EP2855724B1 - Nickel-chromium alloy with good formability, creep strength and corrosion resistance - Google Patents

Description

The invention relates to a nickel-chromium alloy with good high-temperature corrosion resistance, good creep resistance and improved processability.

Nickel alloys with different nickel, chromium and aluminum contents have long been used in furnace construction and in the chemical and petrochemical industries. For this application, a good high-temperature corrosion resistance is required even in carburizing atmospheres and a good heat resistance / creep resistance.

In general, it should be noted that the high temperature corrosion resistance of the alloys listed in Table 1 increases with increasing chromium content. All these alloys form a chromium oxide layer (Cr ₂ O ₃ ) with an underlying, more or less closed, Al ₂ O ₃ layer. Small additions of strongly oxygen-affinitive elements such. B. Y or Ce improve the oxidation resistance. The content of chromium is slowly consumed in the course of use in the application area for the formation of the protective layer. Therefore, a higher chromium content increases the life of the material, because a higher content of the protective layer-forming element chromium retards the time at which the Cr content is below the critical limit and forms oxides other than Cr ₂ O ₃ , eg ferrous and nickel containing oxides are. Further enhancement of high temperature corrosion resistance could be achieved by additions of aluminum and silicon, if required. From a certain minimum content, these elements form a closed layer below the chromium oxide layer and thus reduce the consumption of chromium.

In carburizing atmospheres (CO, H ₂ , CH ₄ , CO ₂ , H ₂ O mixtures), carbon can penetrate the material, causing it to form internal carbides can come. These cause a loss of notched impact strength. Also, the melting point can drop to very low levels (up to 350 ° C) and chromium depletion can occur in the matrix.

High resistance to carburization is achieved by materials with low solubility for carbon and low diffusion rate of carbon. Nickel alloys are therefore generally more resistant to carburization than iron-base alloys because both carbon diffusion and carbon solubility in nickel are lower than in iron. An increase in chromium content results in a higher carburization resistance by forming a protective chromium oxide layer, unless the oxygen partial pressure in the gas is insufficient to form this protective chromium oxide layer. At very low oxygen partial pressures, materials can be used which form a layer of silicon oxide or the even more stable alumina, both of which can form protective oxide layers even at significantly lower oxygen contents.

In the case that the carbon activity is> 1, so-called "metal dusting" can occur with nickel-, iron- or cobalt-base alloys. In contact with the supersaturated gas, the alloys can absorb large amounts of carbon. The segregation processes occurring in the carbon-supersaturated alloy lead to material destruction. The alloy decomposes into a mixture of metal particles, graphite, carbides and / or oxides. This type of material destruction occurs in the temperature range of 500 ° C to 750 ° C.

Typical conditions for the occurrence of metal dusting are strongly carburizing CO, H ₂ or CH ₄ gas mixtures, as they occur in ammonia synthesis, in methanol plants, in metallurgical processes, but also in hardening furnaces.

The resistance to metal dusting tends to increase with increasing nickel content of the alloy ( Grabke, HJ, Krajak, R., Müller-Lorenz, EM, Strauss, S .: Materials and Corrosion 47 (1996), p. 495 ), however, nickel alloys are not generally resistant to metal dusting.

The chromium and aluminum content has a significant influence on the corrosion resistance under metal dusting conditions (see Figure 1). Low chromium nickel alloys (such as alloy Alloy 600, see Table 1) show comparatively high corrosion rates under metal dusting conditions. The nickel alloy Alloy 602 CA (N06025) with a chromium content of 25% and an aluminum content of 2.3% as well as Alloy 690 (N06690) with a chromium content of 30% is significantly more resistant ( Hermse, CGM and van Wortel, JC: Metal dusting: relationship between alloy composition and degradation rate. Corrosion Engineering, Science and Technology 44 (2009), p. 182 - 185 ). Resistance to metal dusting increases with the sum Cr + Al.

The heat resistance or creep resistance at the specified temperatures is u. a. improved by a high carbon content. But even high contents of solid solution strengthening elements such as chromium, aluminum, silicon, molybdenum and tungsten improve the heat resistance. In the range of 500 ° C to 900 ° C, additions of aluminum, titanium and / or niobium can improve strength by precipitating the y 'and / or γ "phase.

Examples of the prior art are listed in Table 1.

Alloys such as Alloy 602 CA (N06025), Alloy 693 (N06693) or Alloy 603 (N06603) are superior in their corrosion resistance compared to Alloy 600 (N06600) or Alloy 601 (N06601) due to the high aluminum content of more than 1.8 % known. Alloy 602 CA (N06025), Alloy 693 (N06693), Alloy 603 (N06603), and Alloy 690 (N06690) show excellent carburization resistance or metal dusting resistance due to their high chromium and / or aluminum content. At the same time, alloys such as Alloy 602 CA (N06025), Alloy 693 (N06693) or Alloy 603 are shown (N06603) due to the high carbon and aluminum content excellent heat resistance and creep resistance in the temperature range in which metal dusting occurs. Alloy 602 CA (N06025) and Alloy 603 (N06603) have excellent heat resistance and creep resistance even at temperatures above 1000 ° C. However, z. For example, the high aluminum content impairs processability, the higher the aluminum content (Alloy 693 - N06693). The same applies to an increased degree for silicon, which forms low-melting intermetallic phases with nickel. In Alloy 602 CA (N06025) or Alloy 603 (N06603) in particular the cold workability is limited by a high proportion of primary carbides.

The US 6623869 B1 discloses a metallic material consisting of ≤ 0.2% C, 0.01-4% Si, 0.05-2.0% Mn, ≤ 0.04% P, ≤ 0.015% S, 10-35% Cr, 30 - 78% Ni, 0.005 - 4.5% Al, 0.005 - 0.2% N, and at least one element 0.015 - 3% Cu or 0.015 - 3% Co, with the remainder being 100% iron. The value of 40Si + Ni + 5Al + 40N + 10 (Cu + Co) is not less than 50, the symbols of the elements meaning the content of the corresponding elements. The material has excellent corrosion resistance in an environment where metal dusting can take place and therefore can be used for stovepipes, piping systems, heat exchanger tubes and the like. Ä. Used in petroleum refineries or petrochemical plants and can significantly improve the life and safety of the plant.

The EP 0 549 286 discloses a high temperature resistant Ni-Cr alloy including 55-65% Ni, 19-25%, Cr 1-4.5% Al, 0.045-0.3% Y, 0.15-1% Ti, 0.005-0, 5% C, 0.1-1.5% Si, 0-1% Mn and at least 0.005% in total of at least one of the elements of the group containing Mg, Ca, Ce, <0.5% in total Mg + Ca, <1% Ce, 0.0001 - 0.1% B, 0 - 0.5% Zr, 0.0001 - 0.2% N, 0 - 10% Co, 0 - 0.5% Cu, 0 - 0 , 5% Mo, 0 - 0.3% Nb, 0 - 0.1% V, 0 - 0.1% W, balance iron and impurities.

in the Datasheet INCONEL alloy 690, October 9, 2009 (2009-10-09), pages 1 to 8 , XP 055085643 of the company Special Metals Corp. the well-known alloy alloy 690 (N 06690) is described.

• eine gute Phasenstabilität
• eine gute Verarbeitbarkeit
• eine gute Korrosionsbeständigkeit an Luft, ähnlich der von Alloy 601 bzw Alloy 690

aufweist.The object underlying the invention is to design a nickel-chromium alloy that exceeds the metal dusting resistance of Alloy 690, so that an excellent metal dusting resistance is ensured, but at the same time

• a good phase stability
• a good processability
• a good corrosion resistance in air, similar to that of Alloy 601 or Alloy 690

having.

• eine gute Warmfestigkeit / Kriechfestigkeit
  hat.

Furthermore, it would be desirable if this alloy additionally

• a good heat resistance / creep resistance
  Has.

und $$\mathrm{Fp}\le 39,9\mathrm{mit}$$

$$\mathrm{Fp}=\mathrm{Cr}+\mathrm{0},\mathrm{272}*\mathrm{Fe}+\mathrm{2},\mathrm{36}*\mathrm{Al}+\mathrm{2},\mathrm{22}*\mathrm{Si}+\mathrm{2},\mathrm{48}*\mathrm{Ti}+\mathrm{1},\mathrm{26}*\mathrm{Nb}+\mathrm{0},\mathrm{374}*\mathrm{Mo}+\mathrm{0},\mathrm{538}*\mathrm{W}-\mathrm{11},\mathrm{8}*\mathrm{C}$$

wobei Cr, Fe, Al, Si, Ti, Nb, C, W und Mo die Konzentration der betreffenden Elemente in Masse-% sind.This object is achieved by a nickel-chromium alloy, with (in wt .-%) 29 to 37% chromium, 0.001 to 1.8% aluminum, 0.10 to 7.0% iron, 0.001 to 0.50% Silicon, 0.005 to 2.0% manganese, 0.00 to 1.00% titanium and / or 0.00 to 1.10% niobium, 0.0002 to 0.05% magnesium and / or calcium, 0.005 to 0, respectively , 12% carbon, 0.001-0.050% nitrogen, 0.001-0.030% phosphorus, 0.0001-0.020% oxygen, max. 0.010% sulfur, max. 2.0% molybdenum, max. 2.0% tungsten, further containing, if necessary, Y with a content of 0.01-0.20%, La with a content of 0.01-0.20%, cerium with a content of 0.001-0.20%, Cerium misch metal with a content of 0.001 to 0.20%, Zr with a content of 0.01-0.20%, where Zr can be wholly or partly substituted by 0.001 to 0.20% Hf, B containing 0.0001 - 0.008%, Co 0.0 to 5.0%, Cu max. 0.5%, V max. 0.5%, balance nickel and the usual process-related impurities, with the following relationships have to be: $$\mathrm{Cr}+\mathrm{al}>30$$

and $$\mathrm{fp}\le 39.9\mathrm{With}$$

$$\mathrm{fp}=\mathrm{Cr}+\mathrm{0}.\mathrm{272}*\mathrm{Fe}+\mathrm{2}.\mathrm{36}*\mathrm{al}+\mathrm{2}.\mathrm{22}*\mathrm{Si}+\mathrm{2}.\mathrm{48}*\mathrm{Ti}+\mathrm{1}.\mathrm{26}*\mathrm{Nb}+\mathrm{0}.\mathrm{374}*\mathrm{Not\; a\; word}+\mathrm{0}.\mathrm{538}*\mathrm{W}-\mathrm{11}.\mathrm{8th}*\mathrm{C}$$

wherein Cr, Fe, Al, Si, Ti, Nb, C, W and Mo are the concentration of the respective elements in mass%.

Advantageous developments of the subject invention can be found in the associated dependent claims.

• 30 bis 37 %
• 31 bis 37 %
• 31 bis 36 %
• 32 bis 35 %
• 32 bis 36 %
• > 32 bis 37 %

The spreading range for the element chromium is between 29 and 37%, whereby preferred ranges can be set as follows:

• 30 to 37%
• 31 to 37%
• 31 to 36%
• 32 to 35%
• 32 to 36%
• > 32 to 37%

• 0,001 bis 1,4 %
• 0,001 bis 1,3 %
• 0,001 bis < 1,0 %
• 0,001 bis 0,60 %
• 0,01 bis 0,60 %
• 0,10 bis 0,60 %
• 0,20 bis 0,60 %

The aluminum content is between 0.001 and 1.8%, whereby here too, depending on the area of use of the alloy, preferred aluminum contents can be set as follows:

• 0.001 to 1.4%
• 0.001 to 1.3%
• 0.001 to <1.0%
• 0.001 to 0.60%
• 0.01 to 0.60%
• 0.10 to 0.60%
• 0.20 to 0.60%

• 0,1 - 4,0 %
• 0,1 - 3,0 %
• 0,1 - < 2,5 %
• 0,1 - 2,0 %
• 0,1 - 1,0 %

The iron content is between 0.1 and 7.0%, whereby, depending on the field of application, defined contents can be set within the following spreading ranges:

• 0.1 - 4.0%
• 0.1 - 3.0%
• 0.1 - <2.5%
• 0.1 - 2.0%
• 0.1 - 1.0%

• 0,001 - 0,20 %
• 0,001 - <0,10 %
• 0,001 - <0,05 %
• 0,01 - <0,20 %

The silicon content is between 0.001 and 0.50%. Preferably, Si within the spreading range can be set in the alloy as follows:

• 0.001 - 0.20%
• 0.001 - <0.10%
• 0.001 - <0.05%
• 0.01 - <0.20%

• 0,005 - 0,50 %
• 0,005 - 0,20 %
• 0,005 - 0,10 %
• 0,005 - <0,05 %
• 0,01 - <0,20 %

The same applies to the element manganese, which may be contained in the alloy with 0.005 to 2.0%. Alternatively, the following spread range is conceivable:

• 0.005 - 0.50%
• 0.005 - 0.20%
• 0.005 - 0.10%
• 0.005 - <0.05%
• 0.01 - <0.20%

• 0,001 - <1,00 %
• 0,001 - 0,60 %
• 0,001 - 0,50 %
• 0,01 - 0,50 %
• 0,10-0,50%
• 0,10 - 0,40 %

The titanium content is between 0.00 and 1.0%. Preferably, Ti within the spreading range can be adjusted in the alloy as follows:

• 0.001 - <1.00%
• 0.001 - 0.60%
• 0.001 - 0.50%
• 0.01 - 0.50%
• 0.10-0.50%
• 0.10 - 0.40%

• 0,001 - 1,0 %
• 0,001 - < 0,70 %
• 0,001 - < 0,50 %
• 0,001 - 0,30 %
• 0,01 - 0,30 %
• 0,10 - 1,10 %.
• 0,20 - 0,80 %.
• 0,20 - 0,50 %.
• 0,25 - 0,45 %.

The Nb content is between 0.00 to 1.1%. Preferably, Nb within the spreading range can be adjusted in the alloy as follows:

• 0.001 - 1.0%
• 0.001 - <0.70%
• 0.001 - <0.50%
• 0.001 - 0.30%
• 0.01 - 0.30%
• 0.10 - 1.10%.
• 0.20 - 0.80%.
• 0.20 - 0.50%.
• 0.25-0.45%.

• 0,0002 - 0,03 %
• 0,0002 - 0,02 %
• 0,0005 - 0,02 %.
• 0,001 - 0,02 %.

Also magnesium and / or calcium is contained in contents of 0.0002 to 0.05%. It is preferably possible to adjust these elements in the alloy as follows:

• 0.0002 - 0.03%
• 0.0002 - 0.02%
• 0.0005 - 0.02%.
• 0.001-0.02%.

• 0,01 - 0,12 %
• 0,02 - 0,12 %
• 0,03 - 0,12 %
• 0,05 - 0,12 %
• 0,05-0,10%

The alloy contains 0.005 to 0.12% carbon. Preferably, this can be adjusted within the spreading range in the alloy as follows:

• 0.01 - 0.12%
• 0.02 - 0.12%
• 0.03 - 0.12%
• 0.05 - 0.12%
• 0.05-0.10%

• 0,003 - 0,04 %

This applies equally to the element nitrogen, which is contained in contents between 0.001 and 0.05%. Preferred contents can be given as follows:

• 0.003 - 0.04%

• 0,001 - 0,020 %

The alloy further contains phosphorus at levels between 0.001 and 0.030%. Preferred contents can be given as follows:

• 0.001-0.020%

The alloy further contains oxygen in amounts between 0.0001 and 0.020%, in particular 0.0001 to 0.010%.

• max. 0,010%

The element sulfur is given in the alloy as follows:

• Max. 0.010%

• Mo max. 1,0 %
• W max. 1,0%
• Mo max. < 0,50 %
• W max. <0,50 %
• Mo max. < 0,05 %
• W max. < 0,05 %

Molybdenum and tungsten are contained singly or in combination in the alloy each containing not more than 2.0%. Preferred contents can be given as follows:

• Mo max. 1.0%
• W max. 1.0%
• Mo max. <0.50%
• W max. <0.50%
• Mo max. <0.05%
• W max. <0.05%

wobei Cr und Al die Konzentration der betreffenden Elemente in Masse-% sind.The following relationship between Cr and Al must be satisfied in order to provide sufficient resistance to metal dusting: $$\mathrm{Cr}+\mathrm{al}>30$$

where Cr and Al are the concentration of the respective elements in mass%.

Preferred areas can be set with $$\mathrm{Cr}+\mathrm{al}\ge 31$$

$$\mathrm{Fp}=\mathrm{Cr}+\mathrm{0},\mathrm{272}*\mathrm{Fe}+\mathrm{2},\mathrm{36}*\mathrm{Al}+\mathrm{2},\mathrm{22}*\mathrm{Si}+\mathrm{2},\mathrm{48}*\mathrm{Ti}+\mathrm{1},\mathrm{26}*\mathrm{Nb}+\mathrm{0},\mathrm{374}*\mathrm{Mo}+\mathrm{0},\mathrm{538}*\mathrm{W}-\mathrm{11},\mathrm{8}*\mathrm{C}$$

wobei Cr, Fe, Al, Si, Ti, Nb, Mo, W und C die Konzentration der betreffenden Elemente in Masse-% sind.In addition, the following relationship must be satisfied for sufficient phase stability: $$\mathrm{fp}\le 39.9\mathrm{With}$$

$$\mathrm{fp}=\mathrm{Cr}+\mathrm{0}.\mathrm{272}*\mathrm{Fe}+\mathrm{2}.\mathrm{36}*\mathrm{al}+\mathrm{2}.\mathrm{22}*\mathrm{Si}+\mathrm{2}.\mathrm{48}*\mathrm{Ti}+\mathrm{1}.\mathrm{26}*\mathrm{Nb}+\mathrm{0}.\mathrm{374}*\mathrm{Not\; a\; word}+\mathrm{0}.\mathrm{538}*\mathrm{W}-\mathrm{11}.\mathrm{8th}*\mathrm{C}$$

wherein Cr, Fe, Al, Si, Ti, Nb, Mo, W and C are the concentration of the respective elements in mass%.

$$\mathrm{Fp}\le 36,6$$

Preferred ranges can be set with: $$\mathrm{fp}\le 38.4$$

$$\mathrm{fp}\le 36.6$$

• 0, 01 - 0,15 %
• 0,01-0,10%
• 0,01 - 0,08%
• 0,01 - 0,05%
• 0,01 - <0,045 %

Optionally, in the alloy, the element yttrium may be adjusted in amounts of 0.01 to 0.20%. Preferably, Y within the spreading range can be set in the alloy as follows:

• 0, 01 - 0.15%
• 0.01-0.10%
• 0.01 - 0.08%
• 0.01 - 0.05%
• 0.01 - <0.045%

• 0,001 - 0,15 %
• 0,001-0,10%
• 0,001 - 0,08 %
• 0,001 - 0,05 %
• 0,01 - 0,05 %

Optionally, in the alloy, the element lanthanum may be adjusted in amounts of 0.001 to 0.20%. Preferably, within the spreading range, La can be set in the alloy as follows:

• 0.001 - 0.15%
• 0.001-0.10%
• 0.001-0.08%
• 0.001 - 0.05%
• 0.01 - 0.05%

• 0,001 - 0,15 %
• 0,001 - 0,10 %
• 0,001 - 0,08 %
• 0,001 - 0,05 %
• 0,01 - 0,05 %

Optionally, in the alloy, the element Ce may be adjusted in amounts of 0.001 to 0.20%. Preferably, Ce within the spreading range can be adjusted in the alloy as follows:

• 0.001 - 0.15%
• 0.001 - 0.10%
• 0.001-0.08%
• 0.001 - 0.05%
• 0.01 - 0.05%

• 0, 001 - 0,15 %
• 0,001-0,10%
• 0,001 - 0,08 %
• 0,001 - 0,05 %
• 0,01 - 0,05 %

Optionally, with simultaneous addition of Ce and La, cerium mischmetal may also be used in amounts of from 0.001 to 0.20%. Preferably, cerium misch metal within the spreading range can be adjusted in the alloy as follows:

• 0, 001 - 0.15%
• 0.001-0.10%
• 0.001-0.08%
• 0.001 - 0.05%
• 0.01 - 0.05%

• 0,01 - 0,15 %
• 0,01 - <0,10 %
• 0,01 - 0,07 %
• 0,01 - 0,05 %

If necessary, the alloy may also be added to Zr. The zirconium content is between 0.01 and 0.20%. Preferably Zr can be adjusted within the spreading range in the alloy as follows:

• 0.01 - 0.15%
• 0.01 - <0.10%
• 0.01 - 0.07%
• 0.01 - 0.05%

• 0,001 - 0,2 % Hafnium.

Optionally, zirconium can also be replaced in whole or in part by

• 0.001-0.2% hafnium.

Optionally, the alloy may also contain from 0.001 to 0.60% tantalum

• 0,0001 - 0,008 %

Optionally, the element boron may be included in the alloy as follows:

• 0.0001 - 0.008%

• 0,0005 - 0,008 %
• 0,0005 - 0,004 %

Preferred contents of boron can be given as follows:

• 0.0005 - 0.008%
• 0.0005 - 0.004%

• 0,01 bis 5,0 %
• 0,01 bis 2,0 %
• 0,1 bis 2,0 %
• 0,01 bis 0,5 %

Further, the alloy may contain, as needed, between 0.00 to 5.0% cobalt, which may be further limited as follows:

• 0.01 to 5.0%
• 0.01 to 2.0%
• 0.1 to 2.0%
• 0.01 to 0.5%

Furthermore, a maximum of 0.5% Cu may be included in the alloy as needed.

• max. <0,05 %
• max. <0,015 %

The content of copper may be further limited as follows:

• Max. <0.05%
• Max. <0.015%

wobei Cr, Fe, Al, Si, Ti, Nb, Cu, Mo, W und C die Konzentration des betreffenden Elements in Masse % sind.If Cu is contained in the alloy, formula 4a must be supplemented by a term with Cu as follows: $$\mathrm{fp}=\mathrm{Cr}+\mathrm{0}.\mathrm{272}*\mathrm{Fe}+\mathrm{2}.\mathrm{36}*\mathrm{al}+\mathrm{2}.\mathrm{22}*\mathrm{Si}+\mathrm{2}.\mathrm{48}*\mathrm{Ti}+\mathrm{1}.\mathrm{26}*\mathrm{Nb}+\mathrm{0}.\mathrm{477}*\mathrm{Cu}+0.374*\mathrm{Not\; a\; word}+\mathrm{0}.\mathrm{538}*\mathrm{W}-\mathrm{11}.\mathrm{8th}*\mathrm{C}$$

wherein Cr, Fe, Al, Si, Ti, Nb, Cu, Mo, W and C are the concentration of the respective element in mass%.

Further, in the alloy, if necessary, at most 0.5% of vanadium may be contained.

• Pb max. 0,002 %
• Zn max. 0,002 %
• Sn max. 0,002 %

Finally, impurities may still contain the elements lead, zinc and tin in amounts as follows:

• Pb max. 0.002%
• Zn max. 0.002%
• Sn max. 0.002%

$$\mathrm{Fa}=\mathrm{Cr}+\mathrm{6},\mathrm{15}*\mathrm{Nb}+\mathrm{20},\mathrm{4}*\mathrm{Ti}+\mathrm{201}*\mathrm{C}$$

wobei Cr, Ti, Nb und C die Konzentration der betreffenden Elemente in Masse-% sind.Furthermore, the following relationship can be satisfied, which ensures a particularly good processability: $$\mathrm{fa}\le 60\mathrm{With}$$

$$\mathrm{fa}=\mathrm{Cr}+\mathrm{6}.\mathrm{15}*\mathrm{Nb}+\mathrm{20}.\mathrm{4}*\mathrm{Ti}+\mathrm{201}*\mathrm{C}$$

wherein Cr, Ti, Nb and C are the concentration of the respective elements in mass%.

Preferred ranges can be set with: $$\mathrm{fa}\le 54$$

$$\mathrm{Fk}=\mathrm{Cr}+\mathrm{19}*\mathrm{Ti}+\mathrm{34},\mathrm{3}*\mathrm{Nb}+\mathrm{10},\mathrm{2}*\mathrm{Al}+\mathrm{12},\mathrm{5}*\mathrm{Si}+\mathrm{98}*\mathrm{C}$$

wobei Cr, Ti, Nb, Al, Si und C die Konzentration der betreffenden Elemente in Masse-% sind.Furthermore, the following relationship can be satisfied, which describes a particularly good hot strength or creep resistance: $$\mathrm{Fk}\ge 40\mathrm{With}$$

$$\mathrm{Fk}=\mathrm{Cr}+\mathrm{19}*\mathrm{Ti}+\mathrm{34}.\mathrm{3}*\mathrm{Nb}+\mathrm{10}.\mathrm{2}*\mathrm{al}+\mathrm{12}.\mathrm{5}*\mathrm{Si}+\mathrm{98}*\mathrm{C}$$

wherein Cr, Ti, Nb, Al, Si and C are the concentration of the respective elements in mass%.

$$\mathrm{Fk}\ge 49$$

Preferred ranges can be set with: $$\mathrm{Fk}\ge 45$$

$$\mathrm{Fk}\ge 49$$

wobei Cr, Ti, Nb, Al, Si, C und B die Konzentration der betreffenden Elemente in Masse-% sind.If boron is present in the alloy, formula 6a must be supplemented by a term with boron as follows: $$\mathrm{Fk}=\mathrm{Cr}+\mathrm{19}*\mathrm{Ti}+\mathrm{34}.\mathrm{3}*\mathrm{Nb}+\mathrm{10}.\mathrm{2}*\mathrm{al}+\mathrm{12}.\mathrm{5}*\mathrm{Si}+\mathrm{98}*\mathrm{C}+\mathrm{2245}*\mathrm{B}$$

wherein Cr, Ti, Nb, Al, Si, C and B are the concentration of the respective elements in mass%.

The alloy of the invention is preferably melted open, followed by treatment in a VOD or VLF plant. But also a melting and pouring in a vacuum is possible. Thereafter, the alloy is poured in blocks or as a continuous casting. If necessary, the block is then annealed at temperatures between 900 ° C and 1270 ° C for 0.1 h to 70 h. Furthermore, it is possible to remelt the alloy additionally with ESU and / or VAR. Thereafter, the alloy is brought into the desired semifinished product. For this, if necessary, annealed at temperatures between 900 ° C and 1270 ° C for 0.1 h to 70 h, then thermoformed, optionally with intermediate anneals between 900 ° C and 1270 ° C for 0.05 h to 70 h. The surface of the material may optionally (also several times) be removed chemically and / or mechanically in between and / or at the end for cleaning. After the end of the hot forming, if necessary, cold forming with degrees of deformation of up to 98% into the desired semifinished product form, optionally with intermediate annealing between 700 ° C. and 1250 ° C. for 0.1 min to 70 h, if necessary under inert gas, such as. As argon or hydrogen, followed by cooling in air, carried out in the moving annealing atmosphere or in a water bath. Thereafter, a solution annealing in the temperature range of 700 ° C to 1250 ° C for 0.1 min to 70 h, optionally under inert gas, such as. As argon or hydrogen, followed by cooling in air, in the moving annealing atmosphere or in a water bath instead. Possibly. In between and / or after the last annealing chemical and / or mechanical cleaning of the material surface can take place.

The alloy according to the invention can be produced and used well in the product forms strip, sheet metal, rod wire, longitudinally welded tube and seamless tube.

These product forms are produced with an average particle size of 5 μm to 600 μm. The preferred particle size range is between 20 μm and 200 μm.

The alloy according to the invention should preferably be used in areas in which carburizing conditions prevail, such as. As in components, especially pipes, in the petrochemical industry. In addition, it is also suitable for furnace construction.

Accomplished tests:

The occurring phases in equilibrium were calculated for the different alloy variants with the program JMatPro from Thermotech. The database used for the calculations was the TTNI7 nickel base alloy database from Thermotech.

The formability is determined in a tensile test according to DIN EN ISO 6892-1 at room temperature. The yield strength R _p0.2 , the tensile strength R _m and the elongation A are determined until the fracture. The elongation A is determined on the broken sample from the extension of the original measuring section L ₀ : $$\mathrm{A}=\left({\mathrm{L}}_{\mathrm{U}}-{\mathrm{<figure-callout\; id="0"\; label="L"\; filenames="imgf0002.png"\; state="\{\{state\}\}">L</figure-callout>}}_{\mathrm{0}}\right)/{\mathrm{<figure-callout\; id="0"\; label="L"\; filenames="imgf0002.png"\; state="\{\{state\}\}">L</figure-callout>}}_{\mathrm{0}}\mathrm{100}\%=\mathrm{.DELTA.L}/{\mathrm{<figure-callout\; id="0"\; label="L"\; filenames="imgf0002.png"\; state="\{\{state\}\}">L</figure-callout>}}_{\mathrm{0}}\mathrm{100}\%$$

With L _u = measuring length after the break.

• Z. B. ist für A₅ die Messlänge L₀ = 5·d₀ mit d₀ = Anfangsdurchmesser einer Rundprobe.

Depending on the measuring length, the elongation at break is provided with indices:

• For example, for A ₅ the measuring length L ₀ = 5 · d ₀ with d ₀ = initial diameter of a round sample.

The experiments were carried out on round samples with a diameter of 6 mm in the measuring range and a measuring length L ₀ of 30 mm. The sampling took place transversely to the forming direction of the semifinished product. The forming speed was 10 MPa / s at R _p0.2 and 40% / min at R _m 6.7 10 ^-3 .

The amount of elongation A in the tensile test at room temperature can be taken as a measure of the deformability. A good workable material should have an elongation of at least 50%.

The hot strength is determined in a hot tensile test according to DIN EN ISO 6892-2. The yield strength R _p0.2 , the tensile strength R _m and the elongation A up to the break are determined analogously to the tensile test at room temperature (DIN EN ISO 6892-1).

The experiments were carried out on round samples with a diameter of 6 mm in the measuring range and an initial measuring length L ₀ of 30 mm. The sampling took place transversely to the forming direction of the semifinished product. The forming speed at R _{p0.2 was} 8.33 10 ^-5 1 / s (0.5% / min) and at R _{m was} 8.33 10 ^-4 1 / s (5% / min).

The sample is installed at room temperature in a tensile testing machine and heated to a desired temperature without load with a tensile force. After reaching the test temperature, the sample is subjected to no load for one hour (600 ° C) or two hours (700 ° C to 1100 ° C) held for a temperature compensation. Thereafter, the sample is loaded with a tensile force to maintain the desired strain rates, and the test begins.

The creep resistance of a material improves with increasing heat resistance. Therefore, the hot strength is also used to evaluate the creep resistance of the various materials.

The corrosion resistance at higher temperatures was determined in an oxidation test at 1000 ° C in air, the test was interrupted every 96 hours and the mass changes of the samples were determined by the oxidation. The samples were placed in the ceramic crucible in the experiment, so that possibly spalling oxide was collected and by weighing the crucible containing the oxides, the mass of the chipped oxide can be determined. The sum of the mass of the chipped oxide and the mass change of the samples is the gross mass change of the respective sample. The specific mass change is the mass change related to the surface of the samples. These are referred to below as m _net for the specific net mass change, m _gross for the specific gross mass change, m _spall for the specific mass change of the chipped oxides. The experiments were carried out on samples with about 5 mm thickness. 3 samples were removed from each batch, the values given are the mean values of these 3 samples.

Description of the properties

• eine gute Phasenstabilität
• eine gute Verarbeitbarkeit,
• eine gute Korrosionsbeständigkeit an Luft, ähnlich der von Alloy 601 bzw. Alloy 690.

The alloy according to the invention, in addition to excellent metal dusting resistance, should also have the following properties:

• a good phase stability
• a good processability,
• a good corrosion resistance in air, similar to that of Alloy 601 or Alloy 690.

It is still desirable

• a good heat resistance / creep resistance

phase stability

In the system nickel-chromium-aluminum-iron with additions of Ti and / or Nb, depending on the alloy contents different embrittling TCP phases such. As the Laves phases, sigma phases or the μ-phases as well as the embrittling η-phase or ε-phases form. (see eg Ralf Bürgel, Handbuch der Hochtemperaturwerkstofftechnik, 3rd edition, Vieweg Verlag, Wiesbaden, 2006, page 370 - 374 ). The calculation of the equilibrium phase components as a function of the temperature of z. B. N06690, the batch 111389, (see Table 2 typical compositions) show computationally the formation of α-chromium (BCC phase in Figure 2) below 720 ° C (T _{s BCC} ) in large proportions. This phase is formed by the fact that it is analytically very different from the basic material is difficult. However, if the formation temperature T _{s BCC of} this phase is very high, then it may well occur, as z. In " E. Slevolden, JZ Albertsen. U. Fink, "Tjeldbergodden Methanol Plant: Metal Dusting Investigations," Corrosion / 2011, paper no. 11144 (Houston, TX: NACE 2011), p. 15 "is described for a variant of Alloy 693 (US 06693) This phase is brittle and leads to an undesirable embrittlement of the material.

Figure 3 and Figure 4 show the phase diagrams of the Alloy 693 variants (out US 4,882,125 Alloy 3 or Alloy 10 from Table 2. Alloy 3 has a formation temperature T _{s BCC} of 1079 ° C, Alloy 10 of 939 ° C. In " E. Slevolden, JZ Albertsen. U. Fink, Tjeldbergodden Methanol Plant: Metal Dusting Investigations, Corrosion / 2011, paper no. 11144 (Houston, TX: NACE 2011), p. 15 "The exact analysis of the alloy in the presence of α-chromium (BCC) is not described, but it can be assumed that among the examples given in Table 2 for Alloy 693, in the analyzes, the mathematically the highest _{Formation temperatures} T _{s BCC} (such as Alloy 10) can form α-chromium (BCC phase.) In a corrected analysis (with reduced formation temperature T _{s BCC} ) was in " E. Slevolden, JZ Albertsen. U. Fink, Tjeldbergodden Methanol Plant: Metal Dusting Investigations, "Corrosion / 2011, paper no. 11144 (Houston, TX: NACE 2011), p.15 In order to avoid the occurrence of such an embrittling phase, in the case of the alloys according to the invention the formation temperature T _{s BCC} ≦ 939 ° C. - the lowest formation temperature T _{s BCC} under the examples of Alloy 693 in Table 2 (off US 4,882,125 Table 1).

$$\mathrm{Fp}=\mathrm{Cr}+\mathrm{0},\mathrm{272}*\mathrm{Fe}+\mathrm{2},\mathrm{36}*\mathrm{Al}+\mathrm{2},\mathrm{22}*\mathrm{Si}+\mathrm{2},\mathrm{48}*\mathrm{Ti}+\mathrm{1},\mathrm{26}*\mathrm{Nb}+\mathrm{0},\mathrm{374}*\mathrm{Mo}+\mathrm{0},\mathrm{538}*\mathrm{W}-\mathrm{11},\mathrm{8}*\mathrm{C}$$

wobei Cr, Al, Fe, Si, Ti, Nb, Mo, W und C die Konzentration der betreffenden Elemente in Masse-% sind. Tabelle 2 mit den Legierungen nach dem Stand der Technik zeigt, dass Fp für Alloy 8, Alloy 3 und Alloy 2 > 39,9 ist und für Alloy 10 gerade 39,9. Für alle anderen Legierungen mit T_{s BCC} < 939°C ist Fp ≤ 39,9.This is especially the case if the following formula is true: $$\mathrm{fp}\le 39.9\mathrm{With}$$

$$\mathrm{fp}=\mathrm{Cr}+\mathrm{0}.\mathrm{272}*\mathrm{Fe}+\mathrm{2}.\mathrm{36}*\mathrm{al}+\mathrm{2}.\mathrm{22}*\mathrm{Si}+\mathrm{2}.\mathrm{48}*\mathrm{Ti}+\mathrm{1}.\mathrm{26}*\mathrm{Nb}+\mathrm{0}.\mathrm{374}*\mathrm{Not\; a\; word}+\mathrm{0}.\mathrm{538}*\mathrm{W}-\mathrm{11}.\mathrm{8th}*\mathrm{C}$$

wherein Cr, Al, Fe, Si, Ti, Nb, Mo, W and C are the concentration of the respective elements in mass%. Table 2 with the prior art alloys shows that Fp for Alloy 8, Alloy 3 and Alloy 2 is> 39.9 and for Alloy 10 is just 39.9. For all other alloys with T _{s BCC} <939 ° C Fp ≤ 39.9.

workability

By way of example, the formability is considered here for the processability.

An alloy can be hardened by several mechanisms so that it has a high heat resistance or creep resistance. Thus, the alloying of another element, depending on the element, causes a greater or lesser increase in strength (solid solution hardening). Far more effective is an increase in strength through fine particles or precipitates (particle hardening). This can be z. B. by the γ'-phase, resulting in additions of Al and other elements such. B: Ti, to form a nickel alloy or by carbides, which is characterized by adding carbon to a chromium-containing nickel alloy (see, for example, Ralf Bürgel, Handbuch der Hochtemperaturwerkstofftechnik, 3rd edition, Vieweg Verlag, Wiesbaden, 2006, pages 358 - 369 ).

Although the increase in the content of the γ'-phase-forming elements, or the C content, increases the heat resistance, but increasingly affects the ductility, even in the solution-annealed state.

For a material that can be formed very easily, strains A5 in the tensile test at room temperature of ≥ 50%, but at least ≥ 45%, are aimed for.

$$\mathrm{Fa}=\mathrm{Cr}+\mathrm{6},\mathrm{15}*\mathrm{Nb}+\mathrm{20},\mathrm{4}*\mathrm{Ti}+\mathrm{201}*\mathrm{C}$$

wobei Cr, Nb, Ti und C die Konzentration der betreffenden Elemente in Masse-% sind.This is achieved in particular if the following relationship is fulfilled between the carbide-forming elements Cr, Nb, Ti and C: $$\mathrm{fa}\le 60\mathrm{With}$$

$$\mathrm{fa}=\mathrm{Cr}+\mathrm{6}.\mathrm{15}*\mathrm{Nb}+\mathrm{20}.\mathrm{4}*\mathrm{Ti}+\mathrm{201}*\mathrm{C}$$

wherein Cr, Nb, Ti and C are the concentration of the respective elements in mass%.

Temperature strength / creep

The chromium content has been set in the inventive alloy ≥ 29%, preferably ≥ 30% or ≥ 31%. In order to ensure the phase stability at such high chromium contents, the aluminum content of ≦ 1.8%, preferably ≦ 1.4%, has been chosen more in the lower range. However, since the aluminum content contributes significantly to the tensile strength or creep resistance (both by solid solution hardening, as well as by γ'-hardening) has the consequence that the target for the hot strength, or the creep strength, not that of Alloy 602 CA but which were taken from Alloy 601, although much higher values for heat resistance and creep resistance would of course be desirable.

$$\mathrm{800}\mathrm{°C}:{\mathrm{Dehngrenze\; R}}_{\mathrm{p}\mathrm{0},\mathrm{2}}>\mathrm{130}\mathrm{MPA};{\mathrm{Zugfestigkeit\; R}}_{\mathrm{m}}>\mathrm{135}\mathrm{MPA}$$

The aim was that the yield strength or the tensile strength at higher temperatures at least in the range of the values of Alloy 601 or Alloy 690 lie (see Table 4). At least 3 of the 4 following relations should be fulfilled: $$\mathrm{600}\mathrm{°\; C}:{\mathrm{Yield\; <figure-callout\; id="0"\; label="point\; R\; p"\; filenames="imgf0002.png"\; state="\{\{state\}\}">point\; R\; </figure-callout>}}_{\mathrm{p}}>\mathrm{140}\mathrm{MPA};{\mathrm{Tensile\; strength\; R}}_{\mathrm{m}}>\mathrm{450}\mathrm{<figure-callout\; id="800"\; label="MPA"\; filenames="imgf0002.png,imgf0003.png"\; state="\{\{state\}\}">MPA</figure-callout>}$$

$$\mathrm{800}\mathrm{°\; C}:{\mathrm{Yield\; <figure-callout\; id="0"\; label="point\; R\; p"\; filenames="imgf0002.png"\; state="\{\{state\}\}">point\; R\; </figure-callout>}}_{\mathrm{p}}>\mathrm{130}\mathrm{MPA};{\mathrm{Tensile\; strength\; R}}_{\mathrm{m}}>\mathrm{135}\mathrm{MPA}$$

$$\mathrm{Fk}=\mathrm{Cr}+\mathrm{19}*\mathrm{Ti}+\mathrm{34},\mathrm{3}*\mathrm{Nb}+\mathrm{10},\mathrm{2}*\mathrm{Al}+\mathrm{12},\mathrm{5}*\mathrm{Si}+\mathrm{98}*\mathrm{C}+\mathrm{2245}*\mathrm{B}$$

wobei Cr, Ti, Nb, Al, Si, C und B die Konzentration der betreffenden Elemente in Masse-% sind.This is achieved in particular if the following relationship between the main hardening elements is fulfilled: $$\mathrm{Fk}\ge 40\mathrm{With}$$

$$\mathrm{Fk}=\mathrm{Cr}+\mathrm{19}*\mathrm{Ti}+\mathrm{34}.\mathrm{3}*\mathrm{Nb}+\mathrm{10}.\mathrm{2}*\mathrm{al}+\mathrm{12}.\mathrm{5}*\mathrm{Si}+\mathrm{98}*\mathrm{C}+\mathrm{2245}*\mathrm{B}$$

wherein Cr, Ti, Nb, Al, Si, C and B are the concentration of the respective elements in mass%.

Corrosion resistance:

The oxidation resistance of a good Chromoxidbildners is sufficient. The alloy according to the invention is therefore said to have a corrosion resistance in air similar to that of Alloy 690 or Alloy 601.

Examples: production:

Tables 3a and 3b show the laboratory scale analyzes of batches smelted together with some of the prior art large scale molten batches used for comparison of Alloy 602CA (N06025), Alloy 690 (N06690), Alloy 601 (N06601). The prior art batches are marked with a T, those of the invention with an E. The batches marked on the laboratory scale are marked with an L, the large-scale blown batches with a G.

The blocks of laboratory-scale molten alloys in Tables 3a and b were annealed between 900 ° C and 1270 ° C for 8 hours and annealed Hot rolling and further intermediate annealing between 900 ° C and 1270 ° C for 0.1 to 1 h hot rolled to a final thickness of 13 mm or 6 mm. The sheets produced in this way were solution-annealed between 900 ° C. and 1270 ° C. for 1 h. From these sheets, the samples required for the measurements were taken.

In the case of the large-scale smelted alloys, a sample was taken from large-scale production from an industrially manufactured sheet with a suitable thickness. From this sample, the samples needed for the measurements were made.

All alloy variants typically had a particle size between 65 and 310 μm.

• Metal Dusting Beständigkeit
• Phasenstabilität
• Umformbarkeit anhand des Zugversuchs bei Raumtemperatur
• Warmfestigkeit / Kriechbeständigkeit mit Hilfe von Warmzugversuchen
• Korrosionsbeständigkeit mit Hilfe eines Oxidationstests

For the example batches in Tables 3a and 3b, the following properties are compared:

• Metal dusting resistance
• phase stability
• Formability based on the tensile test at room temperature
• Hot strength / creep resistance with the help of hot tensile tests
• Corrosion resistance with the help of an oxidation test

On a laboratory scale, batches 2294 to 2314 and 250053 to 250150 were melted. The E-labeled batches according to the invention have the formula (2a) with Cr + Al> 30 and are therefore more resistant to metal dusting than Alloy 690. Batches 2298, 2299, 2303, 2304, 2305, 2308, 2314, 250063, 260065, 250066, 250067, 250068, 250079, 250139, 250140 and 250141 satisfy the formula (2b) Al + Cr ≥ 31. They are therefore particularly good metal dusting resistant.

For the selected prior art alloys in Table 2 and all laboratory lots (Tables 3a and 3b), the phase diagrams were calculated and the formation temperature T _{s BCC was plotted} in Tables 2 and 3a. For the compositions in Tables 2 and 3a and 3b was also the value for Fp calculated according to formula 4a. Fp is greater, the larger the formation temperature T _{s BCC} . All examples of Alloy 693 (N06693) with a higher formation temperature T _{s BCC} than that of Alloy 10 have a Fp> 39.9. The requirement Fp ≦ 39.9 (formula 3a) is thus a good criterion for obtaining a sufficient phase stability in the case of an alloy. All laboratory lots (marked L) in Tables 3a and 3b fulfill the criterion Fp ≤ 39,9.

Table 4 shows the yield strength R _p0.2 , the tensile strength R _m and the elongation A ₅ for room temperature RT and for 600 ° C, furthermore the tensile strength R _m for 800 ° C. In addition, the values for Fa and Fk are entered.

Example batches 156817 and 160483 of the prior art alloy Alloy 602 CA have in Table 4 a relatively low elongation A5 at room temperature of 36 and 42%, respectively, which are below the requirements for good formability. Fa is> 60, which is above the range that indicates good formability. All alloys of the invention show an elongation> 50%. They thus fulfill the requirements. Fa is <60 for all alloys according to the invention. They are therefore in the range of good formability. The elongation is particularly high when Fa is comparatively small.

Example Example 156658 of the prior art Alloy 601 in Table 4 is an example of the range that the yield strength and tensile strength should reach at 600 ° C and 800 ° C, respectively. This is described by the relations 7a to 7d. The value of Fk is> 40. The alloys 2298, 2299, 2303, 2304, 2305, 2308, 2314, 250060, 250063, 260065, 250066, 250067, 250068, 250079, 250139, 250140, 250141, 250143, 250150 satisfy the requirement in that at least 3 of the 4 relations 7a to 7d are fulfilled. For these alloys, Fk is also greater than 40. Laboratory lots 2295, 2303, 250053, 250054 and 250057 are examples of less than 3 of the 4 relations 7a to 7d being met. Then Fk <45 is also.

Table 5 shows the specific mass changes after an oxidation test at 1100 ° C in air after 11 cycles of 96 h for a total of 1056 h. Given in Table 5 are the gross mass change, the net mass change and the specific mass change of the chipped oxides after 1056 h. The prior art alloys Alloy 601 and Alloy 690 showed a significantly higher gross mass change than Alloy 602 CA. This is because Alloy 601 and Alloy 690 form a chromium oxide layer which grows faster than an aluminum oxide layer but has Alloy 602 CA underneath the chromium oxide layer at least partially closed alumina layer. This noticeably reduces the growth of the oxide layer and thus also the specific mass increase. The alloy according to the invention should have a corrosion resistance in air similar to that of Alloy 690 or Alloy 601. Ie. the gross mass change should be below 60 g / m ² . This is the case for all laboratory batches in Table 5, thus also for the invention.

• Zu geringe Cr-Gehalte bedeuten, dass die Cr-Konzentration beim Einsatz der Legierung in einer korrosiven Atmosphäre sehr schnell unter die kritische Grenze sinkt, so dass sich keine geschlossene Chromoxidschicht mehr bilden kann. Deshalb ist 29 % Cr die untere Grenze für Chrom. Zu hohe Cr-Gehalte verschlechtern die Phasenstabilität der Legierung. Deshalb ist 37 % Cr als obere Grenze anzusehen.

The claimed limits for the alloy "E" according to the invention can therefore be explained in detail as follows:

• Too low Cr contents mean that when the alloy is used in a corrosive atmosphere, the Cr concentration drops very quickly below the critical limit, so that no closed chromium oxide layer can form any more. That is why 29% Cr is the lower limit for chromium. Too high Cr contents deteriorate the phase stability of the alloy. Therefore, 37% Cr is considered the upper limit.

A certain minimum aluminum content of 0.001% is required for the manufacturability of the alloy. Excessive Al contents, especially at very high chromium contents, affect the processability and phase stability of the alloy. Therefore, an Al content of 1.8% forms the upper limit.

The cost of the alloy increases with the reduction of the iron content. Below 0.1%, the costs increase disproportionately, as special Starting material must be used. For this reason, 0.1% Fe is the lower limit for cost reasons.

As the iron content increases, the phase stability (formation of embrittling phases) decreases, especially at high chromium contents. Therefore, 7% Fe is a sensible upper limit to ensure the phase stability of the alloy according to the invention.

Si is needed in the production of the alloy. It is therefore necessary a minimum content of 0.001%. Too high levels, in turn, affect processability and phase stability, especially at high chromium levels. The Si content is therefore limited to 0.50%.

A minimum content of 0.005% Mn is required to improve processability. Manganese is limited to 2.0% because this element reduces oxidation resistance.

Titanium increases the high-temperature strength. From 1.0%, the oxidation behavior can be severely degraded, which is why 1.0% is the maximum value.

Niobium, like titanium, enhances high-temperature strength. Higher levels increase costs very much. The upper limit is therefore set at 1.1%.

Even very low Mg contents and / or Ca contents improve the processing by the setting of sulfur, whereby the occurrence of low-melting NiS Eutektika is avoided. For Mg and / or Ca, therefore, a minimum content of 0.0002% each is required. If the contents are too high, intermetallic Ni-Mg phases or Ni-Ca phases may occur, which again significantly impair processability. The Mg and / or Ca content is therefore limited to a maximum of 0.05%.

A minimum content of 0.005% C is required for good creep resistance. C is limited to a maximum of 0.12%, since this element reduces the processability by the excessive formation of primary carbides from this content.

A minimum content of 0.001% N is required, which improves the processability of the material. N is limited to a maximum of 0.05%, since this element reduces the processability by the formation of coarse carbonitrides.

The oxygen content must be ≤ 0.020% to ensure the manufacturability of the alloy. Too low an oxygen content increases the costs. The oxygen content is therefore ≥ 0.0001%.

The content of phosphorus should be ≤ 0.030%, as this surfactant affects the oxidation resistance. Too low a P content increases costs. The P content is therefore ≥ 0.001%.

The levels of sulfur should be adjusted as low as possible, since this surfactant affects the oxidation resistance. It will therefore max. 0.010% S set.

Molybdenum is reduced to max. 2.0% limited as this element reduces oxidation resistance.

Tungsten is limited to max. 2.0% limited as this element also reduces oxidation resistance.

wobei Cr und Al die Konzentration der betreffenden Elemente in Masse-% sind. Nur dann ist der Gehalt an Oxid bildenden Elementen hoch genug um eine Metal Dusting Beständigkeit besser als Alloy 690 zu gewährleisten.The following relationship between Cr and Al must be satisfied in order to provide sufficient resistance to metal dusting: $$\mathrm{Cr}+\mathrm{al}>30$$

where Cr and Al are the concentration of the respective elements in mass%. Only then is the content of oxide-forming elements high enough to ensure metal dusting resistance better than Alloy 690.

$$\mathrm{Fp}=\mathrm{Cr}+\mathrm{0},\mathrm{272}*\mathrm{Fe}+\mathrm{2},\mathrm{36}*\mathrm{Al}+\mathrm{2},\mathrm{22}*\mathrm{Si}+\mathrm{2},\mathrm{48}*\mathrm{Ti}+\mathrm{1},\mathrm{26}*\mathrm{Nb}+\mathrm{0},\mathrm{374}*\mathrm{Mo}+\mathrm{0},\mathrm{538}*\mathrm{W}-\mathrm{11},\mathrm{8}*\mathrm{C}$$

wobei Cr, Fe, Al, Si, Ti, Nb, Mo, W und C die Konzentration der betreffenden Elemente in Masse-% sind. Die Grenzen für Fp sowie mögliche Einbeziehung weiterer Elemente wurden in der vorangegangenen Beschreibung ausführlich begründet.In addition, the following relationship must be satisfied for sufficient phase stability: $$\mathrm{fp}\le 39.9\mathrm{With}$$

$$\mathrm{fp}=\mathrm{Cr}+\mathrm{0}.\mathrm{272}*\mathrm{Fe}+\mathrm{2}.\mathrm{36}*\mathrm{al}+\mathrm{2}.\mathrm{22}*\mathrm{Si}+\mathrm{2}.\mathrm{48}*\mathrm{Ti}+\mathrm{1}.\mathrm{26}*\mathrm{Nb}+\mathrm{0}.\mathrm{374}*\mathrm{Not\; a\; word}+\mathrm{0}.\mathrm{538}*\mathrm{W}-\mathrm{11}.\mathrm{8th}*\mathrm{C}$$

wherein Cr, Fe, Al, Si, Ti, Nb, Mo, W and C are the concentration of the respective elements in mass%. The limits for Fp as well as possible inclusion of further elements have been explained in detail in the previous description.

If necessary, with additions of oxygen-affine elements, the oxidation resistance can be further improved. They do this by incorporating them into the oxide layer and blocking the diffusion paths of the oxygen there on the grain boundaries.

A minimum content of 0.01% Y is necessary to obtain the oxidation resistance-enhancing effect of Y. The upper limit is set at 0.20% for cost reasons.

A minimum content of 0.001% La is necessary to obtain the oxidation resistance enhancing effect of La. The upper limit is set at 0.20% for cost reasons.

A minimum content of 0.001% Ce is necessary to obtain the oxidation resistance-enhancing effect of Ce. The upper limit is set at 0.20% for cost reasons.

A minimum content of 0.001% cerium mischmetal is necessary to obtain the oxidation resistance enhancing effect of the cerium misch metal. The upper limit is set at 0.20% for cost reasons.

If necessary, the alloy can also be given Zr. A minimum content of 0.01% Zr is necessary to obtain the high-temperature strength and oxidation resistance-enhancing effect of Zr. The upper limit is set at 0.20% Zr for cost reasons.

If necessary, Zr can be wholly or partially replaced by Hf, since this element, such as Zr, also increases high-temperature strength and oxidation resistance. Replacement is possible from 0.001%. The upper limit is set at 0.20% Hf for cost reasons.

If necessary, the alloy may also contain tantalum, since tantalum also increases high-temperature strength. Higher levels increase costs very much. The upper limit is therefore set at 0.60%. A minimum level of 0.001% is required to have an effect.

If necessary, boron may be added to the alloy because boron improves creep resistance. Therefore, a content of at least 0.0001% should be present. At the same time, this surfactant deteriorates the oxidation resistance. It will therefore max. 0.008% Boron set.

Cobalt can be contained in this alloy up to 5.0%. Higher contents considerably reduce the oxidation resistance.

Copper is heated to max. 0.5% limited as this element reduces the oxidation resistance.

Vanadium is reduced to max. 0.5% limited as this element reduces the oxidation resistance.

Pb is set to max. 0.002% limited because this element reduces the oxidation resistance. The same applies to Zn and Sn.

$$\mathrm{Fa}=\mathrm{Cr}+\mathrm{6},\mathrm{15}*\mathrm{Nb}+\mathrm{20},\mathrm{4}*\mathrm{Ti}+\mathrm{201}*\mathrm{C}$$

wobei Cr, Nb, Ti und C die Konzentration der betreffenden Elemente in Masse-% sind. Die Grenzen für Fa wurden in der vorangegangenen Beschreibung ausführlich begründet.Furthermore, optionally, the following relationship of carbide-forming elements Cr, Ti and C can be satisfied, which describes a particularly good processability: $$\mathrm{fa}\le 60\mathrm{With}$$

$$\mathrm{fa}=\mathrm{Cr}+\mathrm{6}.\mathrm{15}*\mathrm{Nb}+\mathrm{20}.\mathrm{4}*\mathrm{Ti}+\mathrm{201}*\mathrm{C}$$

wherein Cr, Nb, Ti and C are the concentration of the respective elements in mass%. The boundaries for Fa were substantiated in detail in the foregoing description.

$$\mathrm{Fk}=\mathrm{Cr}+19*\mathrm{Ti}+34,3*\mathrm{Nb}+10,2*\mathrm{Al}+12,5+98\mathrm{°C}$$

wobei Cr, Ti, Nb, Al, Si und C die Konzentration der betreffenden Elemente in Masse-% sind. Die Grenzen für Fa und die mögliche Einbeziehung weiterer Elemente wurden in der vorangegangenen Beschreibung ausführlich begründet.

Tabelle 3b: Zusammensetzung der Laborchargen, Teil 2. Alle Angaben in Masse-% (Für alle Legierungen gilt: Pb: max. 0,002 %, Zn: max. 0,002 %, Sn: max. 0,002 %) (Bedeutung von T, E, G, L, siehe Tabelle 3a) Name Charge S P Mg Ca V Zr Co Y La B Hf Ta Ce O T G Alloy 602 CA 156817 0,002 0,005 0,004 0,001 0,03 0,08 0,05 0,060 - 0,003 - - - 0,001 T G Alloy 602 CA 160483 <0,002 0,007 0,01 0,002 - 0,09 0,04 0,070 - 0,003 - - - 0,001 T G Alloy 601 156656 0,002 0,008 0,012 <0,01 0,03 0,015 0,04 - - 0,001 - - - 0,0001 T G Alloy 690 80116 0,002 0,006 0,03 0,0009 - <0,002 0,02 - - 0,002 - - - 0,0005 T G Alloy 690 111389 0,002 0,005 <0,001 0,0005 - - 0,01 - - - - - - 0,001 E L Cr30TiLa 2294 0,002 0,003 0,012 <0,01 <0, 01 0,002 <0,001 - 0,07 - - <0,005 0,001 0,0001 E L Cr30La 2295 0,002 0,003 0,013 <0,01 <0,01 0,002 <0,001 - 0,06 - - <0,005 0,001 0,0001 E L Cr30CLa 2296 0,003 0,003 0,015 <0,01 <0,01 <0,002 <0,001 - 0,06 - - <0,005 0,001 0,0001 E L Cr30Al1TiLa 2298 0,006 0,002 0,016 <0,01 <0,01 <0,002 <0,001 <0,001 0,06 <0,001 <0,001 <0,005 0,001 0,002 E L Cr30Al1TINbLa 2308 0,002 0,002 0,014 <0,01 <0,01 <0,002 0,001 <0,001 0,09 <0,001 <0,001 <0,005 0,001 0,002 E L Cr30Al1CLaTi 2299 0,003 0,002 0,015 <0,01 <0,01 <0,002 <0,001 <0,001 0,06 <0,001 <0,001 <0,005 0,001 0,002 E L Cr33La 2303 0,003 0,002 0,014 <0,01 <0,01 <0,002 0,001 <0,001 0,06 <0,001 <0,001 <0,005 0,001 0,0001 E L Cr33CLa 2304 0,002 0,002 0,013 <0,01 <0,01 <0,002 0,001 <0,001 0,04 <0,001 <0,001 <0,005 0,001 0,0001 E L Cr33WCLa 2314 0,001 0,003 0,009 <0,01 <0,01 <0,002 0,001 <0,001 0,05 <0,001 <0,001 <0,005 0,001 0,002 E L Cr33Al1TiLa 2305 0,003 0,002 0,018 <0,01 <0,01 <0,002 0,001 <0,001 0,05 <0,001 <0,001 <0,005 0,001 0,0001 E L Cr30C 250054 0,003 0,002 0,007 <0,01 <0,01 <0,002 <0,001 <0,001 - <0,001 <0,001 <0,005 <0,001 0,001 E L Cr30C 250053 0,003 0,002 0,007 <0,01 <0,01 <0,002 <0,001 <0,001 - <0,001 <0,001 <0,005 <0,001 0,003 E L Cr30CNLa 250056 0,001 0,003 0,018 <0,01 <0,01 <0,002 <0,001 <0,001 0,03 <0,001 <0,001 <0,005 <0,001 0,002 E L Cr30Al1Ti 250060 0,003 0,002 0,009 <0,01 <0,01 <0,002 <0,001 <0,001 - <0,001 <0,001 <0,005 <0,001 0,003 E L Cr30Al1Ti 250063 0,003 0,003 0,012 <0,01 <0,01 <0,002 <0,001 <0,001 - <0,001 <0,001 <0,005 <0,001 0,003 E L Cr30Al1TiNb 250066 0,002 0,002 0,012 <0,01 <0,01 <0,002 <0,001 <0,001 - <0,001 <0,001 <0,005 <0,001 0,004 E L Cr30Al1TiNb 250065 0,002 0,002 0,012 <0,01 <0,01 <0,002 <0,001 <0,001 - <0,001 <0,001 <0,005 <0,001 0,005 E L Cr30Al1TiNbZr 250067 0,003 0,002 0,010 <0,01 <0,01 0,069 <0,001 <0,001 - <0,001 <0,001 <0,005 <0,001 0,003 E L Cr30Al1TiNb 250068 0,002 <0,002 0,010 <0,01 <0,01 <0,002 <0,001 <0,001 - <0,001 <0,001 <0,005 <0,001 0,004 E L Cr33C 250057 0,004 0,002 0,008 <0,01 <0,01 <0,002 <0,001 - - - - <0,005 <0,001 0,003 E L Cr33AlTi 250079 0,003 0,002 0,011 <0,01 <0,01 <0,002 <0,001 - - - - <0,005 <0,001 0,004 E L Cr33C1Ti 250139 0,002 0,004 0,008 0,0002 <0,01 0,002 <0,01 0,01 - <0,0005 - - - 0,004 E L Cr33C1Zr 250140 0,003 0,004 0,007 0,0002 <0,01 0,125 <0,01 0,01 - 0,001 - - - 0,003 E L Cr33C1 250141 0,002 0,004 0,008 0,0002 <0,01 0,007 <0,01 0,01 - 0,001 - - - 0,005 E L Cr30C1Y 250143 0,003 0,004 0,001 0,0002 <0,01 0,003 <0,01 0,08 - 0,001 - - - 0,002 E L Cr30Nb1YC 250150 0,004 0,005 0,01 <0,0005 <0,01 0,003 <0,01 0,09 - 0,001 - - - 0,002 Tabelle 4: Ergebnisse der Zugversuche bei Raumtemperatur (RT), 600 °C und 800°C. Die Umformgeschwindigkeit betrug bei Rp_0,2 8,33 10^-5 1/s (0,5%/min) und bei R_m 8,33 10^-4 1/s (5%/min); KG = Korngröße, *) Probe fehlerhaft. Name Chg KG in µm R_p0,2 in MPa RT R_m in MPa RT A₅ in % RT R_p0,2 in MPa 600°C R_m in MPa 600°C A₅ in % 600°C R_p0,2 in MPa 800°C R_m in MPa 800°C Fa Fk T G Alloy 602 CA 156817 76 292 699 36 256 578 41 186 198 63,0 76,9 T G Alloy 602 CA 160483 76 340 721 42 254 699 69 62,2 75,0 T G Alloy 601 156656 136 238 645 53 154 509 55 133 136 63,2 56,3 T G Alloy 690 80116 92 279 641 56 195 469 48 135 154 43,3 41,6 T G Alloy 690 111389 72 285 630 50 188 465 51 36,2 43,6 E L Cr30TiLa 2294 161 285 537 *) 170 452 29 145 171 38,0 39,6 E L Cr30La 2295 189 225 555 *) 131 358 25 110 167 34,0 36,0 E L Cr30CLa 2296 237 295 644 59 197 472 57 192 200 41,9 39,7 E L Cr30Al1TiLa 2298 94 351 704 59 228 490 31 149 161 39,7 51,5 E L Cr30Al1TINbLa 2308 90 288 683 55 200 508 39 174 181 41,6 61,0 E L Cr30Al1CLaTi 2299 253 258 661 62 212 475 59 181 185 42,3 50,0 E L Cr33La 2303 145 272 618 *) 137 433 57 118 171 36,7 39,6 E L Cr33CLa 2304 278 284 640 50 171 439 65 168 209 42,1 41,7 E L Cr33WCLa 2314 298 254 644 66 143 438 67 154 212 43,9 42,4 E L Cr33Al1TiLa 2305 68 276 623 *) 224 472 41 161 166 39,6 53,3 E L Cr30C 250054 207 227 628 63 127 428 64 147 196 38,5 38,4 E L Cr30C 250053 150 215 626 55 119 426 57 128 187 38,5 38,5 E L Cr30CNLa 250056 242 234 612 55 145 440 74 144 204 39,3 38,2 E L Cr30Al1Ti 250060 114 252 662 67 183 509 62 143 154 39,3 50,4 E L Cr30Al1Ti 250063 118 252 659 70 178 510 57 148 1521 39,6 52,9 E L Cr30Al1TiNb 250066 121 240 666 67 186 498 66 245 255 41,4 63,6 E L Cr30Al1TiNb 250065 132 285 685 61 213 521 58 264 265 41,8 64 E L Cr30Al1TiNbZr 250067 112 287 692 67 227 532 65 280 280 41,6 64,2 E L Cr30Al1TiNb 250068 174 261 666 69 205 498 65 297 336 44,9 83,2 E L Cr33C 250057 191 241 638 66 127 414 54 185 197 40,6 39,5 E L Cr33AlTi 250079 101 267 665 68 190 489 56 145 164 39,4 52,0 E L Cr33C1Ti 250139 112 266 679 54 161 495 48 167 187 52,7 48,5 E L Cr33C1Zr 250140 153 269 667 60 177 447 36 164 191 49,1 47,4 E L Cr33C1 250141 302 269 645 58 157 430 52 192 214 48,8 46,6 E L Cr30C1Y 250143 195 264 650 69 166 490 50 174 195 46,8 44,9 E L Cr30Nb1YC 250150 72 287 722 53 188 577 57 181 194 54,0 81,6 Tabelle 5: Ergebnisse der Oxidationsversuche bei 1000 °C an Luft nach 1056 h. Name Charge Versuch Nr m_brutto in g/m² m_netto in g/m² m_spall in g/m² T G Alloy 602 CA 160483 412 8,66 7,83 0,82 T G Alloy 602 CA 160483 425 5,48 5,65 -0,18 T G Alloy 601 156125 403 51,47 38,73 12,74 T G Alloy 690 111389 412 23,61 7,02 16,59 T G Alloy 690 111389 421 30,44 -5,70 36,14 T L Alloy 690 111389 425 28,41 -0,68 29,09 E L Cr30TiLa 2294 412 28,40 -18,37 46,77 E L Cr30La 2295 412 19,44 0,09 19,35 E L Cr30CLa 2296 412 26,83 -11,43 38,27 E L Cr30Al1TiLa 2298 412 49,02 -30,59 79,61 E L Cr30Al1TINbLa 2308 412 42,93 -15,54 58,47 E L Cr30Al1CLaTi 2299 412 30,51 0,08 30,44 E L Cr33La 2303 412 25,98 -8,42 34,40 E L Cr33CLa 2304 412 29,18 -14,42 43,60 E L Cr33WCLa 2314 412 24,37 -10,35 34,72 E L Cr33Al1TiLa 2305 412 49,96 -19,36 69,32 E L Cr30C 250054 421 31,15 -21,76 52,92 E L Cr30C 250053 421 31,37 -26,58 57,95 E L Cr30CNLa 250056 421 23,46 -9,64 33,11 E L Cr30Al1Ti 250060 421 43,30 -19,88 63,17 E L Cr30Al1Ti 250063 421 32,81 -22,15 54,96 E L Cr30Al1TiNb 250066 421 26,93 -16,35 43,28 E L Cr30Al1TiNb 250065 421 25,85 -24,27 50,12 E L Cr30Al1TiNbZr 250067 421 41,59 -15,56 57,16 E L Cr30Al1TiNb 250068 421 42,69 -39,26 81,95 E L Cr33C 250057 421 34,72 -47,71 82,43 E L Cr33AlTi 250079 421 17,02 1,99 15,03 E L Cr33C1Ti 250139 425 57,97 -49,60 107,58 E L Cr33C1Zr 250140 425 23,83 7,22 16,60 E L Cr33C1 250141 425 37,63 -28,71 66,35 E L Cr30C1Y 250143 425 25,78 -1,85 27,63 E L Cr30Nb1YC 250150 425 27,70 -10,02 37,72 Furthermore, optionally, the following relationship between the strength-enhancing elements can be satisfied, which describes a particularly good hot strength / creep resistance: $$\mathrm{Fk}\ge 40\mathrm{With}$$

$$\mathrm{Fk}=\mathrm{Cr}+19*\mathrm{Ti}+34.3*\mathrm{Nb}+10.2*\mathrm{al}+12.5+98\mathrm{°\; C}$$

wherein Cr, Ti, Nb, Al, Si and C are the concentration of the respective elements in mass%. The limits for Fa and the possible inclusion of further elements have been extensively substantiated in the foregoing description.

Table 3b: Composition of laboratory batches, part 2. All data in mass% (For all alloys applies: Pb: max 0.002%, Zn: max 0.002%, Sn: max 0.002%) (meaning of T, E, G, L, see Table 3a) Surname charge S P mg Ca V Zr Co Y La B Hf Ta Ce O T G Alloy 602 CA 156817 0,002 0.005 0,004 0.001 0.03 0.08 0.05 0,060 - 0,003 - - - 0.001 T G Alloy 602 CA 160483 <0.002 0,007 0.01 0,002 - 0.09 0.04 0,070 - 0,003 - - - 0.001 T G Alloy 601 156656 0,002 0,008 0,012 <0.01 0.03 0,015 0.04 - - 0.001 - - - 0.0001 T G Alloy 690 80116 0,002 0,006 0.03 0.0009 - <0.002 0.02 - - 0,002 - - - 0.0005 T G Alloy 690 111389 0,002 0.005 <0.001 0.0005 - - 0.01 - - - - - - 0.001 e L Cr30TiLa 2294 0,002 0,003 0,012 <0.01 <0, 01 0,002 <0.001 - 0.07 - - <0.005 0.001 0.0001 e L Cr30La 2295 0,002 0,003 0,013 <0.01 <0.01 0,002 <0.001 - 0.06 - - <0.005 0.001 0.0001 e L Cr30CLa 2296 0,003 0,003 0,015 <0.01 <0.01 <0.002 <0.001 - 0.06 - - <0.005 0.001 0.0001 e L Cr30Al1TiLa 2298 0,006 0,002 0.016 <0.01 <0.01 <0.002 <0.001 <0.001 0.06 <0.001 <0.001 <0.005 0.001 0,002 e L Cr30Al1TINbLa 2308 0,002 0,002 0,014 <0.01 <0.01 <0.002 0.001 <0.001 0.09 <0.001 <0.001 <0.005 0.001 0,002 e L Cr30Al1CLaTi 2299 0,003 0,002 0,015 <0.01 <0.01 <0.002 <0.001 <0.001 0.06 <0.001 <0.001 <0.005 0.001 0,002 e L Cr33La 2303 0,003 0,002 0,014 <0.01 <0.01 <0.002 0.001 <0.001 0.06 <0.001 <0.001 <0.005 0.001 0.0001 e L Cr33CLa 2304 0,002 0,002 0,013 <0.01 <0.01 <0.002 0.001 <0.001 0.04 <0.001 <0.001 <0.005 0.001 0.0001 e L Cr33WCLa 2314 0.001 0,003 0.009 <0.01 <0.01 <0.002 0.001 <0.001 0.05 <0.001 <0.001 <0.005 0.001 0,002 e L Cr33Al1TiLa 2305 0,003 0,002 0,018 <0.01 <0.01 <0.002 0.001 <0.001 0.05 <0.001 <0.001 <0.005 0.001 0.0001 e L Cr30C 250054 0,003 0,002 0,007 <0.01 <0.01 <0.002 <0.001 <0.001 - <0.001 <0.001 <0.005 <0.001 0.001 e L Cr30C 250053 0,003 0,002 0,007 <0.01 <0.01 <0.002 <0.001 <0.001 - <0.001 <0.001 <0.005 <0.001 0,003 e L Cr30CNLa 250056 0.001 0,003 0,018 <0.01 <0.01 <0.002 <0.001 <0.001 0.03 <0.001 <0.001 <0.005 <0.001 0,002 e L Cr30Al1Ti 250060 0,003 0,002 0.009 <0.01 <0.01 <0.002 <0.001 <0.001 - <0.001 <0.001 <0.005 <0.001 0,003 e L Cr30Al1Ti 250063 0,003 0,003 0,012 <0.01 <0.01 <0.002 <0.001 <0.001 - <0.001 <0.001 <0.005 <0.001 0,003 e L Cr30Al1TiNb 250066 0,002 0,002 0,012 <0.01 <0.01 <0.002 <0.001 <0.001 - <0.001 <0.001 <0.005 <0.001 0,004 e L Cr30Al1TiNb 250065 0,002 0,002 0,012 <0.01 <0.01 <0.002 <0.001 <0.001 - <0.001 <0.001 <0.005 <0.001 0.005 e L Cr30Al1TiNbZr 250067 0,003 0,002 0,010 <0.01 <0.01 0,069 <0.001 <0.001 - <0.001 <0.001 <0.005 <0.001 0,003 e L Cr30Al1TiNb 250068 0,002 <0.002 0,010 <0.01 <0.01 <0.002 <0.001 <0.001 - <0.001 <0.001 <0.005 <0.001 0,004 e L Cr33C 250057 0,004 0,002 0,008 <0.01 <0.01 <0.002 <0.001 - - - - <0.005 <0.001 0,003 e L Cr33AlTi 250079 0,003 0,002 0.011 <0.01 <0.01 <0.002 <0.001 - - - - <0.005 <0.001 0,004 e L Cr33C1Ti 250139 0,002 0,004 0,008 0.0002 <0.01 0,002 <0.01 0.01 - <0.0005 - - - 0,004 e L Cr33C1Zr 250140 0,003 0,004 0,007 0.0002 <0.01 0,125 <0.01 0.01 - 0.001 - - - 0,003 e L Cr33C1 250141 0,002 0,004 0,008 0.0002 <0.01 0,007 <0.01 0.01 - 0.001 - - - 0.005 e L Cr30C1Y 250143 0,003 0,004 0.001 0.0002 <0.01 0,003 <0.01 0.08 - 0.001 - - - 0,002 e L Cr30Nb1YC 250150 0,004 0.005 0.01 <0.0005 <0.01 0,003 <0.01 0.09 - 0.001 - - - 0,002 Surname Chg KG in μm R _p0.2 in MPa RT R _m in MPa RT A ₅ in% RT R _p0.2 in MPa 600 ° C R _m in MPa 600 ° C A ₅ in% 600 ° C R _p0.2 in MPa 800 ° C R _m in MPa 800 ° C fa Fk T G Alloy 602 CA 156817 76 292 699 36 256 578 41 186 198 63.0 76.9 T G Alloy 602 CA 160483 76 340 721 42 254 699 69 62.2 75.0 T G Alloy 601 156656 136 238 645 53 154 509 55 133 136 63.2 56.3 T G Alloy 690 80116 92 279 641 56 195 469 48 135 154 43.3 41.6 T G Alloy 690 111389 72 285 630 50 188 465 51 36.2 43.6 e L Cr30TiLa 2294 161 285 537 *) 170 452 29 145 171 38.0 39.6 e L Cr30La 2295 189 225 555 *) 131 358 25 110 167 34.0 36.0 e L Cr30CLa 2296 237 295 644 59 197 472 57 192 200 41.9 39.7 e L Cr30Al1TiLa 2298 94 351 704 59 228 490 31 149 161 39.7 51.5 e L Cr30Al1TINbLa 2308 90 288 683 55 200 508 39 174 181 41.6 61.0 e L Cr30Al1CLaTi 2299 253 258 661 62 212 475 59 181 185 42.3 50.0 e L Cr33La 2303 145 272 618 *) 137 433 57 118 171 36.7 39.6 e L Cr33CLa 2304 278 284 640 50 171 439 65 168 209 42.1 41.7 e L Cr33WCLa 2314 298 254 644 66 143 438 67 154 212 43.9 42.4 e L Cr33Al1TiLa 2305 68 276 623 *) 224 472 41 161 166 39.6 53.3 e L Cr30C 250054 207 227 628 63 127 428 64 147 196 38.5 38.4 e L Cr30C 250053 150 215 626 55 119 426 57 128 187 38.5 38.5 e L Cr30CNLa 250056 242 234 612 55 145 440 74 144 204 39.3 38.2 e L Cr30Al1Ti 250060 114 252 662 67 183 509 62 143 154 39.3 50.4 e L Cr30Al1Ti 250063 118 252 659 70 178 510 57 148 1521 39.6 52.9 e L Cr30Al1TiNb 250066 121 240 666 67 186 498 66 245 255 41.4 63.6 e L Cr30Al1TiNb 250065 132 285 685 61 213 521 58 264 265 41.8 64 e L Cr30Al1TiNbZr 250067 112 287 692 67 227 532 65 280 280 41.6 64.2 e L Cr30Al1TiNb 250068 174 261 666 69 205 498 65 297 336 44.9 83.2 e L Cr33C 250057 191 241 638 66 127 414 54 185 197 40.6 39.5 e L Cr33AlTi 250079 101 267 665 68 190 489 56 145 164 39.4 52.0 e L Cr33C1Ti 250139 112 266 679 54 161 495 48 167 187 52.7 48.5 e L Cr33C1Zr 250140 153 269 667 60 177 447 36 164 191 49.1 47.4 e L Cr33C1 250141 302 269 645 58 157 430 52 192 214 48.8 46.6 e L Cr30C1Y 250143 195 264 650 69 166 490 50 174 195 46.8 44.9 e L Cr30Nb1YC 250150 72 287 722 53 188 577 57 181 194 54.0 81.6 Surname charge Experiment No. m _gross in g / m ² m _net in g / m ² m _spall in g / m ² T G Alloy 602 CA 160483 412 8.66 7.83 0.82 T G Alloy 602 CA 160483 425 5.48 5.65 -0.18 T G Alloy 601 156125 403 51.47 38.73 12.74 T G Alloy 690 111389 412 23.61 7.02 16.59 T G Alloy 690 111389 421 30.44 -5.70 36.14 T L Alloy 690 111389 425 28.41 -0.68 29,09 e L Cr30TiLa 2294 412 28.40 -18.37 46.77 e L Cr30La 2295 412 19.44 0.09 19.35 e L Cr30CLa 2296 412 26.83 -11.43 38.27 e L Cr30Al1TiLa 2298 412 49.02 -30.59 79.61 e L Cr30Al1TINbLa 2308 412 42.93 -15.54 58.47 e L Cr30Al1CLaTi 2299 412 30.51 0.08 30.44 e L Cr33La 2303 412 25,98 -8.42 34.40 e L Cr33CLa 2304 412 29.18 -14.42 43,60 e L Cr33WCLa 2314 412 24,37 -10.35 34.72 e L Cr33Al1TiLa 2305 412 49.96 -19.36 69.32 e L Cr30C 250054 421 31.15 -21.76 52.92 e L Cr30C 250053 421 31.37 -26.58 57.95 e L Cr30CNLa 250056 421 23.46 -9.64 33.11 e L Cr30Al1Ti 250060 421 43.30 -19.88 63.17 e L Cr30Al1Ti 250063 421 32.81 -22.15 54.96 e L Cr30Al1TiNb 250066 421 26.93 -16.35 43.28 e L Cr30Al1TiNb 250065 421 25.85 -24.27 50.12 e L Cr30Al1TiNbZr 250067 421 41,59 -15.56 57.16 e L Cr30Al1TiNb 250068 421 42.69 -39.26 81,95 e L Cr33C 250057 421 34.72 -47.71 82.43 e L Cr33AlTi 250079 421 17,02 1.99 15,03 e L Cr33C1Ti 250139 425 57.97 -49.60 107.58 e L Cr33C1Zr 250140 425 23.83 7.22 16.60 e L Cr33C1 250141 425 37.63 -28.71 66.35 e L Cr30C1Y 250143 425 25.78 -1.85 27.63 e L Cr30Nb1YC 250150 425 27,70 -10.02 37.72

LIST OF REFERENCE NUMBERS

FIG. 1

Metal loss due to metal dusting as a function of aluminum and chromium content in a high carburizing gas with 37% CO, 9% H ₂ O, 7% CO ₂ , 46% H ₂ , the a _c = 163 and p (0 ₂ ) = 2 , 5 · 10 ^-27 has. (out ( Hermse, CGM and van Wortel, JC: Metal dusting: relationship between alloy composition and degradation rate. Corrosion Engineering, Science and Technology 44 (2009), p. 182 - 185 ).

FIG. 2

Amounts of the phases in the thermodynamic equilibrium as a function of the temperature of Alloy 690 (N06690) using the example of the typical charge 111389.

FIG. 3

Amounts of the phases in the thermodynamic equilibrium as a function of the temperature of Alloy 693 (N06693) using the example of Alloy 3 from Table 2.

FIG. 4

Amounts of the phases in the thermodynamic equilibrium as a function of the temperature of Alloy 693 (N06693) using the example of Alloy 10 from Table 2.

Claims (19)

1. A nickel-chromium alloy comprising (in % by mass) 29 to 37 % chromium, 0.001 to 1.8 % aluminum, 0.10 to 7.0 % iron, 0.001 to 0.50 % silicon, 0.005 to 2.0 % manganese, 0.00 to 1.00 % titanium and/or 0.00 to 1.10 % niobium, respectively 0.0002 to 0.05 % magnesium and/or calcium, 0.005 to 0.12 % carbon, 0.001 to 0.050 % nitrogen, 0.001 to 0.030 % phosphorus, 0.0001 to 0.020 % oxygen, max. 0.010 % sulphur, max. 2.0 % molybdenum, max. 2.0 % tungsten, if necessary, furthermore comprising a content of 0.01 to 0.20 % Y, a content of 0.01 to 0.20 % La, a content of 0.001 to 0.20 % cerium, a content of 0.001 to 0.20 % cerium mischmetall, a content of 0.01 to 0.20 % of Zr, wherein Zr can be completely or partly substituted by 0.001 to 0.20 % Hf, a content of 0.0001 to 0.008 % B, 0.0 to 5.0 % Co, max. 0.5 % Cu, max. 0.5 % V, if necessary, furthermore comprising a rest of nickel and the usual process-related impurities, wherein the following conditions have to be met: $$\mathrm{Cr}+\mathrm{Al}>30$$

   

   and $$\mathrm{Fp}\le 39.9\mathrm{with}$$

   

   $$\mathrm{Fp}=\mathrm{Cr}+\mathrm{0},\mathrm{272}*\mathrm{Fe}+\mathrm{2},\mathrm{36}*\mathrm{Al}+\mathrm{2},\mathrm{22}*\mathrm{Si}+\mathrm{2},\mathrm{48}*\mathrm{Ti}+\mathrm{1},\mathrm{26}*\mathrm{Nb}+\mathrm{0},\mathrm{374}*\mathrm{Mo}+\mathrm{0},\mathrm{538}*\mathrm{W}-\mathrm{11},\mathrm{8}*\mathrm{C}$$

   

   wherein Cr, Fe, Al, Si, Ti, Nb, C, W and Mo are the concentrations of the concerning elements in % by mass.
2. An alloy according to claim 1, comprising a content of chromium comprised between 30 and 37 %.
3. An alloy according to claim 1 or 2, comprising a content of chromium of > 32 to 37 %.
4. An alloy according to one of the claims 1 through 3, comprising a content of aluminum comprised between 0.001 and 1.4 %.
5. An alloy according to one of the claims 1 through 4, comprising a content of iron comprised between 0.1 and 4.0 %.
6. An alloy according to one of the claims 1 through 5, comprising a content of silicon comprised between 0.001 and 0.2 %.
7. An alloy according to one of the claims 1 through 6, comprising a content of manganese comprised between 0.005 and 0.50 %.
8. An alloy according to one of the claims 1 through 7, comprising a content of titanium comprised between 0.001 and 0.60 %.
9. An alloy according to one of the claims 1 through 8, comprising a content of niobium comprised between 0.00 and 1.0 %.
10. An alloy according to one of the claims 1 through 9, comprising a content of carbon comprised between 0.01 and 0.12 %.
11. An alloy according to one of the claims 1 through 10, comprising maximum 0.5 % copper, wherein the formula 4a will be supplemented by a term with Cu: $$\mathrm{Fp}=\mathrm{Cr}+\mathrm{0},\mathrm{272}*\mathrm{Fe}+\mathrm{2},\mathrm{36}*\mathrm{Al}+\mathrm{2},\mathrm{22}*\mathrm{Si}+\mathrm{2},\mathrm{48}*\mathrm{Ti}+\mathrm{1},\mathrm{26}*\mathrm{Nb}+\mathrm{0.477}*\mathrm{Cu}+\mathrm{0},\mathrm{374}*\mathrm{Mo}+\mathrm{0},\mathrm{538}*\mathrm{W}-\mathrm{11},\mathrm{8}*\mathrm{C}$$

    

    and Cr, Fe, Al, Si, Ti, Nb, Cu, W and Mo are the concentrations of the concerning elements in % by mass.
12. An alloy according to one of the claims 1 through 11, in which the contents of the impurities are set at max. 0.002 % Pb, max. 0.002 % Zn, max. 0.002 % Sn.
13. An alloy according to one of the claims 1 through 12, in which the following formula is satisfied und thus an especially good formability is achieved: $$\mathrm{Fa}\le 60$$

    

    with $$\mathrm{Fa}=\mathrm{Cr}+\mathrm{6.15}*\mathrm{Nb}+\mathrm{20.4}*\mathrm{Ti}+\mathrm{201}*\mathrm{C}$$

    

    wherein Cr, Ti, Nb and C are the concentrations of the concerning elements in % by mass.
14. An alloy according to one of the claims 1 through 13, in which the following formulas are satisfied und thus an especially good high-temperature strength/creep strength is achieved: $$\mathrm{Fk}\ge 40$$

    

    with $$\mathrm{Fk}=\mathrm{Cr}+19*\mathrm{Ti}+34,3*\mathrm{Nb}+10,2*\mathrm{Al}+12,5*\mathrm{Si}+98\mathrm{°C}$$

    

    for an alloy without B,
    wherein Cr, Ti, Nb, Al, Si and C are the concentrations of the concerning elements in % by mass, $$\mathrm{respectively\; with\; Fk}=\mathrm{Cr}+\mathrm{19}*\mathrm{Ti}+\mathrm{34.3}*\mathrm{Nb}+\mathrm{10.2}*\mathrm{Al}+\mathrm{12.5}*\mathrm{Si}+\mathrm{98}\mathrm{°C}+\mathrm{2245}*\mathrm{B}$$

    

    for an alloy with B,
    wherein Cr, Ti, Nb, Al, Si, C and B are the concentrations of the concerning elements in % by mass.
15. A utilization of the alloy according to one of the claims 1 through 14 as band, sheet metal, wire, bar, longitudinally welded pipe and seamless pipe.
16. A utilization of the alloy according to one of the claims 1 through 15 for the manufacture of seamless pipes.
17. A utilization of the alloy according to one of the claims 1 through 16 in heavily carburizing atmospheres.
18. A utilization of the alloy according to one of the claims 1 through 16 as structural part in the petrochemical industry.
19. A utilization of the alloy according to one of the claims 1 through 16 in the furnace contruction.

Images