CN114082876A - High-temperature-resistance and high-durability alloy turbine disc forging and preparation method thereof - Google Patents
High-temperature-resistance and high-durability alloy turbine disc forging and preparation method thereof Download PDFInfo
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- 238000005242 forging Methods 0.000 title claims abstract description 95
- 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 31
- 238000010438 heat treatment Methods 0.000 claims abstract description 78
- 239000000243 solution Substances 0.000 claims abstract description 20
- 239000006104 solid solution Substances 0.000 claims abstract description 18
- 230000032683 aging Effects 0.000 claims abstract description 13
- 238000003723 Smelting Methods 0.000 claims description 19
- 238000000034 method Methods 0.000 claims description 17
- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims description 16
- 239000013078 crystal Substances 0.000 claims description 11
- 238000000265 homogenisation Methods 0.000 claims description 11
- 230000006698 induction Effects 0.000 claims description 11
- 101000912561 Bos taurus Fibrinogen gamma-B chain Proteins 0.000 claims description 10
- 229910000601 superalloy Inorganic materials 0.000 claims description 9
- 238000010274 multidirectional forging Methods 0.000 claims description 7
- 229910052804 chromium Inorganic materials 0.000 claims description 6
- 239000012535 impurity Substances 0.000 claims description 6
- 229910052742 iron Inorganic materials 0.000 claims description 6
- 239000000463 material Substances 0.000 claims description 6
- 229910052750 molybdenum Inorganic materials 0.000 claims description 6
- 229910052758 niobium Inorganic materials 0.000 claims description 6
- 239000000126 substance Substances 0.000 claims description 6
- 229910052721 tungsten Inorganic materials 0.000 claims description 6
- 229910052726 zirconium Inorganic materials 0.000 claims description 6
- 229910052759 nickel Inorganic materials 0.000 claims description 5
- 230000007704 transition Effects 0.000 claims description 5
- 238000004090 dissolution Methods 0.000 claims description 4
- 238000004519 manufacturing process Methods 0.000 claims description 4
- 229910052715 tantalum Inorganic materials 0.000 claims description 4
- 239000000203 mixture Substances 0.000 claims description 2
- 238000012545 processing Methods 0.000 abstract description 2
- 230000000052 comparative effect Effects 0.000 description 14
- 238000003754 machining Methods 0.000 description 9
- 238000002844 melting Methods 0.000 description 5
- 230000008018 melting Effects 0.000 description 5
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- 230000018109 developmental process Effects 0.000 description 2
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- 238000005275 alloying Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
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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%
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- 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
Abstract
The invention relates to the technical field of alloy turbine disc processing, in particular to an alloy turbine disc forging with high temperature resistance and high durability and a preparation method thereof. The preparation method comprises the following steps: (a) carrying out die forging on the alloy forging stock to obtain a stock; the forging heating temperature is the sub-solid solution temperature T1The wheel hub deformation is 15% -20%, and the wheel rim deformation is 30% -40%; (b) carrying out die forging forming on the blank after heat treatment to obtain a disc piece; the heat treatment comprises: heating to 900-1000 ℃ at a rate of more than or equal to 80 ℃/h, preserving heat for 1-2 h, and heating to an over-solid solution temperature T at a rate of more than or equal to 120 ℃/h2Preserving the heat for 0.5-2 h; hub transformerThe shape amount is 30-50%, and the wheel rim deformation amount is 0-5%; (c) and (3) performing sub-solution heat treatment and aging heat treatment on the disc. According to the invention, the double-structure turbine disc is obtained through fine control of die forging, the deformation amount 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 disc processing, in particular to an alloy turbine disc forging with high temperature resistance and high durability and a preparation method thereof.
Background
Along with the improvement of the thermal efficiency of the engine, the requirements on the temperature bearing capacity and the creep resistance of the nickel-based deformation turbine disk alloy are continuously improved, and the long-term service temperature reaches 750 ℃ or above. The development process of the turbine disk alloy is generally to add more solid solution strengthening elements and precipitation strengthening phase gamma' phase forming elements continuously, and the development and preparation of the alloy are more and more difficult. Generally, when the temperature of a material exceeds 750 ℃ or above, the high-temperature creep resistance of the fine-grained structure is obviously reduced, so that the turbine disc with rough-grained rim and fine-grained hub is prepared according to the requirement of the service condition of the turbine disc to meet the requirements of high temperature-bearing capacity and high durability of the turbine disc. At present, the high-alloying nickel-based wrought superalloy can be almost rarely made into a double-structure turbine disk, and the double-structure turbine disk is prepared by adopting a gradient heat treatment furnace by taking a powder superalloy turbine disk as an object in the prior art, but the turbine disk obtained by the heat treatment method has poor structure symmetry, poor heat treatment operability, difficulty in accurate control and high manufacturing process cost.
In view of the above, the present invention is particularly proposed.
Disclosure of Invention
The invention aims to provide a preparation method of an alloy turbine disc forging with high temperature resistance and high durability, and aims to solve the technical problems of poor tissue symmetry, poor process operability and the like of a double-structure turbine disc in the prior art.
The second purpose of the invention is to provide an alloy turbine disk forging with high temperature resistance and high durability.
In order to achieve the above purpose of the present invention, the following technical solutions are adopted:
the preparation method of the alloy turbine disc forging with high temperature resistance and high durability comprises the following steps:
(a) carrying out die forging on the alloy forging stock to obtain a stock; in the die forging, the forging heating temperature is the sub-solid solution temperature T1The wheel hub deformation is 15% -20%, and the wheel rim deformation is 30% -40%;
(b) carrying out die forging forming on the blank after heat treatment to obtain a disc piece; the heat treatment comprises: heating to 900-1000 ℃ at a rate of more than or equal to 80 ℃/h, preserving heat for 1-2 h, and heating to an over-solid solution temperature T at a rate of more than or equal to 120 ℃/h2Preserving the 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 plate is 5-25%;
(c) and carrying out sub-solution heat treatment and aging heat treatment on the disc.
According to the preparation method of the alloy turbine disc forging, the double-structure turbine disc is obtained through fine control of die forging, the deformation is accurate and controllable, the obtained structure is higher in symmetry, and the operability is high.
In a particular embodiment of the invention, the sub-solution temperature T1Satisfies the following conditions: t is more than or equal to Ts-100 DEG C1Ts-40 ℃ or lower, and the over-solid solution temperature T2Satisfies the following conditions: ts is less than or equal to T2Ts +20 ℃; ts is the gamma' phase complete dissolution temperature.
In a specific embodiment of the present invention, the temperature of the sub-solution heat treatment is T3，T3Satisfies the following conditions: t is not more than Ts-70 DEG C3Ts-40 ℃ or less; the temperature of the aging heat treatment is 730-830 ℃.
In a specific embodiment of the present invention, in the step (a), the grain size of the alloy forging is grade 8 or finer. Further, the grade difference of the grain sizes of different parts of the alloy forging stock is not more than grade 2.
In a specific embodiment of the present invention, in the step (a), the preparing of the alloy forging includes: and (3) performing homogenization heat treatment on the alloy ingot, and then performing cogging and multidirectional forging.
In a specific embodiment of the present invention, the preparation of the alloy ingot comprises: preparing materials according to alloy components, and smelting by adopting a vacuum induction smelting and vacuum consumable remelting two-connection smelting process; or the alloy is prepared according to alloy components by adopting a triple smelting process of vacuum induction smelting, electroslag remelting and vacuum consumable smelting. Further, smelting a cast ingot by adopting vacuum induction smelting and electroslag remelting continuous directional solidification.
In a specific embodiment of the invention, in the step (b), after the heat treatment, a uniform equiaxed coarse-grained structure with a grain size of 4-6 grades is obtained.
In a specific embodiment of the present invention, in step (b), after the die forging is performed, the grain size of the hub is 7 grades or less, the grain size of the rim is 4 to 6 grades, and the web is a mixed crystal structure in the transition region.
In a particular embodiment of the invention, the alloy is a nickel-base superalloy. Further, the chemical components of the nickel-based superalloy comprise the following components in percentage by mass: c: 0.005% -0.070%, Co: 12% -21%, Cr: 12% -18%, W: 1.0% -5.0%, Mo: 1.0-5.0%, Ti: 2.0% -6.0%, Al: 1.0% -4.0%, B: 0.010-0.020%, Zr: 0.030 to 0.060%, Nb: 0.50 to 1.50%, Ta: 0% -6.0%, Fe: less than or equal to 1 percent, and the balance of Ni and inevitable impurities.
In a specific embodiment of the present invention, step (a) further comprises: and machining and drilling the forged blank.
The invention also provides an alloy turbine disk forging with high temperature resistance and high durability, which is prepared by 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 disc forging, the gradient heat treatment mode in the prior art is replaced by die forging refined control, so that the double-structure turbine disc is obtained, the deformation is accurate and controllable, the obtained structure is higher in symmetry, the operability is high, and the quality of the forging is stable;
(2) compared with the conventional fine-grain turbine disc, the number of primary gamma 'phases is greatly reduced, the number of secondary and tertiary gamma' phases which are compatible with solid solution cooling is increased, and the hub is particularly durable and has better creep resistance;
(3) in the preparation method of the alloy turbine disk forging, the specific temperature rise rate and the heat treatment in the die forging forming process enable the grain size grade difference of the wheel rim coarse grains to be smaller, and the wheel 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 used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
Fig. 1 is a schematic view of the shape of a blank obtained by die forging according to an embodiment of the present invention;
FIG. 2 is a schematic view of a blank after machining a hole according to an embodiment of the present invention;
FIG. 3 is a schematic view of the shape of a disk formed 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 swaging according to an embodiment of the present invention;
FIG. 5 is a schematic view of the wheel rim coarse grain structure of a disc formed by die forging provided by an embodiment of the present invention;
FIG. 6 is a diagram of a coarse grain structure of a web of disk members formed by die forging in accordance with an embodiment of the present invention.
Detailed Description
The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings and the detailed description, but those skilled in the art will understand that the following described embodiments are some, not all, of the embodiments of the present invention, and are only used for illustrating the present invention, and should not be construed as limiting the scope of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention. The examples, in which specific conditions are not specified, were carried out according to conventional conditions or conditions recommended by the manufacturer. The reagents or instruments used are not indicated by the manufacturer, and are all conventional products available commercially.
The preparation method of the alloy turbine disc forging with high temperature resistance and high durability comprises the following steps:
(a) carrying out die forging on the alloy forging stock to obtain a stock; in the die forging, the forging heating temperature is the sub-solid solution temperature T1The wheel hub deformation is 15% -20%, and the wheel rim deformation is 30% -40%;
(b) heat treating the blankThen die forging is carried out to obtain a disc piece; the heat treatment comprises: heating to 900-1000 ℃ at a rate of more than or equal to 80 ℃/h, preserving heat for 1-2 h, and heating to an over-solid solution temperature T at a rate of more than or equal to 120 ℃/h2Preserving the 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 plate is 5-25%;
(c) and carrying out sub-solution heat treatment and aging heat treatment on the disc.
According to the preparation method of the alloy turbine disc forging, the double-structure turbine disc is obtained through fine control of die forging, the deformation is accurate and controllable, the obtained structure is higher in symmetry, and the operability is high.
According to the preparation method, a certain heating rate is adopted and solid solution temperature treatment is carried out before die forging forming, the die forging adopts the scheme that the center is dynamically recrystallized and the rim basically has no deformation, so that the double-structure turbine disc with fine grains of the hub and coarse grains of the rim is obtained, the problems of low high-temperature creep resistance and the like of the conventional deformed high-temperature alloy rim are solved, and the use requirements of the high-temperature and high-durability turbine disc material are met.
The turbine disc is of a structure of a turbine disc for a conventional aero-engine, and comprises a hub, a spoke plate and a rim from the side close to a turbine shaft to the outside in sequence.
In a particular embodiment of the invention, the sub-solution temperature T1Satisfies the following conditions: t is more than or equal to Ts-100 DEG C1Ts-40 ℃ or lower, and the over-solid solution temperature T2Satisfies the following conditions: ts is less than or equal to T2Ts +20 ℃; ts is the gamma' phase total dissolution temperature. Wherein Ts can be measured by a metallographic test method.
As in the different embodiments, the sub-solution temperature T1Can be Ts-100 deg.C, Ts-90 deg.C, Ts-80 deg.C, Ts-70 deg.C, Ts-60 deg.C, Ts-50 deg.C, Ts-40 deg.C, etc.; the excess solid solution temperature T2May be Ts, Ts +5 ℃, Ts +10 ℃, Ts +15 ℃, Ts +20 ℃ and the like.
In a specific embodiment of the present invention, the temperature of the sub-solution heat treatment is T3，T3Satisfies the following conditions: t is not more than Ts-70 DEG C3Ts-40 ℃; the temperature of the aging heat treatment is 730-830 ℃.
As in the different embodiments, the temperature T of the sub-solution heat treatment3Can be Ts-70 deg.C, Ts-60 deg.C, Ts-50 deg.C, Ts-40 deg.C, etc.; the aging heat treatment temperature can be 730 deg.C, 740 deg.C, 750 deg.C, 760 deg.C, 770 deg.C, 780 deg.C, 790 deg.C, 800 deg.C, 810 deg.C, 820 deg.C, 830 deg.C, etc.
Further, the time of the sub-solid solution heat treatment is more than or equal to 1 hour, preferably more than or equal to 2 hours, such as 2-4 hours; 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 4-6 hours.
In a specific embodiment of the present invention, in the step (a), the grain size of the alloy forging is grade 8 or finer. Further, the grade difference of the grain sizes of different parts of the alloy forging stock is not more than grade 2.
In a specific embodiment of the present invention, in the step (a), the preparing of the alloy forging includes: and (3) performing homogenization heat treatment on the alloy ingot, and then performing cogging and multidirectional forging.
In actual operation, the cogging is performed in a manner of restraining 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 modes adopt the conventional operation to obtain the forged blank with the grain size meeting the requirement.
In a specific embodiment of the present invention, the preparation of the alloy ingot comprises: preparing materials according to alloy components, and smelting by adopting a vacuum induction smelting and vacuum consumable remelting two-connection smelting process; or the alloy is prepared according to alloy components and is obtained by adopting a triple process of vacuum induction melting, electroslag remelting and vacuum consumable melting. Further, smelting a cast ingot by adopting vacuum induction smelting and electroslag remelting continuous directional solidification.
In actual operation, the preparation process of the alloy ingot is the conventional preparation process of the corresponding alloy ingot.
In a particular embodiment of the invention, a sensitivity equivalent of
Ultrasonic water immersion flaw detectionThe grain size of the alloy forging stock is measured, the higher flaw detection qualification rate of the disc is ensured, the risk of material scrapping is reduced, and the production cost is reduced.
In a specific embodiment of the present invention, in the step (a), the die forging gives an ingot in which the grain size of the ingot is grade 8 or finer. Further, the level difference of the grain sizes of different parts of the blank is not more than 2 levels.
In a specific embodiment of the invention, in the step (b), after the heat treatment, a uniform equiaxed coarse-grained structure with a grain size of 4-6 grades is obtained.
In a specific embodiment of the present invention, in step (b), after the die forging is performed, the grain size of the hub is 7 grades or smaller, the grain size of the rim is 4-6 grades, and the web is a mixed crystal structure in the transition region.
According to the invention, a certain heating rate and heat treatment temperature are adopted before die forging forming, so that the grain size difference of coarse grains of the wheel rim is smaller, and the wheel rim obtains higher creep resistance. In the die forging forming process, the hub is completely and dynamically recrystallized to obtain a fine grain structure, a large-size primary gamma ' phase existing in a conventional deformed fine grain turbine disc is eliminated, the volume fractions of a secondary gamma ' phase and a tertiary gamma ' phase which are coherently precipitated are increased, the short-time strength, the durability and the creep resistance are improved, and the long-term structure stability is improved.
In a specific embodiment of the invention, in the disc obtained by die forging, the size of a primary gamma 'phase is 100-2000 nm, and the volume fraction of the primary gamma' phase is less than or equal to 5%.
The size of the primary gamma' phase of the alloy in the alloy composition range limited by the invention is 100-10 mu m, the volume fraction is 5-15%, the size is relatively large, and the number is large. In the disc obtained by the method, the number of primary gamma 'phases is greatly reduced, and the large-size primary gamma' phase is eliminated, so that the number of secondary gamma 'phases and tertiary gamma' phases which are coherently precipitated after the disc is subjected to sub-solution heat treatment and aging heat treatment is increased. For GH4096 alloy, the volume fractions of the two-time gamma 'phase and the three-time gamma' phase which are precipitated in a coherent manner are respectively 28-33% and 2-6%; for GH4198 alloy, the volume fractions of the secondary gamma 'phase and the tertiary gamma' phase which are coherently precipitated are 40-45% and 3-8%, respectively.
In a particular embodiment of the invention, the alloy is a nickel-base superalloy. Further, the chemical components of the nickel-based superalloy comprise the following components in percentage by mass: c: 0.005% -0.070%, Co: 12% -21%, Cr: 12% -18%, W: 1.0% -5.0%, Mo: 1.0-5.0%, Ti: 2.0% -6.0%, Al: 1.0% -4.0%, B: 0.010-0.020%, Zr: 0.030 to 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 inevitable impurities. The nickel-base superalloy is, for example, but not limited to, a GH4096 alloy.
In a specific embodiment of the present invention, step (a) further comprises: and machining and drilling the forged blank.
In actual operation, specific machining parameters are adjusted and selected according to actual turbine disk size requirements.
The invention also provides an alloy turbine disk forging with high temperature resistance and high durability, which is prepared by any one of the preparation methods.
In a specific embodiment of the invention, the rim creep performance of the alloy turbine disk forging satisfies the following conditions: the duration time is more than or equal to 350h when the plastic deformation is 0.2 percent at 700 ℃/690 MPa.
Example 1
The embodiment provides a preparation method of a GH4096 alloy turbine disc forging with high temperature resistance and high durability, which comprises the following steps:
(1) the vacuum induction melting and electroslag remelting continuous directional solidification preparation method is adopted to obtain the alloy with the specification of
GH4096 alloy ingot casting; 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: not more than 0.5 percent, the balance being Ni and unavoidableAnd (4) avoiding impurities.
(2) Carrying out high-temperature homogenization heat treatment on the alloy ingot obtained in the step (1), wherein the highest temperature of the homogenization heat treatment is 1200 ℃, the heat preservation time is 48h, then carrying out constrained upsetting and cogging, and obtaining the alloy ingot after multi-directional forging
Cake blank, grain size grade 9, by
The noise level is less than 20%.
(3) Performing die forging on the alloy forging blank obtained in the step (2) to obtain a blank with the grain size of 9 grade; in the die forging, the forging heating temperature is 1070 ℃, the hub deformation is 15%, the rim deformation is 38%, the shape is shown in figure 1, and then the blank shown in figure 2 is obtained by machining and punching.
(4) Heating the blank obtained in the step (3) to 900 ℃ at a speed of 100 ℃/h, and preserving heat for 2h, and heating to 1120 ℃ at a speed of 150 ℃/h, and preserving heat for 1.5h to obtain an isometric crystal structure with a grain size of 4-6 grade; then, die forging and forming are carried out, and the shape of the obtained disc piece is shown in fig. 3, wherein the deformation of the hub is 40%, and a fine crystal structure with the grain size of 7-8 grades is obtained, as shown in fig. 4; the deformation of the wheel rim is less than 5%, a coarse-grain structure with the grain size of 4-6 grades is maintained, as shown in fig. 5, the deformation of the web plate is 20%, and the coarse-grain structure is a mixed-grain structure in a transition region, as shown in fig. 6.
(5) And (4) machining the disc part obtained in the step (4), and then performing sub-solid solution heat treatment at the speed of 1080 ℃/2h and aging heat treatment at the speed of 760 ℃/4h to obtain the double-structure alloy turbine disc forging.
The performance of the GH4096 alloy turbine disc forging prepared by the embodiment is tested, the creep performance of the wheel rim is tested, the experimental condition is 700 ℃/690MPa, and the duration time is 350h when the plastic deformation is 0.2%, which is superior to the creep performance of the conventional fine-grain forging; tensile property at 650 ℃, tensile strength 1420MPa, yield strength 1050 MPa.
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) the vacuum induction melting and electroslag remelting continuous directional solidification preparation method is adopted to obtain the alloy with the specification of
GH4198 alloy ingot of (a); 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 inevitable impurities.
(2) Carrying out high-temperature homogenization heat treatment on the alloy ingot obtained in the step (1), wherein the highest temperature of the homogenization heat treatment is 1200 ℃, the heat preservation time is 48h, then carrying out constrained upsetting and cogging, and obtaining the alloy ingot after multi-directional forging
Cake blank, grain size grade 9, by
The noise level is less than 40%.
(3) Performing die forging on 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 hub deformation is 15%, the rim deformation is 40%, and the crystal grains of different parts of the disc are 8-9 grades. And then machining and punching to obtain a blank.
(4) Heating the blank obtained in the step (3) to 900 ℃ at a speed of 100 ℃/h, and preserving heat for 2h, and heating to 1150 ℃ at a speed of 150 ℃/h, and preserving heat for 1.5h to obtain an isometric crystal structure with a grain size of 4-6 grade; then, die forging and forming are carried out, and the shape of the obtained disc piece is shown in fig. 3, wherein the deformation of the hub is 40%, and a fine crystal structure with the grain size of 7-8 grades is obtained, as shown in fig. 4; the deformation of the wheel rim is less than 5%, a coarse crystal structure with the grain size of 4-6 grades is maintained, and as shown in fig. 5, the deformation of the web plate is 25%, and the web plate is a mixed crystal structure in a transition region.
(5) And (4) machining the disc part obtained in the step (4), and then performing subaqueous solution heat treatment at 1120 ℃/2h and aging heat treatment at 780 ℃/4h to obtain the turbine disc forging.
Testing the creep property of the wheel rim, wherein the duration time is 900h when the experimental condition is 700 ℃/690MPa and the plastic deformation is 0.2%; tensile property at 750 ℃, tensile strength 1180MPa and yield strength 1020 MPa.
Comparative example 1
Comparative example 1 provides a method of making a GH4096 turbine disk comprising the steps of:
(1) the vacuum induction melting and electroslag remelting continuous directional solidification preparation method is adopted to obtain the alloy with the specification of
GH4096 alloy ingot casting; 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 inevitable impurities.
(2) Carrying out high-temperature homogenization heat treatment on the alloy ingot obtained in the step (1), wherein the highest temperature of the homogenization heat treatment is 1200 ℃, the heat preservation time is 48h, then carrying out constrained upsetting and cogging, and obtaining the alloy ingot after multi-directional forging
Biscuit, grain size grade 9, passing
The noise level is less than 20%.
(3) Performing die forging on 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 crystal grains of different parts of the disc are 8-9.5 grades.
(4) And (4) machining the disc part obtained in the step (3), and then performing sub-solid solution heat treatment at 1070 ℃/2h and aging heat treatment at 760 ℃/4h to obtain the fine-grain turbine disc forging.
Testing the creep property of the wheel rim, wherein the experimental condition is 700 ℃/690MPa, and the duration is 140h when the plastic deformation is 0.2%; tensile property at 650 ℃, tensile strength 1430MPa and yield strength 1055 MPa.
Comparative example 2
Comparative example 2 the preparation process of example 1 was referenced, with the following differences: the heat treatment in step (4) is different. The heat treatment of step (4) of comparative example 2 includes: heating to 900 ℃ at a speed of 80 ℃/h, preserving heat for 2h, heating to 1120 ℃ at a speed of 50 ℃/h, and preserving heat for 1.5 h.
The difference in rim grain level of the turbine disk forging produced in comparative example 2 was increased.
Comparative example 3
Comparative example 3 the preparation process of example 1 was referenced, with the following differences: and (4) the deformation amount of the hub and the deformation amount of the rim are different in the step (3) and the step (4). In step (3) of comparative example 3: the wheel hub deformation is 30 percent, and the wheel rim deformation is 25 percent; in step (4) of comparative example 3: the hub deflection is 25% and the rim deflection is 15%.
The hub grain refining effect of the turbine disk forging produced in comparative example 3 is poor, and the rim grain size difference is increased.
Experimental example 1
In order to comparatively illustrate the microstructure differences of the turbine disk forgings prepared by different examples and comparative examples, the microstructures of the turbine disk forgings prepared by different examples and comparative examples are 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 used to illustrate the technical solution of the present invention, and not to limit the same; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and these modifications or substitutions do not depart from the spirit of the corresponding technical solutions of the embodiments of the present invention.
Claims (10)
1. The preparation method of the alloy turbine disc forging with high temperature resistance and high durability is characterized by comprising the following steps:
(a) carrying out die forging on the alloy forging stock to obtain a stock; in the die forging, the forging heating temperature is the sub-solid solution temperature T1The wheel hub deformation is 15% -20%, and the wheel rim deformation is 30% -40%;
(b) carrying out die forging forming on the blank after heat treatment to obtain a disc piece; the heat treatment comprises: heating to 900-1000 ℃ at a rate of more than or equal to 80 ℃/h, preserving heat for 1-2 h, and heating to an over-solid solution temperature T at a rate of more than or equal to 120 ℃/h2Preserving the 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 plate is 5-25%;
(c) and carrying out sub-solution heat treatment and aging heat treatment on the disc.
2. The method according to claim 1, wherein the sub-solution temperature T is1Satisfies the following conditions: t is more than or equal to Ts-100 DEG C1Ts-40 ℃ or less; the excess solid solution temperature T2Satisfies the following conditions: ts is less than or equal to T2Ts +20 ℃; ts is the gamma' phase total dissolution temperature.
3. The method according to claim 1, wherein the temperature of the sub-solution heat treatment is T3，T3Satisfies the following conditions: t is not more than Ts-70 DEG C3Ts-40 ℃ or lower, and Ts is the gamma' phase total dissolution temperature; the temperature of the aging heat treatment is 730-830 ℃.
4. The method according to claim 1, wherein in the step (a), the grain size of the alloy forging is 8 grades or finer;
preferably, the grade difference of the grain sizes of different parts of the alloy forging stock is not more than 2 grade.
5. The method according to claim 1, wherein the preparing of the alloy forging in step (a) comprises: and (3) performing homogenization heat treatment on the alloy ingot, and then performing cogging and multidirectional forging.
6. The method of claim 5, wherein the preparing the alloy ingot comprises: preparing materials according to alloy components, and smelting by adopting a vacuum induction smelting and vacuum consumable remelting two-connection smelting process; or the alloy is prepared according to alloy components by adopting a triple smelting process of vacuum induction smelting, electroslag remelting and vacuum consumable smelting.
7. The preparation method according to claim 1, wherein in the step (b), after the heat treatment, a uniform equiaxed coarse-grained structure with a grain size of 4-6 grades 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 radial plate is a mixed crystal structure of a transition area.
8. The preparation method according to claim 1, wherein the disc obtained by die forging is characterized in that the size of a primary gamma 'phase is 100-2000 nm, and the volume fraction of the primary gamma' phase is less than or equal to 5%.
9. The production method according to any one of claims 1 to 8, wherein the alloy is a nickel-based superalloy;
preferably, the chemical composition of the nickel-base superalloy comprises the following components in percentage by mass: c: 0.005% -0.070%, Co: 12% -21%, Cr: 12% -18%, W: 1.0% -5.0%, Mo: 1.0-5.0%, Ti: 2.0% -6.0%, Al: 1.0% -4.0%, B: 0.010-0.020%, Zr: 0.030 to 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 inevitable impurities.
10. The alloy turbine disk forging with high temperature resistance and high durability, which is prepared by the preparation method of any one of claims 1 to 9.
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