CN117364079A - High-temperature performance toughening method of die and die - Google Patents
High-temperature performance toughening method of die and die Download PDFInfo
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- CN117364079A CN117364079A CN202311639896.3A CN202311639896A CN117364079A CN 117364079 A CN117364079 A CN 117364079A CN 202311639896 A CN202311639896 A CN 202311639896A CN 117364079 A CN117364079 A CN 117364079A
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- 238000000034 method Methods 0.000 title claims abstract description 34
- 239000000956 alloy Substances 0.000 claims abstract description 68
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 66
- 238000006243 chemical reaction Methods 0.000 claims abstract description 54
- 239000011248 coating agent Substances 0.000 claims abstract description 40
- 238000000576 coating method Methods 0.000 claims abstract description 40
- 229910052500 inorganic mineral Inorganic materials 0.000 claims abstract description 33
- 239000011707 mineral Substances 0.000 claims abstract description 33
- 230000008646 thermal stress Effects 0.000 claims abstract description 26
- 239000013078 crystal Substances 0.000 claims abstract description 21
- 239000010410 layer Substances 0.000 claims description 205
- 238000009826 distribution Methods 0.000 claims description 16
- 238000004321 preservation Methods 0.000 claims description 14
- 229910000990 Ni alloy Inorganic materials 0.000 claims description 12
- 238000002425 crystallisation Methods 0.000 claims description 12
- 230000008025 crystallization Effects 0.000 claims description 12
- 229910001096 P alloy Inorganic materials 0.000 claims description 10
- OFNHPGDEEMZPFG-UHFFFAOYSA-N phosphanylidynenickel Chemical group [P].[Ni] OFNHPGDEEMZPFG-UHFFFAOYSA-N 0.000 claims description 10
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical group [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims description 8
- 239000010936 titanium Substances 0.000 claims description 8
- 229910052719 titanium Inorganic materials 0.000 claims description 8
- 229910000881 Cu alloy Inorganic materials 0.000 claims description 7
- YOCUPQPZWBBYIX-UHFFFAOYSA-N copper nickel Chemical compound [Ni].[Cu] YOCUPQPZWBBYIX-UHFFFAOYSA-N 0.000 claims description 7
- 229910000623 nickel–chromium alloy Inorganic materials 0.000 claims description 7
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 claims description 6
- NRTOMJZYCJJWKI-UHFFFAOYSA-N Titanium nitride Chemical compound [Ti]#N NRTOMJZYCJJWKI-UHFFFAOYSA-N 0.000 claims description 6
- 229910001297 Zn alloy Inorganic materials 0.000 claims description 6
- CYKMNKXPYXUVPR-UHFFFAOYSA-N [C].[Ti] Chemical compound [C].[Ti] CYKMNKXPYXUVPR-UHFFFAOYSA-N 0.000 claims description 6
- UQZIWOQVLUASCR-UHFFFAOYSA-N alumane;titanium Chemical compound [AlH3].[Ti] UQZIWOQVLUASCR-UHFFFAOYSA-N 0.000 claims description 6
- 229910052804 chromium Inorganic materials 0.000 claims description 6
- 239000011651 chromium Substances 0.000 claims description 6
- KUNSUQLRTQLHQQ-UHFFFAOYSA-N copper tin Chemical class [Cu].[Sn] KUNSUQLRTQLHQQ-UHFFFAOYSA-N 0.000 claims description 6
- TVZPLCNGKSPOJA-UHFFFAOYSA-N copper zinc Chemical compound [Cu].[Zn] TVZPLCNGKSPOJA-UHFFFAOYSA-N 0.000 claims description 6
- 229910052758 niobium Inorganic materials 0.000 claims description 6
- 239000010955 niobium Substances 0.000 claims description 6
- GUCVJGMIXFAOAE-UHFFFAOYSA-N niobium atom Chemical compound [Nb] GUCVJGMIXFAOAE-UHFFFAOYSA-N 0.000 claims description 6
- WFKWXMTUELFFGS-UHFFFAOYSA-N tungsten Chemical compound [W] WFKWXMTUELFFGS-UHFFFAOYSA-N 0.000 claims description 6
- 229910052721 tungsten Inorganic materials 0.000 claims description 6
- 239000010937 tungsten Substances 0.000 claims description 6
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- 230000001965 increasing effect Effects 0.000 claims description 3
- 239000002345 surface coating layer Substances 0.000 claims description 2
- 238000004519 manufacturing process Methods 0.000 abstract description 12
- 238000012423 maintenance Methods 0.000 abstract description 6
- 230000026267 regulation of growth Effects 0.000 abstract description 3
- 238000010438 heat treatment Methods 0.000 description 34
- 239000000463 material Substances 0.000 description 15
- 239000002131 composite material Substances 0.000 description 10
- 230000001174 ascending effect Effects 0.000 description 3
- 230000033228 biological regulation Effects 0.000 description 3
- 238000000151 deposition Methods 0.000 description 3
- 238000005137 deposition process Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 3
- 230000003028 elevating effect Effects 0.000 description 3
- 238000005240 physical vapour deposition Methods 0.000 description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 2
- 229910052799 carbon Inorganic materials 0.000 description 2
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Classifications
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
- C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
- C23C28/32—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer
- C23C28/321—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one pure metallic layer with at least one metal alloy layer
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/06—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the coating material
- C23C14/0605—Carbon
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/06—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the coating material
- C23C14/0641—Nitrides
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/06—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the coating material
- C23C14/0664—Carbonitrides
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/06—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the coating material
- C23C14/14—Metallic material, boron or silicon
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/58—After-treatment
- C23C14/5806—Thermal treatment
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/58—After-treatment
- C23C14/5893—Mixing of deposited material
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
- C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
- C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
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- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C28/00—Coating for obtaining at least two superposed coatings either by methods not provided for in a single one of groups C23C2/00 - C23C26/00 or by combinations of methods provided for in subclasses C23C and C25C or C25D
- C23C28/30—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer
- C23C28/34—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates
- C23C28/343—Coatings combining at least one metallic layer and at least one inorganic non-metallic layer including at least one inorganic non-metallic material layer, e.g. metal carbide, nitride, boride, silicide layer and their mixtures, enamels, phosphates and sulphates with at least one DLC or an amorphous carbon based layer, the layer being doped or not
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- Chemical & Material Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Inorganic Chemistry (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Moulds For Moulding Plastics Or The Like (AREA)
Abstract
The invention provides a high-temperature performance toughening method of a die and the die. The high-temperature performance toughening method comprises the following steps: forming an alloy layer on at least part of the surface of the die; forming a conversion layer on the surface of the alloy layer; forming a surface coating on the surface of the conversion layer; raising the temperature of the die and preserving heat for a preset time to crystallize the alloy layer and separate out crystals into the conversion layer to form a mineral bridge; the coefficient of thermal expansion of the conversion layer is between the coefficient of thermal expansion of the alloy layer and the coefficient of thermal expansion of the surface coating. Through setting up alloy layer, conversion layer and surface coating in proper order to introduce the growth regulation and control of mineral bridge, realized more accurate and comprehensive thermal stress control, can effectively improve the mould and resist thermal stress's ability, show stability and performance parameter and the life-span that improves the mould under high temperature environment, make the mould can bear higher temperature and more serious operating condition, make the frequency of mould maintenance or change reduce by a wide margin, help reducing manufacturing cost, improve production efficiency.
Description
Technical Field
The invention relates to the technical field of dies, in particular to a high-temperature performance toughening method of a die and the die.
Background
Composite molds play a critical role in modern industrial manufacturing, particularly in the field of ultra-precision manufacturing engineering, where they have a laminated structure of multiple layers of different materials to achieve excellent mechanical properties and high precision.
Thermal stresses (different parts of the mold may be subjected to different degrees of thermal stress), thermal expansion and hot shortness problems induced under high temperature conditions tend to cause damage and performance degradation of the composite mold, which not only affects manufacturing efficiency, but also results in high maintenance and replacement costs. Accordingly, researchers have sought innovative methods to improve the high temperature performance and extend the life of these molds, thereby achieving greater success in high temperature manufacturing and engineering applications.
The matters in the background section are only those known to the inventors and do not, of course, represent prior art in the field.
Disclosure of Invention
Aiming at one or more defects in the prior art, the invention provides a high-temperature performance toughening method of a die, which comprises the following steps:
forming an alloy layer on at least part of the surface of the die;
forming a conversion layer on the surface of the alloy layer;
forming a surface coating on the surface of the conversion layer;
raising the temperature of the die and preserving heat for a preset time to crystallize the alloy layer and separate out crystals into the conversion layer to form a mineral bridge;
wherein the coefficient of thermal expansion of the conversion layer is between the coefficient of thermal expansion of the alloy layer and the coefficient of thermal expansion of the surface coating.
According to one aspect of the present invention, the step of elevating the temperature of the mold and maintaining the same for a preset time includes:
and raising the temperature of the die to above the crystallization temperature of the alloy layer.
According to one aspect of the invention, the same or different temperatures are raised for different parts of the mould, said temperatures being determined according to the thermal stress distribution of the mould.
According to one aspect of the invention, the temperature is also determined according to the hardness, strength, toughness and/or Young's modulus to be achieved at different locations on the mold.
According to one aspect of the present invention, the step of elevating the temperature of the mold and maintaining the same for a preset time includes:
gradually increasing the temperature of the mold.
According to one aspect of the present invention, the step of elevating the temperature of the mold and maintaining the same for a preset time includes:
and preserving heat for different parts on the die for the same or different time, wherein the heat preservation time is determined according to the thermal stress distribution condition of the die.
According to one aspect of the invention, the incubation time is also determined according to the hardness, strength, toughness and/or Young's modulus to be achieved at different locations on the mold.
According to one aspect of the invention, the alloy layer is a nickel alloy layer, a copper-zinc alloy layer or a copper-tin alloy layer.
According to one aspect of the invention, the nickel alloy layer is a nickel-phosphorus alloy layer, a nickel-chromium alloy layer or a nickel-copper alloy layer.
According to one aspect of the invention, the surface coating is a diamond-like layer, a titanium nitride layer, a titanium carbon nitride layer, or a titanium aluminum nitride layer.
According to one aspect of the invention, the conversion layer is a titanium layer, a tungsten layer, a niobium layer, or a chromium layer.
The invention also provides a mould comprising:
a mold base;
an alloy layer formed on at least a portion of a surface of the mold;
a conversion layer formed on the surface of the alloy layer; and
a surface coating layer formed on the surface of the conversion layer;
the thermal expansion coefficient of the conversion layer is between that of the alloy layer and that of the surface coating, and mineral bridges formed by crystals crystallized and separated out from the alloy layer are arranged in the conversion layer.
According to one aspect of the invention, the alloy layer is a nickel alloy layer, a copper-zinc alloy layer or a copper-tin alloy layer.
According to one aspect of the invention, the nickel alloy layer is a nickel-phosphorus alloy layer, a nickel-chromium alloy layer or a nickel-copper alloy layer.
According to one aspect of the invention, the surface coating is a diamond-like layer, a titanium nitride layer, a titanium carbon nitride layer, or a titanium aluminum nitride layer.
According to one aspect of the invention, the conversion layer is a titanium layer, a tungsten layer, a niobium layer, or a chromium layer.
Compared with the prior art, the embodiment of the invention provides a high-temperature performance toughening method of a die, and the alloy layer, the conversion layer and the surface coating are sequentially arranged on at least part of the surface of the die, so that a mineral bridge is formed in the conversion layer, the capability of the die for resisting thermal stress can be effectively improved, the stability and performance parameters (equivalent strength, equivalent toughness and equivalent Young modulus) and the service life of the die in a high-temperature environment are obviously improved, the die can bear higher temperature and more severe working conditions, the maintenance or replacement frequency of the die is greatly reduced, the production cost is reduced, and the production efficiency is improved. Embodiments of the present invention also provide a mold that has excellent performance parameters and resistance to thermal stress, and is capable of withstanding higher temperatures and more severe operating conditions.
Drawings
The accompanying drawings are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate the invention and together with the embodiments of the invention, serve to explain the invention. In the drawings:
FIG. 1 illustrates a flow chart of a method of high temperature performance toughening of a mold according to one embodiment of the present invention;
FIG. 2a shows a schematic view of an alloy layer, conversion layer and surface coating formed on a mold according to one embodiment of the invention;
FIG. 2b shows a schematic diagram of crystallization of an alloy layer according to one embodiment of the invention;
FIG. 2c shows a schematic diagram of alloy layer precipitated crystals according to one embodiment of the invention;
FIG. 2d shows a schematic view of the formation of mineral bridges in the conversion layer by crystals precipitated from the alloy layer according to one embodiment of the invention;
FIG. 3 shows crystallization of a nickel-phosphorus alloy layer at different heat treatment temperatures and soak times;
FIG. 4 shows the growth of mineral bridges at different heat treatment temperatures and soak times;
FIG. 5 shows the effect of different heat treatment temperatures and soak times on the hardness, yield strength, tensile strength, young's modulus of the mold;
fig. 6 shows a schematic view of a mould according to an embodiment of the invention.
Detailed Description
Hereinafter, only certain exemplary embodiments are briefly described. As will be recognized by those of skill in the pertinent art, the described embodiments may be modified in various different ways without departing from the spirit or scope of the present invention. Accordingly, the drawings and description are to be regarded as illustrative in nature and not as restrictive.
In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", etc. indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings are merely for convenience in describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the present invention. Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first" or "a second" may explicitly or implicitly include one or more of the described features. In the description of the present invention, the meaning of "a plurality" is two or more, unless explicitly defined otherwise.
In the description of the present invention, it should be noted that, unless explicitly specified and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be fixedly connected, detachably connected, or integrally connected, and may be mechanically connected, electrically connected, or may communicate with each other, for example; can be directly connected or indirectly connected through an intermediate medium, and can be communicated with the inside of two elements or the interaction relationship of the two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art according to the specific circumstances.
In the present invention, unless expressly stated or limited otherwise, a first feature "above" or "below" a second feature may include both the first and second features being in direct contact, as well as the first and second features not being in direct contact but being in contact with each other through additional features therebetween. Moreover, a first feature being "above," "over" and "on" a second feature includes the first feature being directly above and obliquely above the second feature, or simply indicating that the first feature is higher in level than the second feature. The first feature being "under", "below" and "beneath" the second feature includes the first feature being directly above and obliquely above the second feature, or simply indicating that the first feature is less level than the second feature.
The following disclosure provides many different embodiments, or examples, for implementing different features of the invention. In order to simplify the present disclosure, components and arrangements of specific examples are described below. They are, of course, merely examples and are not intended to limit the invention. Furthermore, the present invention may repeat reference numerals and/or letters in the various examples, which are for the purpose of brevity and clarity, and which do not themselves indicate the relationship between the various embodiments and/or arrangements discussed. In addition, the present invention provides examples of various specific processes and materials, but one of ordinary skill in the art will recognize the application of other processes and/or the use of other materials.
The preferred embodiments of the present invention will be described below with reference to the accompanying drawings, it being understood that the preferred embodiments described herein are for illustration and explanation of the present invention only, and are not intended to limit the present invention.
Currently, researchers have proposed solutions to the performance problem of composite molds in high temperature environments, such as: a heat treatment method and a coating regulation method.
The heat treatment method mainly involves heat treatment of the composite mold at high temperature to improve its structure and performance, but its ability to control the thermal stress distribution is limited, and in a high temperature environment, the mold is still susceptible to complicated thermal stress distribution, leading to possible cracking, deformation and wear. Moreover, the heat treatment method generally involves the overall treatment of the composite mold, and precise regulation and control of different parts of the composite mold cannot be realized, which limits fine optimization of the high-temperature performance of the mold.
The coating regulation and control method focuses on selecting coating materials and adjusting the thickness of the coating to improve the high temperature resistance of the composite material die, but the optimization of the method is limited to the characteristics and the thickness of the selected materials, and cannot cope with the complicated thermal stress problem. Also, the coefficients of thermal expansion of the different materials are different, which may lead to uneven expansion and thermal stress in high temperature environments. In addition, some coating materials may degrade at extremely high temperatures, limiting the maximum operating temperature of the composite mold.
Therefore, the invention aims to provide a high-temperature performance toughening method of a die, which introduces the growth regulation of a mineral bridge, improves the high-temperature performance of the die, optimizes the equivalent strength, equivalent toughness and equivalent Young modulus of the die, improves the performance stability and service life of the die, reduces the maintenance and replacement cost, meets the severe requirements of industrial application on the performance of the composite material die in a high-temperature environment, and realizes larger industrial application potential.
Fig. 1 shows a flow chart of a method 100 for toughening a mold according to an embodiment of the present invention, and fig. 2a to 2d show schematic diagrams of the mold at different toughening stages according to an embodiment of the present invention, respectively, and are described in detail below in connection with fig. 1, 2a to 2 d.
As shown in FIG. 1, the high temperature performance toughening method 100 includes the following steps, each of which is described in detail below.
In step S110: an alloy layer is formed on at least a portion of the surface of the mold.
As shown in fig. 2a, the alloy layer 210 may be formed by depositing a corresponding alloy material on the surface of the mold by a deposition process such as physical vapor deposition, the alloy layer 210 may be a multiphase alloy layer such as a nickel alloy layer, a copper-zinc alloy layer, a copper-tin alloy layer, etc., and the material selection of the alloy layer 210 needs to consider the working temperature of the mold to ensure that the alloy layer 210 can be normally in service at the working temperature of the mold. The nickel alloy layer may be, for example, a nickel-phosphorus alloy layer, a nickel-chromium alloy layer, or a nickel-copper alloy layer, and the alloy layer 210 formed by different alloy materials may bring different characteristics to the mold, for example: the nickel-chromium alloy layer can improve the high temperature resistance of the die, and the nickel-copper alloy layer can improve the strength and the conductivity of the die.
In step S120: and forming a conversion layer on the surface of the alloy layer.
As shown in fig. 2a, the conversion layer 220 may be formed by depositing a corresponding material on the surface of the alloy layer 210 by a deposition process such as physical vapor deposition. The material selection of the conversion layer 220 requires consideration of the operating temperature of the mold to ensure that the conversion layer 220 can function properly at the operating temperature of the mold, and thus, the conversion layer 220 is generally formed using a metallic material. In addition, in order to bridge the difference in thermal expansion coefficients of the alloy layer 210 and the surface coating 230, attention needs to be paid to the thermal expansion coefficient of the material forming the conversion layer 220, ensuring that the thermal expansion coefficient of the conversion layer 220 is between the thermal expansion coefficient of the alloy layer 210 and the thermal expansion coefficient of the surface coating 230. The conversion layer 220 may be, for example, a titanium layer, a tungsten layer, a niobium layer, a chromium layer, or the like.
In step S130: a surface coating is formed on the surface of the conversion layer.
As shown in fig. 2a, the surface coating 230 may be formed by depositing a corresponding material on the surface of the conversion layer 220 by a deposition process such as physical vapor deposition. The surface coating 230 is used to enhance the performance (e.g., high temperature resistance, wear resistance, etc.) of the mold, and the material selection of the surface coating 230 also requires consideration of the mold operating temperature to ensure proper service of the surface coating at the mold operating temperature. The surface coating 230 may be, for example, a diamond-like carbon layer (DLC), a titanium nitride layer, a titanium carbon nitride layer, a titanium aluminum nitride layer, or the like.
In step S140: and (5) raising the temperature of the die and preserving the heat for a preset time.
In particular embodiments, the temperature of the mold may be raised above the crystallization temperature of the alloy layer, but it is also undesirable to raise the mold to too high a temperature so as not to damage the alloy layer, conversion layer, and/or surface coating. Preferably, the temperature of the mold (heat treatment temperature) does not exceed 15% of the crystallization temperature of the alloy layer. As shown in fig. 2b, a local heating device (e.g., a crawler heater, etc.) may be used to heat a portion of the mold where the coating (alloy layer, conversion layer, surface coating) is disposed, or the mold may be placed into an integral heating device (e.g., a heating furnace) to perform integral heating, or other manners or devices may be used to perform integral heating or local heating on the mold, which is not limited by the present invention. When the temperature of the die is raised, the heating temperature of the heating equipment can be gradually raised so as to gradually raise the temperature of the die and reduce the gradient of thermal stress, thereby reducing stress concentration.
Under the high-temperature environment, the alloy layer can be crystallized (the process of converting amorphous substances into crystals), and the structure of the alloy layer is obviously improved as a result of crystallization, so that the alloy layer is more regular and firm, and simultaneously has high-temperature resistance, thereby providing a more reliable foundation for the application of the die under the high-temperature environment. As shown in fig. 2c and 2d, the alloy layer 210 may fully crystallize above the crystallization temperature and precipitate crystals, wherein the precipitated crystals may penetrate into the conversion layer 220 and these crystals may interact with the material (e.g., titanium) in the conversion layer 220, which may promote crystal growth in the conversion layer and form the mineral bridge 240. The mineral bridge 240 is a nano-scale pillar vertically distributed between the alloy layer 210 and the surface coating 230, presented in the form of a small crystal structure, and the mineral bridge 240 exhibits a variety in size and shape (possibly different crystal sizes and different shapes) that reveals the complexity of the growth process of the mineral bridge 240, as well as the variety of features formed at different locations and conditions. The mineral bridge 240 can firmly connect the alloy layer 210, the conversion layer 220 and the surface coating 230, improves the capability of the die against thermal stress, improves the stability of the die in a high-temperature environment, improves the equivalent strength, the equivalent toughness and the equivalent Young modulus of the die, enables the die to bear higher temperature and more severe working conditions, greatly reduces the frequency of die maintenance or replacement, and is beneficial to reducing the production cost and improving the production efficiency.
The heat treatment temperature and the heat preservation time of the die have obvious influence on the crystallization condition of the alloy layer. Fig. 3 shows crystallization of the nickel-phosphorus alloy layer at various heat treatment temperatures and soak times for illustration. As shown in fig. 3, the crystallization degree of the nickel-phosphorus alloy layer is different under different heat treatment temperatures and heat preservation time, the formed crystal structure is different, and the size of the crystal grains is different; wherein, the higher the heat treatment temperature is, the faster the crystallization speed of the alloy layer is; the higher the heat treatment temperature is, the longer the heat preservation time is, and the larger the size of the formed crystal grains is; thus, the alloy layer can form a required crystal structure (such as a crystal with a crystal wall) by carefully controlling the heat treatment temperature and the heat preservation time, thereby providing a good foundation for the growth of mineral bridges.
The heat treatment temperature and the heat preservation time of the die also have significant influence on the growth condition of the mineral bridge, for example, the higher the heat treatment temperature is, the faster the mineral bridge grows, the longer the heat preservation time is, and the higher the density of the mineral bridge is. Fig. 4 shows the growth of mineral bridges at different heat treatment temperatures and holding times, and fig. 5 shows the effect of different heat treatment temperatures and holding times on hardness, yield strength, tensile strength, young's modulus of the mold, for illustration, wherein the alloy layer is a nickel-phosphorus alloy layer, the conversion layer is a titanium layer, and the surface coating is a diamond-like layer. As shown in fig. 4, at different heat treatment temperatures and holding times, the mineral bridges are distributed differently in the conversion layer, and the mineral bridges have different intensities; wherein, under different heat treatment temperatures (the heat preservation time is the same), the distribution density of the mineral bridge is in an ascending trend along with the rise of the heat treatment temperature, and the strength of the mineral bridge is in a trend of ascending and then descending; under different heat preservation time (the heat treatment temperature is the same), the distribution density of the mineral bridge is in an ascending trend along with the extension of the heat preservation time, the strength of the mineral bridge is gradually increased, and then the mineral bridge is stable. As shown in fig. 4 and 5, the distribution (distribution density) and strength of the mineral bridge have a remarkable influence on the capability of resisting thermal stress of the die and the equivalent strength, equivalent toughness and equivalent young's modulus of the die, so that the heat treatment temperature and the heat preservation time can be carefully regulated according to the actual working condition of the die to obtain the most suitable mineral bridge distribution and strength, so that the die achieves the performance parameters of the composite working condition and the capability of resisting thermal stress, and the performance stability and the service life of the die are improved.
Under the high-temperature working environment, different parts of the die can be subjected to the same or different degrees of thermal stress, so that the different parts of the die can be lifted to the same or different temperatures according to the thermal stress distribution condition of the die under the high-temperature working environment, and/or the different parts of the die are insulated for the same or different times, so that proper mineral bridge distribution and strength are formed at each part of the die, and the different parts of the die have the capability of resisting the corresponding thermal stress. Specifically, under a high-temperature working environment, if different parts of the die have similar thermal stress distribution, the integral heating equipment can be used for lifting different parts of the die to the same temperature, and the same time is kept for heat preservation, so that the whole die is uniformly heated, and the temperature gradient is reduced; if different parts of the die have different thermal stress distribution, local heating equipment can be used for corresponding heat treatment temperature and heat preservation time of different parts of the die, so that different parts of the die have the capability of resisting corresponding thermal stress, stress concentration is reduced, and the service life of the die is prolonged.
The different parts of the mould may need the same or different performance characteristics, and therefore, the different parts of the mould may be raised to the same or different temperatures and/or the same or different times may be maintained for the different parts of the mould according to the hardness, strength, toughness and/or young's modulus to be achieved by the different parts of the mould, so as to form suitable mineral bridge distribution and strength at each part of the mould to achieve the required performance.
Compared with the prior art, the high-temperature performance toughening method of the die provided by the invention has the advantages that the alloy layer, the conversion layer and the surface coating are sequentially arranged on at least part of the surface of the die, and the growth regulation and control of a mineral bridge are introduced, so that more accurate and comprehensive thermal stress control is realized, the capability of the die against thermal stress can be effectively improved, the stability and performance parameters and service life of the die in a high-temperature environment are obviously improved, the performance of the die in the high-temperature environment is crucial, and because the higher strength and the better toughness are provided, the die can bear higher temperature and more severe working conditions, the maintenance or replacement frequency of the die is greatly reduced, the production cost is reduced, and the production efficiency is improved.
Fig. 6 shows a schematic view of a mould according to an embodiment of the invention, described in detail below in connection with fig. 6.
As shown in fig. 6, the mold includes a mold base 250, an alloy layer 210, a conversion layer 220, and a surface coating 230. Wherein the alloy layer 210 is formed on at least a portion of the surface of the mold base 250, the conversion layer 220 is formed on the surface of the alloy layer 210, the surface coating 230 is formed on the surface of the conversion layer 220, the surface coating 230 is used for enhancing the performance (such as high temperature resistance, wear resistance, etc.) of the mold, the thermal expansion coefficient of the conversion layer 220 is between the thermal expansion coefficient of the alloy layer 210 and the thermal expansion coefficient of the surface coating 230, and the conversion layer 220 has a mineral bridge 240 formed by the crystallized crystals of the alloy layer 210.
According to one embodiment of the present invention, as shown in fig. 6, the alloy layer 210 may be a multi-phase alloy layer such as a nickel alloy layer, a copper-zinc alloy layer, a copper-tin alloy layer, etc., and the material selection of the alloy layer 210 needs to consider the working temperature of the mold to ensure that the alloy layer 210 can be normally used at the working temperature of the mold. The nickel alloy layer may be for example a nickel-phosphorus alloy layer, a nickel-chromium alloy layer or a nickel-copper alloy layer or the like,
according to one embodiment of the present invention, as shown in fig. 6, the conversion layer 220 may be a titanium layer, a tungsten layer, a niobium layer, a chromium layer, or the like.
According to one embodiment of the present invention, as shown in FIG. 6, the surface coating 230 may be a diamond-like carbon (DLC), titanium nitride, titanium carbon nitride, titanium aluminum nitride, or the like.
Finally, it should be noted that: the foregoing description is only a preferred embodiment of the present invention, and the present invention is not limited thereto, but it is to be understood that modifications and equivalents of some of the technical features described in the foregoing embodiments may be made by those skilled in the art, although the present invention has been described in detail with reference to the foregoing embodiments. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (16)
1. A high-temperature performance toughening method of a die comprises the following steps:
forming an alloy layer on at least part of the surface of the die;
forming a conversion layer on the surface of the alloy layer;
forming a surface coating on the surface of the conversion layer;
raising the temperature of the die and preserving heat for a preset time to crystallize the alloy layer and separate out crystals into the conversion layer to form a mineral bridge;
wherein the coefficient of thermal expansion of the conversion layer is between the coefficient of thermal expansion of the alloy layer and the coefficient of thermal expansion of the surface coating.
2. The high temperature performance toughening method according to claim 1, wherein the step of raising the temperature of the mold and maintaining the temperature for a preset time includes:
and raising the temperature of the die to above the crystallization temperature of the alloy layer.
3. The high temperature performance toughening method according to claim 2, wherein different parts on the die are raised to the same or different temperatures, and the temperatures are determined according to the thermal stress distribution condition of the die.
4. A high temperature performance toughening process according to claim 3 wherein the temperature is also determined based on the hardness, strength, toughness and/or young's modulus to be achieved at different locations on the mould.
5. The high temperature performance toughening method according to any one of claims 1 to 4, wherein the step of raising the temperature of the mold and maintaining the temperature for a preset time includes:
gradually increasing the temperature of the mold.
6. The high temperature performance toughening method according to claim 1, wherein the step of raising the temperature of the mold and maintaining the temperature for a preset time includes:
and preserving heat for different parts on the die for the same or different time, wherein the heat preservation time is determined according to the thermal stress distribution condition of the die.
7. The high temperature performance toughening method of claim 6 wherein the hold time is further determined based on hardness, strength, toughness and/or young's modulus to be achieved at different locations on the mold.
8. The high temperature performance toughening method according to claim 1, wherein the alloy layer is a nickel alloy layer, a copper-zinc alloy layer or a copper-tin alloy layer.
9. The high temperature performance toughening method according to claim 8, wherein the nickel alloy layer is a nickel-phosphorus alloy layer, a nickel-chromium alloy layer or a nickel-copper alloy layer.
10. The high temperature performance toughening method according to claim 1, wherein the surface coating is a diamond-like layer, a titanium nitride layer, a titanium carbon nitride layer or a titanium aluminum nitride layer.
11. The high temperature performance toughening method according to claim 1, wherein the conversion layer is a titanium layer, a tungsten layer, a niobium layer or a chromium layer.
12. A mold, comprising:
a mold base;
an alloy layer formed on at least a portion of a surface of the mold;
a conversion layer formed on the surface of the alloy layer; and
a surface coating layer formed on the surface of the conversion layer;
the thermal expansion coefficient of the conversion layer is between that of the alloy layer and that of the surface coating, and mineral bridges formed by crystals crystallized and separated out from the alloy layer are arranged in the conversion layer.
13. The mold of claim 12, wherein the alloy layer is a nickel alloy layer, a copper-zinc alloy layer, or a copper-tin alloy layer.
14. The mold of claim 13, wherein the nickel alloy layer is a nickel-phosphorus alloy layer, a nickel-chromium alloy layer, or a nickel-copper alloy layer.
15. The mold of claim 12, wherein the surface coating is a diamond-like layer, a titanium nitride layer, a titanium carbon nitride layer, or a titanium aluminum nitride layer.
16. The mold of claim 12, wherein the conversion layer is a titanium layer, a tungsten layer, a niobium layer, or a chromium layer.
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040051026A1 (en) * | 2002-09-18 | 2004-03-18 | Flynn Robert William | Mold core coating |
| CN102167495A (en) * | 2010-12-30 | 2011-08-31 | 江苏凯轮光学仪器有限公司 | Novel die making method for hot pressure forming of aspheric glass lens |
| CN102676778A (en) * | 2012-06-15 | 2012-09-19 | 株洲春华实业有限责任公司 | Strengthening and toughening thermal treatment method for hot-forging die of wearing plate |
| CN104995339A (en) * | 2013-01-15 | 2015-10-21 | 萨夫罗克有限公司 | Method for producing a chromium coating on a metal substrate |
| CN204817678U (en) * | 2015-03-25 | 2015-12-02 | 苏州涂冠镀膜科技有限公司 | Tensile mould of metal |
| KR20170117290A (en) * | 2016-04-12 | 2017-10-23 | 조선대학교산학협력단 | Hot-working die with damage diminution layer |
| CN108044079A (en) * | 2017-12-22 | 2018-05-18 | 西安交通大学 | A kind of high-strength alloy and heat-stable ceramic laminated coating die casting and preparation method thereof |
-
2023
- 2023-12-04 CN CN202311639896.3A patent/CN117364079B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040051026A1 (en) * | 2002-09-18 | 2004-03-18 | Flynn Robert William | Mold core coating |
| CN102167495A (en) * | 2010-12-30 | 2011-08-31 | 江苏凯轮光学仪器有限公司 | Novel die making method for hot pressure forming of aspheric glass lens |
| CN102676778A (en) * | 2012-06-15 | 2012-09-19 | 株洲春华实业有限责任公司 | Strengthening and toughening thermal treatment method for hot-forging die of wearing plate |
| CN104995339A (en) * | 2013-01-15 | 2015-10-21 | 萨夫罗克有限公司 | Method for producing a chromium coating on a metal substrate |
| CN204817678U (en) * | 2015-03-25 | 2015-12-02 | 苏州涂冠镀膜科技有限公司 | Tensile mould of metal |
| KR20170117290A (en) * | 2016-04-12 | 2017-10-23 | 조선대학교산학협력단 | Hot-working die with damage diminution layer |
| CN108044079A (en) * | 2017-12-22 | 2018-05-18 | 西安交通大学 | A kind of high-strength alloy and heat-stable ceramic laminated coating die casting and preparation method thereof |
Non-Patent Citations (1)
| Title |
|---|
| 孙德勤;: "模具表面涂层技术的应用与发展", 铸造技术, no. 01, 18 January 2011 (2011-01-18), pages 114 - 117 * |
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