CN117535559A - Low-density nickel-based high-temperature alloy foil and preparation method and application thereof - Google Patents
Low-density nickel-based high-temperature alloy foil and preparation method and application thereof Download PDFInfo
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- CN117535559A CN117535559A CN202410033998.9A CN202410033998A CN117535559A CN 117535559 A CN117535559 A CN 117535559A CN 202410033998 A CN202410033998 A CN 202410033998A CN 117535559 A CN117535559 A CN 117535559A
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- PXHVJJICTQNCMI-UHFFFAOYSA-N Nickel Chemical compound [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 title claims abstract description 119
- 229910045601 alloy Inorganic materials 0.000 title claims abstract description 97
- 239000000956 alloy Substances 0.000 title claims abstract description 97
- 239000011888 foil Substances 0.000 title claims abstract description 60
- 229910052759 nickel Inorganic materials 0.000 title claims abstract description 60
- 238000002360 preparation method Methods 0.000 title abstract description 10
- 229910000601 superalloy Inorganic materials 0.000 claims abstract description 32
- 229910052727 yttrium Inorganic materials 0.000 claims abstract description 20
- 229910052720 vanadium Inorganic materials 0.000 claims abstract description 18
- 229910052796 boron Inorganic materials 0.000 claims abstract description 12
- 239000000126 substance Substances 0.000 claims abstract description 10
- 229910052721 tungsten Inorganic materials 0.000 claims abstract description 8
- 239000002994 raw material Substances 0.000 claims description 42
- 229910052782 aluminium Inorganic materials 0.000 claims description 20
- 238000007670 refining Methods 0.000 claims description 20
- 238000010438 heat treatment Methods 0.000 claims description 19
- 238000000034 method Methods 0.000 claims description 14
- 238000000137 annealing Methods 0.000 claims description 13
- 238000005266 casting Methods 0.000 claims description 6
- 210000000795 conjunctiva Anatomy 0.000 claims description 6
- 239000000463 material Substances 0.000 claims description 5
- 238000002156 mixing Methods 0.000 claims description 5
- 238000012958 reprocessing Methods 0.000 claims description 4
- 239000012528 membrane Substances 0.000 claims description 3
- 238000004519 manufacturing process Methods 0.000 abstract description 9
- 238000007789 sealing Methods 0.000 abstract description 9
- 230000003647 oxidation Effects 0.000 description 11
- 238000007254 oxidation reaction Methods 0.000 description 11
- 238000005728 strengthening Methods 0.000 description 11
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 description 10
- 230000000694 effects Effects 0.000 description 10
- 230000000052 comparative effect Effects 0.000 description 9
- 239000006104 solid solution Substances 0.000 description 8
- 230000035882 stress Effects 0.000 description 8
- 229910052761 rare earth metal Inorganic materials 0.000 description 7
- 230000002349 favourable effect Effects 0.000 description 6
- 239000011159 matrix material Substances 0.000 description 6
- 238000005097 cold rolling Methods 0.000 description 5
- 238000013461 design Methods 0.000 description 5
- 238000005098 hot rolling Methods 0.000 description 5
- 239000000243 solution Substances 0.000 description 5
- 230000009471 action Effects 0.000 description 4
- 230000007797 corrosion Effects 0.000 description 4
- 238000005260 corrosion Methods 0.000 description 4
- 238000012545 processing Methods 0.000 description 4
- 101000912561 Bos taurus Fibrinogen gamma-B chain Proteins 0.000 description 3
- 230000009286 beneficial effect Effects 0.000 description 3
- 230000015572 biosynthetic process Effects 0.000 description 3
- 229910052804 chromium Inorganic materials 0.000 description 3
- 239000013078 crystal Substances 0.000 description 3
- 239000000203 mixture Substances 0.000 description 3
- 229910052750 molybdenum Inorganic materials 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 238000009966 trimming Methods 0.000 description 3
- 229910017052 cobalt Inorganic materials 0.000 description 2
- 239000010941 cobalt Substances 0.000 description 2
- GUTLYIVDDKVIGB-UHFFFAOYSA-N cobalt atom Chemical compound [Co] GUTLYIVDDKVIGB-UHFFFAOYSA-N 0.000 description 2
- 238000006477 desulfuration reaction Methods 0.000 description 2
- 230000023556 desulfurization Effects 0.000 description 2
- 238000005242 forging Methods 0.000 description 2
- 239000012535 impurity Substances 0.000 description 2
- 229910052742 iron Inorganic materials 0.000 description 2
- 238000002844 melting Methods 0.000 description 2
- 230000008018 melting Effects 0.000 description 2
- 150000002910 rare earth metals Chemical class 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- 238000003723 Smelting Methods 0.000 description 1
- 229910000946 Y alloy Inorganic materials 0.000 description 1
- 230000032683 aging Effects 0.000 description 1
- 238000005275 alloying Methods 0.000 description 1
- 239000003153 chemical reaction reagent Substances 0.000 description 1
- 238000010622 cold drawing Methods 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 239000002826 coolant Substances 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000007872 degassing Methods 0.000 description 1
- 230000003111 delayed effect Effects 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 230000017525 heat dissipation Effects 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000009776 industrial production Methods 0.000 description 1
- 230000002045 lasting effect Effects 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 239000000843 powder Substances 0.000 description 1
- 239000002244 precipitate Substances 0.000 description 1
- 238000001556 precipitation Methods 0.000 description 1
- 239000000047 product Substances 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- -1 rare earth compounds Chemical class 0.000 description 1
- 229910001404 rare earth metal oxide Inorganic materials 0.000 description 1
- 230000006641 stabilisation Effects 0.000 description 1
- 238000011105 stabilization Methods 0.000 description 1
- 238000005482 strain hardening Methods 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
- 230000003245 working effect Effects 0.000 description 1
Classifications
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C19/00—Alloys based on nickel or cobalt
- C22C19/03—Alloys based on nickel or cobalt based on nickel
- C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
- C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
- C22C19/055—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 20% but less than 30%
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C1/00—Making non-ferrous alloys
- C22C1/02—Making non-ferrous alloys by melting
- C22C1/023—Alloys based on nickel
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C1/00—Making non-ferrous alloys
- C22C1/06—Making non-ferrous alloys with the use of special agents for refining or deoxidising
-
- 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 application relates to a low-density nickel-based high-temperature alloy foil, a preparation method and application thereof, wherein the nickel-based high-temperature alloy foil comprises the following chemical components: C. cr, co, W, mo, al, ti, fe, B, V, Y and Ni; wherein, the content of Cr is 18-21% by mass, the content of Co is 0.3-2.2%, the content of W is 0.5-1.5%, the content of Mo is 7.0-8.5%, the content of Al is 0.8-1.2%, the content of Ti is 0.15-0.25%, the content of B is 0.005-0.015%, the content of V is 0.08-0.25%, and the content of Y is 0.01-0.02%. The technical problem that the conventional nickel-based superalloy is difficult to be suitable for manufacturing an aeroengine honeycomb sealing structure serving at the temperature of about 900 ℃ and below is solved.
Description
Technical Field
The application relates to the technical field of high-temperature alloy processing and preparation, in particular to a low-density nickel-based high-temperature alloy foil and a preparation method and application thereof.
Background
The high-temperature alloy is a metal material which takes iron, cobalt and nickel as matrixes and can work for a long time under the action of high temperature above 600 ℃ and certain force. According to the different matrix elements, the alloy is divided into iron-based, nickel-based and cobalt-based superalloys, and according to the different preparation methods, the alloy can be divided into casting, deformation and powder superalloys. The nickel-based deformation superalloy refers to a superalloy taking nickel as a matrix, and a finished product of the superalloy can be prepared by deformation means such as forging, hot rolling, cold rolling or cold drawing.
At present, nickel-based high-temperature alloy foil is used for preparing a honeycomb sealing structure in an aerospace engine, and the nickel-based high-temperature alloy foil is difficult to meet the preparation requirement of the honeycomb sealing structure of the aerospace engine in service at the temperature of about 900 ℃ and below.
Disclosure of Invention
The application provides a low-density nickel-based high-temperature alloy foil and a preparation method and application thereof, so as to solve the technical problem that the conventional nickel-based high-temperature alloy is difficult to be suitable for manufacturing an aeroengine honeycomb sealing structure serving at the temperature of about 900 ℃ and below.
In a first aspect, the present application provides a low density nickel-base superalloy foil, the nickel-base superalloy foil comprising the chemical components: C. cr, co, W, mo, al, ti, fe, B, V, Y and Ni; wherein, the mass fraction of the material is calculated,
18-21% of Cr, 0.3-2.2% of Co, 0.5-1.5% of W, 7.0-8.5% of Mo, 0.8-1.2% of Al, 0.15-0.25% of Ti, 0.005-0.015% of B, 0.08-0.25% of V and 0.01-0.02% of Y.
Optionally, the mass fraction of Al, V and Y satisfies the following relation:
wherein [ Al ] represents the mass fraction of Al, [ V ] represents the mass fraction of V, and [ Y ] represents the mass fraction of Y.
Optionally, the mass fraction of Al, V and Y satisfies the following relation:
wherein [ Al ] represents the mass fraction of Al, [ V ] represents the mass fraction of V, and [ Y ] represents the mass fraction of Y.
Optionally, the content of C is 0.07-0.16% by mass, and the content of Fe is 19-22% by mass.
Optionally, the content of C is 0.07-0.12%, the content of Cr is 18.5-20.6%, the content of Al is 0.95-1.17%, the content of Fe is 20.8-22%, the content of B is 0.005-0.015%, and the content of V is 0.12-0.23%.
Optionally, the content of V is 0.14-0.22% in terms of mass fraction.
Optionally, the nickel-based high temperature alloy foil meets at least one of the following properties at 900 ℃: tensile strength of
220MPa or more and an elongation of 87% or more.
Optionally, the density of the nickel-based high-temperature alloy foil is less than or equal to 8.13g/cm 3 。
In a second aspect, the present application provides a low density nickel-based high temperature alloy foil as described in any one of the embodiments of the first aspect
In aeroengines or gas turbines.
In a third aspect, the present application provides a method of preparing a low density nickel-based high temperature according to any one of the embodiments of the first aspect
A method of alloy foil, the method comprising:
performing first vacuum heating on a first raw material to exhaust gas attached to the first raw material;
performing second vacuum heating on the first raw material subjected to the first vacuum heating to enable the first raw material to be in a molten state, and then performing first refining to obtain a first molten raw material of conjunctiva;
performing membrane breaking treatment on the first molten raw material of the conjunctiva, adding a second raw material, and uniformly mixing to perform second refining and pouring to obtain a flat blank;
reprocessing the flat blank, and then carrying out stress annealing treatment to obtain a low-density nickel-based superalloy foil; wherein,
the temperature of the first refining is 1500-1600 ℃, the temperature of the second refining is 1550-1630 ℃, the temperature of casting is 1430-1510 ℃, and the temperature of stress annealing treatment is 610-630 ℃.
Compared with the prior art, the technical scheme provided by the embodiment of the application has the following advantages:
according to the low-density nickel-based high-temperature alloy foil provided by the embodiment of the application, through reasonable design of chemical components, the prepared nickel-based high-temperature alloy foil has excellent mechanical properties at the service temperature of 900 ℃, has high strength, high-temperature resistance, corrosion resistance, oxidation resistance, high toughness and good welding performance, and meets the design and use requirements of an advanced aeroengine.
Drawings
The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the application and together with the description, serve to explain the principles of the application.
In order to more clearly illustrate the embodiments of the present application or the technical solutions in the prior art, the drawings that are required to be used in the description of the embodiments or the prior art will be briefly described below, and it will be obvious to those skilled in the art that other drawings can be obtained from these drawings without inventive effort.
Fig. 1 is a microstructure of a low-density nickel-based high-temperature alloy foil according to an embodiment of the present application.
Detailed Description
For the purposes of making the objects, technical solutions and advantages of the embodiments of the present application more clear, the technical solutions of the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is apparent that the described embodiments are some embodiments of the present application, but not all embodiments. All other embodiments, which can be made by one of ordinary skill in the art without undue burden from the present disclosure, are within the scope of the present application based on the embodiments herein.
Various embodiments of the present application may exist in a range format; it should be understood that the description in a range format is merely for convenience and brevity and should not be interpreted as a rigid limitation on the scope of the application. It is therefore to be understood that the range description has specifically disclosed all possible sub-ranges and individual values within that range. For example, it should be considered that a description of a range from 1 to 6 has specifically disclosed sub-ranges, such as from 1 to 3, from 1 to 4, from 1 to 5, from 2 to 4, from 2 to 6, from 3 to 6, etc., as well as single numbers within the range, such as 1, 2, 3, 4, 5, and 6, wherever applicable. In addition, whenever a numerical range is referred to herein, it is meant to include any reference number (fractional or integer) within the indicated range.
In this application, unless otherwise indicated, terms of orientation such as "upper" and "lower" are used specifically to refer to the orientation of the drawing in the figures. In addition, in the description of the present application, the terms "include", "comprise", "comprising" and the like mean "including but not limited to". Relational terms such as "first" and "second", and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Herein, "and/or" describing an association relationship of an association object means that there may be three relationships, for example, a and/or B, may mean: a alone, a and B together, and B alone. Wherein A, B may be singular or plural. Herein, "at least one" means one or more, and "a plurality" means two or more. "at least one", "at least one (a) or the like refer to any combination of these items, including any combination of single item(s) or plural items (a). For example, "at least one (individual) of a, b, or c," or "at least one (individual) of a, b, and c," may each represent: a, b, c, a-b (i.e., a and b), a-c, b-c, or a-b-c, wherein a, b, c may be single or multiple, respectively.
Unless specifically indicated otherwise, the various raw materials, reagents, instruments, equipment, and the like used in this application are commercially available or may be prepared by existing methods.
In a first aspect, the present application provides a low-density nickel-based superalloy foil, please refer to a microstructure of the low-density nickel-based superalloy foil shown in fig. 1, wherein the chemical components of the nickel-based superalloy foil include: C. cr, co, W, mo, al, ti, fe, B, V, Y and Ni; wherein, the mass fraction of the material is calculated,
18-21% of Cr, 0.3-2.2% of Co, 0.5-1.5% of W, 7.0-8.5% of Mo, 0.8-1.2% of Al, 0.15-0.25% of Ti, 0.005-0.015% of B, 0.08-0.25% of V and 0.01-0.02% of Y.
In the embodiment of the application, a high Cr design is adopted, and the content of Cr element is increased, so that the strength and high-temperature lasting strength of the alloy can be improved, and the oxidation resistance and corrosion resistance of the alloy can be improved; the content of Mo is improved, the content of W is reduced, the alloy has good welding performance, meanwhile, precipitation of harmful brittle phases is avoided, and under the element composition of the design proportion, the strength of the alloy can be maintained at a higher level; the content of element Co is increased, and the plastic deformation capacity of the alloy is improved by reducing the stacking fault energy of the alloy; the elements B and Y are added into the alloy when the high Cr is adopted, so that the influence on plasticity possibly caused by the high Cr is counteracted, and the B and Y elements dissolved in the gamma matrix can be biased at the grain boundary to play a role in strengthening the grain boundary, so that the formation and the expansion of cracks are delayed, the durability of the alloy is obviously improved, and in addition, the high-temperature oxidation resistance of the alloy can be obviously improved by the combined use of the elements Al, ti and Y. The addition of the element V in the alloy, V being a strong carbide and gamma' -forming element, V being able to replace Ni 3 The position of Al in Al (gamma') improves the stability, V can be dissolved in the matrix, so that the lattice distortion is effectively increased, and the solid solution strengthening effect is generated. The application advantages of V in the honeycomb sealing piece of the gas turbine for the aero-engines, the ground and the warship are particularly reflected in the two aspects of reducing the expansion coefficient of the alloy and improving the heat conductivity of the alloy, and the low expansion coefficient is beneficial to keeping the shape and the size stability of the honeycomb sealing piece at high temperature.
In the examples herein, the roles of Cr, co, mo, al, ti, B, V and Y in the low density nickel-base superalloy are as follows:
cr: mainly exists in a nickel-based superalloy matrix in a solid solution state, has the main functions of improving the oxidation resistance and the hot corrosion resistance of the alloy, has a certain solid solution strengthening effect, and can be combined with C to form granular M distributed along crystals 23 C 6 And plays a role in strengthening grain boundaries. However, when the Cr content is too high, the structural stability and the forming processability of the alloy are reduced, and the alloy in the embodiment of the application is mainly used for honeycomb sealingThe component material has high requirements on the forming processability of the alloy, so the content of Cr is allowed to be lower than that of the common nickel-based wrought superalloy, in exchange for relatively high forming processability and structural stability. Specifically, the Cr content may be 19%, 20%, 21%, 22%, etc.
Co and Mo: both the two elements are solid solution strengthening elements, so that the alloy strength can be improved; however, the higher atomic number increases the alloy density and increases the cost, and the Co and Mo contents are controlled within the above-mentioned numerical ranges, respectively, from the viewpoints of weight reduction and economy. Specifically, the content of Co may be 0.3%, 0.5%, 0.7%, 0.9%, 1.1%, 1.3%, 1.5%, 1.7%, 1.9%, 2.2%, etc., and the content of Mo may be 7.0%, 7.2%, 7.4%, 7.6%, 7.8%, 8.0%, 8.2%, 8.5%, etc.
Al and Ti: both are gamma ' forming elements, and as the content of the gamma ' is increased, the quantity of the gamma ' is increased, and the high-temperature strength and the durability of the material are improved. The addition of Al element forms Al on the alloy surface 2 O 3 The protective film is favorable for improving the oxidation resistance of the alloy, and the Ti is favorable for improving the corrosion resistance. However, too high Al and Ti can precipitate out harmful beta phase, which is unfavorable for tissue stabilization; ti can obviously reduce solidus temperature, reduce hot working window and is unfavorable for hot working performance of alloy; too much Al and Ti deteriorate the weldability and impair the forming processability, and therefore the Al and Ti contents are determined to balance the high temperature property, weldability and forming processability. In order to balance high temperature properties, oxidation resistance, weldability, and formability, the content of Al and Ti is controlled within the above-described range, specifically, the content of Al may be 0.8%, 0.9%, 1.0%, 1.1%, 1.2%, etc., and the content of Ti may be 0.15%, 0.17%, 0.20%, 0.23%, 0.25%, etc.
B: the grain boundary strengthening element can increase the plasticity of the alloy, is beneficial to the coordinated deformation of the grain boundary in the hot working process, and can improve the oxidation resistance and creep resistance of the alloy. However, the B content is too high, so that massive boride is easy to form at the grain boundary, and the mechanical property of the alloy is not facilitated. Specifically, the content of B may be 0.005%, 0.007%, 0.009%, 0.011%, 0.013%, 0.015%, or the like.
V: the addition of the element V in the alloy, V being a strong carbide and gamma' -forming element, V being able to replace Ni 3 The position of Al in Al (gamma') improves the stability, V can be dissolved in the matrix, so that the lattice distortion is effectively increased, and the solid solution strengthening effect is generated. The application advantages of V in the honeycomb structural member of the gas turbine for the aeroengine, the ground and the warship are particularly reflected in the two aspects of reducing the expansion coefficient of the alloy and improving the heat conductivity of the alloy, the low expansion coefficient is favorable for keeping the stability of the shape and the size of the honeycomb structural member at high temperature, early damage caused by expansion and contraction is prevented, the high heat conductivity is favorable for heat dissipation of the honeycomb structural member, particularly, the heat exchange between the gas cooling medium and the body of the honeycomb structural member is accelerated, and the temperature of the honeycomb structural member is favorable for reducing. Based on experimental study, the invention discovers that the combined addition of V and Al has obvious effect on improving the 900 ℃ strength of the nickel-based wrought superalloy. The effect of increasing the medium temperature strength is not obvious when the content of V is too low, and the medium temperature plasticity and the room temperature plasticity of the alloy are reduced when the content of V is too high. Specifically, the V content may be 0.08%, 0.10%, 0.12%, 0.14%, 0.16%, 0.18%, 0.20%, 0.22%, 0.24%, 0.25%.
Y: the common rare earth elements can play a good role in deoxidization, desulfurization and degassing in the alloy smelting process, purify and strengthen grain boundaries, and improve the processing performance of the alloy; the alloy can also be used as micro alloying elements to be biased to grain boundaries to play a role in strengthening the grain boundaries; in addition, the Y as an active element can improve the oxidation resistance of the alloy and improve the surface stability. Compared with single rare earth element, the mixed rare earth element has obvious improvement effect on the durability of the alloy, but too high rare earth element can form a large amount of large-particle rare earth compounds at the grain boundary, which is unfavorable for the performance of the alloy. Specifically, the content of Y may be 0.01%, 0.012%, 0.014%, 0.016%, 0.018%, 0.02%, or the like.
In some embodiments, the mass fraction of Al, V, and Y satisfies the following relationship:
wherein [ Al ] represents the mass fraction of Al, [ V ] represents the mass fraction of V, and [ Y ] represents the mass fraction of Y.
In some embodiments, the mass fraction of Al, V, and Y satisfies the following relationship:
wherein [ Al ] represents the mass fraction of Al, [ V ] represents the mass fraction of V, and [ Y ] represents the mass fraction of Y.
In the embodiment of the application, the contents of Al, V and Y are further controlled, the 900 ℃ strength of the nickel-based wrought superalloy is improved, the grain boundary is purified and strengthened, and the processability of the alloy is improved. Specifically, the ([ Al)]+3.8[V])/5.6[Y]The values of (2) may be 14.5, 15, 16, 17, 18, 19, 20, 21, 22, 23.2, etc., preferably the range of values may be controlled to。
In the embodiment of the application, the content of C is 0.07-0.16% by mass, and the content of Fe is
19-22%.
In the embodiment of the present application, the content of C may be 0.07%, 0.09%, 0.11%, 0.13%, 0.15%, 0.16%, etc., and the content of Fe may be 18%, 19%, 20%, 21%, etc.
In the embodiment of the application, the content of C is 0.07-0.12% by mass, the content of Cr is 18.5-20.6% by mass, the content of Al is 0.95-1.17% by mass, the content of Fe is 20.8-22% by mass, the content of B is 0.005-0.015% by mass, and the content of V is 0.12-0.23% by mass.
In this embodiment, preferably, the content of C may be 0.07 to 0.12%, and the content of Cr may be
18.5 to 20.6%, the content of Al may be 0.95 to 1.17%, the content of Ti may be 0.15 to 0.25%, the content of Fe may be 20.8 to 22%, the content of B may be 0.005 to 0.015%, and the content of V may be 0.12 to 0.23%.
In some embodiments, the content of V is 0.14-0.22% by mass fraction.
In the embodiment of the present application, the content of V may be preferably 0.14 to 0.22%.
In some embodiments, the nickel-based high temperature alloy foil satisfies at least one of the following properties at 900 ℃:
the tensile strength is 220MPa or more, and the elongation is 87% or more.
In the embodiment of the application, the tensile strength of the nickel-based high-temperature alloy foil can be 220MPa, 222MPa, 224MPa, 226MPa and the like under the condition of 900 ℃, and the elongation can be 87%, 88%, 89%, 90% and the like.
In some embodiments, the nickel-based high temperature alloy foil has a density of 8.13g/cm or less 3 。
In embodiments of the present application, the nickel-based high temperature alloy foil may have a density of 8.13g/cm 3 、8.14g/cm 3 、8.15g/cm 3 、
8.16g/cm 3 、8.17g/cm 3 Etc.
In summary, the low-density nickel-based high-temperature alloy foil provided by the embodiment of the application has at least the following partial advantages:
1) The alloy has higher yield strength. 18-21% Cr has a strong solid solution strengthening effect; in addition, by adding two solid solution elements of W and Mo, the solid solution strengthening effect of the alloy is more obvious, the yield strength of the alloy at high temperature is obviously improved, and the service temperature of the alloy is improved to about 900 ℃;
2) The alloy has good hot working and cold working properties. The alloy has a wide hot working window of 400-600 ℃, few surface cracks, good plasticity and high yield in the alloy working process. By controlling 0.8-1.2% of Al and 0.15-0.25% of Ti, the alloy is ensured to have good processing performance while the aging strengthening effect is fully achieved, and the quantity of gamma' phases is controlled to be not more than 20%. Forming mixed rare earth by adding 0.01-0.02% of Y, purifying a crystal boundary, improving the hot workability of the crystal boundary, and improving the strength of the alloy;
3) Alloy oxidation resistanceThe performance is good. Adding 18-21% Cr to form Cr on the alloy surface 23 C 6 Adding 0.8-1.2% Al to form a layer of compact Al on the surface of the alloy 2 O 3 The oxidation resistance is improved; in addition, the added rare earth Y forms rare earth oxide, so that the high-temperature oxidation resistance of the alloy reaches more than 1100 ℃;
4) The addition of 0.08-0.25% of V can reduce the expansion coefficient of the alloy, improve the thermal conductivity of the alloy, and the low expansion coefficient is favorable for keeping the shape and size stability of the honeycomb sealing piece at high temperature, so that the honeycomb sealing piece is very suitable for manufacturing the aerospace engine honeycomb sealing structural piece.
5) The alloy has less harmful impurity elements, high purity, less internal defects and good uniformity of component tissues. The production process flow is short and the production cost is low. Through reasonable C, Y alloy element addition, the better deoxidization, denitrification and desulfurization effects are achieved.
In a second aspect, the present application provides a low density nickel-based high temperature alloy foil as described in any one of the embodiments of the first aspect
In aeroengines or in gas turbines.
In the embodiment of the application, the low-density nickel-based high-temperature alloy foil has excellent performance and is suitable for aviation hair
In the manufacture of engines or gas turbines.
In a third aspect, the present application provides a method of making a low density nickel-base superalloy as described in any of the embodiments of the first aspect
A method of foil, the method comprising:
s1, performing first vacuum heating on a first raw material to discharge gas attached to the first raw material;
specifically, the above S1 includes: co, ni, cr, W, mo, fe and part of the raw material C are placed in an environment with the vacuum degree of 0.5-1.0 Pa for mixed heating, and gas attached to the raw material is discharged;
s2, performing second vacuum heating on the first raw material subjected to the first vacuum heating to enable the first raw material to be in a molten state, and then performing first refining to obtain a first molten raw material of conjunctiva;
specifically, the step S2 includes: heating the raw materials to a molten state in an environment with the vacuum degree of 0.3-0.5 Pa, heating to 1500-1600 ℃, refining at a high temperature for 35-45min, and stopping heating to enable the raw materials to be molten into a film;
s3, performing membrane rupture treatment on the first molten raw material of the conjunctiva, adding a second raw material, and uniformly mixing to perform second refining and pouring to obtain a flat blank;
specifically, the step S3 includes: raising the temperature to break the film of the melting raw material, adding Al, ti, B, V and Y and the rest of the C raw material, and uniformly mixing;
refining the mixed raw materials added with Al, ti, B, V, Y and the rest of C raw materials at 1550-1630 ℃;
pouring the refined raw materials at 1430-1510 ℃ to obtain flat blanks;
s4, reprocessing the flat blank, and then carrying out stress annealing treatment to obtain a low-density nickel-based superalloy foil; wherein,
the temperature of the first refining is 1500-1600 ℃, the temperature of the second refining is 1550-1630 ℃, the temperature of casting is 1430-1510 ℃, and the temperature of stress annealing treatment is 610-630 ℃.
Specifically, the step S4 includes: finishing, hot rolling, annealing and softening treatment, finishing again, cold rolling, intermediate heat treatment and trimming the flat blank to obtain an alloy foil;
and carrying out stress relief annealing treatment on the alloy strip at 610-630 ℃ at a tape running speed of (10-30) m/min to prepare the low-density nickel-based superalloy foil.
In the embodiment of the application, on the basis of the chemical components of the low-density nickel-based high-temperature alloy foil, the prepared low-density nickel-based high-temperature alloy foil has low density and excellent high-temperature strength and high flatness at the service temperature of 900 ℃ by controlling the temperature of the first refining, the temperature of the second refining, the casting temperature and the temperature of stress annealing treatment, and does not have forging, hot rolling and cold rolling crack formation, so that the requirements of the design and the use of an advanced aeroengine are met; the preparation method is simple, reduces energy consumption, shortens the production period, improves the production efficiency, and is suitable for popularization and application in industrial production. In particular to the preparation and processing of the low-density nickel-based high-temperature alloy foil with the thickness of 0.03-0.15 mm. Specifically, the temperature of the first refining may be 1500 ℃, 1510 ℃, 1520 ℃, 1530 ℃, 1540 ℃, 1550 ℃, 1560 ℃, 1570 ℃, 1580 ℃, 1590 ℃, 1600 ℃, etc., the temperature of the second refining may be 1550 ℃, 1560 ℃, 1570 ℃, 1580 ℃, 1620 ℃, 1630 ℃, etc., the temperature of the casting may be 1430 ℃, 1440 ℃, 1450 ℃, 1460 ℃, 1470 ℃, 1480 ℃, 1490 ℃, 1500 ℃, 1510 ℃, etc., the temperature of the stress annealing treatment may be 610 ℃, 620 ℃, 630 ℃, etc. Further, the first raw material may be Co, ni, cr, W, mo, fe and a part of the raw material C; the second feedstock may be Al, ti, B, V and Y and the remainder C feedstock, and the reprocessing may include finishing, hot rolling, annealing softening, finishing again, cold rolling, intermediate heat treating, and trimming.
The method for preparing the low-density nickel-based high-temperature alloy foil is based on the chemical formation of the low-density nickel-based high-temperature alloy foil
For implementation, the specific components of the chemical components of the low-density nickel-based high-temperature alloy foil may refer to the above embodiments, and because the method for preparing the low-density nickel-based high-temperature alloy foil adopts some or all of the technical solutions of the above embodiments, at least the technical solutions of the above embodiments have all the beneficial effects, which are not described herein in detail.
The present application is further illustrated below in conjunction with specific examples. It should be understood that these examples are illustrative only of the present application and are not intended to limit the scope of the present application. The experimental procedures, which are not specified in the following examples, are generally determined according to national standards. If the corresponding national standard does not exist, the method is carried out according to the general international standard, the conventional condition or the condition recommended by the manufacturer.
The specific chemical compositions of the low-density nickel-based high-temperature alloy foil provided in the embodiments of the present application are shown in table 1.
TABLE 1 chemical composition (wt%) of Low Density Nickel-based high temperature alloy foil, balance Ni and unavoidable impurities
Specific steps for preparing the low-density nickel-based high-temperature alloy foils of examples 1-8 and comparative examples 1-6 are as follows:
co, ni, cr, W, mo, fe and part of the raw material C are placed in an environment with the vacuum degree of 0.8Pa for mixed heating, and the gas attached to the raw material is discharged;
heating the raw materials to a molten state in an environment with the vacuum degree of 0.5Pa, heating to 1520 ℃, refining at a high temperature for 38min, and stopping heating to melt the raw material film;
raising the temperature to break the film of the melting raw material, adding Al, ti, B, V and Y and the rest of the C raw material, and uniformly mixing;
refining the mixed raw materials added with Al, ti, B, V, Y and the rest of C raw materials at 1570 ℃;
pouring the refined raw materials at 1470 ℃ to obtain a flat blank;
finishing, hot rolling, annealing and softening treatment, finishing again, cold rolling, intermediate heat treatment and trimming the flat blank to obtain an alloy foil;
and (3) carrying out stress relief annealing treatment on the alloy strip at the temperature of 623 ℃ and carrying out a tape moving speed of 10 m/min to prepare the low-density nickel-based superalloy foil.
Mechanical property tests were performed on the low-density nickel-based high-temperature alloy foils prepared in examples 1 to 8 and comparative examples 1 to 6, and the test results are shown in table 2.
TABLE 2 mechanical Properties of Low Density Nickel-based high temperature alloy foils
In comparative example 1, the content of Mo is not within the range of the examples of the present application; in comparative example 2, the content of Al is not within the range of the examples of the present application; in comparative example 3, the Ti content was not within the range of the examples of the present application; in comparative example 4, the content of V is not within the range of the examples of the present application; in comparative example 5, V was not contained; in comparative example 6, which does not contain Y, and is analyzed in combination with Table 2, it is shown that the mechanical properties of the low-density nickel-based high-temperature alloy foils prepared in comparative examples 1 to 6 are inferior to those of examples 1 to 8.
The foregoing is merely a specific embodiment of the application to enable one skilled in the art to understand or practice the application. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the application. Thus, the present application is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.
Claims (10)
1. The low-density nickel-based superalloy foil is characterized by comprising the following chemical components: C. cr, co, W, mo, al, ti, fe, B, V, Y and Ni; wherein, the mass fraction of the material is calculated,
18-21% of Cr, 0.3-2.2% of Co, 0.5-1.5% of W, 7.0-8.5% of Mo, 0.8-1.2% of Al, 0.15-0.25% of Ti, 0.005-0.015% of B, 0.08-0.25% of V and 0.01-0.02% of Y.
2. The nickel-base superalloy foil according to claim 1, wherein the mass fraction of Al, V and Y satisfies the following relationship:
wherein [ Al ] represents the mass fraction of Al, [ V ] represents the mass fraction of V, and [ Y ] represents the mass fraction of Y.
3. The nickel-base superalloy foil according to claim 2, wherein the mass fraction of Al, V and Y satisfies the following relationship:
wherein [ Al ] represents the mass fraction of Al, [ V ] represents the mass fraction of V, and [ Y ] represents the mass fraction of Y.
4. The nickel-base superalloy foil according to claim 1, wherein the content of C is 0.07-0.16% and the content of Fe is 19-22% in mass fraction.
5. The nickel-base superalloy foil according to claim 4, wherein the content of C is 0.07-0.12%, the content of Cr is 18.5-20.6%, the content of Al is 0.95-1.17%, the content of Fe is 20.8-22%, the content of B is 0.005-0.015%, and the content of V is 0.12-0.23% in terms of mass fraction.
6. The nickel-base superalloy foil according to any of claims 1 to 5, wherein the V is present in an amount of 0.14 to 0.22% by mass.
7. The nickel-base superalloy foil according to claim 1, wherein the nickel-base superalloy foil meets at least one of the following properties at 900 degrees celsius: the tensile strength is 220MPa or more, and the elongation is 87% or more.
8. The nickel-base superalloy foil according to claim 1, wherein the nickel-base superalloy foil has a density of 8.13g/cm or less 3 。
9. Use of a low density nickel-based high temperature alloy foil as claimed in any one of claims 1 to 8 in an aeroengine or gas turbine.
10. A method for preparing the low-density nickel-based high-temperature alloy foil according to any one of claims 1 to 8, which is characterized in that,
the method comprises the following steps:
performing first vacuum heating on a first raw material to exhaust gas attached to the first raw material;
performing second vacuum heating on the first raw material subjected to the first vacuum heating to enable the first raw material to be in a molten state, and then performing first refining to obtain a first molten raw material of conjunctiva;
performing membrane breaking treatment on the first molten raw material of the conjunctiva, adding a second raw material, and uniformly mixing to perform second refining and pouring to obtain a flat blank;
reprocessing the flat blank, and then carrying out stress annealing treatment to obtain a low-density nickel-based superalloy foil; wherein,
the temperature of the first refining is 1500-1600 ℃, the temperature of the second refining is 1550-1630 ℃, the temperature of casting is 1430-1510 ℃, and the temperature of stress annealing treatment is 610-630 ℃.
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