CN114082876B - High-temperature-resistant and high-durability alloy turbine disc forging and preparation method thereof - Google Patents
High-temperature-resistant and high-durability alloy turbine disc forging and preparation method thereof Download PDFInfo
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- CN114082876B CN114082876B CN202111404365.7A CN202111404365A CN114082876B CN 114082876 B CN114082876 B CN 114082876B CN 202111404365 A CN202111404365 A CN 202111404365A CN 114082876 B CN114082876 B CN 114082876B
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- 238000005242 forging Methods 0.000 title claims abstract description 98
- 229910045601 alloy Inorganic materials 0.000 title claims abstract description 85
- 239000000956 alloy Substances 0.000 title claims abstract description 85
- 238000002360 preparation method Methods 0.000 title claims abstract description 30
- 238000010438 heat treatment Methods 0.000 claims abstract description 77
- 239000000243 solution Substances 0.000 claims abstract description 21
- 230000032683 aging Effects 0.000 claims abstract description 13
- 239000006104 solid solution Substances 0.000 claims abstract description 11
- 238000000034 method Methods 0.000 claims description 30
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims description 22
- 238000003723 Smelting Methods 0.000 claims description 17
- 239000013078 crystal Substances 0.000 claims description 12
- 230000006698 induction Effects 0.000 claims description 11
- 229910000601 superalloy Inorganic materials 0.000 claims description 10
- 229910052759 nickel Inorganic materials 0.000 claims description 8
- 238000010274 multidirectional forging Methods 0.000 claims description 7
- 239000012535 impurity Substances 0.000 claims description 6
- 230000007704 transition Effects 0.000 claims description 5
- 238000004090 dissolution Methods 0.000 claims description 3
- 238000012545 processing Methods 0.000 abstract description 2
- 230000000052 comparative effect Effects 0.000 description 14
- 101000912561 Bos taurus Fibrinogen gamma-B chain Proteins 0.000 description 8
- 238000000265 homogenisation Methods 0.000 description 8
- 238000003754 machining Methods 0.000 description 8
- 238000002844 melting Methods 0.000 description 5
- 230000008018 melting Effects 0.000 description 5
- 238000007711 solidification Methods 0.000 description 5
- 230000008023 solidification Effects 0.000 description 5
- 239000000126 substance Substances 0.000 description 5
- 238000010586 diagram Methods 0.000 description 3
- 238000004519 manufacturing process Methods 0.000 description 3
- 239000000463 material Substances 0.000 description 3
- 238000004321 preservation Methods 0.000 description 3
- 238000001514 detection method Methods 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 230000018109 developmental process Effects 0.000 description 2
- 230000007774 longterm Effects 0.000 description 2
- 238000005728 strengthening Methods 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000003153 chemical reaction reagent Substances 0.000 description 1
- 230000001427 coherent effect Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000007654 immersion Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 239000000843 powder Substances 0.000 description 1
- 238000001556 precipitation Methods 0.000 description 1
- 238000012797 qualification Methods 0.000 description 1
- 238000001953 recrystallisation Methods 0.000 description 1
- 238000007670 refining Methods 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 230000035945 sensitivity Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
- 238000010998 test method Methods 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Classifications
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- 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
- B21J5/02—Die forging; Trimming by making use of special dies ; Punching during forging
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
- B21K—MAKING FORGED OR PRESSED METAL PRODUCTS, e.g. HORSE-SHOES, RIVETS, BOLTS OR WHEELS
- B21K1/00—Making machine elements
- B21K1/28—Making machine elements wheels; discs
- B21K1/40—Making machine elements wheels; discs hubs
-
- C—CHEMISTRY; METALLURGY
- C21—METALLURGY OF IRON
- C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
- C21D9/00—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor
- C21D9/34—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor for tyres; for rims
-
- 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
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- 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
The invention relates to the technical field of alloy turbine disk processing, in particular to an alloy turbine disk forging with high temperature resistance and high durability and a preparation method thereof. The preparation method comprises the following steps: (a) die forging the alloy forging stock to obtain a blank; forging heating temperature is sub-solid solution temperature T 1 The deformation of the hub is 15-20%, and the deformation of the rim is 30-40%; (b) Performing die forging forming on the blank after heat treatment to obtain a disc; the heat treatment includes: heating to 900-1000 ℃ at a speed of more than or equal to 80 ℃/h, preserving heat for 1-2 h, heating to an oversoluble solution temperature T at a speed of more than or equal to 120 ℃/h 2 Preserving heat for 0.5-2 h; the deformation of the hub is 30-50%, and the deformation of the rim is 0-5%; (c) The disc is subjected to sub-solution heat treatment and aging heat treatment. According to the invention, through die forging fine control, the double-structure turbine disk is obtained, the deformation is accurate and controllable, the obtained structure has higher symmetry and high operability.
Description
Technical Field
The invention relates to the technical field of alloy turbine disk processing, in particular to an alloy turbine disk forging with high temperature resistance and high durability and a preparation method thereof.
Background
With the improvement of the thermal efficiency of the engine, the requirements on the temperature bearing capacity and creep resistance of the nickel-based deformed turbine disc alloy are continuously improved, and the long-term service temperature can reach 750 ℃ or above. The development process of turbine disc alloys is usually to continuously add more solid solution strengthening elements and precipitation strengthening phase gamma' phase forming elements, and the development and preparation of the alloys are more and more difficult. In general, when the temperature of the material exceeds 750 ℃ and above, the high-temperature creep resistance of the fine grain structure of the high-strength fine grain structure obtained by the nickel-based deformed superalloy turbine disk is obviously reduced, so that the turbine disk with coarse grain rim and fine grain hub is required to be prepared according to the service condition requirement of the turbine disk, and the requirements of the turbine disk on high temperature bearing capacity and high durability are met. The prior high-alloyed nickel-based deformation superalloy can be hardly made into a double-structure turbine disk, but in the prior art, the powder high-temperature alloy turbine disk is basically used as an object, and a gradient heat treatment furnace is adopted to prepare the double-structure turbine disk, but the turbine disk obtained by the heat treatment method has poor symmetry of the structure, poor heat treatment operability, difficulty in accurate control and high manufacturing process cost.
In view of this, the present invention has been made.
Disclosure of Invention
The first aim of the invention is to provide a preparation method of an alloy turbine disc forging with high temperature resistance and high durability, which aims to solve the technical problems of poor tissue symmetry, poor process operability and the like of a double-tissue turbine disc in the prior art.
A second object of the present invention is to provide an alloy turbine disc forging of high temperature resistance and high durability.
In order to achieve the above object of the present invention, the following technical solutions are specifically adopted:
the preparation method of the alloy turbine disk forging with high temperature resistance and high durability comprises the following steps:
(a) Forging the alloy forging stock to obtain a blank; in the die forging, the forging heating temperature is the sub-solid solution temperature T 1 The deformation of the hub is 15-20%, and the deformation of the rim is 30-40%;
(b) Performing die forging forming on the blank after heat treatment to obtain a disc piece; the heat treatment includes: heating to 900-1000 ℃ at a speed of more than or equal to 80 ℃/h, preserving heat for 1-2 h, heating to an oversoluble solution temperature T at a speed of more than or equal to 120 ℃/h 2 Preserving heat for 0.5-2 h; in the die forging forming, the deformation of the hub is 30% -50%, the deformation of the rim is 0% -5%, and the deformation of the web is 5% -25%;
(c) The disc is subjected to a sub-solution heat treatment and an aging heat treatment.
According to the preparation method of the alloy turbine disk forging, the double-structure turbine disk is obtained through die forging refined control, the deformation is accurate and controllable, and the obtained structure has higher symmetry and high operability.
In a specific embodiment of the present invention, the sub-solid solution temperature T 1 The method meets the following conditions: ts-100 ℃ is less than or equal to T 1 At a temperature of less than or equal to Ts-40 ℃, the oversolubility temperature T 2 The method meets the following conditions: ts is less than or equal to T 2 The temperature is less than or equal to Ts+20 ℃; ts is gamma' phaseDissolution temperature.
In a specific embodiment of the present invention, the temperature of the sub-solution heat treatment is T 3 ，T 3 The method meets the following conditions: ts-70 ℃ is less than or equal to T 3 The temperature is less than or equal to Ts-40 ℃; the temperature of the aging heat treatment is 730-830 ℃.
In a specific embodiment of the present invention, in step (a), the alloy forging stock has a grain size of 8 grade or finer. Further, the grain size difference of different parts of the alloy forging stock is not more than grade 2.
In a specific embodiment of the present invention, in step (a), the preparation of the alloy forging stock includes: after homogenizing heat treatment of the alloy ingot, cogging and multidirectional forging are carried out.
In a specific embodiment of the present invention, the preparation of the alloy ingot comprises: proportioning according to alloy components, and smelting by adopting a vacuum induction smelting and vacuum consumable remelting duplex smelting process; or the alloy is prepared according to the alloy components, and is smelted by adopting a triple process of vacuum induction smelting, electroslag remelting and vacuum consumable smelting. Further, vacuum induction melting and electroslag remelting are adopted for continuous directional solidification smelting of cast ingots.
In a specific embodiment of the present invention, in step (b), after the heat treatment, an equiaxed coarse grain structure having a grain size of 4 to 6 grades is obtained.
In a specific embodiment of the present invention, in step (b), after the die forging, the grain size of the hub is 7 or less, the grain size of the rim is 4 to 6, and the web is a mixed crystal structure of the transition zone.
In a specific embodiment of the invention, the alloy is a nickel-based superalloy. Further, the nickel-based superalloy comprises the following chemical components in percentage by mass: c:0.005% -0.070%, co:12% -21%, cr:12% -18%, W:1.0 to 5.0 percent, mo:1.0 to 5.0 percent of Ti:2.0 to 6.0 percent of Al:1.0 to 4.0 percent, B:0.010 to 0.020%, zr:0.030% -0.060%, nb:0.50% -1.50%, ta:0% -6.0%, fe: less than or equal to 1 percent, and the balance of Ni and unavoidable impurities.
In a specific embodiment of the present invention, in step (a), further comprising: and (3) carrying out machining hole digging treatment on the die-forged blank.
The invention also provides the alloy turbine disc forging with high temperature resistance and high durability, which is prepared by adopting any one of the preparation methods.
Compared with the prior art, the invention has the beneficial effects that:
(1) According to the preparation method of the alloy turbine disk forging, the die forging refinement control is used for replacing a gradient heat treatment mode in the prior art, so that the dual-structure turbine disk is obtained, the deformation is accurate and controllable, the obtained structure has higher symmetry and high operability, and the forging quality is stable;
(2) In the preparation method of the alloy turbine disk forging, the hub fine crystals obtained through certain die forging treatment are greatly reduced in the number of primary gamma 'phases compared with the conventional fine crystal turbine disk, the number of secondary and tertiary gamma' phases in solution cooling is improved, and the hub is better in durability and creep resistance particularly;
(3) In the preparation method of the alloy turbine disk forging, the specific temperature rising rate and heat treatment in the die forging forming process enable the grain size difference of the coarse crystals of the rim to be smaller, and the rim can obtain higher creep resistance.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are needed in the description of the embodiments or the prior art will be briefly described, and it is obvious that the drawings in the description below are some embodiments of the present invention, and other drawings can be obtained according to the drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic view of the shape of a blank obtained by swaging according to an embodiment of the present invention;
FIG. 2 is a schematic view of a blank machined and perforated according to an embodiment of the present invention;
FIG. 3 is a schematic view of the shape of a disc member obtained by die forging according to an embodiment of the present invention;
FIG. 4 is a fine grain structure diagram of a hub of a disc formed by die forging according to an embodiment of the present invention;
FIG. 5 is a diagram of a coarse grain structure of a rim of a disc member obtained by die forging according to an embodiment of the present invention;
fig. 6 is a diagram showing a rough crystal structure of a web of a disc member obtained by die forging molding according to an embodiment of the present invention.
Detailed Description
The technical solution of the present invention will be clearly and completely described below with reference to the accompanying drawings and detailed description, but it will be understood by those skilled in the art that the examples described below are some, but not all, examples of the present invention, and are intended to be illustrative of the present invention only and should not be construed as limiting the scope of the present invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention. The specific conditions are not noted in the examples and are carried out according to conventional conditions or conditions recommended by the manufacturer. The reagents or apparatus used were conventional products commercially available without the manufacturer's attention.
The preparation method of the alloy turbine disk forging with high temperature resistance and high durability comprises the following steps:
(a) Forging the alloy forging stock to obtain a blank; in the die forging, the forging heating temperature is the sub-solid solution temperature T 1 The deformation of the hub is 15-20%, and the deformation of the rim is 30-40%;
(b) Performing die forging forming on the blank after heat treatment to obtain a disc piece; the heat treatment includes: heating to 900-1000 ℃ at a speed of more than or equal to 80 ℃/h, preserving heat for 1-2 h, heating to an oversoluble solution temperature T at a speed of more than or equal to 120 ℃/h 2 Preserving heat for 0.5-2 h; in the die forging forming, the deformation of the hub is 30% -50%, the deformation of the rim is 0% -5%, and the deformation of the web is 5% -25%;
(c) The disc is subjected to a sub-solution heat treatment and an aging heat treatment.
According to the preparation method of the alloy turbine disk forging, the double-structure turbine disk is obtained through die forging refined control, the deformation is accurate and controllable, and the obtained structure has higher symmetry and high operability.
In the preparation method, a certain heating rate is adopted and solid solution temperature treatment is carried out before die forging forming, and the die forging adopts a scheme of core dynamic recrystallization and basically no deformation of the rim, so that the double-structure turbine disk with fine hub crystals and coarse rim crystals is obtained, the problems of low high-temperature creep resistance and the like of the conventional deformation superalloy rim are solved, and the use requirements of high-temperature and high-durability turbine disk materials are met.
The turbine disc is of a structure of a conventional turbine disc for an aeroengine, and comprises a hub, a web and a rim from the side of a near turbine shaft outwards in sequence.
In a specific embodiment of the present invention, the sub-solid solution temperature T 1 The method meets the following conditions: ts-100 ℃ is less than or equal to T 1 At a temperature of less than or equal to Ts-40 ℃, the oversolubility temperature T 2 The method meets the following conditions: ts is less than or equal to T 2 The temperature is less than or equal to Ts+20 ℃; ts is the gamma' phase total dissolution temperature. Wherein, ts can be measured by a metallographic test method.
As in the various embodiments, the sub-solid solution temperature T 1 Can be at the temperature of Ts-100 ℃, ts-90 ℃, ts-80 ℃, ts-70 ℃, ts-60 ℃, ts-50 ℃, ts-40 ℃ and the like; the oversolubility temperature T 2 Can be Ts, ts+5deg.C, ts+10deg.C, ts+15deg.C, ts+20deg.C, etc.
In a specific embodiment of the present invention, the temperature of the sub-solution heat treatment is T 3 ，T 3 The method meets the following conditions: ts-70 ℃ is less than or equal to T 3 The temperature is less than or equal to Ts-40 ℃; the temperature of the aging heat treatment is 730-830 ℃.
As in the various embodiments, the temperature T of the sub-solution heat treatment 3 Can be at a temperature of between Ts and 70 ℃, between Ts and 60 ℃, between Ts and 50 ℃, between Ts and 40 ℃, etc.; the aging heat treatment may be performed at a temperature of 730 ℃, 740 ℃, 750 ℃, 760 ℃, 770 ℃, 780 ℃, 790 ℃, 800 ℃, 810 ℃, 820 ℃, 830 ℃, and the like.
Further, the time of the sub-solution heat treatment is more than or equal to 1h, preferably more than or equal to 2h, such as 2-4 h; the time of the aging heat treatment is more than or equal to 2 hours, preferably more than or equal to 4 hours, such as 4 to 6 hours.
In a specific embodiment of the present invention, in step (a), the alloy forging stock has a grain size of 8 grade or finer. Further, the grain size difference of different parts of the alloy forging stock is not more than grade 2.
In a specific embodiment of the present invention, in step (a), the preparation of the alloy forging stock includes: after homogenizing heat treatment of the alloy ingot, cogging and multidirectional forging are carried out.
In actual operation, the cogging is performed by means of constraint upsetting. The homogenization heat treatment is carried out according to the corresponding conventional homogenization heat treatment operation of the alloy, and the cogging and the multidirectional forging mode adopt the conventional operation so as to obtain a forging stock with the grain size meeting the requirement.
In a specific embodiment of the present invention, the preparation of the alloy ingot comprises: proportioning according to alloy components, and smelting by adopting a vacuum induction smelting and vacuum consumable remelting duplex smelting process; or the alloy is prepared according to the alloy components, and is smelted by adopting a triple process of vacuum induction smelting, electroslag remelting and vacuum consumable smelting. Further, vacuum induction melting and electroslag remelting are adopted for continuous directional solidification smelting of cast ingots.
In actual operation, the preparation process of the alloy cast ingot is the conventional preparation process of the corresponding alloy cast ingot.
In a specific embodiment of the present invention, sensitivity equivalent is employed asThe grain size of the alloy forging stock is detected by ultrasonic water immersion flaw detection, so that the higher flaw detection qualification rate of the disc is ensured, the risk of scrapping materials is reduced, and the production cost is reduced.
In a specific embodiment of the present invention, in step (a), the die-forged blank has a grain size of 8 grade or finer. Further, the grain size difference of different parts of the blank is not more than grade 2.
In a specific embodiment of the present invention, in step (b), after the heat treatment, an equiaxed coarse grain structure having a grain size of 4 to 6 grades is obtained.
In a specific embodiment of the present invention, in step (b), after the die forging, the grain size of the hub is 7 or less, the grain size of the rim is 4 to 6, and the web is a mixed crystal structure of the transition zone.
The invention adopts a certain heating rate and heat treatment temperature before die forging forming, can lead the grain size difference of the coarse crystals of the rim to be smaller, and leads the rim to obtain higher creep resistance. In the die forging forming process, the hub is completely and dynamically recrystallized to obtain a fine grain structure, so that the large-size primary gamma ' phase existing in the conventional deformed fine grain turbine disk is eliminated, the volume fractions of the co-precipitated secondary gamma ' phase and the tertiary gamma ' phase are increased, the short-time strength, the durability and the creep resistance are improved, and the long-term structure stability is improved.
In the specific embodiment of the invention, in the disc piece obtained by die forging, the primary gamma prime phase size is 100-2000 nm, and the primary gamma prime phase volume fraction is less than or equal to 5%.
The primary gamma' phase size of the alloy in the alloy composition range defined by the invention is generally between 100 and 10 mu m, the volume fraction is between 5 and 15 percent, the size is relatively large, and the quantity is high. In the disc member obtained by the method, the number of primary gamma 'phases is greatly reduced, and the primary gamma' phases with large size are eliminated, so that the number of secondary gamma 'phases and tertiary gamma' phases are precipitated altogether after the disc member is subjected to sub-solid solution heat treatment and aging heat treatment is increased. For GH4096 alloy, the volume fractions of the secondary gamma 'phase and the tertiary gamma' phase are respectively 28-33% and 2-6%; aiming at GH4198 alloy, the volume fractions of the secondary gamma 'phase and the tertiary gamma' phase which are precipitated in a coherent way are 40-45% and 3-8% respectively.
In a specific embodiment of the invention, the alloy is a nickel-based superalloy. Further, the nickel-based superalloy comprises the following chemical components in percentage by mass: c:0.005% -0.070%, co:12% -21%, cr:12% -18%, W:1.0 to 5.0 percent, mo:1.0 to 5.0 percent of Ti:2.0 to 6.0 percent of Al:1.0 to 4.0 percent, B:0.010 to 0.020%, zr:0.030% -0.060%, nb:0.50% -1.50%, ta:0% -6.0%, fe: less than or equal to 1 percent, and the balance of Ni and unavoidable impurities. Such as, but not limited to, the nickel-base superalloy is a GH4096 alloy.
In a specific embodiment of the present invention, in step (a), further comprising: and (3) carrying out machining hole digging treatment on the die-forged blank.
In actual operation, the specific machining parameters are adjusted and selected according to the actual turbine disk size requirements.
The invention also provides the alloy turbine disc forging with high temperature resistance and high durability, which is prepared by adopting any one of the preparation methods.
In a specific embodiment of the invention, the rim creep performance of the alloy turbine disc forging satisfies: at 700 ℃/690MPa, the duration time when the plastic deformation is 0.2% is more than or equal to 350h.
Example 1
The embodiment provides a preparation method of a GH4096 alloy turbine disk forging with high temperature resistance and high durability, which comprises the following steps:
(1) Vacuum induction melting and electroslag remelting continuous directional solidification are adopted to prepare the alloy with the specification ofIs a GH4096 alloy ingot; the GH4096 alloy comprises the following chemical components in percentage by mass: c:0.050%, co:13%, cr:16%, W:4.0%, mo:4.0%, ti:3.80%, al:2.25%, B:0.015%, zr:0.050%, nb:0.70%, fe: less than or equal to 0.5 percent, and the balance of Ni and unavoidable impurities.
(2) Carrying out high-temperature homogenization heat treatment on the alloy cast ingot obtained in the step (1), wherein the highest temperature of the homogenization heat treatment is 1200 ℃, the heat preservation time is 48 hours, then carrying out constraint upsetting cogging, and obtaining the alloy cast ingot after multidirectional forgingCake base with grain size of 9 grade by +.>Is less than 20%.
(3) Forging the alloy forging stock obtained in the step (2) to obtain a stock with the grain size of 9 grades; in the die forging, the forging heating temperature is 1070 ℃, the hub deformation amount is 15%, the rim deformation amount is 38%, the shape is shown in fig. 1, and then machining and drawing holes are carried out to obtain a blank shown in fig. 2.
(4) Heating the blank obtained in the step (3) to 900 ℃ at 100 ℃/h, preserving heat for 2 hours, and heating to 1120 ℃ at 150 ℃/h, preserving heat for 1.5 hours, so as to obtain an equiaxed crystal structure with the grain size of 4-6 levels being uniform; then die forging and forming are carried out, the shape of the obtained disc is shown in figure 3, wherein the deformation amount of the hub is 40%, and a fine grain structure with the grain size of 7-8 levels is obtained, and the shape is shown in figure 4; the deformation of the rim is less than 5%, the coarse grain structure with the grain size of 4-6 levels is maintained, as shown in figure 5, the deformation of the web is 20%, and the web is a mixed grain structure in a transition zone, as shown in figure 6.
(5) And (3) machining the disc piece obtained in the step (4), and then performing subsolid solution heat treatment at 1080 ℃/2h and aging heat treatment at 760 ℃/4h to obtain the double-structure alloy turbine disc forging piece.
The performance of the GH4096 alloy turbine disk forging prepared by the embodiment is tested, the creep performance of the rim is tested, the duration time when the plastic deformation is 0.2% is 350h under the experimental condition of 700 ℃/690MPa, and the creep performance of the conventional fine-grain forging is better than that of the conventional fine-grain forging; tensile strength at 650 ℃ is 1420MPa, and yield strength is 1050MPa.
Example 2
The embodiment provides a preparation method of a GH4198 alloy turbine disk forging with high temperature resistance and high durability, which comprises the following steps:
(1) Vacuum induction melting and electroslag remelting continuous directional solidification are adopted to prepare the alloy with the specification ofGH4198 alloy ingots; the GH4198 alloy comprises the following chemical components in percentage by mass: c:0.020%, co:20.5%, cr:13%, W:3.8%, mo:4.0%, ti:3.80%, al:3.40%, B:0.015%, zr:0.050%, nb:1.0%, ta:2.5%, fe: less than or equal to 0.5 percent, and the balance of Ni and unavoidable impurities.
(2) Carrying out high-temperature homogenization heat treatment on the alloy cast ingot obtained in the step (1), wherein the highest temperature of the homogenization heat treatment is 1200 ℃, the heat preservation time is 48 hours, then carrying out constraint upsetting cogging, and obtaining the alloy cast ingot after multidirectional forgingCake base with grain size of 9 grade by +.>Is less than 40%.
(3) Forging the alloy forging stock obtained in the step (2) to obtain a disc piece; in the die forging, the forging heating temperature is 1100 ℃, the deformation of the hub is 15%, the deformation of the rim is 40%, and the grains of different parts of the disc are 8-9 grades. And machining and drawing holes to obtain the blank.
(4) Heating the blank obtained in the step (3) to 900 ℃ at 100 ℃/h, preserving heat for 2h, heating to 1150 ℃ at 150 ℃/h, preserving heat for 1.5h, and obtaining an equiaxed crystal structure with uniform grain size of 4-6 levels; then die forging and forming are carried out, the shape of the obtained disc is shown in figure 3, wherein the deformation amount of the hub is 40%, and a fine grain structure with the grain size of 7-8 levels is obtained, and the shape is shown in figure 4; the deformation of the rim is less than 5%, the coarse grain structure with the grain size of 4-6 levels is maintained, as shown in figure 5, the deformation of the web is 25%, and the web is a mixed grain structure in the transition zone.
(5) And (3) machining the disc piece obtained in the step (4), and then carrying out sub-solution heat treatment at 1120 ℃/2h and aging heat treatment at 780 ℃/4h to obtain the turbine disc forging piece.
Testing the creep property of the rim, wherein the duration time is 900 hours when the plastic deformation is 0.2% under the experimental condition of 700 ℃/690 MPa; tensile strength at 750 ℃ is 1180MPa, and yield strength is 1020MPa.
Comparative example 1
Comparative example 1 provides a method of making a GH4096 turbine disk comprising the steps of:
(1) Vacuum induction melting and electroslag remelting are adopted for connectionContinuous directional solidification to obtain the product with the specification ofIs a GH4096 alloy ingot; the GH4096 alloy comprises the following chemical components in percentage by mass: c:0.050%, co:13%, cr:16%, W:4.0%, mo:4.0%, ti:3.80%, al:2.25%, B:0.015%, zr:0.050%, nb:0.70%, fe: less than or equal to 0.5 percent, and the balance of Ni and unavoidable impurities.
(2) Carrying out high-temperature homogenization heat treatment on the alloy cast ingot obtained in the step (1), wherein the highest temperature of the homogenization heat treatment is 1200 ℃, the heat preservation time is 48 hours, then carrying out constraint upsetting cogging, and obtaining the alloy cast ingot after multidirectional forgingCake base with grain size of 9 grade by +.>Is less than 20%.
(3) Forging the alloy forging stock obtained in the step (2) to obtain a disc piece; in the die forging, the forging heating temperature is 1070 ℃, the hub deformation is 15%, the rim deformation is 40%, and the grains of different parts of the disc are 8-9.5 grades.
(4) And (3) machining the disc piece obtained in the step (3), and then performing sub-solution heat treatment at 1070 ℃/2h and aging heat treatment at 760 ℃/4h to obtain the fine-grain turbine disc forging piece.
Testing the creep property of the rim, wherein the duration time is 140 hours when the plastic deformation is 0.2% under the experimental condition of 700 ℃/690 MPa; tensile strength 1430MPa and yield strength 1055MPa at 650 ℃.
Comparative example 2
Comparative example 2 the preparation method of reference example 1 is different in that: the heat treatment in step (4) is different. The heat treatment of step (4) of comparative example 2 includes: the temperature is raised to 900 ℃ at 80 ℃ per hour, the heat is preserved for 2 hours, and the temperature is raised to 1120 ℃ at 50 ℃ per hour, and the heat is preserved for 1.5 hours.
The rim grain grade difference of the turbine disk forging manufactured in comparative example 2 is increased.
Comparative example 3
Comparative example 3 the preparation method of reference example 1 is different in that: the deformation amounts of the hub and the rim in the step (3) and the step (4) are different. In step (3) of comparative example 3: the deformation of the hub is 30%, and the deformation of the rim is 25%; in step (4) of comparative example 3: the wheel hub deformation is 25% and the wheel rim deformation is 15%.
The hub grain refining effect of the turbine disk forging manufactured in comparative example 3 is poor, and the difference in rim grain size is increased.
Experimental example 1
To comparatively illustrate the microstructure differences of the turbine disk forgings produced in the different examples and comparative examples, the microstructure of the turbine disk forgings produced in the different examples and comparative examples was counted, and the results are shown in table 1.
Table 1 microstructure statistics of turbine disk forgings of different examples and comparative examples
Finally, it should be noted that: the above embodiments are only for illustrating the technical solution of the present invention, and not for limiting the same; although the invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical scheme described in the foregoing embodiments can be modified or some or all of the technical features thereof can be replaced by equivalents; such modifications and substitutions do not depart from the spirit of the invention.
Claims (11)
1. The preparation method of the alloy turbine disk forging with high temperature resistance and high durability is characterized by comprising the following steps of:
(a) Forging the alloy forging stock to obtain a blank; in the die forging, the forging heating temperature is the sub-solid solution temperature T 1 The deformation of the hub is 15-20%, and the deformation of the rim is 30-40%;
(b) Performing die forging forming on the blank after heat treatment to obtain a disc piece; the heat treatment includes: heating to 900-1000 ℃ at a speed of more than or equal to 80 ℃/h, preserving heat for 1-2 h, heating to an oversoluble solution temperature T at a speed of more than or equal to 120 ℃/h 2 Preserving heat for 0.5-2 h; in the die forging forming, the deformation of the hub is 30% -50%, the deformation of the rim is 0% -5%, and the deformation of the web is 5% -25%;
(c) Subjecting the disc to sub-solution heat treatment and aging heat treatment;
the temperature of the sub-solution heat treatment is T 3 ，T 3 The method meets the following conditions: ts-70 ℃ is less than or equal to T 3 Less than or equal to Ts-40 ℃, wherein Ts is the total-dissolution temperature of gamma' phase;
in the step (b), after the heat treatment, an equiaxed coarse grain structure with the grain size of 4-6 level uniformity is obtained;
after the die forging forming, the grain size of the hub is 7 grades or finer, the grain size of the rim is 4-6 grades, and the web is a mixed crystal structure of the transition zone.
2. The method according to claim 1, wherein the sub-solid solution temperature T 1 The method meets the following conditions: ts-100 ℃ is less than or equal to T 1 The temperature is less than or equal to Ts-40 ℃; the oversolubility temperature T 2 The method meets the following conditions: ts is less than or equal to T 2 The temperature is less than or equal to Ts+20 ℃; ts is the gamma' phase total dissolution temperature.
3. The method according to claim 1, wherein the aging heat treatment is performed at a temperature of 730 to 830 ℃.
4. The method of claim 1, wherein in step (a), the alloy forging stock has a grain size of 8 grade or finer.
5. The method according to claim 4, wherein the difference in grain size between different portions of the alloy forging stock is not more than level 2.
6. The method of claim 1, wherein in step (a), the preparation of the alloy forging stock comprises: after homogenizing heat treatment of the alloy ingot, cogging and multidirectional forging are carried out.
7. The method of producing as defined in claim 6, wherein the producing of the alloy ingot comprises: proportioning according to alloy components, and smelting by adopting a vacuum induction smelting and vacuum consumable remelting duplex smelting process; or the alloy is prepared according to the alloy components, and is smelted by adopting a triple process of vacuum induction smelting, electroslag remelting and vacuum consumable smelting.
8. The method according to claim 1, wherein the primary gamma prime phase size of the disc member obtained by the die forging is 100-2000 nm, and the primary gamma prime phase volume fraction is less than or equal to 5%.
9. The method of any one of claims 1-8, wherein the alloy is a nickel-based superalloy.
10. The method of claim 9, wherein the nickel-base superalloy comprises, in mass percent: c:0.005% -0.070%, co:12% -21%, cr:12% -18%, W:1.0 to 5.0 percent, mo:1.0 to 5.0 percent of Ti:2.0 to 6.0 percent of Al:1.0 to 4.0 percent, B:0.010 to 0.020%, zr:0.030% -0.060%, nb:0.50% -1.50%, ta:0% -6.0%, fe: less than or equal to 1 percent, and the balance of Ni and unavoidable impurities.
11. The high temperature resistant and high durability alloy turbine disc forging prepared by the preparation method of any one of claims 1-10.
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| CN114871698B (en) * | 2022-05-12 | 2023-06-13 | 中国航发四川燃气涡轮研究院 | Machining method of low-inertia turbine disk |
| CN115044744B (en) * | 2022-06-16 | 2024-05-14 | 深圳市万泽中南研究院有限公司 | Alloy disc heat treatment device and alloy disc heat treatment method |
| CN115156472B (en) * | 2022-06-27 | 2024-08-06 | 中国航发四川燃气涡轮研究院 | Preparation method of high-performance nickel-based alloy deformed turbine disc forging |
| CN115301867B (en) * | 2022-07-25 | 2024-04-26 | 西北工业大学 | Method for preparing high-temperature alloy gradient structure by controlling strain forging and gradient heat treatment |
| CN115058613A (en) * | 2022-07-28 | 2022-09-16 | 北京钢研高纳科技股份有限公司 | GH4096 alloy forging and preparation method and application thereof |
| CN115747577B (en) * | 2022-11-21 | 2024-04-12 | 北京钢研高纳科技股份有限公司 | Deformed superalloy for turbine disk and preparation method thereof |
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