EP1270754B1 - Two-step aging treatment for Ni-Cr-Mo alloys - Google Patents
Two-step aging treatment for Ni-Cr-Mo alloys Download PDFInfo
- Publication number
- EP1270754B1 EP1270754B1 EP02014216A EP02014216A EP1270754B1 EP 1270754 B1 EP1270754 B1 EP 1270754B1 EP 02014216 A EP02014216 A EP 02014216A EP 02014216 A EP02014216 A EP 02014216A EP 1270754 B1 EP1270754 B1 EP 1270754B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- alloy
- hours
- temperature
- alloys
- cooling
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
Links
Images
Classifications
-
- 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
-
- 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
-
- 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
- C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
- C22C19/056—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 10% but less than 20%
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/10—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon
Definitions
- the invention relates to heat treatment processes for nickel-chromium molybdenum-alloys having a chromium content of from 12 to 23.5 weight percent.
- Ni-Cr-Mo alloys and particularly those with chromium content of 15 to 24% have been popular for use in corrosive environments such as encountered in the chemical and petrochemical industries.
- Age-hardening is a process used in the metallurgical industry to give an alloy composition higher strength, as measured by its yield strength, tensile strength, and by notched stress rupture tests typically used in the art.
- Various applications demand a combination of high tensile strength and low thermal expansion properties.
- One such application is in the aerospace industry.
- Another application is seal rings used in land-based gas turbines.
- a combination of high tensile strength and ductility is also very useful for bolts. Because of the demanding operating conditions and performance parameters for metal products in these applications, various methods of age-hardening have been used.
- One common technique is to heat the alloy to a selected high temperature, hold the alloy at that temperature for a period of time and then cool the alloy to room temperature.
- the alloy may be heated to one temperature, cooled, heated again to a second temperature and cooled. Examples of these processes are disclosed in United States Patent No. 3,871,928 .
- the temperatures and time periods used to age harden an alloy depend upon the composition of the alloy. For all age-hardenable commercial alloys there are established times and temperatures used that have become standard in the industry because they are known to produce the desired properties. For Ni-Cr-Mo alloys having high chromium content, that is chromium greater than 12% , the general view in the art is that heat treatment beyond the initial annealing in an effort to improve mechanical properties would be impractical due to the lengthy required times (hundreds to thousands of hours) and such treatments simply have not been done.
- Ni-Cr-Mo alloys and nickel-molybdenum (Ni-Mo) alloys are widely utilized for commercial applications in the chemical industry, for example.
- alloys such as these are not usually considered responsive to heat treatment, and are therefore used in the annealed condition.
- HAYNES® 242TM alloy which will be discussed later.
- Ni-Cr-Mo and Ni-Mo alloys are not commercially age-hardenable does not mean that they do not exhibit any metallurgical response to thermal exposure at intermediate temperatures.
- alloys of this type can exhibit complex secondary phase reactions when exposed in the temperature range from about 538°C to 871°C.
- the phases which form can often be deleterious to both alloy ductility and other aspects of service performance. This is particularly observed with Ni-Mo alloys containing about 25 to 30 % molybdenum. In such materials, exposure at temperatures from about 538°C to 871°C can result in the rapid formation of embrittling Ni 3 Mo or Ni 4 Mo phases in the microstructure. This can be a problem for both component manufacturing and for component performance.
- Ni-Cr-Mo alloys with about 16 % molybdenum and 16 % chromium weight percent content
- the occurrence of these particular intermetallic phases is not usually observed after short term thermal exposures.
- Ni 2 (Mo,Cr) is evidenced in the microstructure.
- a long-range-ordered phase, with structure similar to that of Pt 2 Mo, the Ni 2 (Mo,Cr) phase serves to significantly increase the strength of these materials without a severe loss of ductility.
- the one major drawback is the prolonged aging time required to produce this phase.
- United States Patent No. 4,818,486 discloses a low thermal expansion nickel based alloy that contains 5% to 12% chromium and 10% to 30% molybdenum.
- the patent teaches that the aging times typically required to obtain desired hardness without deleterious phases being formed is well over 1000 hours at temperatures of 649°C to 816°C for most Ni-Mo-Cr alloys.
- the aging time to harden the alloy composition disclosed in the '486 patent is as little as 24 hours at 649°C.
- the alloy of this patent has been marketed under the trademarks 242 alloy and HAYNES 242 alloy.
- HAYNES 242 alloy has been sold for applications requiring high tensile strength and a low coefficient of thermal expansion. Other beneficial properties of the 242 alloy include good thermal stability, good low cycle fatigue resistance, and excellent containment capabilities due to its tensile strength and ductility.
- HAYNES 242 alloy consists of about 8 % (weight percent) chromium, about 20-30 % molybdenum, about 0.35 % to up to about 0.5 % aluminum, up to 0.03 % carbon, up to about 0.8 % manganese, up to about 0.8 % silicon, up to about 2 % iron, up to about 1 % cobalt, up to about 0.006 % boron, and the balance weight percent being nickel.
- Ni-Cr-Mo alloy is disclosed in United States Patent No. 5,019,184 to Crum et al. That alloy contains 19% to 23% chromium and 14 to 17% molybdenum.
- the patent discloses homogenization heat treatment at temperatures ranging from 1149°C to 1260°C for periods of from 5 to 50 hours. The purpose of the treatment is to produce a corrosion resistant alloy having a desired microstructure rather than to strengthen the alloy. No tensile strength data is given for any of these samples disclosed in the patent.
- the alloy of this patent has been commercialized under the designation INCONEL® alloy 686.
- Ni-Cr-Mo alloy Yet another corrosion resistant Ni-Cr-Mo alloy is disclosed in United States Patent No. 4,906,437 to Heubner et al. This alloy contains 22% to 24% chromium and 15% to 16.5% molybdenum. There is no disclosure of any heat treatment or age hardening of this alloy. The alloy disclosed in this patent has been commercialized under the designation VDM NICROFER 923 h Mo or Alloy 59.
- Ni-Cr-Mo alloy A high yield strength Ni-Cr-Mo alloy is disclosed in United States Patent No. 4,129,464 to Matthews et al. This alloy contains 13% to 18% chromium and 13% to 18% molybdenum.
- the patent says that the alloy could be aged using a single step aging treatment of at least 50 hours at 482°C to 593°C, but all examples are aged 168 hours or more. The statement that at least 50 hours is required was an extrapolation of the results obtained from a 168 hours aging treatment.
- the improved age-hardening process involves an alloy with this P value that has been given an age hardening treatment at about 704°C for at least 8 hours and preferably for about 12 to 20 hours, furnace cooling to a temperature from about 538°C to about 718°C and holding the material at that temperature for at least 8 hours and preferably for about 28 to 36 hours, followed by air cooling to room temperature.
- a Ni-Cr-Mo alloy having 12% to 23.5% chromium and treated with this two-step heat treatment or age-hardening process shows improved or comparable tensile strength to the standard aging process used in the lower chromium level 242 alloy. Because of the combination of high yield strength and ductility properties, the alloy and two-step aging process significantly increase affordability of this alloy for applications requiring such properties.
- This age hardening process involves aging the alloy at about 691°C to about 760°C for from 8 to 20 hours, cooling the alloy to a temperature of at from about 538°C to about 718°C, maintaining the alloy within that temperature range for at least 8 hours and preferably for from 24 to 36 hours and cooling the alloy to room temperature.
- Ni-Cr-Mo commercial alloys whose compositions are set forth in Table 1.
- the commercial alloys were HASTELLOY S sheet, HASTELLOY C-276 plate, HASTELLOY C-4 plate, Alloy 59 sheet and INCONEL alloy 686 sheet.
- the designation "n.m.” in Table 1 indicates that the presence of an element was not measured. Table 1 also reports the P value for each alloy.
- the chromium content of the test alloys ranged from 11.56% for alloy H to 26.06% for alloy P. Molybdenum ranged from 9.91% in alloy G to 23.89% in alloy S. All of the alloys contained similar amounts of aluminum, cobalt, iron, and manganese. Tungsten was present within a range of 0.11% to 0.34%. The alloys also contained small amounts of boron, carbon, cerium, copper, magnesium, phosphorus, sulfur, silicon, and vanadium. The test alloys were annealed after hot rolling to 12.7mm plate at annealing temperatures in the range of 1038°C to 1093°C for thirty minutes. The commercial alloys were cut from sheets and plates available from the manufacturer.
- Figure 1 is a graph of the tested alloys based upon the P value of the alloy and the chromium content. Each alloy that had acceptable tensile properties is plotted with a dot. An X is used to plot those alloys whose tensile properties were not acceptable after the alloy was subjected to the two-step aging treatment. A box has been drawn around the acceptable alloys. It is readily apparent from Figure 1 that the acceptable alloys have a chromium content of 12% to 23.5% and a P value within the range of 31.2 to 35.9.
- the test results for Alloy M indicate that the first step should be at least about 8 hours long at a temperature ranging from about 691°C to about 760°C while the second step should be at least about 24 hours long at a temperature ranging from about 538°C to about 691°C.
- the data also indicates that when a higher temperature is used for the first step then a lower temperature can be used for the second step. While first step temperatures of up to 927°C were found to be useful in age hardening the alloy, microstructural examination revealed that an undesirable grain boundary precipitation occurred when the first step temperature was 760°C or greater. This precipitation would be expected to degrade corrosion resistance.
- Ni 2 (Mo,Cr) age hardening begins with short range ordering followed by creation of precipitates that impart the hardening property. Upon continued heating a solvus temperature will be reached at which the precipitates will go back into solution.
- the short range ordering is also related to time and temperature. Both the short range ordering and the solvus temperature vary from one- alloy composition to another. To provide age hardening any two-step aging treatment must involve a selection of times and temperatures that provides either the necessary short range ordering or the initial precipitation of the hardening phase in the first step and avoids the solvus during the second step. This can be seen in the data for Alloy M in Table 3.
- Alloy K has higher molybdenum and lower chromium than Alloys M, N and O. Alloy K was tested at 704°C, 732°C and 760°C for 8, 16 and 32 hours as shown in Table 4. The data shows that the first treatment could be 8 hours at 760°C when the second step was conducted for 40 hours at 704°C or 718°C but not at 732°C. The second step could be run for 8 hours at 704°C when the first step was conducted for 32 hours at 732°C. From this data we conclude that higher temperatures can be used in the second step for alloys having higher molybdenum and lower chromium. Moreover, either step can be as short as 8 hours when the other step is 32 to 40 hours.
- an acceptable age hardening response can be obtained when the first step is at least about 8 hours long at a temperature ranging from about 691°C to about 760°C and the second step is at least about 8 hours long at a temperature of from about 538°C to about 718°C.
- the two-step age-hardening treatment here disclosed can be done in a total time of less than 100 hours and preferably less than 50 hours. Indeed, we prefer to complete the process in from 40 to 48 hours. By using heat treatments totaling less than 100 hours, and preferably not greater than 50 hours, one can produce lower cost, high chromium, Ni-Cr-Mo alloys that have desirable tensile properties. While the process here disclosed may also work when total aging times exceed 100 hours, the energy costs associated with such treatments make the process less desirable and commercially impractical.
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
- Heat Treatment Of Steel (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Heat Treatment Of Articles (AREA)
- Heat Treatment Of Nonferrous Metals Or Alloys (AREA)
Description
- The invention relates to heat treatment processes for nickel-chromium molybdenum-alloys having a chromium content of from 12 to 23.5 weight percent.
- It is well-known that chromium imparts corrosion resistance to nickel base alloys. Therefore, Ni-Cr-Mo alloys and particularly those with chromium content of 15 to 24% have been popular for use in corrosive environments such as encountered in the chemical and petrochemical industries.
- Age-hardening is a process used in the metallurgical industry to give an alloy composition higher strength, as measured by its yield strength, tensile strength, and by notched stress rupture tests typically used in the art. Various applications demand a combination of high tensile strength and low thermal expansion properties. One such application is in the aerospace industry. Another application is seal rings used in land-based gas turbines. A combination of high tensile strength and ductility is also very useful for bolts. Because of the demanding operating conditions and performance parameters for metal products in these applications, various methods of age-hardening have been used. One common technique is to heat the alloy to a selected high temperature, hold the alloy at that temperature for a period of time and then cool the alloy to room temperature. For some alloy compositions, the alloy may be heated to one temperature, cooled, heated again to a second temperature and cooled. Examples of these processes are disclosed in United States Patent No.
3,871,928 . The temperatures and time periods used to age harden an alloy depend upon the composition of the alloy. For all age-hardenable commercial alloys there are established times and temperatures used that have become standard in the industry because they are known to produce the desired properties. For Ni-Cr-Mo alloys having high chromium content, that is chromium greater than 12% , the general view in the art is that heat treatment beyond the initial annealing in an effort to improve mechanical properties would be impractical due to the lengthy required times (hundreds to thousands of hours) and such treatments simply have not been done. - Solid-solution strengthened nickel-chromium-molybdenum (Ni-Cr-Mo) alloys and nickel-molybdenum (Ni-Mo) alloys are widely utilized for commercial applications in the chemical industry, for example. Generally, considered to be single phase materials, discounting the presence of minor carbide phases, alloys such as these are not usually considered responsive to heat treatment, and are therefore used in the annealed condition. There are exceptions, where some particular alloys do exhibit a commercially exploitable age hardening response. However, in these instances the age-hardening response observed is attributable to other elements, such as niobium, aluminum and titanium being present in the alloy composition. The exception to this is HAYNES® 242™ alloy which will be discussed later. The fact that Ni-Cr-Mo and Ni-Mo alloys are not commercially age-hardenable does not mean that they do not exhibit any metallurgical response to thermal exposure at intermediate temperatures. Actually, alloys of this type can exhibit complex secondary phase reactions when exposed in the temperature range from about 538°C to 871°C. Unfortunately, the phases which form can often be deleterious to both alloy ductility and other aspects of service performance. This is particularly observed with Ni-Mo alloys containing about 25 to 30 % molybdenum. In such materials, exposure at temperatures from about 538°C to 871°C can result in the rapid formation of embrittling Ni3Mo or Ni4Mo phases in the microstructure. This can be a problem for both component manufacturing and for component performance.
- For lower molybdenum, higher chromium, content Ni-Cr-Mo alloys with about 16 % molybdenum and 16 % chromium weight percent content, the occurrence of these particular intermetallic phases is not usually observed after short term thermal exposures. With longer term exposure at temperatures from about 538°C to 649°C, there is a distinctly different metallurgical response. After about 500 to 1000 hours the presence of the phase Ni2(Mo,Cr) is evidenced in the microstructure. A long-range-ordered phase, with structure similar to that of Pt2Mo, the Ni2(Mo,Cr) phase serves to significantly increase the strength of these materials without a severe loss of ductility. The one major drawback is the prolonged aging time required to produce this phase.
- There are several United States patents that disclose Ni-Cr-Mo alloys. United States Patent No.
4,818,486 discloses a low thermal expansion nickel based alloy that contains 5% to 12% chromium and 10% to 30% molybdenum. The patent teaches that the aging times typically required to obtain desired hardness without deleterious phases being formed is well over 1000 hours at temperatures of 649°C to 816°C for most Ni-Mo-Cr alloys. However, the aging time to harden the alloy composition disclosed in the '486 patent is as little as 24 hours at 649°C. The alloy of this patent has been marketed under the trademarks 242 alloy and HAYNES 242 alloy. HAYNES 242 alloy has been sold for applications requiring high tensile strength and a low coefficient of thermal expansion. Other beneficial properties of the 242 alloy include good thermal stability, good low cycle fatigue resistance, and excellent containment capabilities due to its tensile strength and ductility. HAYNES 242 alloy consists of about 8 % (weight percent) chromium, about 20-30 % molybdenum, about 0.35 % to up to about 0.5 % aluminum, up to 0.03 % carbon, up to about 0.8 % manganese, up to about 0.8 % silicon, up to about 2 % iron, up to about 1 % cobalt, up to about 0.006 % boron, and the balance weight percent being nickel. - There is a need for a shorter commercially exploitable age hardening process for Ni-Mo-Cr alloys with higher Cr levels (>12% Cr) than found in
U.S. Patent No. 4,818,486 that avoids formation of deleterious Ni3Mo and Ni4Mo phase, as well as mu-phase occurrence. - Another Ni-Cr-Mo alloy is disclosed in United States Patent No.
5,019,184 to Crum et al. That alloy contains 19% to 23% chromium and 14 to 17% molybdenum. The patent discloses homogenization heat treatment at temperatures ranging from 1149°C to 1260°C for periods of from 5 to 50 hours. The purpose of the treatment is to produce a corrosion resistant alloy having a desired microstructure rather than to strengthen the alloy. No tensile strength data is given for any of these samples disclosed in the patent. The alloy of this patent has been commercialized under the designation INCONEL®alloy 686. - Yet another corrosion resistant Ni-Cr-Mo alloy is disclosed in United States Patent No.
4,906,437 to Heubner et al. This alloy contains 22% to 24% chromium and 15% to 16.5% molybdenum. There is no disclosure of any heat treatment or age hardening of this alloy. The alloy disclosed in this patent has been commercialized under the designation VDM NICROFER 923 h Mo or Alloy 59. - A high yield strength Ni-Cr-Mo alloy is disclosed in United States Patent No.
4,129,464 to Matthews et al. This alloy contains 13% to 18% chromium and 13% to 18% molybdenum. The patent says that the alloy could be aged using a single step aging treatment of at least 50 hours at 482°C to 593°C, but all examples are aged 168 hours or more. The statement that at least 50 hours is required was an extrapolation of the results obtained from a 168 hours aging treatment. The patent reports data for three alloys numbered 1, 2 and 3. Alloy 1 is commercially available under the trademark HASTELLOY C-276 alloy. Alloy 2 is commercially available as HASTELLOY C-4 alloy. Alloy 3 is commercially available as HASTELLOY S alloy. - We provide an improved two-step age hardening process for certain nickel-chromium-molybdenum alloys containing from 12% to 23.5% chromium that results in higher yield strength, high tensile strength and comparable other mechanical properties as those observed with the current age-hardening process used in the art, such properties being measured by yield strength, tensile strength, and tensile ductility tests at room temperature. This process works only for those alloys in which the other alloying elements are present in amounts so that the composition has a P value within the range of 31.2 to 35.9 where P is defined by the equation:
The improved age-hardening process involves an alloy with this P value that has been given an age hardening treatment at about 704°C for at least 8 hours and preferably for about 12 to 20 hours, furnace cooling to a temperature from about 538°C to about 718°C and holding the material at that temperature for at least 8 hours and preferably for about 28 to 36 hours, followed by air cooling to room temperature. A Ni-Cr-Mo alloy having 12% to 23.5% chromium and treated with this two-step heat treatment or age-hardening process shows improved or comparable tensile strength to the standard aging process used in the lower chromium level 242 alloy. Because of the combination of high yield strength and ductility properties, the alloy and two-step aging process significantly increase affordability of this alloy for applications requiring such properties. - Recently we have observed that a two stage heat treatment performed over a total time of from 10 to 20 hours can provide acceptable mechanical properties. However, when a similar two step process was tried for Ni-Cr-Mo alloys with higher chromium content, some alloys had acceptable properties while other alloys did not. A higher chromium content is desirable for alloys intended for use as corrosion-resistant alloys in the chemical process industry. Consequently, we saw a need for determining whether there existed a definable class of high chromium content alloys which would exhibit acceptable mechanical properties when subjected to a relatively short two step aging process. This is achieved by the selected alloys according to claim 1 in the age-hardened condition after a treatment according to method as claimed in claim 7 or dependent thereupon.
-
-
Figure 1 is a graph of the alloys tested based upon the P value and chromium content of the alloy. - We provide a two-step aging treatment for Ni-Cr-Mo alloys containing from 12% to 23.5% chromium to produce an alloy for applications requiring corrosion resistance, high tensile strength and excellent tensile ductility. This age hardening process involves aging the alloy at about 691°C to about 760°C for from 8 to 20 hours, cooling the alloy to a temperature of at from about 538°C to about 718°C, maintaining the alloy within that temperature range for at least 8 hours and preferably for from 24 to 36 hours and cooling the alloy to room temperature. We have found, however, that this process provides acceptable mechanical properties for only those alloys that contain alloying elements in amounts that provides a P value of from 31.2 to 35.9, P being defined as:
- We tested 20 nickel base test alloys and 5 Ni-Cr-Mo commercial alloys whose compositions are set forth in Table 1. The commercial alloys were HASTELLOY S sheet, HASTELLOY C-276 plate, HASTELLOY C-4 plate,
Alloy 59 sheet andINCONEL alloy 686 sheet. The designation "n.m." in Table 1 indicates that the presence of an element was not measured. Table 1 also reports the P value for each alloy. - The chromium content of the test alloys ranged from 11.56% for alloy H to 26.06% for alloy P. Molybdenum ranged from 9.91% in alloy G to 23.89% in alloy S. All of the alloys contained similar amounts of aluminum, cobalt, iron, and manganese. Tungsten was present within a range of 0.11% to 0.34%. The alloys also contained small amounts of boron, carbon, cerium, copper, magnesium, phosphorus, sulfur, silicon, and vanadium. The test alloys were annealed after hot rolling to 12.7mm plate at annealing temperatures in the range of 1038°C to 1093°C for thirty minutes. The commercial alloys were cut from sheets and plates available from the manufacturer. The sheets were 3.2mm and the plates were 9.5mm thick. In a first test series all of the alloys were treated with a two-step aging treatment in which they were first aged at 704°C for 16 hours. Finally, the samples were air cooled to room temperature.
Table 1 Composition Alloy Al B C Ce Co Cr Cu Fe Mg Mn Mo Nb Ni P (Phos.) S Si V W "P value" A 0.15 0.002 0.003 0.008 0.05 12.79 0.04 1.11 < 0.002 0.33 21.58 n.m. Bal. < 0.004 0.001 < 0.01 0.01 0.19 33.3 B 0.15 0.002 0.002 0.007 0.04 15.26 0.01 1.13 < 0.002 0.34 19.92 n.m. Bal. < 0.004 0.002 < 0.01 0.02 0.34 33.8 C 0.12 0.003 0.006 0.008 0.05 14.99 0.03 1.05 < 0.002 0.32 18.78 n.m. Bal. 0.002 0.001 0.01 < 0.01 0.15 32.2 D 0.12 0.005 0.002 < 0.005 0.08 17.36 0.03 1.08 0.003 0.32 17.21 n.m. Bal. 0.003 0.001 0.02 < 0.01 0.14 32.7 E 0.17 0.003 0.002 < 0.005 0.06 19.88 0.02 1.05 < 0.002 0.32 15.40 n.m. Bal. 0.005 0.001 0.03 < 0.01 0.14 33.1 F 0.14 0.002 0.003 0.007 0.06 22.18 0.02 1.09 < 0.002 0.31 13.32 n.m. Bal. 0.002 0.001 0.01 < 0.01 0.14 32.8 G 0.13 0.005 0.002 0.005 0.07 25.48 0.02 1.12 0.003 0.32 9.91 n.m. Bal. 0.002 0.001 0.02 < 0.01 0.18 32.2 H 0.15 < 0.002 0.003 0.007 0.05 11.56 0.06 1.17 0.003 0.34 19.75 n.m. Bal.. < 0.004 0.001 0.15 0.02 0.15 30.8 I 0.14 0.002 0.004 0.005 0.06 16.57 0.04 1.08 0.004 0.31 15.60 n.m. Bal. < 0.002 0.003 0.07 0.02 0.15 30.6 J 0.14 0.002 0.005 0.004 0.06 21.28 0.04 1.07 < 0.002 0.31 11.79 n.m. Bal. < 0.002 0.004 0.07 0.02 0.14 30.7 K 0.16 0.002 0.004 0.009 0.06 12.58 0.04 1.17 0.003 0.30 22.48 n.m. Bal. < 0.004 < 0.001 0.15 0.02 0.22 34.4 L 0.13 0.002 0.003 0.004 0.06 17.53 0.04 1.11 0.002 0.31 18.63 n.m. Bal. <0.004 0.003 0.11 0.02 0.15 34.5 M 0.17 0.002 0.006 0.005 0.06 22.28 0.01 1.17 0.002 0.30 14.73 n.m. Bal. 0.005 0.001 0.16 0.02 0.18 34.7 N 0.14 < 0.002 0.007 0.004 0.05 19.92 0.01 0.98 < 0.002 0.29 17.38 0.03 Bal. < 0.002 0.001 0.05 0.03 0.13 35.1 O 0.13 < 0.002 0.007 0.003 0.06 21.13 0.01 1.00 < 0.002 0.30 15.62 0.03 Bal. < 0.002 0.002 0.04 0.03 0.13 34.3 P 0.13 < 0.002 0.006 0.003 0.07 26.06 < 0.01 1.02 < 0.002 0.29 11.82 0.03 Bal. 0.003 0.001 0.06 0.04 0.13 34.6 Q 0.13 < 0.002 0.009 0.002 0.07 23.03 < 0.01 1.02 < 0.002 0.28 16.66 0.03 Bal. 0.003 0.001 0.05 0.03 0.13 36.9 R 0.13 < 0.002 0.007 0.005 0.06 17.92 0.01 1.04 0.002 0.27 20.08 0.03 Bal. 0.005 0.001 0.04 0.03 0.14 36.1 S 0.14 < 0.002 0.006 0.006 0.06 13.45 < 0.01 1.00 0.002 0.27 23.89 0.03 Bal. 0.002 0.001 0.04 0.03 0.15 36.2 T 0.14 < 0.002 0.009 0.002 0.06 23.97 < 0.01 0.99 < 0.002 0.30 13.60 0.03 Bal. 0.003 0.001 0.06 0.04 0.11 34.7 Hastelloy S 0.22 0.008 0.010 n.m 0.09 15.35 n.m 1.12 0.03 0.59 14.80 n.m Bal. n.m 0.005 0.48 0.23 30.0 C. 276 0.30 n.m 0.003 n.m 0.76 15.76 0.06 5.48 0.05 0.51 15.43 0.09 Bal. 0.007 0.002 n.m 0.12 3.39 33.3 C-4 0.34 n.m 0.002 Ti 0.23. n.m 15.54 0.02 1.01 0.05 0.18 15.41 n.m. Bal. n.m. n.m. 0.04 0.02 n.m. 30.1 59 0.30 n.m 0.002 n.m 0.08 22.75 0.01 0.65 n.m. 0.17 15.45 n.m. Bal. 0.002 0.002 0.05 n.m. n.m. 35.6 686 n.m. n.m 0.005 Ti 0.07 n.m 20.17 n.m 0.21 n.m. 0.23 16,08 n.m. Bal. 0.002 0.001 0.01 n.m. 3.94 34.7 - All of the samples were tested to determine their tensile properties. The tests determined yield strength, ultimate tensile strength, and percent elongation by following the standard ASTM E-8 test procedures for such alloys. The results of the first test series are reported in Table 2
TABLE 2 Room Temperature Tensile Properties Alloy 0.2%Yield Strength Ultimate Tensile Strength Percent Elongation MPa ksi MPa ksi A 816 118.3 1306 189.4 40.1 B 823 119.3 1300 188.5 40.7 C 723 104.8 1229 178.3 43.4 D 709 102.9 1222 177.3 43.5 E 690 100.0 1198 173.7 44.1 F 508 73.7 962 139.5 47.6 G 324 47.0 738 107.1 61.8 H 359 52.0 841 122.0 65.1 I 341 49.5 806 116.9 64.3 J 304 44.1 743 107.8 64.1 K 822 119.2 1338 194.0 41.1 L 659 95.6 1170 169.7 47.9 M 663 96.1 1166 169.1 45.8 N 644 93.4 1158 168.0 47.3 O 629 91.2 1145 166.1 47.3 P 343 49.8 761 110.4 60.7 Q 747 108.4 1227 177.9 34.5 R 809 117.4 1305 189.3 32.4 S 962 139.5 1473 213.6 28.0 T 409 59.3 825 119.7 57.8 HASTELLOYS 465 67.5 918 133.1 47.1 C-276 369 53.5 803 116.4 56.7 C-4 497 72.1 947 137.4 47.6 Alloy 59594 86.2 1066 154.6 47.3 INCONEL alloy 686682 98.9 1169 169.6 45.0 - Only test alloys A through F and K through O and commercial
alloys INCONEL alloy 686 andalloy 59 had acceptable tensile properties. Alloys G, H, I, J, P and T, as well as all the commercial alloys exceptINCONEL alloy 686 andalloy 59, have unacceptably low yield strengths. The acceptable alloys had elongation values greater than 40 percent and yield strengths greater than 500 MPa. Alloys Q, R and S did not posses enough tensile ductility as measured by the percent elongation. Microstructure analysis confirmed that this was due to the presence of undesirable precipitation of an unidentified phase. Since the chromium content and molybdenum content of the commercial alloys and alloys H, I, J, Q and R are within the range of chromium content and molybdenum content of the acceptable alloys it is clear that neither chromium content nor molybdenum content is the sole predictor of acceptable tensile properties in this class of alloys. We concluded that it is the interaction of nearly all of the alloying elements that is the predictor of such properties. Indeed, we discovered that when the alloy has a P value in the range of 31.2 to 35.9 acceptable tensile properties were achieved with this two-step aging process. An exception to this behavior was found in the HASTELLOY C-276 alloy which has a P value in the desired range, but did not have sufficient yield strength. However, the amount of 5.48% Fe in that alloy is sufficient to best call it a Ni-Cr-Mo-Fe alloy. Therefore, we suggest that a limit of about 3% Fe is needed for the above relationship to hold. -
Figure 1 is a graph of the tested alloys based upon the P value of the alloy and the chromium content. Each alloy that had acceptable tensile properties is plotted with a dot. An X is used to plot those alloys whose tensile properties were not acceptable after the alloy was subjected to the two-step aging treatment. A box has been drawn around the acceptable alloys. It is readily apparent fromFigure 1 that the acceptable alloys have a chromium content of 12% to 23.5% and a P value within the range of 31.2 to 35.9. - Those skilled in the art will recognize that while chromium and molybdenum must be present within the ranges encompassed by the test specimens, other alloying elements are not so limited. Indeed, those elements could be present in amounts within the ranges set forth in the UNS descriptions for commercially available Ni-Cr-Mo alloys which include those tested here and alloys such as C-2000® alloy, C-22® alloy, SM 2060 Mo alloy and MAT-21 alloy. More specifically there could be up to 0.05% aluminum, 0.015% boron, 0.02% carbon, 2.5% cobalt, 2.0% copper, 3.0% iron, 1.5% manganese, 1.25% niobium, 0.04% phosphorus, 0.03 % sulfur, 0.75% silicon, 2.2% tantalum, 0.7% titanium, 0.35% vanadium and 4.5% tungsten and 0.1% of a rare earth element.
- Having now defined the alloys that can benefit from the two-step age hardening process we considered what time and temperature range for each step would be acceptable. A series of aging treatments was given to Alloy M. After the aging treatments were performed the hardness was measured to determine whether the samples had age hardened. The results are shown in Table 3. A sample was determined to have age hardened if it had a Rockwell C (Rc) hardness value of more than 20.0. A sample in the unaged condition confirmed that the material started out with a hardness of less than 20.0. The test results for Alloy M indicate that the first step should be at least about 8 hours long at a temperature ranging from about 691°C to about 760°C while the second step should be at least about 24 hours long at a temperature ranging from about 538°C to about 691°C. The data also indicates that when a higher temperature is used for the first step then a lower temperature can be used for the second step. While first step temperatures of up to 927°C were found to be useful in age hardening the alloy, microstructural examination revealed that an undesirable grain boundary precipitation occurred when the first step temperature was 760°C or greater. This precipitation would be expected to degrade corrosion resistance.
- As is well-known in the art, Ni2(Mo,Cr) age hardening begins with short range ordering followed by creation of precipitates that impart the hardening property. Upon continued heating a solvus temperature will be reached at which the precipitates will go back into solution. The short range ordering is also related to time and temperature. Both the short range ordering and the solvus temperature vary from one- alloy composition to another. To provide age hardening any two-step aging treatment must involve a selection of times and temperatures that provides either the necessary short range ordering or the initial precipitation of the hardening phase in the first step and avoids the solvus during the second step. This can be seen in the data for Alloy M in Table 3. When the first step was 704°C or 732°C for 16 hours, sufficient short range ordering did not occur to support a second step of 538°C, while the solvus was reached at 621°C. When the first step was 760°C for 16 hours, sufficient short range ordering did occur to support a second step of 538°C while the solvus was again reached at 621°C.
- After reviewing the data for Alloy M we treated Alloys N and O using an aging of 704°C for 16 hours as the first step followed by a second aging at 593°C, 621°C or 649°C. We also treated Alloy K using a first aging treatment for 8 or 16 hours at 760°C, for 16 or 32 hours at 732°C or for 16 hours at 704°C and a second step between 593°C and 621°C for 8, 12, 16 or 32 hours. The treatment and results of that test work are shown in Table 4. For Alloys N and O hardening occurs with a second step aging treatment at 593°C or 621°C, but not at 649°C. The fact that Alloys N and O could be successfully hardened at 621°C, while Alloy M did not harden at that temperature, is attributable to the higher molybdenum and lower chromium in Alloys N and O compared to Alloy M.
- Alloy K has higher molybdenum and lower chromium than Alloys M, N and O. Alloy K was tested at 704°C, 732°C and 760°C for 8, 16 and 32 hours as shown in Table 4. The data shows that the first treatment could be 8 hours at 760°C when the second step was conducted for 40 hours at 704°C or 718°C but not at 732°C. The second step could be run for 8 hours at 704°C when the first step was conducted for 32 hours at 732°C. From this data we conclude that higher temperatures can be used in the second step for alloys having higher molybdenum and lower chromium. Moreover, either step can be as short as 8 hours when the other step is 32 to 40 hours.
- For other nickel-chromium-molybdenum alloys we can expect to see similar results although the temperature combinations may be different. Furthermore, the combinations that work are related to the chromium and molybdenum levels in the alloy. Yet, for alloys containing chromium content of 12% to 23.5% and a P value within the range of 31.2 to 35.9, an acceptable age hardening response can be obtained when the first step is at least about 8 hours long at a temperature ranging from about 691°C to about 760°C and the second step is at least about 8 hours long at a temperature of from about 538°C to about 718°C.
Table 3 The Effect of Different Aging Treatments on the Hardness of Alloy M 1st Step Temp 1st Step Time (h) 2nd Step Temp 2nd Step Time (h) Hardness (Rc) Unaged --- --- --- < 20.0 649°C/1200°F 16 538°C/1000°F 32 < 20.0 649°C/1200°F 16 566°C/1050°F 32 < 20.0 M9°C/1200°F 16 593°C/1100°F 32 < 20.0 649°C/1200°F 16 621°C/1150°F 32 < 20.0 649°C/1200°F 16 649°C/1200°F 32 < 20.0 677°C/1250°F 16 538°C/1000°F 32 < 20.0 677°C/1250°F 16 566°C/1050°F 32 < 20.0 677°C/1250°F 16 593°C/1100°F 32 < 20.0 677°C/1250°F 16 621°C/1150°F 32 < 20.0 677°C/1250°F 16 649°C/1200°F 32 < 20.0 704°C/1300°F 16 538°C/1000°F 32 < 20.0 704°C/1300°F 16 566°C/1050°F 32 20.7 704°C/1300°F 16 593°C/1100°F 32 28.6 704°C/1300°F 16 621°C/1150°F 32 < 20.0 704°C/1300°F 16 649°C/1200°F 32 < 20.0 732°C/1350°F 16 538°C/1000°F 32 < 20.0 732°C/1350°F 16 566°C/1050°F 32 27.4 732°C/1350°F 16 593°C/1100°F 32 31.2 732°C/1350°F 16 621°C/1150°F 32 < 20.0 732°C/1350°F 16 649°C/1200°F 32 < 20.0 760°C/1400°F 16 538°C/1000°F 32 24.9 760°C/1400°F 16 566°C/1050°F 32 26.6 760°C/1400°F 16 593°C/1100°F 32 28.4 760°C/1400°F 16 621°C/1150°F 32 < 20.0 760°C/1400°F 16 649°C/1200°F 32 < 20.0 816°C/1500°F 16 593°C/1100°F 32 31.0 871°C/1600°F 16 593°C/1100°F 32 30.4 927°C/1700°F 16 593°C/1100°F 32 27.8 704°C/1300°F 4 593°C/1100°F 4 < 20.0 704°C/1300°F 4 593°C/1100°F 8 < 20.0 704°C/1300°F 4 593°C/1100°F 16 < 20.0 704°C/1300°F 4 593°C/1100°F 44 < 20.0 704°C/1300°F 8 593°C/1100°F 4 < 20.0 704°C/1300°F 8 593°C/1100°F 8 < 20.0 704°C/1300°F 8 593°C/1100°F 16 < 20.0 704°C/1300°F 8 593°C/1100°F 32 20.1 704°C/1300°F 8 593°C/1100°F 40 29.4 704°C/1300°F 16 593°C/1100°F 4 < 20.0 704°C/1300°F 16 593°C/1100°F 8 < 20.0 704°C/1300°F 16 593°C/1100°F 16 < 20.0 704°C/1300°F 16 593°C/1100°F 24 20.4 Table 4 The Effect of Different Aging Treatments on the Hardness of Alloys N and O Alloy 1st Step Temp. 1st Step Time (h) 2nd Step Temp. 2nd Step Time (h) Hardness (Rc) K Unaged --- --- --- < 20 K 740°C/1300°F 16 593°C/1100°F 32 36.7 K 740°C/1300°F 16 649°C/1200°F 32 40.3 K 732°C/1350°F 16 677°C/1250°F 16 37.0 K 732°C/1350°F 32 704°C/1300°F 8 37.0 K 732°C/1350°F 16 704°C/1300°F 12 36.9 K 760°C/1400°F 16 704°C/1300°F 32 37.9 K 760°C/1400°F 8 704°C/1300°F 40 36.9 K 760°C/1400°F 16 718°C/1325°F 32 < 20 K 760°C/1400°F 8 718°C/1325°F 40 30.7 K 760°C/1400°F 16 732°C/1350°F 32 < 20 K 760°C/1400°F 8 732°C/1350°F 40 < 20 N Unaged --- --- --- < 20 N 704°C/1300°F 16 593°C/1100°F 32 30.7 N 704°C/1300°F 16 621°C/1150°F 32 32.7 N 704°C/1300°F 16 649°C/1200°F 32 < 20 O Unaged --- --- --- < 20 O 704°C/1300°F 16 593°C/1100°F 32 30.2 O 704°C/1300°F 16 621°C/1150°F 32 23.9 O 704°C/1300°F 16 649°C/1200°F 32 < 20 - This process represents a significant advancement. Prior to the present invention Ni-Cr-Mo alloys having greater that 12% chromium were not produced in the age hardened condition since the required aging times were considered to be too great. Because of the energy costs associated with such long treatments the estimated cost of a higher chromium, age-hardened alloy was considered too high and no such alloys are in commercial existence. The two-step age-hardening treatment here disclosed can be done in a total time of less than 100 hours and preferably less than 50 hours. Indeed, we prefer to complete the process in from 40 to 48 hours. By using heat treatments totaling less than 100 hours, and preferably not greater than 50 hours, one can produce lower cost, high chromium, Ni-Cr-Mo alloys that have desirable tensile properties. While the process here disclosed may also work when total aging times exceed 100 hours, the energy costs associated with such treatments make the process less desirable and commercially impractical.
Claims (11)
- An age hardened nickel-chromium-molybdenum alloy having superior yield strength, in weight percent comprised of:
from 12% to 23.5% chromium; from 13% to 23% molybdenum; up to 0.5% aluminum; up to 0.02% carbon; up to 1.5% manganese; up to 3% iron; up to 2.5% cobalt; up to 4.5% tungsten; up to 0.015% boron; up to 1.25% niobium; up to 0.75% silicon; up to 2.2% tantalum; up to 0.35% vanadium; up to 2.0% copper; up to 0.04% phosphorus; up to 0.7% titanium; up to 0.03% sulfur; optionally 0.001% to 0.004% magnesium;
a balance of nickel plus unavoidable impurities;
wherein the alloy has a P value of from 31.2 to 35.9, P being defined as:
and the alloy is obtained by a two step heat treatment comprised of:aging the alloy at 691°C to 760°C for at least 8 hours;cooling the alloy to a temperature of from 538°C to 718°C; and eithermaintaining the alloy within that temperature range for at least 8 hours; orcooling the alloy to room temperature, wherein the two step heat treatment is completed in not more than 100 hours. - The alloy of claim 1 wherein the two step heat treatment is comprised of:aging the alloy at 704°C to 760°C for 16 hours;cooling the alloy to a temperature of 593°C to 621°C;maintaining the alloy at that temperature for 32 hours ; andcooling the alloy to room temperature.
- The alloy of claim 1 wherein the alloy is comprised of:
from 0.12% to 0.2% aluminum; from 0.002% to 0.006% carbon; from 0.30% to 0.34% manganese; from 1.0% to 1.7% iron; from 0.05% to 0.8% cobalt; 0.10% to 0.34% tungsten; and from 0.002% to 0.005% boron. - The alloy of claim 3 comprising in weight percent:
from 0.005% to 0.009% cerium; from 0.01% to 0.06% copper; from 0.001% to 0.004% magnesium; from 0.002% to 0.005% phosphorus; from 0.001% to 0.004% sulfur; and from 0.01% to 0.02% vanadium. - The alloy of any preceding claim further comprising after cooling the alloy to a temperature of from 538°C to 718°C cooling is continued until the alloy reaches room temperature and then heating the alloy to a temperature from 538°C to 718°C.
- The alloy of claim 1 wherein the two step heat treatment is completed in not more than 50 hours.
- A method for treating an age hardened nickel-chromium-molybdenum alloy having a composition comprised of from 12% to 23.5% chromium, from 13% to 23% molybdenum, up to 0.5% aluminum, up to 0.02% carbon, up to 1.5% manganese, up to 3% iron, up to 2.5% cobalt, up to 4.5% tungsten, up to 0.015% boron, up to 1.25% niobium, up to 0.75% silicon, up to 2.2% tantalum, up to 0.7% titanium, up to 2.0% copper, up to 0.35% vanadium, up to 0.03% sulfur, optionally 0.001% to 0.004% magnesium, up to 0.04% phosphorus, up to 0.1 % of a rare earth element, and the balance nickel plus unavoidable impurities, wherein the alloy has a P value of from 31.2 to 35.9, P being defined as:
the method comprised of:aging the alloy at 691°C to 760°C for at least 8;cooling the alloy to a temperature of from 538°C to 718°C; and eithermaintaining the alloy within that temperature range for at least 8 hours, or after cooling the alloy to a temperature of at least 538°C cooling is continued until the alloy reaches room temperature and then heating again the alloy to a temperature of from 538°C to 718°C, and maintaining the alloy within that temperature range for at least 8 hours ; andcooling the alloy to room temperature, wherein the two step heat treatment is completed in not more than 100 hours. - The method of claim 7 wherein the two step heat treatment is completed in not more than 50 hours.
- The method of claim 7 wherein the alloy is aged at 704°C to 760°C for 16 hours, cooled to a temperature of 593°C to 621°C, maintained at that temperature for 32 hours, and cooled to a room temperature.
- The method of claim 7 wherein the alloy is furnace cooled to a temperature of from 538°C to 718°C.
- The method of claim 7 further comprising
Applications Claiming Priority (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US165650 | 1988-03-08 | ||
US09/894,179 US6544362B2 (en) | 2001-06-28 | 2001-06-28 | Two step aging treatment for Ni-Cr-Mo alloys |
US894179 | 2001-06-28 | ||
US10/165,650 US6638373B2 (en) | 2001-06-28 | 2002-06-07 | Two step aging treatment for Ni-Cr-Mo alloys |
Publications (2)
Publication Number | Publication Date |
---|---|
EP1270754A1 EP1270754A1 (en) | 2003-01-02 |
EP1270754B1 true EP1270754B1 (en) | 2012-04-25 |
Family
ID=26861569
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP02014216A Expired - Lifetime EP1270754B1 (en) | 2001-06-28 | 2002-06-26 | Two-step aging treatment for Ni-Cr-Mo alloys |
Country Status (9)
Country | Link |
---|---|
EP (1) | EP1270754B1 (en) |
JP (1) | JP4206229B2 (en) |
KR (1) | KR20030003017A (en) |
CN (1) | CN1246490C (en) |
AU (1) | AU785025B2 (en) |
CA (1) | CA2391903C (en) |
GB (1) | GB2377944B (en) |
MX (1) | MXPA02006453A (en) |
TW (1) | TWI224146B (en) |
Families Citing this family (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6860948B1 (en) * | 2003-09-05 | 2005-03-01 | Haynes International, Inc. | Age-hardenable, corrosion resistant Ni—Cr—Mo alloys |
KR20030003016A (en) * | 2001-06-28 | 2003-01-09 | 하이네스인터내셔널인코포레이티드 | AGING TREATMENT FOR Ni-Cr-Mo ALLOYS |
US7785532B2 (en) | 2006-08-09 | 2010-08-31 | Haynes International, Inc. | Hybrid corrosion-resistant nickel alloys |
JP4816950B2 (en) * | 2006-11-10 | 2011-11-16 | 三菱マテリアル株式会社 | Ni-base alloy excellent in corrosion resistance and wear resistance and conductor roll made of the Ni-base alloy |
CN101333613B (en) * | 2008-08-06 | 2010-06-09 | 钢铁研究总院 | Nickel-based expansion alloy for metal connector of medium temperature plate type solid-oxide fuel battery |
DE102011013091A1 (en) * | 2010-03-16 | 2011-12-22 | Thyssenkrupp Vdm Gmbh | Nickel-chromium-cobalt-molybdenum alloy |
US9761883B2 (en) | 2011-11-03 | 2017-09-12 | Johnson Controls Technology Company | Battery grid with varied corrosion resistance |
CN103740983B (en) * | 2013-12-19 | 2015-11-04 | 重庆材料研究院有限公司 | High tough corrosion-resistant ageing strengthening type nickel-base alloy and direct aging heat treating method |
JP5725630B1 (en) * | 2014-02-26 | 2015-05-27 | 日立金属Mmcスーパーアロイ株式会社 | Ni-base alloy with excellent hot forgeability and corrosion resistance |
RU2672647C1 (en) * | 2017-08-01 | 2018-11-16 | Акционерное общество "Чепецкий механический завод" | Corrosive-resistant alloy |
EP3950177A4 (en) * | 2019-09-06 | 2023-01-11 | Hitachi Metals, Ltd. | Ni-based alloy, ni-based alloy powder, ni-based alloy member, and product provided with ni-based alloy member |
CN114045452A (en) * | 2021-11-15 | 2022-02-15 | 贵州航宇科技发展股份有限公司 | Forging and heat treatment method of Haynes242 alloy forging |
CN114182139B (en) * | 2021-12-10 | 2022-12-02 | 西北工业大学 | Precipitation strengthening nickel-based high-temperature alloy and preparation method thereof |
CN116716518B (en) * | 2023-06-30 | 2024-02-09 | 江西宝顺昌特种合金制造有限公司 | Hastelloy C-4 tube plate and preparation method thereof |
Family Cites Families (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US4043810A (en) * | 1971-09-13 | 1977-08-23 | Cabot Corporation | Cast thermally stable high temperature nickel-base alloys and casting made therefrom |
US3871928A (en) * | 1973-08-13 | 1975-03-18 | Int Nickel Co | Heat treatment of nickel alloys |
JPS5837382B2 (en) * | 1976-06-04 | 1983-08-16 | 三菱重工業株式会社 | Heat treatment method for nickel-based heat-resistant alloy |
US4129464A (en) * | 1977-08-24 | 1978-12-12 | Cabot Corporation | High yield strength Ni-Cr-Mo alloys and methods of producing the same |
US4245698A (en) * | 1978-03-01 | 1981-01-20 | Exxon Research & Engineering Co. | Superalloys having improved resistance to hydrogen embrittlement and methods of producing and using the same |
JPH064900B2 (en) * | 1984-12-19 | 1994-01-19 | 日立金属株式会社 | Corrosion resistance High strength Ni-based alloy |
US5556594A (en) * | 1986-05-30 | 1996-09-17 | Crs Holdings, Inc. | Corrosion resistant age hardenable nickel-base alloy |
US5217684A (en) * | 1986-11-28 | 1993-06-08 | Sumitomo Metal Industries, Ltd. | Precipitation-hardening-type Ni-base alloy exhibiting improved corrosion resistance |
JPH03257131A (en) * | 1990-03-07 | 1991-11-15 | Mitsubishi Materials Corp | Cutlery material made of ni-based alloy precipitation hardened with intermetallic compound and production thereof |
US5360496A (en) * | 1991-08-26 | 1994-11-01 | Aluminum Company Of America | Nickel base alloy forged parts |
DE4203328C1 (en) * | 1992-02-06 | 1993-01-07 | Krupp Vdm Gmbh, 5980 Werdohl, De |
-
2002
- 2002-06-25 KR KR1020020035498A patent/KR20030003017A/en not_active Application Discontinuation
- 2002-06-26 AU AU50645/02A patent/AU785025B2/en not_active Expired
- 2002-06-26 GB GB0214712A patent/GB2377944B/en not_active Expired - Lifetime
- 2002-06-26 EP EP02014216A patent/EP1270754B1/en not_active Expired - Lifetime
- 2002-06-27 MX MXPA02006453A patent/MXPA02006453A/en active IP Right Grant
- 2002-06-27 CN CNB021472084A patent/CN1246490C/en not_active Expired - Lifetime
- 2002-06-27 CA CA002391903A patent/CA2391903C/en not_active Expired - Lifetime
- 2002-06-28 JP JP2002190729A patent/JP4206229B2/en not_active Expired - Lifetime
- 2002-06-28 TW TW091114334A patent/TWI224146B/en not_active IP Right Cessation
Also Published As
Publication number | Publication date |
---|---|
TWI224146B (en) | 2004-11-21 |
GB0214712D0 (en) | 2002-08-07 |
CN1246490C (en) | 2006-03-22 |
MXPA02006453A (en) | 2004-05-05 |
KR20030003017A (en) | 2003-01-09 |
AU785025B2 (en) | 2006-08-24 |
GB2377944A (en) | 2003-01-29 |
JP2003027163A (en) | 2003-01-29 |
EP1270754A1 (en) | 2003-01-02 |
CN1412331A (en) | 2003-04-23 |
GB2377944B (en) | 2005-03-23 |
CA2391903C (en) | 2009-09-29 |
GB2377944A9 (en) | 2003-03-13 |
JP4206229B2 (en) | 2009-01-07 |
CA2391903A1 (en) | 2002-12-28 |
AU5064502A (en) | 2003-01-02 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
EP1270755B1 (en) | Aging treatment for Ni-Cr-Mo alloys | |
JP4861651B2 (en) | Advanced Ni-Cr-Co alloy for gas turbine engines | |
US3046108A (en) | Age-hardenable nickel alloy | |
EP1270754B1 (en) | Two-step aging treatment for Ni-Cr-Mo alloys | |
EP1512767A1 (en) | Age-hardenable, corrosion resistant Ni-Cr-Mo alloys | |
EP3775307B1 (en) | High temperature titanium alloys | |
KR102660878B1 (en) | METHOD FOR PRODUCING TWO-PHASE Ni-Cr-Mo ALLOYS | |
JP3308090B2 (en) | Fe-based super heat-resistant alloy | |
US6638373B2 (en) | Two step aging treatment for Ni-Cr-Mo alloys | |
JP2010265550A (en) | AGING TREATMENT FOR Ni-Cr-Mo ALLOY | |
JP2002097537A (en) | Co-ni based heat resistant alloy and manufacturing method | |
JP3794999B2 (en) | Nickel-base alloy, nickel-base alloy heat treatment method, and nuclear component using nickel-base alloy | |
US5429690A (en) | Method of precipitation-hardening a nickel alloy | |
RU2791029C1 (en) | Nickel alloy with good corrosion resistance and high tensile strength and method for production of semi-products | |
RU2808314C2 (en) | Method for producing nickel alloy powder with good corrosion resistance and high tensile strength and its application (options) | |
JPS6343457B2 (en) | ||
JPH0684535B2 (en) | Method for producing nickel-based alloy | |
JPH11140570A (en) | Nickel alloy with high strength and high corrosion resistance, and its production |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
PUAI | Public reference made under article 153(3) epc to a published international application that has entered the european phase |
Free format text: ORIGINAL CODE: 0009012 |
|
AK | Designated contracting states |
Kind code of ref document: A1 Designated state(s): AT BE CH CY DE DK ES FI FR GB GR IE IT LI LU MC NL PT SE TR |
|
AX | Request for extension of the european patent |
Free format text: AL;LT;LV;MK;RO;SI |
|
17P | Request for examination filed |
Effective date: 20030409 |
|
AKX | Designation fees paid |
Designated state(s): AT DE FR IT SE |
|
GRAP | Despatch of communication of intention to grant a patent |
Free format text: ORIGINAL CODE: EPIDOSNIGR1 |
|
GRAS | Grant fee paid |
Free format text: ORIGINAL CODE: EPIDOSNIGR3 |
|
GRAA | (expected) grant |
Free format text: ORIGINAL CODE: 0009210 |
|
AK | Designated contracting states |
Kind code of ref document: B1 Designated state(s): AT DE FR IT SE |
|
REG | Reference to a national code |
Ref country code: AT Ref legal event code: REF Ref document number: 555222 Country of ref document: AT Kind code of ref document: T Effective date: 20120515 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R096 Ref document number: 60242722 Country of ref document: DE Effective date: 20120621 |
|
REG | Reference to a national code |
Ref country code: SE Ref legal event code: TRGR |
|
PLBE | No opposition filed within time limit |
Free format text: ORIGINAL CODE: 0009261 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT |
|
26N | No opposition filed |
Effective date: 20130128 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R097 Ref document number: 60242722 Country of ref document: DE Effective date: 20130128 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 15 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 16 |
|
REG | Reference to a national code |
Ref country code: FR Ref legal event code: PLFP Year of fee payment: 17 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: FR Payment date: 20210625 Year of fee payment: 20 Ref country code: DE Payment date: 20210629 Year of fee payment: 20 Ref country code: IT Payment date: 20210621 Year of fee payment: 20 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: AT Payment date: 20210604 Year of fee payment: 20 |
|
PGFP | Annual fee paid to national office [announced via postgrant information from national office to epo] |
Ref country code: SE Payment date: 20210630 Year of fee payment: 20 |
|
REG | Reference to a national code |
Ref country code: DE Ref legal event code: R071 Ref document number: 60242722 Country of ref document: DE |
|
REG | Reference to a national code |
Ref country code: SE Ref legal event code: EUG |
|
REG | Reference to a national code |
Ref country code: AT Ref legal event code: MK07 Ref document number: 555222 Country of ref document: AT Kind code of ref document: T Effective date: 20220626 |