EP3102712B1 - Alliage nickel-chrome-titane-aluminium durcissant par trempe et présentant une bonne résistance à l'usure, au fluage et à la corrosion, et une bonne usinabilité - Google Patents

Alliage nickel-chrome-titane-aluminium durcissant par trempe et présentant une bonne résistance à l'usure, au fluage et à la corrosion, et une bonne usinabilité Download PDF

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EP3102712B1
EP3102712B1 EP15704949.5A EP15704949A EP3102712B1 EP 3102712 B1 EP3102712 B1 EP 3102712B1 EP 15704949 A EP15704949 A EP 15704949A EP 3102712 B1 EP3102712 B1 EP 3102712B1
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resistance
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EP3102712A2 (fr
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Heike Hattendorf
Jutta KLÖWER
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VDM Metals International GmbH
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    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
    • C22C19/053—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 30% but less than 40%
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
    • C22C19/055—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 20% but less than 30%
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C19/00—Alloys based on nickel or cobalt
    • C22C19/03—Alloys based on nickel or cobalt based on nickel
    • C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
    • C22C19/058—Alloys based on nickel or cobalt based on nickel with chromium without Mo and W
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01L—CYCLICALLY OPERATING VALVES FOR MACHINES OR ENGINES
    • F01L3/00—Lift-valve, i.e. cut-off apparatus with closure members having at least a component of their opening and closing motion perpendicular to the closing faces; Parts or accessories thereof
    • F01L3/02—Selecting particular materials for valve-members or valve-seats; Valve-members or valve-seats composed of two or more materials

Definitions

  • the invention relates to a nickel-chromium-titanium-aluminum wrought alloy with very good wear resistance, at the same time very good high temperature corrosion resistance, good creep resistance, and good processability.
  • Austenitic, thermosetting nickel-chromium-titanium-aluminum alloys with different nickel, chromium, titanium and aluminum contents have long been used for exhaust valves of engines.
  • a good wear resistance, a good heat resistance / creep resistance, a good fatigue strength and a good high-temperature corrosion resistance (especially in exhaust gases) is required.
  • DIN EN 10090 specifies austenitic alloys for exhaust valves, of which nickel alloys 2.4955 and 2.4952 (NiCr20TiAl) have the highest hot and creep strengths of all alloys specified in this standard.
  • Table 1 shows the composition of the nickel alloys mentioned in DIN EN 10090
  • Tables 2 to 4 show the tensile strengths, the 0.2% proof stress and creep resistance values after 1000 h.
  • NiCr20TiAl has significantly higher tensile strengths, 0.2% yield strengths and higher creep rupture strength than NiFe25Cr20NbTi.
  • the EP 0 639 654 A2 discloses an iron-nickel-chromium alloy consisting of (in weight%) up to 0.15% C, up to 1.0% Si, up to 3.0% Mn, 30 to 49% Ni, 10 to 18% Cr, 1.6 to 3.0% Al, one or more elements from the group IVa to Va with a total content of 1.5 to 8.0%, remainder Fe and unavoidable impurities, where Al is an indispensable additional element and one or more elements from the already mentioned group IVa to Va, the following formula must satisfy in atom%: 0.45 ⁇ Al / (Al + Ti + Zr + Hf + V + Nb + Ta) ⁇ 0.75
  • the WO 2008/007190 A2 discloses a wear resistant alloy consisting of (in weight%) 0.15 to 0.35% C, up to 1.0% Si, up to 1.0% Mn,> 25 to ⁇ 40% Ni, 15 to 25 % Cr, up to 0.5% Mo, up to 0.5% W,> 1.6 to 3.5% Al,> 1.1% to 3% in the sum Nb + Ta, up to 0.015% B, balance Fe and unavoidable impurities, where Mo + 0.5W ⁇ 0.75%; Ti + Nb ⁇ 4.5% and 13 ⁇ (Ti + Nb) / C ⁇ 50.
  • the alloy is particularly useful for the manufacture of exhaust valves for internal combustion engines.
  • the good wear resistance of this alloy is based on the high proportion of primary carbides that form due to the high carbon content. However, a high proportion of primary carbides causes processing problems in the production of this alloy as a wrought alloy.
  • the hot strength or creep strength is in the range of 500 ° C to 900 ° C on the additions of aluminum, titanium and / or Niobium (or other elements such as Ta, ..) which lead to the elimination of the ⁇ 'and / or ⁇ "phase
  • the high strength or the creep strength by high levels of solid solution strengthening elements such as chromium, aluminum, silicon, molybdenum and Tungsten improves, as well as by a high carbon content.
  • alloys with a chromium content around 20% form a chromium oxide layer (Cr 2 O 3 ) protecting the material.
  • 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 improves 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 cobalt and nickel oxides.
  • a maximum of 0.5% vanadium may be present in the alloy.
  • Preferred additional ranges can be set with Cr + Fe + Co ⁇ 27 % Cr + Fe + Co ⁇ 28 % Cr + Fe + Co ⁇ 29 %
  • Preferred additional ranges can be set with fh ⁇ 1 % fh ⁇ 3 % fh ⁇ 4 % fh ⁇ 5 % fh ⁇ 6 % fh ⁇ 7 %
  • the alloy of the present invention is preferably melted in the vacuum induction furnace (VIM), but may be melted open, followed by treatment in a VOD or VLF plant. After casting in blocks or possibly as a continuous casting, the alloy is optionally annealed at temperatures between 600 ° C and 1100 ° C for 0.1 to 100 hours, if necessary under inert gas, such as. As argon or hydrogen, followed by a cooling in air or in the moving annealing atmosphere. Thereafter, a remelting by means of VAR or ESU, possibly followed by a second remelting process by means of VAR or ESU.
  • VIM vacuum induction furnace
  • the blocks are optionally annealed at temperatures between 900 ° C and 1270 ° C for 0.1 to 70 hours, then hot formed, possibly with one or more intermediate anneals between 900 ° C and 1270 ° C for 0.05 hours to 70 hours.
  • Hot working can be done, for example, by forging or hot rolling.
  • the surface of the material may also be removed (also several times) in the process from time to time and / or at the end for cleaning chemically (eg by pickling) and / or mechanically (eg by machining, by blasting or by grinding) become.
  • the leadership of the thermoforming process can be carried out so that the semi-finished already recrystallized with particle sizes between 5 and 100 microns, preferably between 5 and 40 microns, is present.
  • inert gas such as. As argon or hydrogen
  • a cold forming for example, rolling, drawing, hammering, embossing, pressing
  • degrees of deformation up to 98% in the desired semi-finished mold possibly with intermediate annealing between 700 ° C and 1270 ° C for 0.1 min to 70 hours, if necessary under inert gas, such.
  • the final properties reach the alloys according to the invention, or the parts produced therefrom, by annealing between 600 ° C. and 900 ° C. for 0.1 to 300 hours, followed by air and / or oven cooling.
  • the alloy according to the invention is cured by precipitation of a finely divided ⁇ 'phase.
  • a two-stage anneal may be performed in which the first anneal is in the range of 800 ° C to 900 ° C for 0.1 to 300 hours, followed by air cooling and / or furnace cooling and a second anneal between 600 ° C and 800 ° C for 0.1 to 300 hours followed by air cooling.
  • 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 a mean grain size of 3 ⁇ m to 600 ⁇ m.
  • the preferred range is between 5 ⁇ m and 70 ⁇ m, in particular between 5 and 40 ⁇ m.
  • the alloy of the invention can be well by means of forging, upsetting hot extrusion, hot rolling u. ⁇ . process processes. By means of these methods u. a. Manufacture components such as valves, hollow valves or bolts.
  • the alloy according to the invention should preferably be used in areas for valves, in particular exhaust valves of internal combustion engines. But also a use in components of gas turbines, as fastening bolts, in springs and in turbochargers is possible.
  • the parts produced from the alloy according to the invention in particular z.
  • As the valves or the valve seat surfaces can be subjected to further surface treatments such. As one, nitriding to increase the wear resistance on.
  • the force measuring module (s) is the more accurate one.
  • the volume loss of the pin was measured and used as a measure of the wear resistance rating of the pin material.
  • the hot strength was determined in a hot tensile test according to DIN EN ISO 6892-2.
  • the yield strength R p0.2 and the tensile strength R m were determined.
  • 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 was placed in a tensile testing machine at room temperature and heated to the desired temperature with no tensile force. After reaching the test temperature, the sample was held without load for one hour (600 ° C) or two hours (700 ° C to 1100 ° C) for temperature compensation. Thereafter, the tensile load was applied to the sample to maintain the desired strain rates and testing was begun.
  • 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 800 ° C in air, the test being interrupted every 96 hours and the mass changes of the samples determined by the oxidation.
  • the samples were placed in the ceramic crucible in the experiment, so that possibly chipping 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 sample is the gross mass change of the 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 performed. 3 samples were removed from each batch, the values given are the mean values of these 3 samples.
  • 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. This makes it possible to identify phases whose formation in the area of application embrittles the material.
  • the temperature ranges can be identified in which z. B. the thermoforming should not take place because it forms phases that strongly solidify the material and thus lead to cracking during thermoforming. For a good processability, especially in the hot forming, such.
  • the new material is said to have better wear resistance than the reference alloy NiCr20TiAl.
  • Stellite 6 was also tested for comparison. Stellite 6 is a highly wear-resistant cobalt-based casting alloy with a network of tungsten carbides consisting of approximately 28% Cr, 1% Si, 2% Fe, 6% W, 1.2% C, but the rest of Co due to its high carbide content be poured directly into the desired shape got to. Due to its network of tungsten carbides, Stellite 6 achieves a very high hardness of 438 HV30, which is very advantageous for wear.
  • the alloy "E” according to the invention is intended to come as close as possible to the volume loss of Stellite 6.
  • the aim is in particular to reduce the high-temperature wear between 600 and 800 ° C, which is the relevant temperature range z. B. for an application as an outlet valve. Therefore, in particular the following criteria should apply to the alloys "E” according to the invention: Mean value of volume loss Alloy "E” ⁇ 0.5 ⁇ Mean value of volume loss Reference NiCr 20 TiAl at 600 ° C or 800 ° C.
  • Table 3 shows the lower end of the 0.2% yield strength spreading band for NiCr20TiAl when cured at temperatures between 500 and 800 ° C
  • Table 2 shows the lower end of the tensile strength spreading band.
  • the 0.2% proof stress of the alloy according to the invention should be at least in this range for 600 ° C. or not more than 50 MPa below 800 ° C. in order to obtain sufficient strength. Ie. In particular, the following values should be achieved: 600 ° C : Yield point R p 0.2 ⁇ 650 MPa 800 ° C : Yield point R p 0.2 ⁇ 390 MPa
  • the inequalities (5a) and (5b) are achieved when the following relationship between Ti, Al, Fe, Co, Cr, and C is satisfied.
  • fh ⁇ 0 With fh 6.49 + 3.88 Ti + 1.36 al - 0.301 Fe + 0.759 - 0.0209 Co Co - 0.428 Cr - 28.2 C where Ti, Al, Fe, Co, Cr and C are the concentration of the respective elements in mass% and fh is given in%.
  • the alloy according to the invention is said to have a corrosion resistance in air similar to that of NiCr20TiAl.
  • the heat resistance or creep strength in the range of 500 ° C. to 900 ° C. is based on the addition of aluminum, titanium and / or niobium, which precipitate the ⁇ 'and / or ⁇ . " If the hot forming of these alloys is carried out in the precipitation area of these phases, there is a danger of cracking, ie the hot forming should preferably take place above the solvus temperature T s ⁇ ' (or T s ⁇ " ) of these phases. So that a sufficient temperature range for hot forming is available, the solvus temperature T s ⁇ ' (or T s ⁇ " ) should be less than 1020 ° C.
  • Tables 5a and 5b show the analyzes of the laboratory-scale molten batches together with some large scale smelted batches of the prior art (NiCr20TiAl) used for comparison.
  • the batches of the prior art are marked with a T, the inventive with an E.
  • the melted laboratory scale batches are marked with an L, the industrially molten batches with a G.
  • Lot 250212 is NiCr20TiAl, but melted as a laboratory batch, and serves for reference.
  • the blocks of the laboratory-scale molten alloys in Table 5a and b were annealed between 1100 ° C and 1250 ° C for 0.1 to 70 hours, and by hot rolling and further intermediate annealing between 1100 ° C and 1250 ° C for 0.1 to Hot rolled for 1 hour to a final thickness of 13 mm or 6 mm.
  • the temperature control during hot rolling was such that the sheets were recrystallized.
  • the large-scale molten comparative batches were melted by VIM and poured into blocks. These blocks were remelted ESU. These blocks were between 1100 ° C and 1250 ° C for 0.1 min to 70 h, optionally under inert gas, such as. As argon or hydrogen, followed by cooling in air, annealed in the moving annealing atmosphere or in a water bath and hot rolled by hot rolling and further intermediate annealing between 1100 ° C and 1250 ° C for 0.1 to 20 hours to a final diameter between 17 and 40 mm. The temperature control during hot rolling was such that the sheets were recrystallized.
  • All alloy variants typically had a particle size of 21 to 52 ⁇ m (see Table 6).
  • Table 6 shows Vickers hardness HV30 before and after cure annealing.
  • the hardness HV30 in the cured state is in the range of 366 to 416 for all alloys except batch 250330.
  • the batch 250330 has a somewhat lower hardness of 346 HV30.
  • Table 7 shows the means ⁇ standard deviations of the measurements taken. If the standard deviation is missing, this is a single value.
  • the composition of the batches is roughly described in Table 7 in the column Alloy for orientation.
  • the maximum values for the volume loss of the alloys according to the invention from the inequalities (4a) for 600 and 800 ° C and (4b) for 25 ° C and 300 ° C registered
  • Figure 1 shows the volume loss of the pin of NiCr20TiAl Charge 320776 according to the prior art as a function of the test temperature measured with 20 N, sliding 1 mm, 20 Hz and with the force measuring module (a).
  • the experiments at 25 and 300 ° C were carried out for one hour and the experiments at 600 and 800 ° C were carried out for 10 hours.
  • the volume loss decreases strongly with the temperature up to 600 ° C, d. H. the wear resistance noticeably improves at higher temperatures.
  • the high temperature range at 600 and 800 ° C shows a comparatively low volume loss and thus a low wear, which is based on the formation of a so-called "glaze" layer between pin and disc.
  • This "Glaze” layer consists of compacted metal oxides and material of pen and disc.
  • the volume loss increases again slightly due to the increased oxidation.
  • Figure 2 shows the volume loss of the pin made of NiCr20TiAl Charge 320776 according to the prior art as a function of the test temperature measured with 20 N, sliding 1 mm, 20 Hz and with the force measuring module (s).
  • lot 320776 qualitatively the same behavior as with the force modulus (a) shows: the volume loss decreases strongly with temperature up to 600 ° C, whereby the values at 600 and 800 ° C are still smaller than those with the force measuring module ( a) measured.
  • the volume losses at 600 and 800 ° C are very low, so that differences between different alloys can no longer be reliably measured. Therefore, a test at 800 ° C with 20 N for 2 hours + 100 N for 5 hours, sliding 1 mm, 20 Hz was performed with the force measuring module (s) to produce a slightly larger wear in the high temperature range. The results are plotted in Figure 3 together with the volume losses measured with 20 N, 1 mm glide path, 20 Hz and force measurement module (s) at different temperatures. The volume loss in the high temperature range of wear has been increased so much.
  • Figure 4 shows the volume loss of the pen for different laboratory batches compared to NiCr20TiAl, lot 320776 and Stellite 6 at 25 ° C after 1 hour measured at 20 N, glide path 1 mm, 20 Hz with force measuring module (a) and (n).
  • the values with force measuring module (s) were systematically smaller than those with force measuring module (a).
  • NiCr20TiAl as laboratory batch 250212 and as large-scale batch 320776 had a similar volume loss within the scope of the measurement accuracy.
  • the laboratory batches can thus be compared directly with the large-scale batches in terms of wear measurements.
  • the charge 250325 with approx.
  • Figure 5 shows the volume loss of the pin for alloys with different carbon contents compared to NiCr20TiAl, lot 320776 at 25 ° C measured at 20 N, glide path 1 mm, 20 Hz with force measuring module (a) after 10 hours. Neither a reduction of carbon content to 0.01% for lot 250211 nor an increase to 0.211% for lot 250214 showed a change in volume loss as compared to lot 320776.
  • Figure 6 shows the volume loss of the pin for various alloys compared to NiCr20TiAl, lot 320776 at 300 ° C with 20N, glide path 1 mm, 20 Hz after 1 hour measured with force measuring modules (a) and (n).
  • the values with force measuring module (s) are systematically smaller than those with force measuring module (a). Taking this into account below, it can be seen that at 300 ° C Stellite 6 was worse than Charge 320776.
  • Co-containing laboratory melts 250329 and 250330 showed no reduction in wear volume as in Room temperature, but this was in the range of the wear volume of NiCr20TiAl, lot 320776 and thus showed no increase as in Stellite 6.
  • the volume loss of all 3 Co containing batches 250209, 250329 and 250330 was well below the maximum value from the criterion (4b).
  • the Fe-containing laboratory melts 250206 and 250327 showed a volume loss which decreased with the increasing Fe content, which was thus below the maximum value (4b).
  • the laboratory batch 250326 according to the invention with the Cr content of 30% had a volume loss in the range of the charge NiCr20TiAl, 320776, which was thus below the maximum value (4b).
  • Figure 7 shows the volume loss of the pin for various alloys compared to NiCr20TiAl, lot 320776 at 600 ° C measured at 20 N, glide path 1 mm, 20 Hz and with force measuring module (a) and (n) after 10 hours.
  • the values with force measuring module (s) were systematically smaller than those with force measuring module (a).
  • the reference laboratory batch 250212 also had the high temperature range of wear to NiCr20TiAl with 0.066 ⁇ 0.02 mm 3, a similar volume loss, such as the large-scale batch 320776 with 0.053 ⁇ 0.0028 mm 3.
  • the laboratory batches can thus be compared with the large-scale batches in terms of wear measurements even in this temperature range.
  • Stellite 6 showed a volume loss of 0.009 ⁇ 0.002 mm 3 (force measuring module (s)), reduced by a factor of 3. Furthermore, it was found that neither a reduction of the carbon content to 0.01% for batch 250211 nor an increase to 0.211% for batch 250214 resulted in a change in the volume loss compared to batch 320776 and 250212 (force measuring module (a)). , Also, the addition of 1.4% manganese on Charge 250208 and 4.6% tungsten on Charge 250210 resulted in no significant change in volume loss compared to Charge 320776 and 250212.
  • Figure 8 shows the volume loss of the pin for the various alloys compared to NiCr20TiAl Charge 320776 at 800 ° C with 20 N for 2 hours followed by 100 N for 3 hours, all with 1 mm sliding path, 20 Hz measured with force measuring module (s). Even at 800 ° C, it was confirmed that in the high temperature range of wear, the reference laboratory batch 250212 to NiCr20TiAl at 0.292 ⁇ 0.016 mm 3 had a comparable volume loss as the large scale batch 320776 with 0.331 ⁇ 0.081 mm 3 . The laboratory batches could thus be compared directly with the large-scale batches in terms of wear measurements even at 800 ° C.
  • the 2.5% iron batch 250325, at 0.136 ⁇ 0.025 mm 3 showed a significant reduction in volume loss compared to lots 320776 and 250212 below the maximum of 0.156 mm 3 ( Figure 4a).
  • a further reduction of volume loss in comparison to the batch 320,776th showed 0.057 ⁇ 0.007 mm 3 in the 250327 29% Fe, the volume loss was 0.043 ⁇ 0.02 mm 3.
  • the volume loss of 0.144 ⁇ 0.012 mm 3 was similar to that of laboratory batch 250325 with 6.5% iron below the maximum of 0.156 mm 3 from the inequality (Fig.
  • the volume loss of the pin in the wear test could be greatly reduced in the alloys according to the invention by a Cr content of between 25 and 35%.
  • the charge 250326 according to the invention with 30% Cr at 800 ° C. shows a reduction in the volume loss to 0.042 ⁇ 0.011 mm 3 and also at 600 ° C. to 0.026 mm 3 , both equal to 50% of the volume loss of NiCr 2 O TiAl, the respective maximum value ( 4a).
  • the volume loss of 0.2588 mm 3 was also below the maximum value of (4b), as well as at 25 ° C to 1.41 ⁇ 0.18 mm 3 (force measuring module (s)). Therefore, chromium contents between 25 and 35% are particularly advantageous for wear at higher temperatures.
  • the volume losses measured at 800 ° C in the laboratory batches 250325 (6.5% Fe), 250206 (11% Fe) and 250327 (29% Fe) showed that the volume loss of the pin in the wear test was due to an Fe content can be greatly reduced so that it was less than or equal to 50% of the volume loss of NiCr20TiAl (4a) at either temperature, with the first% being particularly effective. Even at 25 ° C and 300 ° C of the alloys with an Fe content satisfies the inequalities (4b). In particular, at 300 ° C, the alloys even had a volume loss reduced by more than 30%. Thus, an optional content of iron between 0 and 20% is advantageous. An iron content also reduces the metal cost of this alloy.
  • NiCr20TiAl alloys lots 320776 and 250212, had a sum of Cr + Fe + Co of 20.3% and 20.2%, both less than 26%, and met criteria (4a) and (4b) for a very good wear resistance, but especially the criteria (4a) for a good High temperature wear resistance not. Also, lots 250211, 250214, 250208 and 250210, in particular, did not meet the criteria (4a) for good high-temperature wear resistance and had a total Cr + Fe + Co of 20.4%, 20.2%, 20.3% and 20, respectively , 3% all less than 26%.
  • Table 8 shows the yield strength R p0.2 and the tensile strength R m for room temperature (RT) at 600 ° C and at 800 ° C.
  • RT room temperature
  • the measured grain sizes and the values for fh are entered.
  • the minimum values from inequalities (5a) and (5b) are entered in the last line.
  • Figure 10 shows the yield strength R p02 and the tensile strength R m for 600 ° C
  • Figure 11 for 800 ° C.
  • Batches 321863, 321426 and 315828 smelted on an industrial scale had values between 841 and 885 MPa for the yield strength R p02 at 600 ° C. and values between 472 and 481 MPa at 800 ° C.
  • the reference batch 250212 with a similar analysis as the large-scale batches, had a slightly higher aluminum content of 1.75%, resulting in a slightly higher yield strength R p02 of 866 MPa at 600 ° C and of 491 MPa at 800 ° C ,
  • a certain amount of iron may be advantageous in the alloy for cost reasons.
  • Batch 250327 with 29% Fe barely met the inequality (5b) because, like the consideration of the laboratory batch 250212 (reference, similar to the large-scale batches Fe less than 3%) or also the large-scale batches and the batches according to the invention 250325 (6.5 % Fe), 250206 (11% Fe) and 250327 (29% Fe) showed that an increasing alloy content of Fe reduced the yield strength R p0.2 in the tensile test (see also Figure 11). Therefore, an optional alloy content of 20% Fe is to be regarded as the upper limit for the alloy according to the invention.
  • the laboratory batch 250326 according to the invention showed that with an addition of 30% Cr, the yield strength R p0.2 in the tensile test at 800 ° C. decreased to 415 MPa, which was still significantly above the minimum value of 390 MPa. Therefore, an alloy content of 35% Cr is to be regarded as an upper limit for the alloy according to the invention.
  • Table 9 shows the specific mass changes after an oxidation test at 800 ° C in air after 6 cycles of 96 h for a total of 576 h. Given in Table 9 is the specific gross mass change, the net specific mass change and the specific mass change of the chipped oxides after 576 hours.
  • the example batches of the prior art alloys NiCr20TiAl, lots 321426 and 250212 showed a specific gross mass change of 9.69 and 10.84 g / m 2 and a net specific mass change of 7.81 and 10.54 g, respectively / m 2 . Lot 321426 showed minor flakes.
  • the batch 250326 according to the invention was with an increased Cr content of 30% a specific gross mass change of 6.74 g / m 2 and a specific net change in mass of 6.84 g / m 2, which were below the range of the reference alloys NiCr20TiAl , Increasing the Cr content improves the corrosion resistance. Thus, a Cr content of 25 to 35% is advantageous for the oxidation resistance of the alloy according to the invention.
  • Co-containing batches 250209 (Co 9.8%) and 250329 (Co 30%) also had a specific gross mass change of 10.05 and 9.91 g / m 2 and a specific net mass change of 9.81 and 9.81 g / m 2, respectively 9.71 g / m 2 , which were also within the range of NiCr20TiAl reference alloys.
  • the batch behaved 250330 (29% Co, 10% Fe) having a specific gross mass change of 9.32 g / m 2 and a specific net change in mass of 8.98 g / m 2.
  • a Co content of up to 30% also does not adversely affect the oxidation resistance.
  • All alloys according to Table 5 b contain Zr, which contributes as a reactive element to improve the corrosion resistance.
  • other reactive elements such as Y, La, Ce, cerium mischmetal, Hf may be added to improve the efficacy in a similar manner.
  • Titanium enhances the high temperature strength at temperatures in the range up to 900 ° C by promoting the formation of the ⁇ 'phase. At least 1.0% is necessary to obtain sufficient strength. Too high titanium contents increase the solvus temperature T s ⁇ ' too much, so that the workability deteriorates significantly. Therefore, 3.0% is considered the upper limit.
  • Aluminum increases the high temperature strength at temperatures in the range up to 900 ° C by promoting the formation of the ⁇ 'phase. At least 0.6% is necessary to obtain sufficient strength. Too high aluminum contents increase the solvus temperature T s ⁇ ' too strong, so that the workability deteriorates significantly. Therefore, 2.0% is considered the upper limit.
  • Carbon improves creep resistance. A minimum content of 0.005% C is required for good creep resistance. Carbon is limited to a maximum of 0.10%, since this element reduces the processability due to the excessive formation of primary carbides.
  • N is limited to a maximum of 0.050%, since this element reduces the processability by the formation of coarse carbonitrides.
  • the content of phosphorus should be less than or equal to 0.030%, since this surfactant affects the oxidation resistance. Too low a phosphorus content increases the costs. The phosphorus content is therefore ⁇ 0.0005%.
  • the levels of sulfur should be adjusted as low as possible, since this surfactant affects oxidation resistance and processability. It will therefore max. 0.010% S set.
  • the oxygen content must be less than or equal to 0.020% to ensure the manufacturability of the alloy.
  • Si content is therefore limited to 0.70%.
  • Mg contents and / or Ca contents improve the processing by the setting of sulfur, whereby the occurrence of low melting NiS eutectic is avoided. If the contents are too high, intermetallic Ni-Mg phases or Ni-Ca phases may occur, which again significantly impair processability.
  • the Mg content or the Ca content is therefore limited to a maximum of 0.05%.
  • Molybdenum is reduced to max. 2.0% limited as this element reduces oxidation resistance.
  • Tungsten is limited to max. 2.0%, since this element also reduces oxidation resistance and has no measurable positive effect on wear resistance at the carbon contents possible in wrought alloys.
  • Niobium increases the high-temperature strength. Higher levels increase costs very much. The upper limit is therefore set at 0.5%.
  • 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.
  • Iron increases wear resistance, especially in the high temperature range. Also, it reduces the cost. It may therefore optionally be between 0 and 20% in the alloy. Excessive iron content reduces the yield strength too much, especially at 800 ° C. Therefore, 20% is to be considered as the upper limit.
  • Cobalt increases wear resistance and heat resistance / creep resistance, especially in the high temperature range. It may therefore optionally be between 0 and 20% in the alloy. Too high cobalt levels increase the costs too much. Therefore, 20% is to be considered as the upper limit.
  • the alloy may also contain Zr to improve high temperature strength and oxidation resistance.
  • the upper limit is set at 0.20% Zr for cost reasons because Zr is a rare element.
  • 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.
  • Nickel stabilizes the austenitic matrix and is required to form the ⁇ 'phase, which is the hot strength / creep resistance. With a nickel content below 35%, the hot strength / creep resistance is reduced too much, which is why 35% is the lower limit.
  • the oxidation resistance can be further improved by adding oxygen-affine elements such as yttrium, lanthanum, cerium, hafnium. They do this by incorporating them into the oxide layer and blocking the diffusion paths of the oxygen there on the grain boundaries.
  • the upper limit of yttrium is set at 0.20% for cost reasons, since yttrium is a rare element.
  • the upper limit of lanthanum is set at 0.20% for cost reasons, since lanthanum is a rare element.
  • cerium is a rare element.
  • cerium mischmetal instead of Ce and or La also cerium mischmetal can be used.
  • the upper limit of cerium mischmetal is set at 0.20% for cost reasons.
  • the upper limit of hafnium is set at 0.20% for cost reasons, since hafnium is a rare element.
  • the alloy may also contain tantalum, since tantalum also increases high-temperature strength by promoting ⁇ 'phase formation. Higher levels increase costs very much as tantalum is a rare element. The upper limit is therefore set at 0.60%.
  • Pb is set to max. 0.002% limited because this element reduces the oxidation resistance and the high temperature strength. The same applies to Zn and Sn.
  • Table 1 Composition of the nickel alloys for exhaust valves mentioned in DIN EN 10090. All data in mass%, description Chemical composition, mass fraction in% short name Material number C Si Mn P max. S max. Cr Not a word Ni Fe al Ti other NiFe25Cr20NbTi 2,4955 0.04 -0.10 Max. 1.0 Max. 1.0 0,030 0,015 18.00 - 21.00 rest 23.00 - 28.00 0.30 - 1.00 1,00 - 2,00 Nb + Ta: 1.00-2.00 B: max 0.008 NiCr20TiAl 2.4952 0.04-0.10 Max. 1.0 Max. 1.0 0,020 0,015 18.00 - 21.00 minute 65 max 3,00 1.00 - 1.80 1.80 - 2.70 Cu: max.
  • NiCr20TiAl 443 9.69 7.81 1.88 T L 250212 NiCr20TiAl (Ref) 443 10.84 10.54 0.30 L 250325 NiCr20TI2.5Al2 Fe7 443 10.86 10.61 0.25 L 250206 NiCr20TI2.5Al2 Fe10 443 9.26 9.05 0.21 L 250327 NiCr20TI2.5Al2 Fe30 443 10.92 11,50 -0.57 L 250209 NiCr20TI2.5Al2 Co10 443 10.05 9.81 0.24 L 250329 NiCr20TI2.4Al1.5 Co30 443 9.91 9.71 0.19 L 250330 NiCr20TI2.4Al1.5 Fe10Co30 443 9.32 8.98 0.34 e L 250326 NiCr30TI2.4Al1.5 443 6.74 6.84 -0.10

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Claims (20)

  1. Alliage nickel-chrome-titane-aluminium de corroyage durcissant, comprenant une très bonne résistance à l'usure avec simultanément une très bonne résistance à la corrosion à des températures élevées, une bonne résistance au fluage et une bonne maniabilité comprenant (en % en masse) 25 à 35 % de chrome, 1,0 à 3,0 % de titane, 0,6 à 2,0 % d'aluminium, 0,005 à 0,10 % de carbone, 0,0005 à 0,050 % d'azote, 0,0005 à 0,030 % de phosphore, max. 0,010 % de soufre, max. 0,020 % d'oxygène, max. 0,70 % de silicium, max. 2,0 % de manganèse, max. 0,05 % de magnésium, max. 0,05 % de calcium, max. 2,0 % de molybdène, max. 2,0 % de tungstène, max. 0,5 % de niobium, max. 0,5 % de cuivre, max. 0,5 % de vanadium, si nécessaire, 0 à 20 % de Fe, si nécessaire, 0 à 15 % de cobalt, si nécessaire, 0 à 0,20 % de Zr, si nécessaire, 0,0001 à 0,008 % de bore, les éléments suivants pouvant être facultativement présents dans l'alliage :
    Y 0 - 0,20 % et/ou
    La 0 - 0,20 % et/ou
    Ce 0 - 0,20 % et/ou
    Cérium « Mischmetall » 0 - 0,20 % et/ou
    Hf 0 - 0,20 % et/ou
    Ta 0 - 0,20 %
    le reste étant du nickel et des impuretés usuelles résultant de l'élaboration, la teneur en nickel étant supérieure à 35 %, les relations suivantes devant être satisfaites : Cr + Fe + Co ≥ 26 %
    Figure imgb0050
     pour obtenir une bonne résistance à l'usure et fh ≥ 0 avec
    Figure imgb0051
     fh = 6,49 + 3,88 Ti + 1,36 Al − 0,301 Fe + 0,759 − 0,0209 Co Co − 0,428 Cr − 28,2 C
    Figure imgb0052
     pour qu'une solidité suffisante soit obtenue à des températures élevées, Ti, Al, Fe, Co, Cr et C étant les concentrations des éléments concernés en % en masse et fh étant indiqué en %.
  2. Alliage selon la revendication 1, comprenant une teneur en chrome comprise entre 26 et 35 %.
  3. Alliage selon la revendication 2, comprenant une teneur en chrome comprise entre 27 et 35 %.
  4. Alliage selon les revendications 1 à 3, comprenant une teneur en titane comprise entre 1,5 et 3,0 %.
  5. Alliage selon l'une des revendications 1 à 4, comprenant une teneur en aluminium comprise entre 0,9 et 2,0 %.
  6. Alliage selon l'une des revendications 1 à 5, comprenant une teneur en carbone comprise entre 0,01 et 0,10 %.
  7. Alliage selon l'une des revendications 1 à 6, comprenant une teneur en niobium de max. 0,20 %.
  8. Alliage selon l'une des revendications 1 à 7, comprenant, si nécessaire, une teneur en fer comprise entre > 0 et 15,0 %.
  9. Alliage selon l'une des revendications 1 à 8, comprenant une teneur en cobalt comprise entre > 0 et 12 %.
  10. Alliage selon l'une des revendications 1 à 9, comprenant une teneur en bore comprise entre 0,0005 et 0,006 %.
  11. Alliage selon l'une des revendications 1 à 10, dans lequel la teneur en nickel est supérieure à 40 %.
  12. Alliage selon l'une des revendications 1 à 11, dans lequel la teneur en nickel est supérieure à 45 %.
  13. Alliage selon l'une des revendications 1 à 12, dans lequel la teneur en nickel est supérieure à 50 %.
  14. Alliage selon l'une des revendications 1 à 13 avec Cr + Fe + Co ≥ 27 %
    Figure imgb0053
     Cr, Fe et Co étant les concentrations des éléments concernés en % en masse.
  15. Alliage selon l'une des revendications 1 à 14 avec fh ≥ 1 avec
    Figure imgb0054
     fh = 6,49 + 3,88 Ti + 1,36 Al − 0,301 Fe + 0,759 − 0,0209 Co Co − 0,428 Cr − 28,2 C
    Figure imgb0055
     Cr, Fe, Co et C étant les concentrations des éléments concernés en % en masse et fh étant indiqué en %.
  16. Alliage selon l'une des revendications 1 à 15, dans lequel facultativement la relation suivante entre Cr, Mo, W. Fe. Co, Ti, Al et Nb doit être satisfaite pour qu'une maniabilité suffisante soit obtenue : fver = ≤ 7 avec
    Figure imgb0056
     fver = 32,77 + 0,5932 Cr + 0,3642 Mo + 0,513 W + 0,3123 − 0,0076 Fe Fe + 0,3351 − 0,003745 Co − 0,0109 Fe Co + 40,67 Ti * Al + 33,28 Al 2 − 13,6 TiAl 2 − 22,99 Ti − 92,7 Al + 2,94 Nb
    Figure imgb0057
     Cr, Mo, W, Fe. Co, Ti, Al et Nb étant les concentrations des éléments concernés en % en masse et fh étant indiqué en %.
  17. Alliage selon l'une des revendications 1 à 16, dans lequel les impuretés sont ajustées à des teneurs en Pb de max. 0,002 %, en Zn de max. 0,002 %, en Sn de max. 0,002 %.
  18. Utilisation de l'alliage selon l'une des revendications 1 à 17 comme une bande, une tôle, un fil, une tige, une tube soudée longitudinalement et une tube sans soudure.
  19. Utilisation de l'alliage selon l'une des revendications 1 à 18 pour des soupapes, notamment celles des moteurs à combustion interne.
  20. Utilisation de l'alliage selon l'une des revendications 1 à 18 comme des composants de turbines à gaz, comme des boulons de fixation, dans des ressorts, dans des turbocompresseurs.
EP15704949.5A 2014-02-04 2015-01-12 Alliage nickel-chrome-titane-aluminium durcissant par trempe et présentant une bonne résistance à l'usure, au fluage et à la corrosion, et une bonne usinabilité Active EP3102712B1 (fr)

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PCT/DE2015/000009 WO2015117585A2 (fr) 2014-02-04 2015-01-12 Alliage nickel-chrome-titane-aluminium durcissant par trempe et présentant une bonne résistance à l'usure, au fluage et à la corrosion, et une bonne usinabilité

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Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ITUA20161551A1 (it) 2016-03-10 2017-09-10 Nuovo Pignone Tecnologie Srl Lega avente elevata resistenza all’ossidazione ed applicazioni di turbine a gas che la impiegano
ITUA20163944A1 (it) * 2016-05-30 2017-11-30 Nuovo Pignone Tecnologie Srl Process for making a component of a turbomachine, a component obtainable thereby and turbomachine comprising the same / Processo per ottenere un componente di turbomacchina, componente da esso ottenibile e turbomacchina che lo comprende
DE102017007106B4 (de) 2017-07-28 2020-03-26 Vdm Metals International Gmbh Hochtemperatur-Nickelbasislegierung
CN108441705B (zh) * 2018-03-16 2020-06-09 中国航发北京航空材料研究院 一种高强度镍基变形高温合金及其制备方法
JP6719142B2 (ja) * 2018-06-28 2020-07-08 株式会社東亜鍛工所 中空エンジンバルブの製造方法
CN112077166B (zh) * 2020-07-16 2022-05-20 河北五维航电科技股份有限公司 一种超超临界汽轮机用高温汽封弹簧的制备方法
CN112322940B (zh) * 2020-11-10 2022-04-05 中南大学 一种高强韧耐腐蚀的富Ni多组分合金及其制备方法
DE102022110384A1 (de) 2022-04-28 2023-11-02 Vdm Metals International Gmbh Verwendung einer Nickel-Eisen-Chrom-Legierung mit hoher Beständigkeit in hoch korrosiven Umgebungen und gleichzeitig guter Verarbeitbarkeit und Festigkeit
DE102022110383A1 (de) 2022-04-28 2023-11-02 Vdm Metals International Gmbh Verwendung einer Nickel-Eisen-Chrom-Legierung mit hoher Beständigkeit in aufkohlenden und sulfidierenden und chlorierenden Umgebungen und gleichzeitig guter Verarbeitbarkeit und Festigkeit
CN115821115B (zh) * 2022-11-18 2024-01-09 江阴市诚信合金材料有限公司 一种高稳定性镍铬电阻合金丝及其生产工艺

Family Cites Families (53)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3573901A (en) * 1968-07-10 1971-04-06 Int Nickel Co Alloys resistant to stress-corrosion cracking in leaded high purity water
JPS4810695B1 (fr) 1969-10-11 1973-04-06
JPS4720813U (fr) 1971-03-16 1972-11-09
JPS50109812A (fr) 1974-02-09 1975-08-29
JPS58117848A (ja) 1982-01-06 1983-07-13 Mitsubishi Metal Corp 燃焼雰囲気ですぐれた高温耐食性および高温耐酸化性を示す高強度ｎｉ基鋳造合金
JPS6070155A (ja) 1983-09-28 1985-04-20 Hitachi Metals Ltd 排気弁用Νｉ基合金
JPS60211028A (ja) 1984-04-03 1985-10-23 Daido Steel Co Ltd 排気バルブ用合金
JPS61284558A (ja) 1985-06-10 1986-12-15 Sumitomo Metal Ind Ltd 耐水素割れ性にすぐれたＮｉ基合金の製造法
US4882125A (en) 1988-04-22 1989-11-21 Inco Alloys International, Inc. Sulfidation/oxidation resistant alloys
DE4111821C1 (fr) 1991-04-11 1991-11-28 Vdm Nickel-Technologie Ag, 5980 Werdohl, De
JP3132602B2 (ja) 1991-09-28 2001-02-05 大同特殊鋼株式会社 摩擦圧接バルブの製造方法
ATE123819T1 (de) * 1991-12-20 1995-06-15 Inco Alloys Ltd Gegen hohe temperatur beständige ni-cr-legierung.
JPH0711366A (ja) 1993-06-24 1995-01-13 Sumitomo Metal Ind Ltd 熱間加工性および高温水中の耐食性に優れた合金
JP3058794B2 (ja) * 1993-08-19 2000-07-04 日立金属株式会社 Ｆｅ−Ｎｉ−Ｃｒ基超耐熱合金、エンジンバルブおよび排ガス触媒用ニットメッシュ
JPH07216511A (ja) 1994-01-31 1995-08-15 Sumitomo Metal Ind Ltd 高温強度に優れた高クロムオーステナイト耐熱合金
JPH08127848A (ja) 1994-11-01 1996-05-21 Sumitomo Metal Ind Ltd 高温強度に優れた高クロムオーステナイト耐熱合金
DE19524234C1 (de) 1995-07-04 1997-08-28 Krupp Vdm Gmbh Knetbare Nickellegierung
JPH108924A (ja) 1996-06-21 1998-01-13 Daido Steel Co Ltd 大型ディーゼルエンジン用バルブの製造方法
RU2125110C1 (ru) 1996-12-17 1999-01-20 Байдуганов Александр Меркурьевич Жаропрочный сплав
JPH10219377A (ja) 1997-02-07 1998-08-18 Daido Steel Co Ltd ディーゼルエンジンの高耐食性吸排気バルブ用合金及び吸排気バルブの製造方法
JPH1122427A (ja) 1997-07-03 1999-01-26 Daido Steel Co Ltd ディーゼルエンジンバルブの製造方法
US6761854B1 (en) 1998-09-04 2004-07-13 Huntington Alloys Corporation Advanced high temperature corrosion resistant alloy
US5997809A (en) 1998-12-08 1999-12-07 Inco Alloys International, Inc. Alloys for high temperature service in aggressive environments
JP2000328163A (ja) 1999-05-21 2000-11-28 Daido Steel Co Ltd ディーゼルエンジン用排気バルブ合金及び排気バルブの製造方法
KR100372482B1 (ko) 1999-06-30 2003-02-17 스미토모 긴조쿠 고교 가부시키가이샤 니켈 베이스 내열합금
DE19957646A1 (de) 1999-11-30 2001-05-31 Krupp Vdm Gmbh Verfahren zur Herstellung einer warmfesten Legierung mit guter Hochtemperaturoxidationsbeständigkeit
EP1466027B1 (fr) 2000-01-24 2006-08-30 Inco Alloys International, Inc. ALLIAGE Ni-Co-Cr RESISTANT A LA CORROSION ET DE BONNE TENUE MECANIQUE A TEMPERATURE ELEVEE
JP3965869B2 (ja) 2000-06-14 2007-08-29 住友金属工業株式会社 Ｎｉ基耐熱合金
JP3952861B2 (ja) 2001-06-19 2007-08-01 住友金属工業株式会社 耐メタルダスティング性を有する金属材料
JP2003138334A (ja) 2001-11-01 2003-05-14 Hitachi Metals Ltd 高温耐酸化性及び高温延性に優れたＮｉ基合金
EP1325965B1 (fr) 2001-12-21 2005-10-05 Hitachi Metals, Ltd. Alliage à base de Ni amelioree en resistence a l'oxydation, haute résistance thermique et deformation a chaud
JP4277113B2 (ja) 2002-02-27 2009-06-10 大同特殊鋼株式会社 耐熱ばね用Ｎｉ基合金
EP1558776B8 (fr) * 2002-11-04 2009-04-29 Paralloy Limited Alliages haute temperature
DE10302989B4 (de) 2003-01-25 2005-03-03 Schmidt + Clemens Gmbh & Co. Kg Verwendung einer Hitze- und korrosionsbeständigen Nickel-Chrom-Stahllegierung
JP3951943B2 (ja) 2003-03-18 2007-08-01 本田技研工業株式会社 耐過時効特性にすぐれた高強度の排気バルブ用耐熱合金
JP4830466B2 (ja) 2005-01-19 2011-12-07 大同特殊鋼株式会社 ９００℃での使用に耐える排気バルブ用耐熱合金およびその合金を用いた排気バルブ
JP2006274443A (ja) 2005-03-03 2006-10-12 Daido Steel Co Ltd 非磁性高硬度合金
US7651575B2 (en) * 2006-07-07 2010-01-26 Eaton Corporation Wear resistant high temperature alloy
US8568901B2 (en) 2006-11-21 2013-10-29 Huntington Alloys Corporation Filler metal composition and method for overlaying low NOx power boiler tubes
FR2910912B1 (fr) 2006-12-29 2009-02-13 Areva Np Sas Procede de traitement thermique de desensibilisation a la fissuration assistee par l'environnement d'un alliage a base nickel, et piece realisee en cet alliage ainsi traitee
JP4978790B2 (ja) 2007-08-27 2012-07-18 三菱マテリアル株式会社 樹脂成形用金型部材
DE102007062414B4 (de) 2007-12-20 2009-12-24 Ecoloop Gmbh Autothermes Verfahren zur kontinuierlichen Vergasung von kohlenstoffreichen Substanzen
DE102007062417B4 (de) * 2007-12-20 2011-07-14 ThyssenKrupp VDM GmbH, 58791 Austenitische warmfeste Nickel-Basis-Legierung
DE102008051014A1 (de) 2008-10-13 2010-04-22 Schmidt + Clemens Gmbh + Co. Kg Nickel-Chrom-Legierung
CH699716A1 (de) 2008-10-13 2010-04-15 Alstom Technology Ltd Bauteil für eine hochtemperaturdampfturbine sowie hochtemperaturdampfturbine.
JP4780189B2 (ja) 2008-12-25 2011-09-28 住友金属工業株式会社 オーステナイト系耐熱合金
JP5284252B2 (ja) 2009-12-10 2013-09-11 株式会社神戸製鋼所 耐割れ性に優れたＮｉ−Ｃｒ−Ｆｅ合金系溶接金属
KR101740164B1 (ko) * 2009-12-10 2017-06-08 신닛테츠스미킨 카부시키카이샤 오스테나이트계 내열 합금
DE102011013091A1 (de) 2010-03-16 2011-12-22 Thyssenkrupp Vdm Gmbh Nickel-Chrom-Kobalt-Molybdän-Legierung
DE102012011162B4 (de) 2012-06-05 2014-05-22 Outokumpu Vdm Gmbh Nickel-Chrom-Legierung mit guter Verarbeitbarkeit, Kriechfestigkeit und Korrosionsbeständigkeit
DE102012011161B4 (de) 2012-06-05 2014-06-18 Outokumpu Vdm Gmbh Nickel-Chrom-Aluminium-Legierung mit guter Verarbeitbarkeit, Kriechfestigkeit und Korrosionsbeständigkeit
DE102014001328B4 (de) * 2014-02-04 2016-04-21 VDM Metals GmbH Aushärtende Nickel-Chrom-Eisen-Titan-Aluminium-Legierung mit guter Verschleißbeständigkeit, Kriechfestigkeit, Korrosionsbeständigkeit und Verarbeitbarkeit
DE102014001330B4 (de) * 2014-02-04 2016-05-12 VDM Metals GmbH Aushärtende Nickel-Chrom-Kobalt-Titan-Aluminium-Legierung mit guter Verschleißbeständigkeit, Kriechfestigkeit, Korrosionsbeständigkeit und Verarbeitbarkeit

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None *

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