CN111036811A - High-temperature alloy forging heat treatment method and product thereof - Google Patents
High-temperature alloy forging heat treatment method and product thereof Download PDFInfo
- Publication number
- CN111036811A CN111036811A CN201911267658.8A CN201911267658A CN111036811A CN 111036811 A CN111036811 A CN 111036811A CN 201911267658 A CN201911267658 A CN 201911267658A CN 111036811 A CN111036811 A CN 111036811A
- Authority
- CN
- China
- Prior art keywords
- forging
- equal
- sample
- temperature
- less
- 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.)
- Granted
Links
- 238000005242 forging Methods 0.000 title claims abstract description 57
- 229910045601 alloy Inorganic materials 0.000 title claims abstract description 55
- 239000000956 alloy Substances 0.000 title claims abstract description 55
- 238000010438 heat treatment Methods 0.000 title claims abstract description 39
- 238000000034 method Methods 0.000 title claims abstract description 32
- 238000004321 preservation Methods 0.000 claims description 20
- 229910000601 superalloy Inorganic materials 0.000 claims description 19
- 238000001816 cooling Methods 0.000 claims description 18
- 239000002994 raw material Substances 0.000 claims description 6
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 5
- 238000011056 performance test Methods 0.000 claims description 3
- 238000005336 cracking Methods 0.000 abstract description 4
- 239000000463 material Substances 0.000 description 12
- 230000003647 oxidation Effects 0.000 description 6
- 238000007254 oxidation reaction Methods 0.000 description 6
- 238000011161 development Methods 0.000 description 3
- 239000000126 substance Substances 0.000 description 3
- 238000012360 testing method Methods 0.000 description 3
- 229910001030 Iron–nickel alloy Inorganic materials 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 2
- 239000013078 crystal Substances 0.000 description 2
- 239000000203 mixture Substances 0.000 description 2
- 239000010959 steel Substances 0.000 description 2
- 238000012935 Averaging Methods 0.000 description 1
- 229910020598 Co Fe Inorganic materials 0.000 description 1
- 229910002519 Co-Fe Inorganic materials 0.000 description 1
- 229910000599 Cr alloy Inorganic materials 0.000 description 1
- 229910001374 Invar Inorganic materials 0.000 description 1
- 229910017709 Ni Co Inorganic materials 0.000 description 1
- 229910003267 Ni-Co Inorganic materials 0.000 description 1
- 229910003262 Ni‐Co Inorganic materials 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 150000002739 metals Chemical class 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000005070 sampling Methods 0.000 description 1
- 229910000859 α-Fe Inorganic materials 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
- B21J1/00—Preparing metal stock or similar ancillary operations prior, during or post forging, e.g. heating or cooling
- B21J1/003—Selecting material
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
- B21J1/00—Preparing metal stock or similar ancillary operations prior, during or post forging, e.g. heating or cooling
- B21J1/06—Heating or cooling methods or arrangements specially adapted for performing forging or pressing operations
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21J—FORGING; HAMMERING; PRESSING METAL; RIVETING; FORGE FURNACES
- B21J5/00—Methods for forging, hammering, or pressing; Special equipment or accessories therefor
- B21J5/002—Hybrid process, e.g. forging following casting
-
- 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
- C22C19/057—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being less 10%
-
- 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
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
- Forging (AREA)
Abstract
A forging and heat treatment method of high-temperature alloy and a product thereof belong to the technical field of alloy forging. The alloy comprises the following components in percentage by weight: mo: 21-24, Cr: 7-10, Wu: 5-8, Fe: 2, Mn: less than or equal to 0.8, Al: less than or equal to 0.5, C: less than or equal to 0.03, and the balance being Ni. The method has the advantages that the product manufactured by the method can reach 760 ℃, and when the product is used at 760 ℃, the product has low expansion and high strength, and when the product is used at 650 ℃, the product is stretched at the high temperature: the tensile strength (MPa) is not less than 896, the yield strength (MPa) is not less than 552, the elongation (%) is not less than 13, and the reduction of area (%) is not less than 16, thereby effectively reducing the cracking risk of the alloy in the forging process.
Description
Technical Field
The invention relates to a forging method, in particular to a forging method of a high-temperature alloy.
Background
Thermal expansion of metals and alloys is the result of uncoordinated vibrations of the lattice. The volume of the ordinary metal material is almost linearly expanded with the temperature rise, and the ferrite heat-resistant steel is usually about 10 to 14X10 in terms of linear expansion coefficient a between 20 ℃ and 80 DEG C6The Ni-based superalloy is about 12-16X 10 DEG C6The Fe-Ni based superalloy has a temperature of 14 to 17X10 DEG C6V. DEG C, 16 to 19X10 for austenitic steel6V. C. Certain alloys with specific compositional proportions have abnormally low or constant coefficients of expansion and are referred to as low expansion alloys. From the earliest commercial low expansion Fe-Ni alloys (Fe-36% Ni, Invar alloy), Fe-Ni-Co (International alloy designation IN9XX, domestic alloy designation GH9XX) series low expansion alloys, to Ni-Co-Fe series low expansion alloys and the recently developed Thermo-Span, In738, Haynes242 and USC141 low expansion alloys, people have been developing various low expansion alloys that can meet the requirements at different temperatures by adjusting the alloy components. Recently, with rapid development in the fields of aviation and energy, high-temperature low-expansion alloys and rapid development thereof have been promoted. Currently, high temperature low expansion alloys are widely used to fabricate seal rings, shafts, casings, blades, fasteners and other structural components requiring approximately constant dimensions in certain high temperature environments for gas and steam turbines.
Previous researches show that the poor high-temperature oxidation resistance of the low-expansion alloy can seriously affect the use temperature range of the low-expansion alloy, and the low-thermal expansion property and the high oxidation resistance are a pair of contradictions in the low-expansion high-temperature alloy, which mutually affect and restrict the development of the high-temperature low-expansion alloy.
IN order to keep the low expansion coefficient of the alloy low, the low expansion alloy developed earlier generally does not contain Cr, Al and other elements which are oxidation resistant, so that the oxidation resistance of the alloy is poor, as disclosed IN patent US4200459, US5192497, published patent No. Sho 54-90013, Japanese patent laid-open No. Hei 5-70894, alloy IN907, IN909 and HRA929, etc. In order to improve the oxidation resistance of the alloy, the addition of elements such as Cr and Al is tried, such as patents US4006012, CN1053094A, US4200459.CN1053094A, CN102485930A, Japanese patent 2007-225702, Japanese patent 2010-95940 and the like. The improved low expansion alloy HRA929C contained 8.0% Cr, IN783 contained 20% Cr, Thermal-Span contained 5.5% Cr, Haynes242 contained 8.0% Cr, and USC141 contained 20% Cr. The increase of the amount of Cr in the alloy improves the oxidation resistance of the alloy, but also increases the design difficulty of keeping the alloy at high temperature and low expansibility, because the addition of Cr causes the thermal expansion coefficient of the alloy to be greatly increased along with the increase of the temperature. At the end of the 80 s, Haynes, Inc. developed a high temperature, low expansion Ni-Mo-Cr alloy containing Cr (2%), Mo (25%), Ni (8%), Hayness242 alloy having a coefficient of thermal expansion between 20 ℃ and 750 of about 14X106/℃.
Haynes 244 is a novel 760 ℃ low-thermal expansion high-strength alloy, and the chemical component of the alloy is Ni-8Cr-22.5 Mo-6W. The Haynes 244 material is close to the Haynes242 material, compared with the Haynes242 material, the use temperature of the Haynes242 is limited to about 650 ℃, the use temperature of the Haynes 244 can reach 760 ℃, the strength of the Haynes 244 material is obviously higher than that of the Haynes242 material at 760 ℃, the requirement of high-temperature low-thermal-expansion alloy can be met, parts produced by the Haynes 244 material are widely used in various advanced combustion engines at present, and the Haynes 244 material is a preferred high-quality part of an aero-engine. The Haynes 244 alloy is relatively narrow in forging temperature range compared to other types of superalloys and is susceptible to forging cracks during forging. If the selected forging temperature is too low, surface cracks after forging are serious, if the temperature is too high, the grain size is coarse or the structure performance can not meet the use requirement, and the influence of the heat treatment temperature on the high-temperature performance and the structure is large. The material is a novel material in the domestic forging industry, the forging and heat treatment parameters and the performance and tissue rules of the product have no reference values, and the material is easy to crack in the forging process and is difficult to apply to the current industrial manufacturing.
Disclosure of Invention
The invention provides a forging and heat treatment method of high-temperature alloy, the service temperature of a product manufactured by the method can reach 760 ℃, the expansion is low, the strength is high, and the product is manufactured by the method under the high-temperature stretching state at 650 ℃: the tensile strength (MPa) is not less than 896, the yield strength (MPa) is not less than 552, the elongation (%) is not less than 13, and the reduction of area (%) is not less than 16, thereby effectively reducing the cracking risk of the alloy in the forging process.
A high-temperature alloy forging heat treatment method comprises the following steps:
step 1: selecting N first samples from high-temperature alloy raw materials, wherein N is an odd number and is more than or equal to 3, and forging temperature ThLength of heat preservation WxNext, the forging deformation of the sample is set to Sa(ii) a Each of the first samples was then tested for grain size GmWherein T ish+1＝Th+T0,Sa+1＝Sa+S0Selecting a first sample with different forging deformation SaTime grain size GmG or more0Has a lowest temperature value of T in ThminSelecting a first sample with different grain sizes GmForging strain SaGreater than or equal to S0T ofhThe highest value of the medium temperature is Tmax(ii) a Selecting a first sample at different forging temperatures ThTime grain size GmG or more0S ofaThe lowest middle deformation is SminSelecting a first sample with different grain sizes GmForging temperature ThGreater than or equal to T0S ofaThe highest middle deformation is Smax；
Step 2: the grain size G of the sample forged in the step 1mG or more0Each sample of (a) is prepared into N second samples, wherein N is an odd number and N is more than or equal to 3, and each second sample is heated at a heating temperature TiThe heat preservation time is WyIs subjected to a heat treatment followed by cooling, wherein Ti+1＝Ti+T0,Wy+1＝Wy+W0Then testing each secondGrain size G of samplenSelecting the grain size G of a second sample at different heat preservation time WynG or more0Heating temperature T ofiThe lowest temperature value of (a) is Tmin2Selecting the grain size G of a second sample at different heat preservation time WynG or more0Heating temperature T ofiThe highest temperature value of (a) is Tmax2；
And step 3: the grain size G of the sample forged in the step 2nG or more0Each of the samples of (1) is prepared into N third samples, wherein N is an odd number and N is more than or equal to 3, and each of the third samples is heated at a heating temperature TjThe heat preservation time is WzIs subjected to a heat treatment followed by cooling, wherein Tj+1＝Tj+T0,Wz+1＝Wz+W0Then each third sample was tested for grain size GpSelecting the grain size G of a third sample at different heat preservation time lengths WzpG or more0Heating temperature T ofjThe lowest temperature value of (a) is Tmin3Selecting the grain size G of a third sample at different heat preservation time lengths WzpG or more0Heating temperature T ofjThe highest temperature value of (a) is Tmax3；
And 4, step 4: performing structure and performance tests on the third sample in the step 3, and selecting the lowest grain size G of the forge piece when the structure and performance parameters of the third sample are qualifiedminMaximum grain size Gmax。
Further, said T0Constant value, T0At 5 deg.C, 10 deg.C, 20 deg.C, 30 deg.C, 40 deg.C or 50 deg.C.
Further, said S0Constant value, S05%, 10%, 20%, 30%, 40% or 50%.
Further, W is0Is a constant value, W05 minutes, 10 minutes, 20 minutes, 30 minutes, or 50 minutes.
Further, said G0Grain size grade, G0Grade 1 or more.
Further, the forging deformation SaS is more than or equal to 10 percenta≤30％。
Further, the heat preservation time length WxThe effective thickness of the bar is multiplied by 6min/10mm, and W is more than or equal to 60minxLess than or equal to 120 min; w isyW is less than or equal to 65minyLess than or equal to 70 min; w iszW is more than or equal to 15hz≤17h.
Furthermore, the cooling mode is water cooling or air cooling.
Further, the cooling mode in the second step adopts water cooling, and the cooling mode in the third step adopts air cooling; or air cooling is adopted in the cooling mode in the step two, and water cooling is adopted in the step three.
Further, the temperature T is heatedhT is more than or equal to 1080 DEG Ch≤1150℃；TiT is more than or equal to 1050 DEG Ch≤1150℃；TjT is more than or equal to 700 DEG Ch≤780℃。
Further, the structure and performance parameters of the third sample set the acceptable values as the following parameters: under the state of stretching at room temperature: the tensile strength (MPa) is more than or equal to 1241, the yield strength (MPa) is more than or equal to 758, the percentage of elongation (%)) is more than or equal to 17, and the percentage of reduction of area (%)) is more than or equal to 18;
under the high-temperature stretching state at 650 ℃: the tensile strength (MPa) is not less than 896, the yield strength (MPa) is not less than 552, the elongation (%) is not less than 13, and the reduction of area (%) is not less than 16.
Further, the high-temperature alloy raw material comprises the following components in percentage by weight: mo: 21-24, Cr: 7-10, Wu: 5-8, Fe: 2, Mn: less than or equal to 0.8, Al: less than or equal to 0.5, C: less than or equal to 0.03, and the balance being Ni.
Further, the high-temperature alloy raw material comprises the following components in percentage by weight: mo: 22-23, Cr: 7.5-8.5, Wu: 5.4-6.7, Fe: 2, Mn: less than or equal to 0.8, Al: less than or equal to 0.5, C: less than or equal to 0.03, and the balance being Ni.
Further, the structural and performance parameters of the superalloy product meet the following conditions: under the state of stretching at room temperature: the tensile strength (MPa) is more than or equal to 1241, the yield strength (MPa) is more than or equal to 758, the percentage of elongation (%)) is more than or equal to 17, and the percentage of reduction of area (%)) is more than or equal to 18;
under the high-temperature stretching state at 650 ℃: the tensile strength (MPa) is not less than 896, the yield strength (MPa) is not less than 552, the elongation (%) is not less than 13, and the reduction of area (%) is not less than 16.
Further, the forging temperature of the superalloy product is set to T or moreminAnd is less than or equal to TmaxAnd the forging deformation is set to be S or moreminAnd is less than or equal to SmaxForging the blank, wherein the heat preservation time length is set to be more than or equal to WminAnd is less than or equal to Wmax，The grain size of the product is more than or equal to GminAnd is less than or equal to Gmax。
The invention provides a forging and heat treatment method of high-temperature alloy, the service temperature of the product manufactured by the method can reach 760 ℃, the expansion is low, the strength is high, and the product manufactured by the method is in a high-temperature stretching state at 650 ℃: the tensile strength (MPa) is not less than 896, the yield strength (MPa) is not less than 552, the elongation (%) is not less than 13, and the reduction of area (%) is not less than 16, thereby effectively reducing the cracking risk of the alloy in the forging process.
Drawings
FIG. 1 is a flow chart of a high temperature alloy forging heat treatment method.
Detailed Description
The technical solution of the present invention will be further described with reference to the accompanying drawings and the detailed description.
The chemical composition of a superalloy is shown in table 1:
TABLE 1 chemical composition of the superalloy
The alloy with the components adopts the following forging and heat treatment method, and the steps are as follows:
step 1: the alloy raw materials in the table 1 are respectively sawed into 5 sections of materials with the diameter of 200mm multiplied by 70mm for forging, and the heating temperature ThSetting the temperature at 1000 ℃,1050 ℃,1080 ℃,1100 ℃,1150 ℃ and the heat preservation time WxAccording to the formula: calculating the effective thickness of the bar multiplied by 6min/10mm and the deformation quantity SaSelecting 10%, 15%, 21%, 29% and 30%, checking the grain size of the forged piece after forging, and averaging to obtain the crystal grains after forging at each fire, as shown in table 2 below.
TABLE 2 Heat treatment protocol and results for the first sample
Step 2: the grain size G of the sample forged in the step 1mPreparing 5 second samples from each sample of grade 1 or more, and heating each second sample at a heating temperature TiThe heat preservation time is WyPerforming heat treatment and water cooling, wherein the heating temperature TiSelecting 1050 ℃,1080 ℃,1100 ℃, 1130 ℃ and 1150 ℃; length of heat preservation Wy5 different time durations of 60min, 65min, 68min, 70min and 75min are selected; the test scheme is as shown in Table 3 below, the grain size of the forged piece is checked after forging, the average value is taken to obtain the crystal grains after forging at each time, and the grain size G is selectednThe forged materials of grade 2 were processed into 5 third samples, and heat-treated according to the recipe shown in Table 4.
TABLE 3 Heat treatment protocol for the second sample
TABLE 4 Heat treatment protocol for the third sample
And step 3: sampling the third test block subjected to the heat treatment for physical/mechanical performance test, and referring to the table 5-6, the tensile strength (MPa) of the alloy at room temperature is more than or equal to 1241, the yield strength (MPa) is more than or equal to 758, the elongation (%). is more than or equal to 17, and the reduction of area (%). is more than or equal to 18; under the high-temperature stretching state at 650 ℃: the tensile strength (MPa) is not less than 896, the yield strength (MPa) is not less than 552, the elongation (%) is not less than 13, and the reduction of area (%) is not less than 16, thereby effectively reducing the cracking risk of the alloy in the forging process.
TABLE 5 tensile Properties at Room temperature
TABLE 6 high-temperature tensile Properties
Claims (10)
1. A high-temperature alloy forging heat treatment method is characterized by comprising the following steps:
step 1: selecting N first samples from high-temperature alloy raw materials, wherein N is an odd number and is more than or equal to 3, and forging temperature ThLength of heat preservation WxNext, the forging deformation of the sample is set to Sa(ii) a Each of the first samples was then tested for grain size GmWherein T ish+1＝Th+T0,Sa+1＝Sa+S0Selecting a first sample with different forging deformation SaTime grain size GmG or more0Has a lowest temperature value of T in ThminSelecting a first sample with different grain sizes GmForging strain SaGreater than or equal to S0T ofhThe highest value of the medium temperature is Tmax(ii) a Selecting a first sample at different forging temperatures ThTime grain size GmG or more0S ofaThe lowest middle deformation is SminSelecting a first sample with different grain sizes GmForging temperature ThGreater than or equal to T0S ofaThe highest middle deformation is Smax；
Step 2: the grain size G of the sample forged in the step 1mG or more0Each sample of (2) was made into N second samplesWherein N is an odd number and N.gtoreq.3, subjecting each second sample to a heating temperature TiThe heat preservation time is WyIs subjected to a heat treatment followed by cooling, wherein Ti+1＝Ti+T0,Wy+1＝Wy+W0Then each second sample was tested for grain size GnSelecting the grain size G of a second sample at different heat preservation time WynG or more0Heating temperature T ofiThe lowest temperature value of (a) is Tmin2Selecting the grain size G of a second sample at different heat preservation time WynG or more0Heating temperature T ofiThe highest temperature value of (a) is Tmax2；
And step 3: the grain size G of the sample forged in the step 2nG or more0Each of the samples of (1) is prepared into N third samples, wherein N is an odd number and N is more than or equal to 3, and each of the third samples is heated at a heating temperature TjThe heat preservation time is WzIs subjected to a heat treatment followed by cooling, wherein Tj+1＝Tj+T0,Wz+1＝Wz+W0Then each third sample was tested for grain size GpSelecting the grain size G of a third sample at different heat preservation time lengths WzpG or more0Heating temperature T ofjThe lowest temperature value of (a) is Tmin3Selecting the grain size G of a second sample at different heat preservation time lengths WzpG or more0Heating temperature T ofjThe highest temperature value of (a) is Tmax3；
And 4, step 4: performing structure and performance tests on the third sample in the step 3, and selecting the lowest grain size G of the forge piece when the structure and performance parameters of the third sample are qualifiedminMaximum grain size Gmax。
2. A superalloy forging heat treatment process as in claim 1, wherein T is0Constant value, T0At 5 deg.C, 10 deg.C, 20 deg.C, 30 deg.C, 40 deg.C or 50 deg.C.
3. A superalloy forging and heat treatment method as in claim 1,the method is characterized in that: said S0Constant value, S05%, 10%, 20%, 30%, 40% or 50%.
4. A superalloy forging and heat treating method as claimed in claim 1, wherein: w is0Is a constant value, W05 minutes, 10 minutes, 20 minutes, 30 minutes, or 50 minutes.
5. A superalloy forging and heat treating method as claimed in claim 1, wherein: w isxThe effective thickness of the bar is 6min/10 mm.
6. A superalloy forging and heat treating method as claimed in claim 1, wherein: said G0Grain size grade, G0Grade 1 or more.
7. A superalloy forging and heat treating method as claimed in claim 1, wherein: the cooling mode is water cooling or air cooling.
8. A superalloy article formed by the forging and heat treating method of claims 1-7, wherein the superalloy raw material comprises, by weight: mo: 21-24, Cr: 7-10, Wu: 5-8, Fe: 2, Mn: less than or equal to 0.8, Al: less than or equal to 0.5, C: less than or equal to 0.03, and the balance being Ni.
9. A superalloy article as formed by the forging and heat treatment method of claim 8, wherein the superalloy article has texture and performance parameters that satisfy the following criteria: under the state of stretching at room temperature: the tensile strength (MPa) is more than or equal to 1241, the yield strength (MPa) is more than or equal to 758, the percentage of elongation (%)) is more than or equal to 17, and the percentage of reduction of area (%)) is more than or equal to 18;
under the high-temperature stretching state at 650 ℃: the tensile strength (MPa) is not less than 896, the yield strength (MPa) is not less than 552, the elongation (%) is not less than 13, and the reduction of area (%) is not less than 16.
10. A superalloy article formed by the forging and heat treating method of claim 8, wherein: the forging temperature of the superalloy product is set to T or higherminAnd is less than or equal to TmaxAnd the forging deformation is set to be S or moreminAnd is less than or equal to SmaxForging the blank, wherein the heat preservation time length is set to be more than or equal to WminAnd is less than or equal to WmaxThe grain size of the product is more than or equal to GminAnd is less than or equal to Gmax。
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911267658.8A CN111036811B (en) | 2019-12-11 | 2019-12-11 | High-temperature alloy forging heat treatment method and product thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911267658.8A CN111036811B (en) | 2019-12-11 | 2019-12-11 | High-temperature alloy forging heat treatment method and product thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111036811A true CN111036811A (en) | 2020-04-21 |
| CN111036811B CN111036811B (en) | 2022-05-13 |
Family
ID=70235701
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911267658.8A Active CN111036811B (en) | 2019-12-11 | 2019-12-11 | High-temperature alloy forging heat treatment method and product thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111036811B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114807796A (en) * | 2022-03-22 | 2022-07-29 | 西安聚能高温合金材料科技有限公司 | Heat treatment process for improving high-temperature plasticity of GH2909 alloy |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6233500B1 (en) * | 1997-06-19 | 2001-05-15 | The United States Of America As Represented By The Secretary Of The Air Force | Optimization and control of microstructure development during hot metal working |
| CN104732012A (en) * | 2015-02-13 | 2015-06-24 | 西北工业大学 | Method for establishing relations between grain sizes and forging thermal parameters of GH4169 alloy forged part |
| CN105648373A (en) * | 2016-04-08 | 2016-06-08 | 中国第重型机械股份公司 | Forging grain control method for 617 nickel base alloy rotor forge piece for 700-DEG C ultra-supercritical unit |
| CN106381364A (en) * | 2016-10-20 | 2017-02-08 | 四川六合锻造股份有限公司 | Method for improving grain size of blade steel 2Cr12MoV |
| CN107245683A (en) * | 2017-06-08 | 2017-10-13 | 太原钢铁(集团)有限公司 | Forge organizational controls method in nickel-base alloy footpath |
-
2019
- 2019-12-11 CN CN201911267658.8A patent/CN111036811B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6233500B1 (en) * | 1997-06-19 | 2001-05-15 | The United States Of America As Represented By The Secretary Of The Air Force | Optimization and control of microstructure development during hot metal working |
| CN104732012A (en) * | 2015-02-13 | 2015-06-24 | 西北工业大学 | Method for establishing relations between grain sizes and forging thermal parameters of GH4169 alloy forged part |
| CN105648373A (en) * | 2016-04-08 | 2016-06-08 | 中国第重型机械股份公司 | Forging grain control method for 617 nickel base alloy rotor forge piece for 700-DEG C ultra-supercritical unit |
| CN106381364A (en) * | 2016-10-20 | 2017-02-08 | 四川六合锻造股份有限公司 | Method for improving grain size of blade steel 2Cr12MoV |
| CN107245683A (en) * | 2017-06-08 | 2017-10-13 | 太原钢铁(集团)有限公司 | Forge organizational controls method in nickel-base alloy footpath |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114807796A (en) * | 2022-03-22 | 2022-07-29 | 西安聚能高温合金材料科技有限公司 | Heat treatment process for improving high-temperature plasticity of GH2909 alloy |
Also Published As
| Publication number | Publication date |
|---|---|
| CN111036811B (en) | 2022-05-13 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| JP3010050B2 (en) | Nickel-based article and alloy having fatigue crack propagation resistance and method of manufacturing | |
| RU2377336C2 (en) | Alloy for gasturbine engine | |
| US8470106B2 (en) | Method of heat treatment for desensitizing a nickel-based alloy relative to environmentally-assisted cracking, in particular for a nuclear reactor fuel assembly and for a nuclear reactor, and a part made of the alloy and subjected to the treatment | |
| AU784826B2 (en) | Aging treatment for Ni-Cr-Mo alloys | |
| JP7223121B2 (en) | High-strength fastener material by forged titanium alloy and its manufacturing method | |
| CN111036811B (en) | High-temperature alloy forging heat treatment method and product thereof | |
| CA2391903C (en) | Two-step aging treatment for ni-cr-mo alloys | |
| EP2205771B1 (en) | Method, nickel base alloy and component | |
| US6638373B2 (en) | Two step aging treatment for Ni-Cr-Mo alloys | |
| US2766156A (en) | Heat-treatment of nickel-chromiumcobalt alloys | |
| US6610155B2 (en) | Aging treatment for Ni-Cr-Mo alloys | |
| US8663404B2 (en) | Heat treatment method and components treated according to the method | |
| JPH03134144A (en) | Nickel-base alloy member and its manufacture | |
| RU2772725C1 (en) | Method for heat treatment of products from heat-resistant nickel alloy ep741np | |
| RU2721261C1 (en) | Heat-resistant deformable nickel-based alloy with low temperature coefficient of linear expansion and article made from it | |
| JP3314408B2 (en) | Manufacturing method of titanium alloy member | |
| CN114216763B (en) | Evaluation method for laser selective melting forming performance of titanium alloy material | |
| JPS62167839A (en) | Ni base alloy and its manufacture | |
| JPH0633206A (en) | Method for heat-treating ni-base alloy | |
| JP2024527351A (en) | Nickel-Based Alloys | |
| Gaurav et al. | Hot Deformation Characterization of Haynes-242 | |
| CN114045452A (en) | Forging and heat treatment method of Haynes242 alloy forging | |
| US20020079029A1 (en) | Heat treatment process | |
| CN116179966A (en) | Iron-based high-temperature alloy and preparation method and application thereof | |
| CN117862388A (en) | Forging process of deep-sea thin-wall sealing ring Inconel 718 nickel-based alloy forging |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of invention: Forging heat treatment method and product of superalloy Effective date of registration: 20221219 Granted publication date: 20220513 Pledgee: Guizhou Branch of Export Import Bank of China Pledgor: Guizhou Aviation Technical Development Co.,Ltd. Registration number: Y2022520000055 |
|
| PE01 | Entry into force of the registration of the contract for pledge of patent right | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Date of cancellation: 20231024 Granted publication date: 20220513 Pledgee: Guizhou Branch of Export Import Bank of China Pledgor: Guizhou Aviation Technical Development Co.,Ltd. Registration number: Y2022520000055 |
|
| PC01 | Cancellation of the registration of the contract for pledge of patent right | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of invention: A high-temperature alloy forging heat treatment method and its product Effective date of registration: 20231109 Granted publication date: 20220513 Pledgee: Guizhou Branch of Export Import Bank of China Pledgor: Guizhou Aviation Technical Development Co.,Ltd. Registration number: Y2023520000064 |
|
| PE01 | Entry into force of the registration of the contract for pledge of patent right |