NICKEL-CHROMIUM-IRON-ALUMINUM ALLOY HAVING GOOD PROCESSABILITY, CREEP RESISTANCE AND CORROSION RESISTANCE, AND USE THEREOF

Abstract

A nickel-chromium-iron-aluminum alloy contains (in wt. %)>17 to 33% chromium, 1.8 to <4.0% aluminum, 0.10 to 15.0% iron, 0.001 to 0.50% silicon, 0.001 to 2.0% manganese, 0.00 to 0.60% titanium, 0.0002 to 0.05% each of magnesium and/or calcium, 0.005 to 0.12% carbon, 0.001 to 0.050% nitrogen, 0.0001 to 0.020% oxygen, 0.001 to 0.030% phosphorus, not more than 0.010% sulfur, not more than 2.0% molybdenum, not more than 2.0% tungsten, the remainder nickel with nickel ≥50% and the usual process-related impurities, for use in solar power tower plants using nitrate salt melts as the heat transfer medium, wherein the following relations must be satisfied: Fp≤39.9 (2a) with Fp=Cr+0.272*Fe+2.36*Al+2.22*Si+2.48*Ti+0.374*Mo+0.538*W−11.8*C (3a), wherein Cr, Fe, Al, Si, Ti, Mo, W and C is the concentration of the respective elements in % by weight.

Claims

1: A nickel-chromium-aluminum-iron alloy containing (in mass-%) >17 to 33% chromium, 1.8 to <4.0% aluminum, 0.10 to 15.0% iron, 0.001 to 0.50% silicon, 0.001 to 2.0% manganese, 0.00 to 0.60% titanium, respectively 0.0002 to 0.05% magnesium and/or calcium, 0.005 to 0.12% carbon, 0.001 to 0.050% nitrogen, 0.0001 to 0.020% oxygen, 0.001 to 0.030% phosphorus, max. 0.010% sulfur, max. 2.0% molybdenum, max. 2.0% tungsten, the rest nickel with nickel ≥50% and the common process-related impurities for the use in solar tower power plants using nitrate salt melts as the heat-transfer medium, wherein the following relationship must be satisfied:
Fp≤39.9 with  (2a)
Fp=Cr+0.272*Fe+2.36*Al+2.22*Si+2.48*Ti+0.374*Mo+0.538*W−11.8*C   (3a) wherein Cr, Fe, Al, Si, Ti, Mo, W and C are the concentrations of the elements in question in mass-%.

2: The alloy according to claim 1, especially for all components that are used are in contact with the molten salt.

3: The alloy according to claim 1, wherein the alloy is usable up to a maximum temperature of 800° C.

4: The alloy according to claim 1, with a chromium content of >18 to 33%.

5: The alloy according to claim 1, with an aluminum content of 1.8 to 3.8%.

6: The alloy according to claim 1, with an iron content of 0.1 to 12.0%.

7: The alloy according to claim 1, with a silicon content of 0.001-<0.40%.

8: The alloy according to claim 1, with a manganese content of 0.001 to 0.50%.

9: The alloy according to claim 1, with a titanium content of 0.001 to 0.50%.

10: The alloy according to claim 1, with a carbon content of 0.01 to 0.10%.

11: The alloy according to claim 1, optionally with an yttrium content of 0.001 to 0.20%; a lanthanum content of 0.001 to 0.20%; a cerium content of 0.001 to 0.20%; a cerium mixed metal content of 0.001 to 0.20%; a zirconium content of 0.001 to 0.20%; and a hafnium content of 0.001 to 0.20%.

12. (canceled)

13. (canceled)

14. (canceled)

15: The alloy according to claim 1, optionally with a content of niobium of 0.0 to 1.1%, wherein the formula (3a) is supplemented by a term for Nb:
Fp=Cr+0.272*Fe+2.36*Al+2.22*Si+2.48*Ti+1.26*Nb+0.374*Mo+0.538*W−11.8*C  (3b) and Cr, Fe, Al, Si, Ti, Nb, Mo, W and C are the concentrations of the elements in question in mass-%.

16. (canceled)

17. (canceled)

18: The alloy according to claim 1, optionally with a content of boron of 0.0001 to 0.008%.

19: The alloy according to claim 1, optionally further containing 0.0 to 5.0% cobalt.

20: The alloy according to claim 1, further containing at most 0.5% copper, wherein the formula (3a) is supplemented by a term for Cu:
Fp=Cr+0.272*Fe+2.36*Al+2.22*Si+2.48*Ti+0.477*Cu+0.374*Mo+0.538*W−11.8*C  (3c). and Cr, Fe, Al, Si, Ti Cu, Mo, W and C are the concentrations of the elements in question in mass-%.

21: The alloy according to claim 1, further containing at most 0.5% vanadium

22: The alloy according to claim 1, wherein the impurities are adjusted in contents of max. 0.002% lead, max. 0.002% zinc, max. 0.002% tin.

23: The alloy according to claim 1, in which the following formula is satisfied and thus a particularly good processability is achieved: Fa□60 (4a) with Fa=Cr+20.4*Ti+201*C (5a) for an alloy without Nb, wherein Cr, Ti and C are the concentrations of the elements in question in mass-%, or with Fa=Cr+6.15*Nb+20.4*Ti+201*C (5b) for an alloy containing Nb, wherein Cr, Nb, Ti and C are the concentrations of the elements in question in mass-%.

24: The alloy according to claim 1, in which the following formula is satisfied and thus a particularly hot strength/creep strength is achieved: Fk≥47 (6a) with Fk=Cr+19*Ti+10.2*Al+12.5*Si+98*C (7a) for an alloy without B and Nb, wherein Cr, Ti, Al, Si and C are the concentrations of the elements in question in mass-%, or with Fk=Cr+19*Ti+34.3*Nb+10.2*Al+12.5*Si+98*C+2245*B (7b) for an alloy containing B and/or Nb, wherein Cr, Ti, Nb, Al, Si, C and B are the concentrations of the elements in question in mass-%.

25: A use of the alloy according to claim 1 as strip, sheet, wire, rod, longitudinally welded tube and seamless tube.

26: A use of the alloy according to claim 1 for the manufacture of strip, sheet, wire, rod, longitudinally welded tube and seamless tubes.

Description

EXAMPLES

[0284] Manufacture:

[0285] Tables 5a and 5b show the analyses of the batches smelted on the laboratory scale together with some batches of Alloy 602CA (N06025), Alloy 690 (N06690), Alloy 601 (N06601) smelted on the industrial scale according to the prior art and used for comparison. The batches according to the prior art are identified with a T and those according to the invention with an E. The batches smelted on the laboratory scale are marked with an L, the batches smelted on the industrial scale with a G.

[0286] The ingots of the alloys in Table 5a and b, smelted on the laboratory scale in vacuum, were annealed between 900° C. and 1270° C. for 8 hours and hot-rolled to a final thickness of 13 mm and 6 mm by means of hot rolling and further intermediate annealings between 900° C. and 1270° C. for 0.1 to 1 hour. The sheets produced in this way were solution-annealed between 900° C. and 1270° C. for 1 hour. The specimens needed for the measurements were manufactured from these sheets.

[0287] For the alloys smelted on the industrial scale, a sample was taken from the industrial-scale fabrication of a commercially fabricated sheet having appropriate thickness. The specimens needed for the measurements were manufactured from these sheets.

[0288] All alloy variants typically had a grain size of 70 to 505 m.

[0289] For the exemplary batches in Table 5a and b, the following properties were compared: [0290] Corrosion resistance in nitrate salt melts [0291] Phase stability [0292] The formability on the basis of the tension test at room temperature [0293] The hot strength/creep resistance by means of hot tension tests [0294] The corrosion resistance by means of an oxidation test [0295] Corrosion resistance in nitrate salt melts:

[0296] In the batches 2301 and 250129 to 250138 and 250147 to 250149, smelted on the laboratory scale, as well as the batches 250164, 250311 and 250526, aluminum is greater than or equal to 1.8%.

[0297] This aluminum content is sufficiently high, so that a closed aluminum oxide layer is able to form underneath the chromium oxide layer. Thus they meet the requirement that was imposed on the corrosion resistance in salt melts.

[0298] Phase stability:

[0299] For the chosen alloys according to the prior art in Table 4 and for all laboratory batches (Tables 5a and 5b), the phase diagrams were therefore calculated and the solvus temperature T.sub.s BCC was entered in Tables 4 and 5a. For the compositions in Tables 4 and 5a and b, the value for Fp was also calculated according to formula 3d. Fp becomes greater with increasing solvus temperature T.sub.s BCC. All examples of N06693 with a higher solvus temperature T.sub.s BCC higher than that of Alloy 10 have an Fp >39.9. The requirement Fp≤39.9 (formula 2a) is therefore a good criterion for achieving an adequate phase stability for an alloy. All laboratory batches in Tables 5a and b meet the criterion Fp≤39.9.

[0300] Formability (processability):

[0301] Offset yield strength R.sub.p0.2, the tensile strength R.sub.m and the elongation A.sub.5 for room temperature (RT) and for 600° C. are entered in Table 6, as is further the tensile strength R.sub.m for 800° C.

[0302] Moreover, the values for Fa and Fk are entered.

[0303] In Table 6, the exemplary batches 156817 and 160483 of the alloy according to the prior art, Alloy 602 CA, have a relatively small elongation A.sub.5 at room temperature of 36 and 42% respectively, which lie below the requirements for a good formability. Fa is greater than 60 and thus above the range that characterizes a good formability. All alloys according to the invention (E) exhibit an elongation greater than 50%. Thus they meet the requirements. Fa is smaller than 60 for all alloys according to the invention. Thus they lie in the range in which a good formability is ensured. The elongation is particularly high when Fa is relatively small.

[0304] Hot strength/creep strength

[0305] The exemplary batch 156656 of the alloy according to the prior art, Alloy 601 in Table 6, is an example of the minimum requirements of offset yield strength and tensile strength at 600° C. and 800° C.; in contrast, the exemplary batches 156817 and 160483 of the alloy according to the prior art, Alloy 602 CA, are examples of very good values of offset yield strength and tensile strength at 600° C. and 800° C. Alloy 601 represents a material that exhibits the minimum requirements of hot strength and creep strength that are described in relationships 8a to 8d. Alloy 602 CA represents a material that exhibits an outstanding hot strength and creep strength that are described in relationships 9a to 9d. For both alloys, the value for Fk is much larger than 47 and for Alloy 602 CA it is additionally even much higher than the value of Alloy 601, which reflects the elevated strength values of Alloy 602 CA. The alloys according to the invention (E) all exhibit an offset yield strength and tensile strength at 600° C. and 800° C. in the range of or clearly above that of Alloy 601, and therefore satisfy the relationships 8a to 8d. They lie in the range of the values of Alloy 602 CA and, with the exception of batch 250526 and batch 250311, also meet the desirable requirements, i.e. 3 of the 4 relationships 9a to 9d. Fk also is larger than 47 for all alloys according to the invention in the examples in Table 6, or larger than 54 and thus in the range that is characterized by a good hot strength and creep resistance. Among the laboratory batches that are not according to the invention, batches 2297 and 2300 are an example that does not satisfy the relationships 8a to 8d and also has an Fk smaller than 47.

[0306] Corrosion resistance in air:

[0307] Table 7 shows the specific changes in mass after an oxidation test at 1100° C. in air after 11 cycles of 96 hours, i.e. in total 1056 hours. In Table 7, the specific gross change in mass, the specific net change in mass and the specific change in mass of the spalled oxides after 1096 hours are indicated. The exemplary batches of the alloys according to the prior art, Alloy 601 and Alloy 690, exhibit a much higher gross change in mass than Alloy 602 CA, wherein that of Alloy 601 is in turn much larger than that of Alloy 690. Both form a chromium oxide layer that grows more rapidly than an aluminum oxide layer. Alloy 601 still contains approximately 1.3% Al. This content is too small in order to form an even only partly closed aluminum oxide layer, for which reason the aluminum in the interior of the metallic material is oxidized underneath the oxide layer (internal oxidation). This causes a large increase in mass in comparison with Alloy 690. Alloy 602CA contains approximately 2.3% aluminum. For this alloy, therefore, a closed aluminum oxide layer is able to form underneath the chromium oxide layer. This reduces the growth of the oxide layer markedly and thus also the specific increase in mass. All alloys according to the invention (E) contain at least 2% aluminum and therefore have a similarly small or smaller gross increase in mass than Alloy 602 CA. Also, all alloys according to the invention exhibit spalling in the range of the measurement accuracy, similarly to the exemplary batches of Alloy 602 CA, whereas Alloy 601 and Alloy 690 exhibit great spalling.

[0308] The claimed limits for the alloy “E” according to the invention can therefore be justified individually as follows: Too low chromium contents mean that the chromium concentration during use of the alloy in a corrosive atmosphere decreases very rapidly below the critical limit, so that a closed chromium oxide layer can no longer be formed. Therefore a content of >17% chromium is the lower limit. Too high chromium contents worsen the phase stability of the alloy, especially at the high aluminum contents of ≥1.8%. Therefore 33% chromium is to be regarded as the upper limit.

[0309] The formation of an aluminum oxide layer underneath the chromium oxide layer reduces the oxidation rate. Below 1.8% aluminum, the aluminum oxide layer is too incomplete to develop its effect fully. Too high aluminum contents impair the processability of the alloy. Therefore an aluminum content of <4.0% forms the upper limit.

[0310] The costs for the alloy increase with the reduction of the iron content. Below 0.1%, the costs rise disproportionally, since special primary material must be used. For cost reasons, therefore, 0.1% iron is to be regarded as the lower limit. With increase of the iron content, the phase stability is reduced (formation of embrittling phases), especially at high chromium and aluminum contents. Therefore 15% Fe is a practical upper limit in order to ensure the phase stability of the alloy according to the invention.

[0311] Silicon is needed for the manufacture of the alloy. A minimum content of 0.001% is therefore necessary. Too high contents in turn impair the processability and the phase stability, especially at high aluminum and chromium contents. The silicon content is therefore restricted to 0.50%.

[0312] A minimum content of 0.001% manganese is necessary for improvement of the processability. Manganese is limited to 2.0%, since this element reduces the oxidation resistance.

[0313] Titanium increases the high temperature strength. At 0.60% and above, the oxidation behavior may be impaired, which is why 0.60% is the maximum value.

[0314] Even very low magnesium contents and/or calcium contents improve the processing by the binding of sulfur, whereby the occurrence of low-melting nickel-sulfur eutectics is avoided. For magnesium and/or calcium, therefore, a minimum content of 0.0002% is necessary. At too high contents, intermetallic nickel-magnesium phases or nickel-calcium phases may occur, which again greatly worsen the processability. The magnesium content and/or calcium content is therefore limited to at most 0.05%.

[0315] A minimum content of 0.005% carbon is necessary for a good creep resistance. Carbon is limited to at most 0.12%, since above such a content this element reduces the processability by the excessive formation of primary carbides.

[0316] A minimum content of 0.001% nitrogen is necessary, whereby the processability of the material is improved. Nitrogen is limited to at most 0.05%, since the processability is reduced due to the formation of coarse carbonitrides.

[0317] The oxygen content must be smaller than or equal to 0.020%, in order to ensure the manufacturability of the alloy. A too low oxygen content increases the costs. The oxygen content is therefore ≥0.0001%.

[0318] The content of phosphorus should be smaller than or equal to 0.030%, since this surface-active element impairs the oxidation resistance. A too low phosphorus content increases the costs.

[0319] The phosphorus content is therefore ≥0.001%.

[0320] The content of sulfur should be adjusted as low as possible, since this surface-active element impairs the oxidation resistance. Therefore at most 0.010% sulfur is specified.

[0321] Molybdenum is limited to at most 2.0%, since this element reduces the oxidation resistance.

[0322] Tungsten is limited to at most 2.0%, since this element likewise reduces the oxidation resistance.

[0323] Nickel is the residual element. A too low nickel content reduces the phase stability, especially at high chromium contents.

[0324] Nickel must therefore be larger than or equal to 50%.

[0325] Beyond this, the following relationship must be satisfied in order that adequate phase stability is ensured:

Fp≤39.9 with  (2a)

Fp=Cr+0.272*Fe+2.36*Al+2.22*Si+2.48*Ti+0.374*Mo+0.538*W−11.8*C  (3a)

wherein Cr, Fe, Al, Si, Ti, Mo, W and C are the concentrations of the elements in question in mass-%. The limits for Fp and the possible incorporation of further elements have been justified in detail in the foregoing text.

[0326] If necessary, the oxidation resistance may be further improved with additions of oxygen-affine elements, such as, for example, yttrium, lanthanum, cerium, cerium mixed metal. These elements are incorporated in the oxide layer, where they block the paths of diffusion of the oxygen at the grain boundaries.

[0327] A minimum content of 0.001% yttrium is necessary to obtain the effect of the yttrium that increases the oxidation resistance.

[0328] For cost reasons, the upper limit is set to 0.20%.

[0329] A minimum content of 0.001% lanthanum is necessary to obtain the effect of the lanthanum that increases the oxidation resistance. For cost reasons, the upper limit is set to 0.20%.

[0330] A minimum content of 0.001% cerium is necessary to obtain the effect of the cerium that increases the oxidation resistance. For cost reasons, the upper limit is set to 0.20%.

[0331] A minimum content of 0.001% cerium mixed metal is necessary to obtain the effect of the cerium mixed metal that increases the oxidation resistance. For cost reasons, the upper limit is set to 0.20%.

[0332] If necessary, niobium may be added, since niobium also increases the high-temperature strength. Higher contents very greatly increase the costs. The upper limit is therefore set at 1.10%.

[0333] If necessary, the alloy may also contain tantalum, since tantalum also increases the high-temperature strength and the oxidation resistance. Higher contents very greatly increase the costs. The upper limit is therefore set at 0.60%. A minimum content of 0.001% is necessary in order to achieve an effect.

[0334] If necessary, the alloy may also contain zirconium. A minimum content of 0.001% zirconium is necessary to obtain the effect of the zirconium that increases the high-temperature strength and the oxidation resistance. For cost reasons, the upper limit is set to 0.20% zirconium.

[0335] If necessary, the alloy may also contain hafnium. A minimum content of 0.001% hafnium is necessary to obtain the effect of the hafnium that increases the high-temperature strength and the oxidation resistance. For cost reasons, the upper limit is set to 0.20% hafnium.

[0336] If necessary, boron may be added to the alloy, since boron improves the creep resistance. Therefore a content of at least 0.0001% should be present. At the same time, this surface-active element worsens the oxidation resistance. Therefore at most 0.008% boron is specified.

[0337] Cobalt up to 5.0% may be contained in this alloy. Higher contents markedly reduce the oxidation resistance.

[0338] Copper is limited to at most 0.5%, since this element reduces the oxidation resistance.

[0339] Vanadium is limited to at most 0.5%, since this element reduces the oxidation resistance.

[0340] Lead is limited to at most 0.002%, since this element reduces the oxidation resistance. The same is true for zinc and tin.

[0341] Furthermore, optionally the following relationship, which describes a particularly good processability, may be satisfied for the carbide-forming elements chromium, titanium and carbon:

Fa≤60 with  (4a)

Fa=Cr+20.4*Ti+201*C  (5a)

wherein Cr, Ti, and C are the concentrations of the elements in question in mass-%, The limits for Fa and the possible incorporation of further elements have been justified in detail in the foregoing text.

[0342] Furthermore, optionally the following relationship, which describes a particularly good hot strength and creep strength, may be satisfied between the elements that increase the strength:

Fk≤47 with  (6a)

Fk=Cr+19*Ti+10.2*Al+12.5*Si+98*C  (7a)

wherein Cr, Ti, Al, Si and C are the concentrations of the elements in question in mass. The limits for Fa and the possible incorporation of further elements have been justified in detail in the foregoing text.

TABLE-US-00001 TABLE 1 Alloys according to ASTM B 168-191), ASTM B167-182), ASTM B443-183), ASTM B 163-184), ASTM B622-155), ASTM B409-066). All values in mass-%, .sup.7) in no ASTM standard, from the UNS list. Legierung Ni Cr Co Mo W Nb Nb + Ta Fe Mn Al C Alloy 800H- 30.0- 19.0- 39.5 1.5 0.15- 0.05 N08810.sup.6) 4) 35.0 23.0 min max 0.60 0.10 Alloy 600- 72.0 14.0- 6.0- 1.0 0.15 N06600.sup.1)2)4) min 17.0 10.0 max max Alloy 601- 58.0- 21.0- Rest 1.0 1.0- 0.10 N06601.sup.1)2)4) 63.0 25.0 max 1.7 max Alloy 617- 44.5 20.0- 10.0- 8.0- 3.0 1.0 0.8- 0.05- N06617.sup.1)2) min 24.0 15.0 10.0 max max 1.5 0.15 Alloy 690- 58.0 27.0- 7.0- 0.5 0.05 N06690.sup.1)2)4) min 31.0 11.0 max max Alloy 693- Rest 27.0- 0.5- 2.5- 1.0 2.5- 0.15 N06693.sup.1)2) 31.0 2.5 6.0 max 4.0 max Alloy 602CA- Rest 24.0- 8.0- 0.15 1.8- 0.15- N06025.sup.1)2)4) 26.0 11.0 max 2.4 0.25 Alloy 603- Rest 24.0- 8.0- 0.15 2.4- 0.20- N06603.sup.1)2) 26.0 11.0 max 3.0 0.40 Alloy 699XA- Rest 26.0- 0.50 2.5 0.50 1.9- 0.005- N06699.sup.1)2)4) 30.0 max max max 3.0 0.10 Alloy 214 Rest 15.0- 2.0 0.50 0.50 2.0- 0.50 4.0- 0.05 N07214 .sup.7) 17.0 max max max 4.0 max 5.0 max Alloy 625- 58.0 20.0- 1.0 8.0- 3.15- 5.0 0.50 0.40 0.10 N06625 .sup.3) min 23.0 max 10.0 4.15 max max max max Alloy 120 35.0- 23.0- 3.0 2.50 2.50 0.4- Rest 1.50 0.04 0.20- N08120.sup.6)4) 39.0 27.0 max max max 0.9 max max 0.1 Alloy 242 Rest 7.0- 1.0 24.0- 2.5 0.80 0.05 0.03 N10242.sup.5) 9.0 max 26.0 max max max max Alloy 230 Rest 20.0- 4.0 0.30- 13.0- 3.0 0.80- 0.20- 0.05- N06230.sup.5) 24.0 max 3.0 15.0 max 1.0 0.50 0.15 Legierung Cu Si S Ti P Zr Y B N La Alloy 800H-N08810.sup.6) 4) 0.75 1.0 0.015 0.15- max max max 0.60 Alloy 600-N06600.sup.1)2)4) 0.5 0.5 0.015 max max max Alloy 601-N06601.sup.1)2)4) 0.5 0.5 0.015 max max max Alloy 617-N06617.sup.1)2) 1.0 0.5 0.015 0.6 0.006 max max max max max Alloy 690-N06690.sup.1)2)4) 0.5 1.0 0.015 max max max Alloy 693-N06693.sup.1)2) 0.5 0.5 0.01 1.0 max max max max Alloy 602CA- 0.1 0.5 0.010 0.1- 0.020 0.01- 0.05- N06025.sup.1)2)4) max max max 0.2 max 0.10 0.12 Alloy 603-N06603.sup.1)2) 0.50 0.5 0.010 0.01- 0.020 0.01- 0.01- max max max 0.25 max 0.10 0.15 Alloy 699XA- 0.50 0.50 0.01 0.60 0.02 0.10 0.008 0.05 N06699.sup.1)2)4) max max max max max max max max Alloy 214 N07214 .sup.7) max 0.015 0.50 0.015 max 0.002- 0.006 0.2 max max max 0.05 0.040 max Alloy 625-N06625 .sup.3) 0.50 0.015 0.40 0.015 max max max max Alloy 120 N08120.sup.6)4) 0.50 1.0 0.03 0.20 0.040 0.010 0.15- max max max max max max 0.30 Alloy 242 N10242.sup.5) 0.50 0.80 0.015 0.030 0.006 max max max max max Alloy 230 N06230.sup.5) 0.10 0.25- 0.015 0.030 0.015 0.005- max 0.75 max max max 0.05 Legierung = Alloy

TABLE-US-00002 TABLE 2 Composition in mass-% of the alloys investigated in (Kruizenga et al., Materials Corrosion of High Temperature Alloys Immersed in 600 C. Binary Nitrate Salt, Sandia Report, SAND 2013-2526, 2013). Legierung UNS Cr Mo Ni Mn Si Fe Co W Al Other Alloy214.sup.1) N07214 16 — 75 0.5 0.2 3 — — 4.5 Zr(0.1 max) Alloy224.sup.2) — 20.50 0.21 46.44 0.33 0.31 27.62 0.38 — 3.86 Ti(0.35) Alloy 625.sup.2) N06625 21.76 8.28 61.0 0.21 0.25 4.46 0.08 — 0.20 Nb(3.38), Ti (0.24) Alloy 120.sup.2) N08120 24.91 0.27 37 0.68 0.50 36.41 0.15 — 0.08 Alloy242.sup.2) N10242 8.05 24.79 65.44 0.29 — 1.24 — — 0.13 Cu(0.06) Alloy230.sup.2) N02230 22.37 1.27 59.41 0.49 0.42 1.32 0.19 14.16 0.32 Cu(0.05) Legierung = Alloy .sup.1)nominal compositions of alloys, .sup.2)actual composition tested from heat

TABLE-US-00003 TABLE 3 Corrosion after 3000 hours in 60% sodium nitrate/40% potassium nitrate salt melt of the alloys investigated in [Kruizenga et al., 2013, Materials Corrosion of High Temperature Alloys Immersed in 600° C. Binary Nitrate Salt]. Metal loss Density Descaling loss μm/year Dichte Entzunderungsverlust.sup.1) Metallverlust.sup.1) Alloy Cr Al Si [g/cm.sup.3] [mg/cm.sup.2] [μm/Jahr] Alloy 214 N07208 16 4.5 0.2 8.05 1.56 5.7 Alloy 224 — 20.5 3.86 0.31 8.sup.a) 2.27 8.3 Alloy 625 N06625 21.76 0.20 0.25 8.44 4.86 16.8 Alloy 120 N08120 24.91 0.08 0.50 8.07 4.97 18 Alloy 242 N10242 8.05 0.13 — 9.05 5.88 18.98 Alloy 230 N02230 22.37 0.31 0.42 8.97 7.25 23.6 .sup.1)nach 3000 Stunden; .sup.a)Dichte angenommen. .sup.1)After 3000 hours; .sup.a)Density assumed.

TABLE-US-00004 TABLE 4 Typical compositions of some alloys according to ASTM B 168-11. and Table 2 (prior art). Legierung Charge C S Cr Ni Mn Si Mo Ti Nb Alloy 600 164310 0.07 0.002 15.8 73.8 0.28 0.32 — 0.2 — N06600 Alloy 601 156656 0.053 0.0016 22.95 59.58 0.72 0.24 — 0.47 — N06601 Alloy 690 111389 0.022 0.002 28.45 61.95 0.12 0.32 — 0.29 — N06690 Alloy 693  Alloy 10 *) 0.015 ≤0.01 29.42 60.55 0.014 0.075 — 0.02 1.04 N06693 Alloy 693 Alloy 8 *) 0.007 ≤0.01 30.00 60.34 0.11 0.38 — 0.23 1.13 N06693 Alloy 693 Alloy 3 *) 0.009 ≤0.01 30.02 57.79 0.01 0.14 — 0.02 2.04 N06693 Alloy 693 Alloy 2 *) 0.006 ≤0.01 30.01 60.01 0.12 0.14 — 0.01 0.54 N06693 Alloy 602 163968 0.170 ≤0.01 25.39 62.12 0.07 0.07 — 0.13 N06025 Alloy 603 52475 0.225 0.002 25.20 61.6 0.09 0.03 — 0.16 0.01 N06603 Alloy 214 16 75 0.5 0.2 — N07214 Alloy 224 20.5 46.44 0.33 0.31 0.21 0.35 T.sub.s sec Legierung Cu Fe P Al Zr Y B Co in ° C. Fp Alloy 600 0.01 9.42 0.009 0.16 — — 0.001 — — 19.1 N06600 Alloy 601 0.04 14.4 0.008 1.34 0.015 0 0.001 — 669 31.2 N06601 Alloy 690 0.01 8.45 0.005 0.31 — 0 0 — 720 32.7 N06690 Alloy 693 0.03 5.57 — 3.2 — — 0.002 — 939 39.9 N06693 Alloy 693 0.03 4.63 — 3.08 — — 0.002 — 979 41.3 N06693 Alloy 693 0.03 5.57 — 4.3 — — 0.002 — 1079 44.5 N06693 Alloy 693 0.03 5.80 — 3.27 — — 0.002 — 948 40.3 N06693 Alloy 602 0.01 9.47 0.008 2.25 0.08 0.08 0.005 — 690 31.8 N06025 Alloy 603 0.01 9.6 0.007 2.78 0.07 0.08 0.003 — 707 32.2 N06603 Alloy 214 3 — 4.5 0.1 — — 542 27.9 N07214 Alloy 224 27.62 — 3.86 — — 0.38 819 38.3 All values in mass-% *) Alloy composition from US Patent 4,88,125 Table 1. Legierung = Alloy; Charge = Batch

TABLE-US-00005 TABLE 5a Composition of the laboratory batches, Part 1. Name Chg C N Cr Ni Mn Si Mo Ti T G Alloy 602 CA 156817 0.171 0.036 25.2 62.1 0.06 0.07 0.01 0.17 T G Alloy 602 CA 160483 0.172 0.025 25.7 62.0 0.06 0.05 0.02 0.14 T G Alloy 601 156856 0.053 0.018 23.0 59.6 0.72 0.24 0.04 0.47 T G Alloy 690 80116 0.010 0.025 27.8 62.8 0.18 0.15 0.01 0.31 T G Alloy 690 111389 0.022 0.024 28.5 62.0 0.12 0.82 <0.01 0.29 L Cr30Al1La 2297 0.018 0.023 29.9 68.0 0.25 0.09 <0.01 <0.01 L Cr30Al1LaT 2300 0.019 0.021 30.2 67.5 0.25 0.08 <0.01 <0.01 L Cr30Al1TiLa 2298 0.018 0.022 29.9 67.5 0.25 0.08 <0.01 0.3 L Cr30Al1TiNbLa 2308 0.017 0.028 30.1 67.1 0.25 0.08 <0.01 0.31 L Cr30Al1CLaTi 2299 0.060 0.021 30.1 67.6 0.25 0.09 <0.01 0.01 L Cr30Al1CLa 2302 0.049 0.02 30.1 67.1 0.28 0.09 <0.01 <0.01 E L Cr30Al2La 2301 0.015 0.021 30.2 66.6 0.25 0.08 <0.01 <0.01 L Cr30Al1Ti 250060 0.017 0.027 29.5 67.9 0.24 0.11 <0.01 0.31 L Cr30Al1Ti 250063 0.017 0.024 29.9 67.4 0.25 0.10 <0.01 0.31 L Cr30Al1TiNb 250066 0.016 0.022 29.9 67.1 0.24 0.09 <0.01 0.31 L Cr30Al1TiNb 250065 0.017 0.025 30.3 67.1 0.24 0.10 0.01 0.3 L Cr30Al1TiNbZr 250067 0.019 0.020 29.7 67.2 0.25 0.10 0.02 0.31 L Cr30Al1TiNb 250068 0.017 0.024 29.8 66.6 0.25 0.09 0.01 0.31 E L Cr28Al2 250129 0.018 0.025 28.2 68.3 0.25 0.10 <0.01 <0.01 E L Cr28Al2Y 250130 0.022 0.022 28.1 68.6 0.25 0.07 <0.01 <0.01 E L Cr28Al2YC1 250132 0.059 0.022 28.3 68.2 0.27 0.06 <0.01 <0.01 E L Cr28Al2Nb.5C1 250133 0.047 0.022 28.3 67.7 0.25 0.06 0.01 <0.01 E L Cr28Al2Nb.5C1 250148 0.049 0.019 27.9 67.9 0.25 0.07 <0.01 <0.01 E L Cr28Al21C1 250134 0.048 0.026 28.2 67.1 0.25 0.09 0.02 <0.01 E L Cr28Al21C1 250147 0.045 0.017 28.4 67.5 0.27 0.07 0.02 <0.01 E L Cr28Al21C1Y 250149 0.054 0.020 27.9 67.2 0.27 0.06 0.01 <0.01 E L Cr28Al2TiC1 250137 0.063 0.024 28.2 67.7 0.27 0.09 <0.01 0.15 E L Cr28Al2TiC1 250138 0.053 0.018 28.3 68.4 0.27 0.05 <0.01 0.16 E L Cr25Fe9Al3Y 250164 0.065 0.004 25.42 61.44 0.09 0.09 0.01 <0.01 E L Cr25Fe9Al3C1YZrTi 250311 0.063 0.023 25.45 61.80 0.06 0.06 0.01 0.15 E L Cr29Al2NbFe4 250526 0.020 0.033 29.72 63.88 0.04 0.05 0.01 0.01 T.sub.s sec Name Chg Nb Cu Fe Al W in ° C. Fp T G Alloy 602 CA 156817 <0.01 0.01 9.6 2.36 — 683 31.9 T G Alloy 602 CA 160483 0.01 0.01 9.4 2.17 — 683 31.8 T G Alloy 601 156856 0.01 0.04 14.4 1.34 0.01 669 31.2 T G Alloy 690 80116 <0.01 0.01 8.5 0.14 — 683 31.4 T G Alloy 690 111389 0.01 0.01 8.5 0.31 — 720 32.7 L Cr30Al1La 2297 <0.01 <0.01 0.56 1.04 <0.01 737 32.5 L Cr30Al1LaT 2300 <0.01 <0.01 0.54 1.3 <0.01 737 33.3 L Cr30Al1TiLa 2298 <0.01 <0.01 0.55 1.28 <0.01 759 33.8 L Cr30Al1TiNbLa 2308 0.28 <0.01 0.53 1.25 0.01 772 34.3 L Cr30Al1CLaTi 2299 <0.01 <0.01 0.54 1.25 0.01 780 32.7 L Cr30Al1CLa 2302 <0.01 <0.01 0.57 1.65 <0.01 780 33.8 E L Cr30Al2La 2301 <0.01 <0.01 0.54 2.25 <0.01 809 35.6 L Cr30Al1Ti 250060 <0.01 <0.01 0.54 1.15 0.01 759 33.3 L Cr30Al1Ti 250063 <0.01 <0.01 0.53 1.39 <0.01 759 34.2 L Cr30Al1TiNb 250066 0.31 <0.01 0.50 1.42 0.01 772 34.6 L Cr30Al1TiNb 250065 0.31 <0.01 0.05 1.41 0.01 768 34.8 L Cr30Al1TiNbZr 250067 0.31 <0.01 0.53 1.47 0.01 776 34.4 L Cr30Al1TiNb 250068 0.88 <0.01 0.53 1.43 0.02 799 35.2 E L Cr28Al2 250129 <0.01 0.01 0.57 2.51 <0.01 740 34.3 E L Cr28Al2Y 250130 <0.01 <0.01 0.51 2.61 <0.01 766 34.3 E L Cr28Al2YC1 250132 0.01 0.02 0.60 2.61 0.02 762 34.1 E L Cr28Al2Nb.5C1 250133 0.50 0.02 0.52 2.76 0.02 800 35.2 E L Cr28Al2Nb.5C1 250148 0.56 0.03 0.48 2.62 0.01 779 34.5 E L Cr28Al21C1 250134 1.06 0.03 0.48 2.84 0.02 850 36.1 E L Cr28Al21C1 250147 0.90 0.02 0.43 2.15 0.02 774 34.3 E L Cr28Al21C1Y 250149 1.04 0.03 0.45 2.64 <0.01 800 35.1 E L Cr28Al2TiC1 250137 <0.01 0.03 0.5 2.88 <0.01 788 34.9 E L Cr28Al2TiC1 250138 <0.01 0.03 0.45 2.62 0.01 774 34.5 E L Cr25Fe9Al3Y 250164 <0.01 <0.01 9.74 3.00 — 770 28.4 E L Cr25Fe9Al3C1YZrTi 250311 0.01 <0.01 9.46 2.50 — 748 28.0 E L Cr29Al2NbFe4 250526 0.15 0.01 4.00 2.04 <0.01 — 31.8 All values in mass-% (T: alloy according to the prior art, E: alloy according to the invention, L: smelted on the laboratory scale, G: smelted on the industrial scale). Chg = Batch

TABLE-US-00006 TABLE 5b Composition of the laboratory batches, Part 2. Name Chg S P Mg Ca V Zr Co T G Alloy 602 CA 156817 0.002 0.005 0.004 0.001 0.03 0.08 0.05 T G Alloy 602 CA 160483 <0.002 0.007 0.010 0.002 — 0.09 0.04 T G Alloy 601 156856 0.002 0.008 0.012 <0.01 0.03 0.015 0.04 T G Alloy 690 80116 0.002 0.006 0.030 0.0009 — <0.002 0.02 T G Alloy 690 111389 0.002 0.005 <0.001 0.0005 — — 0.01 L Cr30Al1La 2297 0.004 0.003 0.015 <0.01 <0.01 <0.002 — L Cr30Al1LaT 2300 0.003 0.002 0.014 <0.01 <0.01 <0.002 <0.001 L Cr30Al1TiLa 2298 0.004 0.002 0.016 <0.01 <0.01 <0.002 <0.001 L Cr30Al1TiNbLa 2308 0.002 0.002 0.014 <0.01 <0.01 <0.002 — L Cr30Al1CLaTi 2299 0.003 0.002 0.015 <0.01 <0.01 <0.002 <0.001 L Cr30Al1CLa 2302 0.003 0.002 0.013 <0.01 <0.01 <0.002 0.001 E L Cr30Al2La 2301 0.003 0.002 0.015 <0.01 <0.01 <0.002 <0.001 L Cr30Al1Ti 250060 0.003 0.002 0.009 <0.01 <0.01 <0.002 <0.001 L Cr30Al1Ti 250063 0.003 0.003 0.012 <0.01 <0.01 <0.002 <0.001 L Cr30Al1TiNb 250066 0.002 0.002 0.012 <0.01 <0.01 <0.002 <0.001 L Cr30Al1TiNb 250065 0.002 0.002 0.012 <0.01 <0.01 <0.002 <0.001 L Cr30Al1TiNbZr 250067 0.003 0.002 0.010 <0.01 <0.01 0.069 <0.001 L Cr30Al1TiNb 250068 0.002 <0.002 0.010 <0.01 <0.01 <0.002 <0.001 E L Cr28Al2 250129 0.004 0.003 0.011 0.0002 <0.01 <0.002 — E L Cr28Al2Y 250130 0.003 0.003 0.013 <0.0002 <0.01 <0.002 — E L Cr28Al2YC1 250132 0.003 0.004 0.009 0.0012 0.01 0.003 <0.01 E L Cr28Al2Nb.5C1 250133 0.005 0.003 0.009 0.0012 <0.01 0.004 0.01 E L Cr28Al2Nb.5C1 250148 0.004 0.004 0.010 0.0005 0.01 — <0.01 E L Cr28Al21C1 250134 0.006 0.002 0.009 0.0009 <0.01 0.006 0.01 E L Cr28Al21C1 250147 0.002 0.002 0.010 0.0005 <0.01 0.01 0.01 E L Cr28Al21C1Y 250149 0.004 0.005 0.013 <0.0005 <0.01 0.006 <0.01 E L Cr28Al2TiC1 250137 0.005 0.004 0.008 0.0002 <0.01 0.004 <0.01 E L Cr28Al2TiC1 250138 0.005 0.004 0.010 0.0002 <0.01 0.003 0.01 E L Cr25Fe9Al3Y 250164 0.004 0.002 0.022 <0.001 <0.01 <0.01 0.01 E L Cr25Fe9Al3C1YZrTi 250311 0.002 0.002 0.010 <0.001 <0.01 0.09 0.01 E L Cr29Al2NbFe4 250526 0.003 0.002 0.012 <0.001 <0.01 <0.001 <0.01 Name Chg Y La B Hf Ta Ce O T G Alloy 602 CA 156817 0.060 — 0.003 — — — 0.001 T G Alloy 602 CA 160483 0.070 — 0.003 — — — 0.001 T G Alloy 601 156856 — — 0.001 — — — 0.0001 T G Alloy 690 80116 — — 0.002 — — — 0.0005 T G Alloy 690 111389 — — — — — — 0.001 L Cr30Al1La 2297 <0.001 0.062 <0.001 <0.001 <0.005 0.001 0.0001 L Cr30Al1LaT 2300 <0.001 0.051 <0.001 <0.001 <0.005 0.001 0.001 L Cr30Al1TiLa 2298 <0.001 0.058 <0.001 <0.001 <0.005 0.001 0.002 L Cr30Al1TiNbLa 2308 <0.001 0.093 <0.001 <0.001 <0.005 0.001 0.002 L Cr30Al1CLaTi 2299 <0.001 0.064 <0.001 <0.001 <0.005 0.001 0.002 L Cr30Al1CLa 2302 <0.001 0.057 <0.001 <0.001 <0.005 0.001 0.0001 E L Cr30Al2La 2301 <0.001 0.058 <0.001 <0.001 <0.005 0.001 0.002 L Cr30Al1Ti 250060 <0.001 <0.001 <0.001 <0.001 <0.005 <0.001 0.003 L Cr30Al1Ti 250063 <0.001 <0.001 <0.001 <0.001 <0.005 <0.001 0.003 L Cr30Al1TiNb 250066 <0.001 <0.001 <0.001 <0.001 <0.005 <0.001 0.004 L Cr30Al1TiNb 250065 <0.001 <0.001 <0.001 <0.001 <0.005 <0.001 0.005 L Cr30Al1TiNbZr 250067 <0.001 <0.001 <0.001 <0.001 <0.005 <0.001 0.003 L Cr30Al1TiNb 250068 <0.001 <0.001 <0.001 <0.001 <0.005 <0.001 0.004 E L Cr28Al2 250129 — — <0.0005 — — — 0.001 E L Cr28Al2Y 250130 0.063 — <0.0005 — — — 0.001 E L Cr28Al2YC1 250132 0.07 — 0.001 — — — 0.001 E L Cr28Al2Nb.5C1 250133 0.01 — — — — — 0.001 E L Cr28Al2Nb.5C1 250148 <0.01 — — — — — 0.003 E L Cr28Al21C1 250134 0.01 — <0.0005 — — — 0.003 E L Cr28Al21C1 250147 0.01 — 0.0012 — — — 0.001 E L Cr28Al21C1Y 250149 0.08 — 0.0012 — — — 0.002 E L Cr28Al2TiC1 250137 <0.01 — 0.0012 — — — 0.001 E L Cr28Al2TiC1 250138 <0.01 — 0.0012 — — — 0.004 E L Cr25Fe9Al3Y 250164 0.05 — 0.001 — — — 0.001 E L Cr25Fe9Al3C1YZrTi 250311 0.08 — 0.003 — — — 0.002 E L Cr29Al2NbFe4 250526 0 — 0.003 — — — 0.003 All values in mass-% (The following values apply for all alloys: Pb: max. 0.002%, Zn: max. 0.002%, Sn: max. 0.002%) (See Table 5a for the meaning of T, E, G, L). Chg = Batch

TABLE-US-00007 TABLE 6 Results of the tension tests at room temperature (RT), 600° C. and 800° C. The forming speed was 8.33 10.sup.−5 s.sup.−1 (0.5%/min) for R.sub.p0.2 and 8.33 10.sup.−4 s.sup.−1 (5%/min) for R.sub.m; KG in R.sub.p0.2 in R.sub.m in A.sub.s in R.sub.p0.2 in MPa R.sub.m in MPa A.sub.s in % R.sub.p0.2 in MPa R.sub.m in MPa Name Chg μm MPa RT MPa RT % RT 600° C. 600° C. 600° C. 800° C. 800° C. Fa Fk T Alloy 602 CA 156817 76 292 699 36 256 578 41 186 198 63.0 76.9 T Alloy 602 CA 160483 76 840 721 42 254 699 69 186 197 62.2 79.6 T Alloy 601 156856 136 238 645 53 154 509 54 133 136 43.3 56.3 T Aloy 690 80116 92 279 641 66 195 469 48 135 154 36.2 41.6 T Alloy 690 111389 72 285 630 50 188 465 51 36.8 43.6 Cr30Al1La 2297 233 221 637 67 131 460 61 134 167 33.5 43.4 Cr30Al1LaT 2300 205 229 650 71 131 469 65 132 160 33.9 46.3 Cr30Al1TiLa 2298 94 351 704 69 228 490 31 149 161 39.7 51.5 Cr30Al1TiNbLa 2308 90 288 683 55 200 508 39 174 181 41.6 61.0 Cr30Al1CLaTi 2299 253 258 661 62 212 475 69 181 185 42.3 50.0 Cr30Al1CLa 2302 212 853 673 59 233 480 59 189 194 40.0 52.9 E Cr30Al2La 2301 155 375 716 66 298 504 49 275 277 33.2 55.6 Cr30Al1Ti 250060 114 252 662 67 183 509 62 143 154 39.3 50.4 Cr30Al1Ti 250063 118 3252 659 70 178 510 57 148 152 39.6 52.9 Cr30Al1TiNb 250066 121 240 666 67 186 498 66 245 255 41.4 53.6 Cr30Al1TiNb 250065 132 285 685 61 213 521 58 264 265 41.8 64.0 Cr30Al1TiNbZr 250067 112 287 692 67 227 532 65 280 280 41.6 64.2 Cr30Al1TiNb 250068 174 261 666 69 205 498 65 297 336 44.9 83.2 E Cr28Al2 250129 269 334 674 66 191 224 31.8 56.8 E Cr28Al2Y 250130 167 322 693 63 252 522 53 220 244 32.6 57.9 E Cr28Al2YC1 250132 189 301 669 65 226 226 40.2 64.0 E Cr28Al2Nb.5C1 250133 351 399 725 57 334 522 33 285 363 40.8 78.9 E Cr28Al2Nb.5C1 250148 365 353 704 60 284 523 58 259 344 41.2 79.5 E Cr28Al21C1 250134 384 448 794 59 410 579 28 343 377 44.4 99.4 E Cr28Al21C1 250147 350 372 731 57 306 547 49 309 384 43.0 89.1 E Cr28Al21C1Y 250149 298 415 784 53 339 528 27 340 400 45.1 99.2 E Cr28Al2TiC1 250137 142 379 745 59 327 542 29 311 314 44.0 70.4 E Cr28Al2TiC1 250138 224 348 705 61 278 510 46 247 296 42.2 66.5 E Cr25Fe9Al3Y 250164 117 363 731 61 310 496 28 209 210 42.2 66.7 E Cr25Fe9Al3C1YZrTi 250311 505 270 678 60 207 489 56 203 211 38.1 64.6 E Cr29Al2NbFe4 250526 111 313 702 64 203 521 63 147 33.7 59.9 Chg = Batch; KG = grain size

TABLE-US-00008 TABLE 7 Results of the oxidation tests at 1000° C. in air after 1056 hours. Batch m.sub.gross m.sub.net Test no. m.sub.grutto m.sub.netto m  Versuch in in in Name Chg Nr g/m.sup.2 g/m.sup.2 g/m.sup.2 T Alloy 602 CA 160483 412 8.66 7.83 0.82 T Alloy 602 CA 160483 425 5.48 5.65 −0.18 T Alloy 601 156125 403 51.47 38.73 12.74 T Alloy 690 111389 412 23.61 7.02 18.59 T Alloy 690 111389 421 30.44 −5.70 36.14 T Alloy 690 111389 425 28.41 −0.68 29.09 Cr30Al1La 2297 412 36.08 −7.25 43.33 Cr30Al1LaT 2300 412 41.38 −2.48 43.86 Cr30Al1TiLa 2298 412 49.02 −30.59 79.61 Cr30Al1TiNbLa 2306 412 40.43 16.23 24.20 Cr30Al1CLaTi 2308 412 42.93 −15.54 58.47 Cr30Al1CLa 2299 412 30.51 0.08 30.44 Cr30Al2La 2302 412 27.25 9.57 17.68 E Cr30Al1Ti 2301 412 8.43 6.74 1.69 Cr30Al1Ti 250060 421 43.30 −19.86 63.17 Cr30Al1TiNb 250063 421 32.81 −22.15 54.96 Cr30Al1TiNb 250066 421 26.93 −16.35 43.28 Cr30Al1TiNbZr 250065 421 25.85 −24.27 50.12 Cr30Al1TiNb 250067 421 41.59 −15.56 57.16 Cr28Al2 250068 421 42.69 −39.25 81.95 E Cr28Al2Y 250129 425 3.72 3.55 0.16 E Cr28Al2YC1 250130 425 4.68 4.90 −0.23 E Cr28Al2Nb.5C1 250132 425 3.94 5.01 −1.07 E Cr28Al2Nb.5C1 250133 425 2.56 3.98 −1.42 E Cr28Al21C1 250148 425 3.15 3.21 −0.07 E Cr28Al21C1 250134 425 3.34 4.23 −0.89 E Cr28Al21C1Y 250147 425 2.72 2.62 0.10 E Cr28Al2TiC1 250149 425 8.44 3.84 −0.40 E Cr28Al2TiC1 250137 425 3.62 4.24 −0.62 E Cr30Al1La 250138 425 3.87 4.28 −0.41 E Cr25Fe9Al3Y 250164 427 5.96 4.53 1.43 E Cr25Fe9Al3C1YZrTi 250311 449 4.11 4.53 −0.42 E Cr29Al2NbFe4 250526 453 5.26 4.99 0.26 indicates data missing or illegible when filed