be done at 1473K (1200"C), which is a standard temperature in commercial HIP furnaces and enables a wider range of vendors than if higher HIP temperatures were required, result in good gamma prime solutioning and homogenization. In addition, the levels of the grain boundary strengthening elements Carbon (C), Zirconium (Z) and Boron (B) can be adjusted by those skilled in the art as necessary to achieve a high casting and processing yield while the grain boundary strength is kept high. DS (columnar grained) compositions need some Carbon (C), Boron (B) and Zirconium (Zr). Hafnium is needed in higher amounts, wherein Silicon should be kept low (in wt%): 3.0-13.0 Cobalt (Co) 12.0 - 13.5 Chromium (Cr) 1.5 - 2.0 Molybdenum (Mo) 1.7-2.7 Tungsten (W) 4.0-4.8 Aluminum (Al) 1.7 - 2.7 Titanium (Ti) 3.8-4.4 Niobium (Nb), 0.04-0.15 Carbon (C), 0.005 - 0.03 Boron (B) 0.005 - 0.05 Zirconium (Zr) 0.005 - 0.02 Silicon (Si) 1.2 - 2.0 Hafnium (Hf) or even more preferred (in wt%): 5.0 Cobalt (Co) 12.5 Chromium (Cr) 1.8 Molybdenum (Mo) 2.0 Tungsten (W) 4.4 Aluminum (Al) 2.0 Titanium (Ti) 4.1 Niobium (Nb), 0.07 Carbon (C), 0.015 Boron (B) 0.01 Zirconium (Zr) 0.01 Silicon (Si) 1.4 Hafnium (Hf). Furthermore, for DS (columnar grains) casting, it is customary to add high levels of Hf. The embodiment LD1DS with a composition, in wt%, given by Ni-5Co-12.5Cr-l.8Mo-2.0W-4.4Al-2.0Ti-4.lNb-l.4Hf-0.07C-0.01Si-0.01Zr-0.015B has a density' of 8.04kg / dm3, a gamma prime particle content of 56.8mol%. All carbides are now assumed to be HfC. It should also be added that other high creep strength alloys used for later stage blades have at least as high densities as IN792. CM247CC is at 8.5kg / dm3. Further advantageous composition are given by 1. Ni-7Co-12Cr-1.9Mo-2.5W-4.2AI-2.3Ti-5Nb-0.08C-0.02B-0.04Zr-0.02Si-0.5Hf 2. Ni-4Co-12.7Cr-1.6Mo-2.6W-4AI-1.9Ti-5.2Nb-0.1C-0.01B-0.03Zr-0.015Si-1Hf 3. Ni-6Co-11.7Cr-1.7Mo-2.1W-4.5Ai-2.2Ti-4.6Nb-0.02C-0.02B-0.02Zr-0.02Si-1.5Hf 4. Ni-8Co-13Cr-1.8Mo-2.3W-4.3AI-2.5Ti-4.8Nb-0.05C-0.025B-0.015Zr-0.01Si-0.7Hf 5. Ni-10Co-12.2Cr-1.5Mo-2.8W-4.6AI-2Ti-4.9Nb-0.03C-0.015B-0.01Zr-0.02Si-1.2Hf 6. Ni-9Co-12.9Cr-1.6Mo-2.2W-4.8Ai-2.4Ti-5Nb-0.1C-0.C15B-0.025Zr-0.02Si-0.8Hf 7. Ni-11Co-12.5Cr-1.7Mo-2.6W-4.4AI-2.1Ti-4.7Nb-0.08C-0.02B-0.03Zr-0.02Si-1.8Hf 8. Ni-12Co-13.2Cr-1.8Mo-2.5W-4.5AI-2.2Ti-5.3Nb-0.07C-0.015B-0.04Zr-0.01Si-1.4Hf 9. Ni-13Co-12.8Cr-1.9Mo-2.7W-4.6AI-2.3Ti-4.8Nb-0.1C-0.025B-0.02Zr-0.02Si-1.6Hf 10. Ni-10Co-12.3Cr-1.5MO-2.4W-4.7AI-2.5Ti-5.1Nb-0.09C-0.015B-0.03Zr-0.02Si-1.7Hf 11. Ni-11Co-13Cr-2Mo-2.6W-4.8AI-2.4Ti-46Nb-0.07C-0.01B-0.025Zr-0.015Si-1.9Hf 12. Ni-12Co-12.6Cr-1.6Mo-2.8W-4.6AI-2.2Ti-4.9Nb-0.08C-0.015B-0.04Zr-0.02Si-1.5Hf 5 13. Ni-8Co-12.4Cr-1.7Mo-2.3W-4.2Ai-2.3Ti-4.5Nb-0.09C-0.028-0.03Zr-0.015Si-1.8Hf 14. Ni-9Co-11.8Cr-1.6Mo-2.5W-4.1Ai-2.4Ti-4.7Nb-0.04C-0.02B-0.02Zr-0.01Si-0.9Hf 15. Ni-10Co-12.6Cr-1.9Mo-2.7W-4.3AI-2.1Ti-5.4Nb-0.06C-0.015B-0.04Zr-0.02Si-1.7Hf

Claims

1. Nickel based superalloy, comprising (in wt%) 3.0-13.0 Cobalt (Co) 11.5% - 13.5% Chromium (Cr), especially 12.0% - 13.0% Chromium (Cr) 1.5% - 2.0% Molybdenum (Mo) 1.7% - 2.7% Tungsten (W) 3.8% - 4.8% Aluminum (Al) especially 4.0% - 4.5% Aluminum (Al) 1.7-2.7 Titanium (Ti) 3.8 - 5.5 Niobium (Nb), 0.005 - 0.20 Carbon (C), up to 0.03 Boron (B) up to 0.05 Zirconium (Zr) 0.005 - 0.50 Silicon (Si) up to 2.0 Hafnium (Hf) up to 5.0 Iron (Fe) especially the rest being Nickel (Ni) and unavoidable impurities.

2. Nickel based superalloy according to claim 1, comprising (in wt%) 3.0 - 13.0 Cobalt (Co) 12.0 - 13.5 Chromium (Cr) 1.5 - 2.0 Molybdenum (Mo) 1.7 - 2.7 Tungsten (W) 3.8-4.8 Aluminum (Al) 1.7 - 2.7 Titanium (Ti) 4.1 -4.8 Niobium (Nb) 0.005 - 0.035 Carbon (C) 0.04 - 0.50 Silicon (Si) up to 0.7 Hafnium (Hf).

3. Nickel based superalloy according to claim 1 or 2, comprising (in wt%)Ni- 5Co - 12.5Cr - 1.8Mo - (2.2-2.4)W - (4.1-4.4)A1 - (2.0-2.4)Ti - 4.4Nb -0.015C - (0.05 - 0.25)Si.

4. Nickel base superalloy according to claim 2 or 3, comprising (in wt%)5.0 Cobalt (Co)12.5 Chromium (Cr)1.8 Molybdenum (Mo)2.2 Tungsten (W)4.4 Aluminum (Al)2.0 Titanium (Ti)4.4 Niobium (Nb)0.015 Carbon (C)0.05 Silicon (Si).

5. Nickel based superalloy according to claim 2 or 3, comprising (in wt%)5.0 Cobalt (Co)12.5 Chromium (Cr)1.8 Molybdenum (Mo)2.4 Tungsten (W)4.4 Aluminum (Al)2.4 Titanium (Ti)4.4 Niobium (Nb)0.015 Carbon (C)0.05 Silicon (Si).

6. Nickel based superalloy according to claim 2 or 3, comprising (in wt%)5.0 Cobalt (Co)12.5 Chromium (Cr)1.8 Molybdenum (Mo)2.4 Tungsten (W)4.1 Aluminum (Al)2.4 Titanium (Ti)4.4 Niobium (Nb) 0.015 Carbon (C) 0.25 Silicon (Si).

7. Nickel based superalloy according to any of the claims 1 to 6, to which between 0.005wt% and 0.015wt% Boron (B) has been added to increase the tolerance for low angle boundary formation during SX casting.

8. Nickel based superalloy according to claim 1, comprising (in wt%) 3.0-13.0 Cobalt (Co)12.0 - 13.5 Chromium (Cr)1.5 - 2.0 Molybdenum (Mo)1.7-2.7 Tungsten (W)4.0 - 4.8 Aluminum (Al)1.7 - 2.7 Titanium (Ti)3.8-4.4 Niobium (Nb), 0.04 - 0.15 Carbon (C), 0.005 - 0.03 Boron (B) 0.005 - 0.05 Zirconium (Zr) 0.005 - 0.02 Silicon (Si) 1.2-2.0 Hafnium (Hf).

9. Nickel based superalloy according to claim 8, comprising (in wt%)5.0 Cobalt (Co)12.5 Chromium (Cr)1.8 Molybdenum (Mo)2.0 Tungsten (W)4.4 Aluminum (Al)2.0 Titanium (Ti)4.1 Niobium (Nb),0.07 Carbon (C),0.015 Boron (B)0.01 Zirconium (Zr)0.01 Silicon (Si)1.4 Hafnium (Hf).

10. Nickel based superalloy according to claim 1, comprising (in wt%)3.0-13.0 Cobalt (Co)12.0 - 13.5 Chromium (Cr)1.5 - 2.0 Molybdenum (Mo)1.7 - 2.7 Tungsten (W)4.0 - 4.8 Aluminum (Al)1.7-2.7 Titanium (Ti)4.3 - 5.3 Niobium (Nb),0.04-0.15 Carbon (C),0.005 - 0.03 Boron (B)0.005 - 0.05 Zirconium (Zr)0.005 - 0.02 Silicon (Si)up to 0.7 Hafnium (Hf).

11. Nickel based superalloy according to claim 10, comprising (in wt%)Ni - 5Co - 12.5Cr - 1.8Mo - (2.2-2.4)W - 4.4A1 - (2.0-2.4)Ti - 4.9Nb - 0.07C -O.OlSi - 0.01 Zr.

12. Nickel based superalloy according to claim 10 or 11, comprising (in wt%)5.0 Cobalt (Co)12.5 Chromium (Cr)1.8 Molybdenum (Mo)2.2 Tungsten (W)4.4 Aluminum (Al)2.0 Titanium (Ti)4.9 Niobium (Nb),0.07 Carbon (C),0.015 Boron (B)0.01 Zirconium (Zr)0.01 Silicon (Si).

13. Nickel based superalloy according to claim 10 or 11, comprising (in wt%)5.0 Cobalt (Co)12.5 Chromium (Cr)1.8 Molybdenum (Mo)2.4 Tungsten (W)4.4 Aluminum (Al)2.4 Titanium (Ti)4.9 Niobium (Nb),0.07 Carbon (C),0.015 Boron (B)0.01 Zirconium (Zr)0.01 Silicon (Si).

14. Nickel based superalloy according to any of the preceding claims, comprising no Rhenium (Re) and / orno Ruthenium (Ru) and / orno Tantalum (Ta).

15. Nickel base superalloy according to any of the claims 11 to 14, especially according to any of the claims 1 to 7, to which between 0.1 and 5.0 wt% Iron (Fe) are added.

16. Nickel based superalloy according to any of the preceding claims 1 to 14, comprising no Iron (Fe).

17. Component for a gas turbine, especially a blade or vane, made of an alloy according to any of the preceding claims.

18. Component according to claim 17, having an equiaxed microstructure (CC), with an alloy according to any claims 10 to 13,especially having amounts of Zirconium (Zr) and / or Boron (B) in the alloy, especially at least 50% higher than impurity level, orhaving an directionally solidified microstructure,5 especially a SX with an alloy according to any claims 2 to 7 orhaving columnar structure with an alloy according to any claims 8 or 9by having as low as possible amounts of Zirconium (Zr) and / or Boron (B) in the alloy.10 19. Method to produce a component according to claim 17 or 18,using conventional casting (CC), directional solidification (DS) casting, single crystal (SX) castingoradditive manufacturing processes such as15 laser powder bed fusion, selective electron beam processes or liquid metal deposition processes.16