CN107109535A - Adonic containing manganese - Google Patents

Adonic containing manganese Download PDF

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Publication number
CN107109535A
CN107109535A CN201680003506.5A CN201680003506A CN107109535A CN 107109535 A CN107109535 A CN 107109535A CN 201680003506 A CN201680003506 A CN 201680003506A CN 107109535 A CN107109535 A CN 107109535A
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CN
China
Prior art keywords
product
alloy
manganese
amount
nickel
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Pending
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CN201680003506.5A
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Chinese (zh)
Inventor
W·雷蒙德·克里布
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Materion Corp
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Materion Corp
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Publication of CN107109535A publication Critical patent/CN107109535A/en
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    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C9/00—Alloys based on copper
    • C22C9/06—Alloys based on copper with nickel or cobalt as the next major constituent
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D1/00—General methods or devices for heat treatment, e.g. annealing, hardening, quenching or tempering
    • C21D1/06—Surface hardening
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D1/00—General methods or devices for heat treatment, e.g. annealing, hardening, quenching or tempering
    • C21D1/18—Hardening; Quenching with or without subsequent tempering
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D8/00—Modifying the physical properties by deformation combined with, or followed by, heat treatment
    • C21D8/02—Modifying the physical properties by deformation combined with, or followed by, heat treatment during manufacturing of plates or strips
    • C21D8/0221—Modifying the physical properties by deformation combined with, or followed by, heat treatment during manufacturing of plates or strips characterised by the working steps
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D8/00—Modifying the physical properties by deformation combined with, or followed by, heat treatment
    • C21D8/02—Modifying the physical properties by deformation combined with, or followed by, heat treatment during manufacturing of plates or strips
    • C21D8/0247—Modifying the physical properties by deformation combined with, or followed by, heat treatment during manufacturing of plates or strips characterised by the heat treatment
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D8/00—Modifying the physical properties by deformation combined with, or followed by, heat treatment
    • C21D8/06—Modifying the physical properties by deformation combined with, or followed by, heat treatment during manufacturing of rods or wires
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D8/00—Modifying the physical properties by deformation combined with, or followed by, heat treatment
    • C21D8/10—Modifying the physical properties by deformation combined with, or followed by, heat treatment during manufacturing of tubular bodies
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D9/00—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor
    • C21D9/0081—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor for slabs; for billets
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D9/00—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor
    • C21D9/08—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor for tubular bodies or pipes
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D9/00—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor
    • C21D9/46—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor for sheet metals
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D9/00—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor
    • C21D9/52—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor for wires; for strips ; for rods of unlimited length
    • C—CHEMISTRY; METALLURGY
    • C21—METALLURGY OF IRON
    • C21D—MODIFYING THE PHYSICAL STRUCTURE OF FERROUS METALS; GENERAL DEVICES FOR HEAT TREATMENT OF FERROUS OR NON-FERROUS METALS OR ALLOYS; MAKING METAL MALLEABLE, e.g. BY DECARBURISATION OR TEMPERING
    • C21D9/00—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor
    • C21D9/52—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor for wires; for strips ; for rods of unlimited length
    • C21D9/525—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor for wires; for strips ; for rods of unlimited length for wire, for rods
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C9/00—Alloys based on copper
    • C22C9/02—Alloys based on copper with tin as the next major constituent
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C9/00—Alloys based on copper
    • C22C9/05—Alloys based on copper with manganese as the next major constituent
    • 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
    • C22F1/08—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of copper or alloys based thereon

Abstract

A kind of adonic, the manganese containing about 1.9wt% to about 21wt%.

Description

Copper-nickel-tin alloy containing manganese
The cross reference of related application
This application claims the preferential of the U.S. Provisional Patent Application submitted on March 18th, 2015 the 62/134,731st Power, entire contents are incorporated herein by reference.
Background technology
The present invention relates to copper-ni-sn-manganese alloy.
Copper alloy for oil exploration and production necessarily exhibits high impact toughness (for example, at least 20ft-lbs).In smelting In the study of the Chinese classic, term " toughness " refers to that alloy absorbs energy and the ability being plastically deformed in the case of without fracture.Therefore, it is tough Property needs the balance of intensity and ductility.Alloy may also be exposed to Corrosive Materia such as hydrogen sulfide (H2S) and hostile environment, such as High bearing wear and friction.Hydrogen sulfide is a kind of colourless gas, the stink with similar rotten egg.Except with high corrosion Outside property, hydrogen sulfide is heavier than air, and has severe toxicity, inflammable, explosive.In addition, aircraft landing system is needed during take-off and landing There is high resistance to low velocity, high capacity sliding axle load.
Need new alloy of the exploitation with high impact toughness, corrosion resistance and resistance to bearing wear and friction.
The content of the invention
The present invention relates to copper-ni-sn-manganese alloy.The alloy show high impact toughness and it is good corrosion-resistant, wear-resisting and Rub resistance, specifically, these characteristics can be strengthened by manufacturing deformation (cold working).
A kind of alloy for including the manganese of copper, nickel, tin and about 1.9wt% to about 20wt% is disclosed in embodiment.
In certain embodiments, the amount of nickel is about 5wt% to about 25wt%, and/or the amount of tin is about 5wt% to about 10wt%.
The amount of manganese can be about 1.9wt% to about 10wt%, including about 1.9wt% to about 5wt%, about 1.9wt% are to about 2wt% and about 2.0wt% are to about 10wt%.
Other embodiments disclose the product for including copper-ni-sn-manganese alloy.Amount of the manganese in the alloy be About 1.9wt% to about 20wt%.
The product can selected from bushing, Instrument shell, connector, centralizer, fastener, drill collar, for plastics forming Mould, welding arm, electrode and certified ingot (certified ingot).
In certain embodiments, the product is banding, bar-shaped, strip, tubulose or tabular.
The alloy can include about 5wt% to about 25wt% nickel and about 5wt% to about 10wt% tin.
Alternatively, the product has at least one size more than about 5 inches.
The product can be aircraft landing system or its part.
Further embodiment discloses the method for preparing product.Methods described includes providing a kind of copper-nickel-tin alloy；And And based on the gross weight of the product, 0.2-20wt% manganese is added into copper-nickel-tin alloy.
Alternatively, methods described also includes carrying out cold working to the product.
In certain embodiments, the amount of nickel described in the product is about 5wt% to about 25wt%, and/or the product Described in tin amount described in the amount of product be about 5wt% to about 10wt%.
The amount of the manganese be about 0.2wt% to about 10wt%, including about 0.2wt% to about 5wt%, about 0.2wt% is to about 2wt%, and about 0.2wt% to about 1.9wt%.
These and other non-limiting features of the present invention are discussed further below.
Brief description of the drawings
It is the brief description of accompanying drawing below, the purpose is to illustrate embodiment disclosed herein, rather than is used for Limit its scope.
Fig. 1 is the flow chart for the illustrative methods for representing the disclosure.
Embodiment
Part disclosed herein, process and device can be more completely understood for refer to the attached drawing.These accompanying drawings are only to show The surface of meaning property, is in order that the presentation for obtaining the disclosure is more convenient and simple, therefore does not show wherein equipment or part deliberately Relative size and size, and/or do not define or limit the scope of exemplary embodiment.
For the sake of clarity, concrete term has been used in describing below, but these terms are only used for example in reference figure The specific structure of property embodiment, does not define or limit the content of the invention.In the the accompanying drawings and the following description, it is to be understood that The intimate part of similar numerals.
Singulative " one " and it is " described " include plural referents, unless the context clearly determines otherwise.
Numerical value in the description and claims of this application should be understood to include：When being reduced to having for identical digit Numerical value as identical numerical value during effect numeral, although and being less than herein described be used for different from the numerical value of above-mentioned record Determine the numerical value of the experimental error of the conventional measurement technology of numerical value.
Number range disclosed herein includes the end points and can be independently combinable (for example, the scope bag of " 2 grams to 10 grams " Include 2 grams and 10 grams of end points, and all medians).The end points and any value of number range disclosed herein are not limited to accurately Scope or value；These scopes and value are substantially and inaccurate, it may include the value approximate with these scopes and/or value.
The value modified by the term such as " about " and " substantially " can be not limited to the exact value specified.Represent approximate situation Language can correspond to the precision of the instrument for measuring the value.Modifier " about " should also be considered as open by the exhausted of two end points To the scope of value definition.For example, " about 2 to about 4 " statement also discloses that the scope of " from 2 to 4 ".
Herein, term " rotation nodular alloy " refers to its chemical composition so as to undergo the alloy of spinodal decomposition. Term " rotation nodular alloy " refers to alloy, rather than physical state.Therefore, " rotation nodular alloy " may have been subjected to or can It can be decomposed without experience rotation nodular, and during being likely to be at or being not at spinodal decomposition.
Fig. 1 shows the illustrative methods 100 for article of manufacture.Methods described 100 includes：Melt copper-nickel-tin alloy Change 110；Based on the gross weight of product 120,0.2-20wt% manganese is added into the copper-nickel-tin alloy；Casting alloy 125； Alternatively, solution annealing 130；Alternatively, cold working 140 is carried out to product；And alternatively, heat treated article 150.
Copper-the nickel-tin alloy can be rotation nodular alloy.
After the copper, nickel and tin that prepare a collection of proper proportion, its combination of fusing 110.It is described fusing 110 can with expectation The gas combustion of cured product geometric dimensions matching, carry out in electric induction or electric arc furnaces.Generally, fusion temperature is at least about 2057 ° F, overheat depends on casting technique, and in the range of 150 to 400 °F.
The addition 120 of manganese can by least about 2100 °F, preferably within the temperature range of about 2200 to about 2350 °F, Manganese is melted in melt.
Next, the alloy is cast 125.The casting of alloy can be carried out after melting temperature is stable, be led to simultaneously Appropriate overheat is crossed, continuous casting ingot or shape is processed into.In addition, casting can also be used to prepare ingot, semi-finished product, near net portion Part, shot-peening, pre-alloyed powder or other discrete forms.
In certain embodiments, some magnesium are added during the fusing 110, addition 120 and/or solution annealing 130, with Low-alloyed oxygen content drops.The magnesia of formation can be removed from alloy block.
Intensity can also be improved by processing hardening (for example, cold working 140) and/or rotation section Ageing Treatment.These are special Levy and improve overall strength-ductility, while other performance is improved, such as intensity-impact flexibility, corrosion resistance and bearing matter Amount.
Cold working is by being plastically deformed come reinforced metal.Generally at a temperature of less than its recrystallization temperature extruding, it is curved It is bent, stretch or shear the metal and can realize the effect.For example, the alloy can be hammered, stretched and otherwise shape Into.This cold working process can increase hardness, yield strength and/or the tensile strength of the product formed by the alloy.
The mechanism of rotation section timeliness/decomposition is that multiple components are separated into the not same district with different chemical compositions and physical property Domain or micro-structural.What the crystal that particularly there is body phase to constitute in the central area of phasor underwent goes out molten process.The present invention's Spinodal decomposition at the surface of the alloy causes Surface hardened layer.
The spinodal structure of heat treatment keeps original geometry, and because atomic size is similar, the product is in warm It is indeformable during processing.
Copper-the nickel-tin alloy can be rotation nodular alloy.In most cases, rotation nodular alloy is in their phase Exception, referred to as compatibility gap are shown in figure.Within the temperature range of the relative narrower in the compatibility gap, atomic arrangement Occur in existing lattice structure.Resulting two phase structure is stable at a temperature of significantly lower than the gap.
Copper-ni-sn rotation nodular alloy shows such as high intensity, excellent tribological property in seawater and sour environment And the beneficial characteristics such as highly corrosion resistant.The increase of the yield strength of base metals may be by the rotation in the copper-nickel-tin alloy Nodel line, which is decomposed, to be caused.
Compared with conventional high-performance ferrous iron, nickel and titanium alloy, copper alloy has very high conduction and thermal conductivity.Tradition Copper alloy be rarely used in the application higher to hardness requirement.However, copper-ni-sn rotation nodular alloy is in hardening casting and forges High rigidity and high conductivity are respectively provided with the conditions of making.
Inert gas (e.g., including argon and/or carbon dioxide/carbon monoxide) can be used and/or protectiveness lid is used (such as vermiculite, aluminum oxide and/or graphite) keeps the neutral or reducing condition to protect oxidable element.
Active metal, such as magnesium, calcium, beryllium and/or tungsten, to ensure the dissolving of low concentration can be added after incipient melting Oxygen.
After melting temperature is stabilized by appropriate overheat, blank, the part of continuously casting are formed by casting Or shot-peening.
Alternatively, at a temperature of about 1350 to about 1625 °F, the solution annealing 130 of about 1 to about 12 hour is carried out.
Cold working 140, which refers to be less than under recrystallization temperature, deforms metal machinery.When deflection increase, the metal becomes Deformation must be more difficult to.In other words, material is processing hardening or strain hardening.This step is optional.
It is optionally possible to further strengthen the metal by heat treatment 150.In certain embodiments, the heat treatment About 1 to about 8 hour is reheated within the temperature range of being included in about 600 to about 950 °F to be hardened.
The amount of the nickel can be about 5wt% to about 25wt%, including about 10wt% is to about 20wt% and about 15wt%.More In specific embodiment, the amount of the nickel can be about 8wt% to about 16wt%, about 14wt% to about 16wt%, and about 8wt% is to about 10wt%, or about 10wt% to about 12wt%.
The amount of the tin can be about 5wt to about 10wt%, including about 6wt% to about 9wt% and about 7wt% to about 8wt%. In more specifically embodiment, the amount of the tin can be about 5wt% to about 9wt%, or about 7wt% is to about 9wt%, or about 5wt% to about 7wt%.
The amount of the manganese can be at least about 0.2wt%, including at least about 0.5wt%, at least about 1wt% and at least about 1.5wt%.In more specifically embodiment, the amount of the manganese can be at least 4wt%, and at least 5wt%, about 4wt% are to about 12wt%, about 5wt% are to about 21wt%, and about 16wt% is to about 21wt%, or about 19wt% to about 21wt%.In some embodiments In, the amount at most 10wt% of the manganese, including at most 5wt%, at most at most 3wt%, at most 2wt%, 1.9wt%, at most 1.8wt%, at most 1.7wt%, at most 1.6wt%, and at most 1.5wt%.
In certain embodiments, the copper-ni-sn-manganese alloy contains about 7wt% to about 9wt% nickel peace treaty 5wt% to about 7wt% tin.These embodiments also will contain about 0.2wt% to about 21wt% manganese, and surplus is copper.Can be special It is contemplated that these embodiments can contain about 5wt% to about 21wt%, about 16wt% is to about 21wt%, or about 19wt% is to about 21wt% manganese, surplus is copper.
In other specific embodiments, the copper-ni-sn-manganese alloy contains about 14wt% to about 16wt% nickel peace treaty 7wt% to about 9wt% tin.These embodiments also will contain about 0.21wt% to about 21wt% manganese, and surplus is copper.Can be special It is contemplated that these embodiments can contain about 5wt% to about 21wt%, about 16wt% is to about 21wt%, or about 19wt% is to about 21wt% manganese, surplus is copper.
The alloy can also include one or more other metals, such as beryllium, chromium, silicon, molybdenum, iron and zinc.
In certain embodiments, the copper alloy contains about 1wt% to about 5wt% beryllium.
The copper alloy can contain about 0.7wt% to about 6wt% cobalt.
In a particular embodiment, the alloy includes about 2wt% beryllium and about 0.3wt% cobalt.
In other embodiments, the alloy can contain about 5wt% to about 7wt% beryllium.
Amount of the chromium in the alloy is that, less than about 5wt%, including about 0.5wt% is to about 2.0wt% peace treaties 0.6wt% to about 1.2wt%.
The product can be strip, bar-shaped, banding, tubulose or tabular.
In certain embodiments, the product is bushing, Instrument shell, connector, centralizer, fastener, drill collar, is used for Mould, welding arm, electrode, cast member (cast component) or the certified ingot of plastics forming.The product can be with It is aircraft landing system or its part.
It should be appreciated that above disclosure and further feature and the variant of function or its alternative solution can be combined Into many other different systems or application.Various unpredictable at present or meaning can be carried out behind those skilled in the art Alternative solution, modification, change or improvement outside material, these schemes are still covered by appended claims.

Claims (20)

1. a kind of alloy, includes copper, nickel, tin and about 1.9wt% to about 21wt% manganese.
2. alloy according to claim 1, wherein the amount of the nickel is about 5wt% to about 25wt%.
3. alloy according to claim 1, wherein the amount of the tin is about 5wt to about 10wt%.
4. alloy according to claim 1, wherein the amount of the manganese is about 1.9wt% to about 10wt%.
5. alloy according to claim 1, wherein the amount of the manganese is about 1.9wt% to about 5wt%.
6. alloy according to claim 1, wherein the amount of the manganese is about 1.9wt% to about 2wt%.
7. alloy according to claim 1, wherein the amount of the manganese is about 2wt% to about 10wt%.
8. a kind of product for including copper-ni-sn-manganese alloy, wherein amount of the manganese in the alloy is about 1.9wt% to about 21wt%.
9. product according to claim 8, wherein the product be selected from bushing, it is Instrument shell, connector, centralizer, tight Firmware, drill collar, the mould for forming plastics, welding arm, electrode, cast member and certified ingot.
10. product according to claim 8, wherein the product is banding, bar-shaped, strip, tubulose or tabular.
11. product according to claim 8, wherein the alloy includes about 5wt% to about 25wt% nickel and about 5wt% To about 10wt% tin.
12. product according to claim 8, wherein at least one size of the product is greater than about 5 inches.
13. a kind of method for preparing product, including copper-nickel-tin alloy of manganese of the casting also containing 0.2wt% to 21wt% is to make The standby product.
14. method according to claim 13, in addition to cold working is carried out to the product.
15. method according to claim 13, be additionally included in using or without using it is cold worked under the premise of be heat-treated Make the product precipitation-hardening.
16. method according to claim 13, wherein amount of the nickel in the product is about 5wt% to about 25wt%；And amount of the wherein described tin in the product is about 5wt% to about 10wt%.
17. method according to claim 13, wherein amount of the manganese in the product is about 0.2wt% to about 10wt%.
18. method according to claim 13, wherein amount of the manganese in the product is about 0.2wt% to about 5wt%.
19. method according to claim 13, wherein amount of the manganese in the product is about 0.2wt% to about 2wt%.
20. method according to claim 13, wherein amount of the manganese in the product is about 0.2wt% to about 1.9wt%.
CN201680003506.5A 2015-03-18 2016-03-18 Adonic containing manganese Pending CN107109535A (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
US201562134731P 2015-03-18 2015-03-18
US62/134,731 2015-03-18
PCT/US2016/023109 WO2016149610A1 (en) 2015-03-18 2016-03-18 Copper-nickel-tin alloy with manganese

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EP (1) EP3271489A1 (en)
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WO (1) WO2016149610A1 (en)

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EP3656023A1 (en) * 2017-07-20 2020-05-27 Materion Corporation Electronic connectors with magnetic copper alloys
CN111719065B (en) * 2020-06-08 2021-11-16 广东中发摩丹科技有限公司 Cu-Ni-Sn-Si-Ag-P multi-element alloy foil and preparation method thereof
CN114196850B (en) * 2021-12-22 2022-08-23 宁波兴业盛泰集团有限公司 Low residual stress copper alloy for lead frame and preparation method thereof

Citations (1)

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Publication number Priority date Publication date Assignee Title
US20090317290A1 (en) * 2006-04-28 2009-12-24 Maher Ababneh Multicomponent Copper Alloy and Its Use

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Publication number Priority date Publication date Assignee Title
US4052204A (en) * 1976-05-11 1977-10-04 Bell Telephone Laboratories, Incorporated Quaternary spinodal copper alloys
JPH02225651A (en) * 1988-11-15 1990-09-07 Mitsubishi Electric Corp Manufacture of high strength cu-ni-sn alloy

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20090317290A1 (en) * 2006-04-28 2009-12-24 Maher Ababneh Multicomponent Copper Alloy and Its Use

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WO2016149610A1 (en) 2016-09-22
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US20160273078A1 (en) 2016-09-22
EP3271489A1 (en) 2018-01-24

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Application publication date: 20170829