CN115612888A - Thermal shock resistant copper alloy material for rocket engine and preparation method thereof - Google Patents

Thermal shock resistant copper alloy material for rocket engine and preparation method thereof Download PDF

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CN115612888A
CN115612888A CN202211174627.XA CN202211174627A CN115612888A CN 115612888 A CN115612888 A CN 115612888A CN 202211174627 A CN202211174627 A CN 202211174627A CN 115612888 A CN115612888 A CN 115612888A
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copper alloy
alloy material
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rocket engine
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喻吉良
李龙飞
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Shaanxi University of Science and Technology
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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
    • 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
    • C21D9/0075—Heat treatment, e.g. annealing, hardening, quenching or tempering, adapted for particular articles; Furnaces therefor for rods of limited length
    • 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
    • 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
    • C22F1/02—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working in inert or controlled atmosphere or vacuum
    • 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
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    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
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Abstract

The invention discloses a thermal shock resistant copper alloy material for a rocket engine and a preparation method thereof, belongs to the technical field of alloy preparation, and aims to solve the technical problem that the performance of the existing copper alloy material is sharply reduced after the existing copper alloy material is subjected to low-temperature and high-temperature thermal shock. The hot punching performance of the copper alloy is greatly improved through multi-element alloying of elements such as titanium, chromium, zirconium, tantalum, niobium, hafnium, lanthanum and the like and proper proportion, and the mechanical property and the heat conduction property of the alloy material subjected to cold-hot circulation are greatly improved through solid solution strengthening and aging strengthening; the copper alloy material prepared by the invention still has high strength and high heat conductivity after 10 heat cycles (-196 ℃ -500 ℃); the alloy material can be used in the fields of rocket engine combustion chamber inner wall and the like, and can also be widely applied in the fields of aviation, aerospace, atomic energy, electronic technology, steel and mechanical manufacturing and the like.

Description

Thermal shock resistant copper alloy material for rocket engine and preparation method thereof
Technical Field
The invention belongs to the technical field of alloy preparation, and particularly relates to a thermal shock resistant copper alloy material for a rocket engine and a preparation method thereof.
Background
High-strength high-conductivity copper alloy is a functional material with excellent physical and mechanical properties, its tensile strength is 2-10 times that of pure copper, its electric conductivity is 50% -95% of pure copper, and is generally higher than 80% IACS. The high-strength copper alloy has excellent physical and chemical properties, higher strength and good plasticity, and has the characteristics of oxidation resistance, fatigue resistance, creep resistance, no hydrogen embrittlement, stress relaxation resistance, stress corrosion resistance and the like. At present, the high-strength and high-conductivity copper alloy is mainly applied to the fields of electronic communication, high-speed rail transit, spot welding electrodes, lead frame materials, rocket engine combustion chamber inner walls and the like. The high-strength, high-conductivity and high-heat-resistance copper alloy is required to have higher heat-resistance temperature and high-temperature softening resistance on the basis of the original high-strength and high-conductivity copper alloy, namely to have better high-temperature structure stability and high-temperature mechanical property. The Cu-Cr-Zr alloy has good strength, hardness, electrical conductivity, thermal conductivity, high temperature softening resistance, high temperature creep property and low cycle fatigue property, is a high-strength high-conductivity alloy which is quite concerned at present, and can be applied to the fields of integrated circuit lead frames, resistance welding electrodes, electric locomotive overhead conductors, continuous casting machine crystallizers, contact materials, rocket engine thrust chamber inner wall materials and the like. As a Cu-Cr-Zr alloy is used as a future nuclear fusion reactor material, the traditional Cu-Cr-Zr alloy is difficult to meet the requirements of high tensile strength, high yield strength and low creep rate at 450 ℃, so that the development of a new generation of high-performance copper alloy material becomes a research hotspot. In a rocket engine, the performance of the existing copper alloy material is sharply reduced after the existing copper alloy material is subjected to low-temperature and high-temperature thermal shock, so that potential safety hazards are caused.
Disclosure of Invention
In order to overcome the defects of the prior art, the invention aims to provide a high-strength copper alloy material for a rocket engine and a preparation method thereof, which are used for solving the technical problem that the performance of the existing copper alloy material is sharply reduced after the existing copper alloy material is subjected to low-temperature and high-temperature thermal shock.
In order to achieve the purpose, the invention adopts the following technical scheme to realize the purpose:
the invention discloses a thermal shock resistant copper alloy material for a rocket engine, which comprises the following preparation raw materials in percentage by mass: 0.1 to 0.7 percent of Ti,0.1 to 1.0 percent of Cr, 0.06 to 0.6 percent of Zr, 0.1 to 0.9 percent of Ta, 2 to 30 percent of Nb, 0.1 to 0.5 percent of Hf, 0.01 to 0.09 percent of La and the balance of Cu.
The invention discloses a high-strength high-conductivity copper alloy material for a rocket engine, which comprises the following preparation raw materials in percentage by mass: 0.1 to 0.7 percent of Ti,0.1 to 1.0 percent of Cr, 2 to 30 percent of Nb, 0.1 to 0.5 percent of Hf, 0.01 to 0.09 percent of La and the balance of Cu.
The invention discloses a high-strength high-conductivity copper alloy material for a rocket engine, which comprises the following preparation raw materials in percentage by mass: 0.1 to 0.7 percent of Ti,0.1 to 1.0 percent of Cr, 2 to 30 percent of Nb, 0.1 to 0.5 percent of Hf and the balance of Cu.
The invention discloses a high-strength high-conductivity copper alloy material for a rocket engine, which comprises the following preparation raw materials in percentage by mass: 0.1 to 1.0 percent of Cr, 2 to 30 percent of Nb, 0.1 to 0.5 percent of Hf and the balance of Cu.
The invention discloses a thermal shock resistant copper alloy material for a rocket engine, which comprises the following preparation raw materials in percentage by mass: 2 to 30 percent of Nb, 0.1 to 0.5 percent of Hf and the balance of Cu.
The invention discloses a thermal shock resistant copper alloy material for a rocket engine, which comprises the following preparation raw materials in percentage by mass: 0.06-0.6% of Zr, 2-30% of Nb and the balance of Cu.
The invention discloses a thermal shock resistant copper alloy material for a rocket engine, which comprises the following preparation raw materials in percentage by mass: 0.06-0.6% of Zr, 0.1-0.9% of Ta, 2-30% of Nb, 0.1-0.5% of Hf and the balance of Cu.
The invention discloses a thermal shock resistant copper alloy material for a rocket engine, which comprises the following preparation raw materials in percentage by mass: 0.1 to 0.9 percent of Ta, 2 to 30 percent of Nb, 0.1 to 0.5 percent of Hf and the balance of Cu.
The invention discloses a thermal shock resistant copper alloy material for a rocket engine, which comprises the following preparation raw materials in percentage by mass: 0.06-0.6% of Zr, 0.1-0.9% of Ta, 2-30% of Nb and the balance of Cu.
The invention also discloses a preparation method of the thermal shock resistant copper alloy material for the rocket engine, which comprises the following steps:
s1: mixing the alloy elements of the preparation raw materials according to the mass percentage relationship, and then pressing into an electrode;
s2: placing the electrode in a vacuum electron beam melting furnace under vacuum degree of less than 3 × 10 -2 Smelting for 1-3 times under the condition of Pa to obtain a semi-finished product ingot; the current of the vacuum electron beam melting electron beam gun is 2.0A-3.0A, and the melting speed is 10 mm/min-30 mm/min;
s3: placing the electrode in a vacuum consumable arc furnace under vacuum degree of less than 5 × 10 -2 Smelting for 1-3 times under the condition of Pa to obtain a copper alloy ingot; the current of the vacuum consumable arc melting is 2KA to 8KA, and the melting voltage is 25V to 35V;
s4: carrying out solid solution treatment on the copper alloy cast ingot for 4-10h at the temperature of 800-1000 ℃;
s5: forging the copper alloy ingot after the solution treatment at the temperature of 700-900 ℃ to obtain a copper alloy bar blank:
s6: making the copper alloy bar blank in vacuum degree less than 2X 10 -2 Pa, and carrying out solid solution aging at the aging temperature of 400-600 ℃; forging the copper alloy bar blank subjected to the aging treatment at the temperature of 600-800 ℃ to obtain a copper alloy forging blank;
s7: the copper alloy forging stock is processed under the vacuum degree of less than 2 multiplied by 10 -2 And (3) carrying out solution aging under the condition of Pa, wherein the aging temperature is 400-600 ℃, and obtaining the heat-resistant and impact-resistant copper alloy material for the rocket engine.
Compared with the prior art, the invention has the following beneficial effects:
the invention discloses a thermal shock resistant copper alloy material for a rocket engine, which greatly improves the hot stamping property of the copper alloy through multi-element alloying of elements such as titanium, chromium, zirconium, tantalum, niobium, hafnium, lanthanum and the like and proper proportion, and greatly improves the mechanical property and the heat conducting property of the alloy material after cold and hot cycles through solid solution strengthening and aging strengthening; relevant experimental data prove that the copper alloy material prepared by the invention still has high strength and high heat conductivity after undergoing 10 thermal cycles (-196 ℃ -500 ℃), and still has good performance after undergoing low-temperature and high-temperature thermal shock; the alloy material can be used in the fields of rocket engine combustion chamber inner wall and the like, and can also be widely applied in the fields of aviation, aerospace, atomic energy, electronic technology, steel, mechanical manufacturing and the like.
The invention also discloses a preparation method of the thermal shock resistant copper alloy material for the rocket engine, compared with the prior art, the method has the advantages of short process flow, low energy consumption, simplicity, environmental protection and capability of realizing industrial scale production, and the material prepared by the method has the advantages of high purity, uniform and fine microstructure and stable performance, and has wide application prospect.
Drawings
FIG. 1 is a microstructure diagram of a thermal shock resistant copper alloy material for rocket motors prepared in example 1.
Detailed Description
To make the features and effects of the present invention comprehensible to those skilled in the art, general description and definitions are made below with reference to terms and expressions mentioned in the specification and claims. Unless defined otherwise, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention belongs. The theory or mechanism described and disclosed herein, whether correct or incorrect, should not limit the scope of the present invention in any way, i.e., the present disclosure may be practiced without limitation to any particular theory or mechanism.
All features defined herein as numerical ranges or percentage ranges, such as values, amounts, levels and concentrations, are for brevity and convenience only. Accordingly, the description of numerical ranges or percentage ranges should be considered to cover and specifically disclose all possible subranges and individual numerical values (including integers and fractions) within the range. In this document, unless otherwise specified, "comprising," including, "" having, "or similar terms, shall encompass the meaning of" consisting of 8230, 8230%, "consisting of" and "consisting essentially of 8230; \8230, consist of," e.g., "A comprising a" shall encompass the meaning of "A comprising a and the other" and "A comprising only a". In this context, for the sake of brevity, not all possible combinations of features in the various embodiments or examples are described. Therefore, as long as there is no contradiction between combinations of these technical features, any combinations of the technical features in the respective embodiments or examples may be made, and all possible combinations should be considered as the scope of the present specification.
The invention will be further illustrated with reference to the following specific examples. It should be understood that these examples are for illustrative purposes only and are not intended to limit the scope of the present invention. Further, it should be understood that various changes or modifications of the present invention may be made by those skilled in the art after reading the teaching of the present invention, and such equivalents may fall within the scope of the present invention as defined in the appended claims. In the description of the present invention and the following examples, "%" represents weight percent, "parts" represents parts by weight, and proportions represent weight ratios, unless otherwise specified.
Example 1
A preparation method of a thermal shock resistant copper alloy material for a rocket engine comprises the following steps:
the preparation raw materials of the thermal shock resistant copper alloy material for the rocket engine comprise the following components in percentage by mass: 0.1% of Ti0.1%, 0.1% of Cr0.1%, 2% of Nb, 0.1% of Hf0, 0.01% of La0, and the balance of Cu;
step 1: mixing the alloy elements of the preparation raw materials according to the mass percentage relationship, and then pressing into an electrode; step 2: will generate electricityPlacing the electrode in a vacuum electron beam melting furnace, and controlling the vacuum degree to be less than 3 multiplied by 10 -2 Smelting for 1 time under the condition of Pa to obtain a semi-finished product ingot; the current of the vacuum electron beam melting electron beam gun is 2.0A, and the melting speed is 10mm/min;
and step 3: placing the electrode in a vacuum consumable arc furnace under vacuum degree of less than 5 × 10 -2 Smelting for 1 time under the condition of Pa to obtain a copper alloy ingot; the current of the vacuum consumable arc melting is 2KA, and the melting voltage is 25V; and 4, step 4: carrying out solution treatment on the copper alloy cast ingot for 4-10h at the temperature of 800 ℃;
and 5: forging the copper alloy ingot subjected to the solution treatment at the temperature of 700 ℃ to obtain a copper alloy bar blank; step 6: making the copper alloy bar blank in vacuum degree less than 2X 10 -2 Carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 400 ℃; forging the copper alloy bar blank subjected to the aging treatment at the temperature of 600 ℃ to obtain a copper alloy forging blank; and 7: the copper alloy forging stock is processed under the vacuum degree of less than 2 multiplied by 10 -2 Pa, and aging at 400 ℃ to obtain the heat-resistant impact-resistant copper alloy material for the rocket engine.
The microstructure of the copper alloy material for the rocket engine prepared in the embodiment is shown in fig. 1, and it can be seen from fig. 1 that the coarse dendritic structures are completely crushed, the microstructure is uniform, and the reinforcing phase is uniformly distributed in the copper matrix. The prepared copper alloy material has fine and uniform crystal grains and is in an equiaxial shape.
The copper alloy material for the rocket engine prepared by the embodiment has the room temperature tensile strength of 852MPa and the elongation after fracture of 16 percent; the tensile strength at 500 ℃ is 321MPa, and the elongation after fracture is 19%; the room temperature thermal conductivity is 260W/m.K. After 10 thermal cycles (196 ℃ below zero to 500 ℃), the copper alloy material has the temperature tensile strength of 392MPa, the elongation after fracture of 10 percent, the tensile strength of 189MPa at 500 ℃, the elongation after fracture of 10 percent and the thermal conductivity of 230W/m.K to 246W/m.K. The copper alloy material prepared by the invention still has high strength and high heat conductivity after 10 heat cycles (-196 ℃ -500 ℃); the alloy material can be used in the fields of rocket engine combustion chamber inner wall and the like, and can also be widely applied in the fields of aviation, aerospace, atomic energy, electronic technology, steel and mechanical manufacturing and the like.
Example 2
A preparation method of a thermal shock resistant copper alloy material for a rocket engine comprises the following steps:
the preparation raw materials of the thermal shock resistant copper alloy material for the rocket engine comprise: 0.7% of Ti0.7%, 1.0% of Cr1.0%, 30% of Nb, 0.5% of Hf0, 0.09% of La0 and the balance of Cu;
step 1: mixing the alloy elements of the preparation raw materials according to the mass percentage relationship, and then pressing into an electrode; step 2: placing the electrode in a vacuum electron beam melting furnace under vacuum degree of less than 3 × 10 -2 Smelting for 3 times under the condition of Pa to obtain a semi-finished product ingot; the current of the vacuum electron beam melting electron beam gun is 3.0A, and the melting speed is 30mm/min;
and step 3: placing the electrode in a vacuum consumable arc furnace under vacuum degree of less than 5 × 10 -2 Smelting for 3 times under the condition of Pa to obtain a copper alloy ingot; the current of the vacuum consumable arc melting is 8KA, and the melting voltage is 35V; and 4, step 4: carrying out solution treatment on a copper alloy cast ingot for 10 hours at the temperature of 1000 ℃;
and 5: forging the copper alloy cast ingot subjected to the solution treatment at the temperature of 900 ℃ to obtain a copper alloy bar blank; step 6: making the copper alloy bar blank in vacuum degree less than 2X 10 -2 Carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 600 ℃; forging the copper alloy bar blank subjected to the aging treatment at the temperature of 800 ℃ to obtain a copper alloy forging blank;
and 7: the copper alloy forging stock is processed under the vacuum degree of less than 2 multiplied by 10 -2 And (3) carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 600 ℃, and obtaining the heat-resistant and impact-resistant copper alloy material for the rocket engine. The copper alloy material for the rocket engine prepared in the embodiment has the room-temperature tensile strength of 915MPa and the elongation after fracture of 21%; the tensile strength at 500 ℃ is 379MPa, and the elongation after fracture is 25%; the thermal conductivity at room temperature is 275W/m.K. After 10 heat cycles (196 ℃ below zero to 500 ℃), the copper alloy material has the temperature tensile strength of 493MPa, the elongation after fracture of 19 percent, the tensile strength of 237MPa at 500 ℃ and the elongation after fracture of 16 percent, and the heat conduction systemThe number was 246W/m.K.
Example 3
A preparation method of a thermal shock resistant copper alloy material for a rocket engine comprises the following steps:
the preparation raw materials of the thermal shock resistant copper alloy material for the rocket engine comprise: 0.4% of Ti0.4%, 0.55% of Cr0.55%, 16% of Nb, 0.3% of Hf0, 0.05% of La0 and the balance of Cu;
step 1: mixing the alloy elements of the preparation raw materials according to the relation of mass percentage, and then pressing into an electrode; step 2: placing the electrode in a vacuum electron beam melting furnace under the vacuum degree of less than 3 x 10 -2 Smelting for 2 times under the condition of Pa to obtain a semi-finished product ingot; the current of the vacuum electron beam melting electron beam gun is 2.5A, and the melting speed is 20mm/min;
and step 3: placing the electrode in a vacuum consumable arc furnace at a vacuum degree of less than 5 × 10 -2 Smelting for 2 times under the condition of Pa to obtain a copper alloy ingot; the current of the vacuum consumable arc melting is 5KA, and the melting voltage is 30V; and 4, step 4: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 5: forging the copper alloy cast ingot subjected to the solution treatment at the temperature of 800 ℃ to obtain a copper alloy bar blank; step 6: making the copper alloy bar blank in vacuum degree less than 2X 10 -2 Carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃; forging the copper alloy bar blank subjected to the aging treatment at the temperature of 700 ℃ to obtain a copper alloy forging blank;
and 7: the copper alloy forging stock is processed in vacuum degree less than 2 x 10 -2 And (3) carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃, and obtaining the heat-resistant and impact-resistant copper alloy material for the rocket engine. The copper alloy material for the rocket engine prepared by the embodiment has the room temperature tensile strength of 900MPa and the elongation after fracture of 19 percent; the tensile strength at 500 ℃ is 355MPa, and the elongation after fracture is 20%; the room temperature thermal conductivity coefficient is 263W/m.K. After 10 thermal cycles (196 ℃ below zero to 500 ℃), the tensile strength of the copper alloy material at the temperature of 406MPa, the elongation after fracture is 13%, the tensile strength at the temperature of 500 ℃ is 1957MPa, the elongation after fracture is 13%, and the heat conductivity coefficient is 237W/m.K.
Example 4
A preparation method of a thermal shock resistant copper alloy material for a rocket engine comprises the following steps:
the preparation raw materials of the thermal shock resistant copper alloy material for the rocket engine comprise: 0.1% of Ti0.1%, 0.1% of Cr0.1%, 2% of Nb, 0.1% of Hf0, and the balance of Cu;
step 1: mixing the alloy elements of the preparation raw materials according to the mass percentage relationship, and then pressing into an electrode; and 2, step: placing the electrode in a vacuum electron beam melting furnace under the vacuum degree of less than 3 x 10 -2 Smelting for 2 times under the condition of Pa to obtain a semi-finished product ingot; the current of the vacuum electron beam melting electron beam gun is 2.5A, and the melting speed is 20mm/min;
and 3, step 3: placing the electrode in a vacuum consumable arc furnace under vacuum degree of less than 5 × 10 -2 Smelting for 2 times under the condition of Pa to obtain a copper alloy ingot; the current of the vacuum consumable arc melting is 5KA, and the melting voltage is 30V; and 4, step 4: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 5: forging the copper alloy cast ingot subjected to the solution treatment at the temperature of 800 ℃ to obtain a copper alloy bar blank; step 6: making the copper alloy bar blank in vacuum degree less than 2X 10 -2 Pa, and carrying out solid solution aging at the aging temperature of 500 ℃; forging the copper alloy bar blank subjected to the aging treatment at the temperature of 700 ℃ to obtain a copper alloy forging blank; and 7: the copper alloy forging stock is processed in vacuum degree less than 2 x 10 -2 And (3) carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃, and obtaining the heat-resistant and impact-resistant copper alloy material for the rocket engine.
The copper alloy material for the rocket engine prepared by the embodiment has the room-temperature tensile strength of 859MPa and the elongation after fracture of 16 percent; the tensile strength at 500 ℃ is 327MPa, and the elongation after fracture is 20%; the thermal conductivity at room temperature is 265W/m.K. After 10 thermal cycles (196 ℃ below zero to 500 ℃), the copper alloy material has the temperature tensile strength of 433MPa, the elongation after fracture of 10-19%, the tensile strength of 225MPa at 500 ℃, the elongation after fracture of 15% and the thermal conductivity of 243W/m.K.
Example 5
A preparation method of a thermal shock resistant copper alloy material for a rocket engine comprises the following steps:
the preparation raw materials of the thermal shock resistant copper alloy material for the rocket engine comprise: 0.7% of Ti0.7%, 1.0% of Cr1.0%, 30% of Nb, 0.5% of Hf0, and the balance of Cu;
step 1: mixing the alloy elements of the preparation raw materials according to the mass percentage relationship, and then pressing into an electrode; step 2: placing the electrode in a vacuum electron beam melting furnace under the vacuum degree of less than 3 x 10 -2 Smelting for 2 times under the condition of Pa to obtain a semi-finished product ingot; the current of the vacuum electron beam melting electron beam gun is 2.5A, and the melting speed is 20mm/min;
and step 3: placing the electrode in a vacuum consumable arc furnace at a vacuum degree of less than 5 × 10 -2 Smelting for 2 times under the condition of Pa to obtain a copper alloy ingot; the current of the vacuum consumable arc melting is 5KA, and the melting voltage is 30V; and 4, step 4: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 5: forging the copper alloy cast ingot subjected to the solution treatment at the temperature of 800 ℃ to obtain a copper alloy bar blank; and 6: making the copper alloy bar blank be less than 2X 10 vacuum degree -2 Pa, and carrying out solid solution aging at the aging temperature of 500 ℃; forging the copper alloy bar blank subjected to the aging treatment at the temperature of 700 ℃ to obtain a copper alloy forging blank;
and 7: the copper alloy forging stock is processed under the vacuum degree of less than 2 multiplied by 10 -2 And (3) carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃, and obtaining the heat-resistant and impact-resistant copper alloy material for the rocket engine. The copper alloy material for the rocket engine prepared by the embodiment has the room temperature tensile strength of 901MPa and the elongation after fracture of 20 percent; the tensile strength at 500 ℃ is 359MPa, and the elongation after fracture is 22%; the room temperature thermal conductivity was 270W/m.K. After 10 thermal cycles (196 ℃ below zero to 500 ℃), the copper alloy material has the warm tensile strength of 429MPa, the elongation after fracture of 15 percent, the tensile strength of 217MPa at 500 ℃, the elongation after fracture of 15 percent and the thermal conductivity of 239W/m.K.
Example 6
A preparation method of a thermal shock resistant copper alloy material for a rocket engine comprises the following steps:
the preparation raw materials of the thermal shock resistant copper alloy material for the rocket engine comprise: 0.4% of Ti0.4%, 0.55% of Cr0.55%, 16% of Nb, 0.3% of Hf0, and the balance of Cu;
step 1: mixing the alloy elements of the preparation raw materials according to the mass percentage relationship, and then pressing into an electrode; step 2: placing the electrode in a vacuum electron beam melting furnace under vacuum degree of less than 3 × 10 -2 Smelting for 2 times under the condition of Pa to obtain a semi-finished product ingot; the current of the vacuum electron beam melting electron beam gun is 2.5A, and the melting speed is 20mm/min;
and step 3: placing the electrode in a vacuum consumable arc furnace under vacuum degree of less than 5 × 10 -2 Smelting for 2 times under the condition of Pa to obtain a copper alloy ingot; the current of the vacuum consumable arc melting is 5KA, and the melting voltage is 30V; and 4, step 4: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 5: forging the copper alloy cast ingot subjected to the solution treatment at the temperature of 800 ℃ to obtain a copper alloy bar blank; and 6: making the copper alloy bar blank be less than 2X 10 vacuum degree -2 Pa, and carrying out solid solution aging at the aging temperature of 500 ℃; forging the copper alloy bar blank subjected to the aging treatment at the temperature of 700 ℃ to obtain a copper alloy forging blank;
and 7: the copper alloy forging stock is processed under the vacuum degree of less than 2 multiplied by 10 -2 Pa, and carrying out solid solution aging at the aging temperature of 500 ℃ to obtain the heat-resistant impact-resistant copper alloy material for the rocket engine. The copper alloy material for the rocket engine prepared in the embodiment has the room-temperature tensile strength of 895MPa and the elongation after fracture of 19%; the tensile strength at 500 ℃ is 355MPa, and the elongation after fracture is 22%; the room temperature thermal conductivity is 267W/m.K. After 10 heat cycles (196 ℃ below zero to 500 ℃), the copper alloy material has the temperature tensile strength of 456MPa, the elongation after fracture of 10-19%, the tensile strength of 189-237 MPa at 500 ℃, the elongation after fracture of 10-16% and the thermal conductivity of 245W/m.K.
Example 7
A preparation method of a thermal shock resistant copper alloy material for a rocket engine comprises the following steps:
the preparation raw materials of the thermal shock resistant copper alloy material for the rocket engine comprise: 0.1% of Cr0%, 2% of Nb, 0.1% of Hf0, and the balance of Cu;
step 1: mixing the alloy elements of the preparation raw materials according to the mass percentage relationship, and then pressing into an electrode; and 2, step: placing the electrode in a vacuum electron beam melting furnace under the vacuum degree of less than 3 x 10 -2 Smelting for 2 times under the condition of Pa to obtain a semi-finished product ingot; the current of the vacuum electron beam melting electron beam gun is 2.5A, and the melting speed is 20mm/min;
and 3, step 3: placing the electrode in a vacuum consumable arc furnace at a vacuum degree of less than 5 × 10 -2 Smelting for 2 times under the condition of Pa to obtain a copper alloy ingot; the current of the vacuum consumable arc melting is 5KA, and the melting voltage is 30V; and 4, step 4: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 5: forging the copper alloy cast ingot subjected to the solution treatment at the temperature of 800 ℃ to obtain a copper alloy bar blank; step 6: making the copper alloy bar blank in vacuum degree less than 2X 10 -2 Pa, and carrying out solid solution aging at the aging temperature of 500 ℃; forging the copper alloy bar blank subjected to the aging treatment at the temperature of 700 ℃ to obtain a copper alloy forging blank;
and 7: the copper alloy forging stock is processed in vacuum degree less than 2 x 10 -2 And (3) carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃, and obtaining the heat-resistant and impact-resistant copper alloy material for the rocket engine. The copper alloy material for the rocket engine prepared in the embodiment has the room temperature tensile strength of 875MPa and the elongation after fracture of 79%; tensile strength at 500 ℃ of 357MPa and elongation after fracture of 22%; the room temperature thermal conductivity is 271W/m.K. After 10 thermal cycles (196 ℃ below zero to 500 ℃), the copper alloy material has the temperature tensile strength of 463MPa, the elongation after fracture of 16%, the tensile strength of 217MPa, the elongation after fracture of 12% and the thermal conductivity of 246W/m.K at 500 ℃.
Example 8
A preparation method of a thermal shock resistant copper alloy material for a rocket engine comprises the following steps:
the preparation raw materials of the thermal shock resistant copper alloy material for the rocket engine comprise: 1.0 percent of Cr1, 30 percent of Nb, 0.5 percent of Hf0, and the balance of Cu;
step 1: mixing the alloy elements of the preparation raw materials according to the mass percentage relationship, and then pressing into an electrode; step 2: placing the electrode in a vacuum electron beam melting furnace under the vacuum degree of less than 3 x 10 -2 Smelting for 2 times under the condition of Pa to obtain a semi-finished product ingot; the current of the vacuum electron beam melting electron beam gun is 2.5A, and the melting speed is 20mm/min;
and step 3: placing the electrode in a vacuum consumable arc furnace under vacuum degree of less than 5 × 10 -2 Smelting for 2 times under the condition of Pa to obtain a copper alloy ingot; the current of the vacuum consumable arc melting is 5KA, and the melting voltage is 30V; and 4, step 4: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 5: forging the copper alloy cast ingot subjected to the solution treatment at the temperature of 800 ℃ to obtain a copper alloy bar blank; and 6: making the copper alloy bar blank in vacuum degree less than 2X 10 -2 Carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃; forging the copper alloy bar blank subjected to the aging treatment at the temperature of 700 ℃ to obtain a copper alloy forging blank;
and 7: the copper alloy forging stock is processed in vacuum degree less than 2 x 10 -2 And (3) carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃, and obtaining the heat-resistant and impact-resistant copper alloy material for the rocket engine. The copper alloy material for the rocket engine prepared in the embodiment has the room temperature tensile strength of 902MPa and the elongation after fracture of 17%; the tensile strength at 500 ℃ is 345MPa, and the elongation after fracture is 22 percent; the room temperature thermal conductivity coefficient is 263W/m.K. After 10 heat cycles (196 ℃ below zero to 500 ℃), the copper alloy material has the temperature tensile strength of 432MPa, the elongation after fracture of 10-19%, the tensile strength at 500 ℃ of 189-237 MPa, the elongation after fracture of 12% and the thermal conductivity of 231W/m.K.
Example 9
A preparation method of a thermal shock resistant copper alloy material for a rocket engine comprises the following steps:
the preparation raw materials of the thermal shock resistant copper alloy material for the rocket engine comprise: 0.55 percent of Cr0, 16 percent of Nb, 0.3 percent of Hf0, and the balance of Cu;
step 1: mixing the alloy elements of the preparation raw materials according to the mass percentage relationship, and then pressing into an electrode; step 2: placing the electrode in a vacuum electron beam melting furnace under vacuum degree of less than 3 × 10 -2 Smelting for 2 times under the condition of Pa to obtain a semi-finished product ingot; the current of the vacuum electron beam melting electron beam gun is 2.5A, and the melting speed is 20mm/min;
and step 3: placing the electrode in a vacuum consumable arc furnace at a vacuum degree of less than 5 × 10 -2 Smelting for 2 times under the condition of Pa to obtain a copper alloy ingot; the current of the vacuum consumable arc melting is 5KA, and the melting voltage is 30V; and 4, step 4: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 5: forging the copper alloy cast ingot subjected to the solution treatment at the temperature of 800 ℃ to obtain a copper alloy bar blank; step 6: making the copper alloy bar blank be less than 2X 10 vacuum degree -2 Pa, and carrying out solid solution aging at the aging temperature of 500 ℃; forging the copper alloy bar blank subjected to the aging treatment at the temperature of 700 ℃ to obtain a copper alloy forging blank; and 7: the copper alloy forging stock is processed in vacuum degree less than 2 x 10 -2 And (3) carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃, and obtaining the heat-resistant and impact-resistant copper alloy material for the rocket engine.
The copper alloy material for the rocket engine prepared in the embodiment has the room-temperature tensile strength of 883MPa and the elongation after fracture of 17%; the tensile strength at 500 ℃ is 360MPa, and the elongation after fracture is 22%; the thermal conductivity at room temperature is 261W/m.K. After 10 thermal cycles (196 ℃ below zero to 500 ℃), the copper alloy material has the warm tensile strength of 470MPa, the elongation after fracture of 18 percent, the tensile strength of 220MPa at 500 ℃, the elongation after fracture of 13 percent and the thermal conductivity of 239W/m.K.
Example 10
A preparation method of a thermal shock resistant copper alloy material for a rocket engine comprises the following steps:
the preparation raw materials of the thermal shock resistant copper alloy material for the rocket engine comprise: nb2%, hf0.1%, and the balance of Cu;
step 1: mixing the alloy elements of the preparation raw materials according to the mass percentage relationship, and then pressing into an electrode; and 2, step: placing the electrode in a vacuum electron beam melting furnace under the vacuum degree of less than 3 x 10 -2 Smelting for 2 times under the condition of Pa to obtain a semi-finished product ingot; the current of the vacuum electron beam melting electron beam gun is 2.5A, and the melting speed is 20mm/min;
and step 3: placing the electrode in a vacuum consumable arc furnace under vacuum degree of less than 5 × 10 -2 Smelting for 2 times under the condition of Pa to obtain a copper alloy ingot; the current of the vacuum consumable arc melting is 5KA, and the melting voltage is 30V; and 4, step 4: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 5: forging the copper alloy cast ingot subjected to the solution treatment at the temperature of 800 ℃ to obtain a copper alloy bar blank; step 6: making the copper alloy bar blank in vacuum degree less than 2X 10 -2 Carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃; forging the copper alloy bar blank subjected to the aging treatment at the temperature of 700 ℃ to obtain a copper alloy forging blank; and 7: the copper alloy forging stock is processed in vacuum degree less than 2 x 10 -2 Pa, and carrying out solid solution aging at the aging temperature of 500 ℃ to obtain the heat-resistant impact-resistant copper alloy material for the rocket engine.
The copper alloy material for the rocket engine prepared in the embodiment has room temperature tensile strength of 879MPa and elongation after fracture of 17%; tensile strength at 500 ℃ of 362MPa and elongation after fracture of 20%; the room temperature thermal conductivity is 268W/m.K. After 10 thermal cycles (196 ℃ below zero to 500 ℃), the copper alloy material has the temperature tensile strength of 412MPa, the elongation after fracture of 12 percent, the tensile strength of 207MPa at 500 ℃ and the elongation after fracture of 13 percent, and the thermal conductivity of 236W/m.K.
Example 11
A preparation method of a thermal shock resistant copper alloy material for a rocket engine comprises the following steps:
the preparation raw materials of the thermal shock resistant copper alloy material for the rocket engine comprise: 30% of Nb, 0.5% of Hf0 and the balance of Cu;
step 1: will make intoMixing the alloy elements of the raw materials according to the mass percentage relationship, and then pressing into an electrode; step 2: placing the electrode in a vacuum electron beam melting furnace under the vacuum degree of less than 3 x 10 -2 Smelting for 2 times under the condition of Pa to obtain a semi-finished product ingot; the current of the vacuum electron beam melting electron beam gun is 2.5A, and the melting speed is 20mm/min;
and step 3: placing the electrode in a vacuum consumable arc furnace at a vacuum degree of less than 5 × 10 -2 Smelting for 2 times under the condition of Pa to obtain a copper alloy ingot; the current of the vacuum consumable arc melting is 5KA, and the melting voltage is 30V; and 4, step 4: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 5: forging the copper alloy cast ingot subjected to the solution treatment at the temperature of 800 ℃ to obtain a copper alloy bar blank; step 6: making the copper alloy bar blank in vacuum degree less than 2X 10 -2 Pa, and carrying out solid solution aging at the aging temperature of 500 ℃; forging the copper alloy bar blank subjected to the aging treatment at the temperature of 700 ℃ to obtain a copper alloy forging blank; and 7: the copper alloy forging stock is processed in vacuum degree less than 2 x 10 -2 And (3) carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃, and obtaining the heat-resistant and impact-resistant copper alloy material for the rocket engine.
The copper alloy material for the rocket engine prepared in the embodiment has the room temperature tensile strength of 880MPa and the elongation after fracture of 17%; the tensile strength at 500 ℃ is 349MPa, and the elongation after fracture is 20%; the room temperature thermal conductivity is 269W/m.K. After 10 thermal cycles (196 ℃ below zero to 500 ℃), the copper alloy material has 457MPa of warm tensile strength, 13 percent of elongation after fracture, 205MPa of tensile strength at 500 ℃, 12 percent of elongation after fracture and 233W/m.K of thermal conductivity.
Example 12
A preparation method of a thermal shock resistant copper alloy material for a rocket engine comprises the following steps:
the preparation raw materials of the thermal shock resistant copper alloy material for the rocket engine comprise: 16% of Nb, 0.3% of Hf0 and the balance of Cu;
step 1: mixing the alloy elements of the preparation raw materials according to the mass percentage relationship,then pressing into an electrode; step 2: placing the electrode in a vacuum electron beam melting furnace under the vacuum degree of less than 3 x 10 -2 Smelting for 2 times under the condition of Pa to obtain a semi-finished product ingot; the current of the vacuum electron beam melting electron beam gun is 2.5A, and the melting speed is 20mm/min;
and 3, step 3: placing the electrode in a vacuum consumable arc furnace at a vacuum degree of less than 5 × 10 -2 Smelting for 2 times under the condition of Pa to obtain a copper alloy ingot; the current of the vacuum consumable arc melting is 5KA, and the melting voltage is 30V; and 4, step 4: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 5: forging the copper alloy cast ingot subjected to the solution treatment at the temperature of 800 ℃ to obtain a copper alloy bar blank; step 6: making the copper alloy bar blank in vacuum degree less than 2X 10 -2 Carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃; forging the copper alloy bar blank subjected to the aging treatment at the temperature of 700 ℃ to obtain a copper alloy forging blank; and 7: the copper alloy forging stock is processed in vacuum degree less than 2 x 10 -2 Pa, and carrying out solid solution aging at the aging temperature of 500 ℃ to obtain the heat-resistant impact-resistant copper alloy material for the rocket engine.
The copper alloy material for the rocket engine prepared in the embodiment has the room-temperature tensile strength of 903MPa and the elongation after fracture of 21%; tensile strength at 500 ℃ is 372MPa, and elongation after fracture is 23%; the room temperature thermal conductivity is 265W/m.K. After 10 heat cycles (196 ℃ below zero to 500 ℃), the copper alloy material has the temperature tensile strength of 472MPa, the elongation after fracture of 10-19%, the tensile strength of 215MPa, the elongation after fracture of 13% and the thermal conductivity of 239W/m.K at 500 ℃.
Example 13
A preparation method of a thermal shock resistant copper alloy material for a rocket engine comprises the following steps:
the preparation raw materials of the thermal shock resistant copper alloy material for the rocket engine comprise: zr0.06%, nb2%, hf0.1%, and the balance of Cu;
step 1: mixing the alloy elements of the preparation raw materials according to the mass percentage relationship, and then pressing into an electrode; step 2: placing the electrode in the vacuumIn an empty electron beam melting furnace, the vacuum degree is less than 3 multiplied by 10 -2 Smelting for 2 times under the condition of Pa to obtain a semi-finished product ingot; the current of the vacuum electron beam melting electron beam gun is 2.5A, and the melting speed is 20mm/min;
and step 3: placing the electrode in a vacuum consumable arc furnace under vacuum degree of less than 5 × 10 -2 Smelting for 2 times under the condition of Pa to obtain a copper alloy ingot; the current of the vacuum consumable arc melting is 5KA, and the melting voltage is 30V; and 4, step 4: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 5: forging the copper alloy cast ingot subjected to the solution treatment at the temperature of 800 ℃ to obtain a copper alloy bar blank; step 6: making the copper alloy bar blank in vacuum degree less than 2X 10 -2 Carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃; forging the copper alloy bar blank subjected to the aging treatment at the temperature of 700 ℃ to obtain a copper alloy forging blank;
and 7: the copper alloy forging stock is processed in vacuum degree less than 2 x 10 -2 And (3) carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃, and obtaining the heat-resistant and impact-resistant copper alloy material for the rocket engine. The copper alloy material for the rocket engine prepared by the embodiment has the room temperature tensile strength of 852-915 MPa and the elongation after fracture of 16 percent; tensile strength at 500 ℃ of 329MPa and elongation after fracture of 20%; the room temperature thermal conductivity coefficient is 263W/m.K. After 10 thermal cycles (196 ℃ below zero to 500 ℃), the copper alloy material has the temperature tensile strength of 412MPa, the elongation after fracture of 17 percent, the tensile strength of 220MPa at 500 ℃, the elongation after fracture of 15 percent and the thermal conductivity of 230 to 246W/m.K.
Example 14
A preparation method of a thermal shock resistant copper alloy material for a rocket engine comprises the following steps:
the preparation raw materials of the thermal shock resistant copper alloy material for the rocket engine comprise: zr0.6%, nb30%, hf0.5%, and the balance of Cu;
step 1: mixing the alloy elements of the preparation raw materials according to the mass percentage relationship, and then pressing into an electrode; step 2: placing the electrode in a vacuum electron beam melting furnace, and keeping the vacuum degree lower than3×10 -2 Smelting for 2 times under the condition of Pa to obtain a semi-finished product ingot; the current of the vacuum electron beam melting electron beam gun is 2.5A, and the melting speed is 20mm/min;
and step 3: placing the electrode in a vacuum consumable arc furnace under vacuum degree of less than 5 × 10 -2 Smelting for 2 times under the condition of Pa to obtain a copper alloy ingot; the current of the vacuum consumable arc melting is 5KA, and the melting voltage is 30V; and 4, step 4: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 5: forging the copper alloy cast ingot subjected to the solution treatment at the temperature of 800 ℃ to obtain a copper alloy bar blank; and 6: making the copper alloy bar blank in vacuum degree less than 2X 10 -2 Pa, and carrying out solid solution aging at the aging temperature of 500 ℃; forging the copper alloy bar blank subjected to the aging treatment at the temperature of 700 ℃ to obtain a copper alloy forging blank;
and 7: the copper alloy forging stock is processed in vacuum degree less than 2 x 10 -2 And (3) carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃, and obtaining the heat-resistant and impact-resistant copper alloy material for the rocket engine. The copper alloy material for the rocket engine prepared in the embodiment has the room temperature tensile strength of 832MPa and the elongation after fracture of 18%; tensile strength at 500 ℃ of 362MPa and elongation after fracture of 21%; the room temperature thermal conductivity coefficient is 263W/m.K. After 10 thermal cycles (196 ℃ below zero to 500 ℃), the copper alloy material has the temperature tensile strength of 455MPa, the elongation after fracture of 16%, the tensile strength of 213MPa at 500 ℃, the elongation after fracture of 12% and the thermal conductivity of 230W/m.K to 246W/m.K.
Example 15
A preparation method of a thermal shock resistant copper alloy material for a rocket engine comprises the following steps:
the preparation raw materials of the thermal shock resistant copper alloy material for the rocket engine comprise: zr0.33%, nb16%, hf0.3%, and the balance of Cu;
step 1: mixing the alloy elements of the preparation raw materials according to the mass percentage relationship, and then pressing into an electrode; step 2: placing the electrode in a vacuum electron beam melting furnace under vacuum degree of less than 3 × 10 -2 Smelting for 2 times under the condition of Pa,obtaining a semi-finished cast ingot; the current of the vacuum electron beam melting electron beam gun is 2.5A, and the melting speed is 20mm/min;
and 3, step 3: placing the electrode in a vacuum consumable arc furnace at a vacuum degree of less than 5 × 10 -2 Smelting for 2 times under the condition of Pa to obtain a copper alloy ingot; the current of the vacuum consumable arc melting is 5KA, and the melting voltage is 30V; and 4, step 4: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 5: forging the copper alloy cast ingot subjected to the solution treatment at the temperature of 800 ℃ to obtain a copper alloy bar blank; and 6: making the copper alloy bar blank in vacuum degree less than 2X 10 -2 Carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃; forging the copper alloy bar blank subjected to the aging treatment at the temperature of 700 ℃ to obtain a copper alloy forging blank;
and 7: the copper alloy forging stock is processed in vacuum degree less than 2 x 10 -2 And (3) carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃, and obtaining the heat-resistant and impact-resistant copper alloy material for the rocket engine. The copper alloy material for the rocket engine prepared by the embodiment has the room temperature tensile strength of 907MPa and the elongation after fracture of 19 percent; tensile strength at 500 ℃ of 356MPa and elongation after fracture of 23%; the room temperature thermal conductivity is 269W/m.K. After 10 thermal cycles (196 ℃ below zero to 500 ℃), the copper alloy material has the warm tensile strength of 482MPa, the elongation after fracture of 17 percent, the tensile strength of 230MPa at 500 ℃, the elongation after fracture of 15 percent and the thermal conductivity of 239W/m.K.
Example 16
A preparation method of a thermal shock resistant copper alloy material for a rocket engine comprises the following steps:
the preparation raw materials of the thermal shock resistant copper alloy material for the rocket engine comprise: zr0.06%, nb2%, and the balance of Cu;
step 1: mixing the alloy elements of the preparation raw materials according to the mass percentage relationship, and then pressing into an electrode; step 2: placing the electrode in a vacuum electron beam melting furnace under the vacuum degree of less than 3 x 10 -2 Smelting for 2 times under the condition of Pa to obtain a semi-finished product ingot; the electron beam gun current for vacuum electron beam melting2.5A, the melting speed is 20mm/min;
and step 3: placing the electrode in a vacuum consumable arc furnace under vacuum degree of less than 5 × 10 -2 Smelting for 2 times under the condition of Pa to obtain a copper alloy ingot; the current of the vacuum consumable arc melting is 5KA, and the melting voltage is 30V; and 4, step 4: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 5: forging the copper alloy cast ingot subjected to the solution treatment at the temperature of 800 ℃ to obtain a copper alloy bar blank; and 6: making the copper alloy bar blank be less than 2X 10 vacuum degree -2 Carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃; forging the copper alloy bar blank subjected to the aging treatment at the temperature of 700 ℃ to obtain a copper alloy forging blank;
and 7: the copper alloy forging stock is processed under the vacuum degree of less than 2 multiplied by 10 -2 And (3) carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃, and obtaining the heat-resistant and impact-resistant copper alloy material for the rocket engine. The copper alloy material for the rocket engine prepared in the embodiment has the room temperature tensile strength of 900MPa and the elongation after fracture of 21%; the tensile strength at 500 ℃ is 370MPa, and the elongation after fracture is 25%; the room temperature thermal conductivity is 269W/m.K. After 10 thermal cycles (196 ℃ below zero to 500 ℃), the copper alloy material has the warm tensile strength of 431MPa, the elongation after fracture of 18 percent, the tensile strength of 227MPa at 500 ℃, the elongation after fracture of 16 percent and the thermal conductivity of 239W/m.K.
Example 17
A preparation method of a thermal shock resistant copper alloy material for a rocket engine comprises the following steps:
the preparation raw materials of the thermal shock resistant copper alloy material for the rocket engine comprise: zr0.6%, nb30%, and the balance of Cu;
step 1: mixing the alloy elements of the preparation raw materials according to the relation of mass percentage, and then pressing into an electrode; and 2, step: placing the electrode in a vacuum electron beam melting furnace under the vacuum degree of less than 3 x 10 -2 Smelting for 2 times under the condition of Pa to obtain a semi-finished product ingot; the current of the vacuum electron beam melting electron beam gun is 2.5A, and the melting speed is 20mm/min;
and 3, step 3: placing the electrode in a vacuum consumable arc furnace under vacuum degree of less than 5 × 10 -2 Smelting for 2 times under the condition of Pa to obtain a copper alloy ingot; the current of the vacuum consumable arc melting is 5KA, and the melting voltage is 30V; and 4, step 4: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 5: forging the copper alloy cast ingot subjected to the solution treatment at the temperature of 800 ℃ to obtain a copper alloy bar blank; step 6: making the copper alloy bar blank in vacuum degree less than 2X 10 -2 Carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃; forging the copper alloy bar blank subjected to the aging treatment at the temperature of 700 ℃ to obtain a copper alloy forging blank;
and 7: the copper alloy forging stock is processed under the vacuum degree of less than 2 multiplied by 10 -2 Pa, and carrying out solid solution aging at the aging temperature of 500 ℃ to obtain the heat-resistant impact-resistant copper alloy material for the rocket engine. The copper alloy material for the rocket engine prepared in the embodiment has the room-temperature tensile strength of 887MPa and the elongation after fracture of 20 percent; tensile strength at 500 ℃ of 362MPa and elongation after fracture of 20%; the room temperature thermal conductivity is 270W/m.K. After 10 thermal cycles (196 ℃ below zero to 500 ℃), the copper alloy material has the warm tensile strength of 455MPa, the elongation after fracture of 17 percent, the tensile strength of 1225MPa at 500 ℃, the elongation after fracture of 15 percent and the thermal conductivity of 228W/m.K.
Example 18
A preparation method of a thermal shock resistant copper alloy material for a rocket engine comprises the following steps:
the preparation raw materials of the thermal shock resistant copper alloy material for the rocket engine comprise: zr0.33%, nb16%, and the balance of Cu;
step 1: mixing the alloy elements of the preparation raw materials according to the mass percentage relationship, and then pressing into an electrode; step 2: placing the electrode in a vacuum electron beam melting furnace under the vacuum degree of less than 3 x 10 -2 Smelting for 2 times under the condition of Pa to obtain a semi-finished product ingot; the current of the vacuum electron beam melting electron beam gun is 2.5A, and the melting speed is 20mm/min;
and step 3: placing the electrode in a vacuum consumable arc furnace under the condition that the vacuum degree is less than5×10 -2 Smelting for 2 times under the condition of Pa to obtain a copper alloy ingot; the current of the vacuum consumable arc melting is 5KA, and the melting voltage is 30V; and 4, step 4: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 5: forging the copper alloy cast ingot subjected to the solution treatment at the temperature of 800 ℃ to obtain a copper alloy bar blank; and 6: making the copper alloy bar blank be less than 2X 10 vacuum degree -2 Carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃; forging the copper alloy bar blank subjected to the aging treatment at the temperature of 700 ℃ to obtain a copper alloy forging blank;
and 7: the copper alloy forging stock is processed in vacuum degree less than 2 x 10 -2 And (3) carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃, and obtaining the heat-resistant and impact-resistant copper alloy material for the rocket engine. The copper alloy material for the rocket engine prepared in the embodiment has room temperature tensile strength of 877MPa and elongation after fracture of 19%; the tensile strength at 500 ℃ is 365MPa, and the elongation after fracture is 20%; the thermal conductivity at room temperature is 262W/m.K. After 10 thermal cycles (196 ℃ below zero to 500 ℃), the tensile strength of the copper alloy material at room temperature is 475MPa, the elongation after fracture is 15%, the tensile strength at 500 ℃ is 210MPa, the elongation after fracture is 12%, and the thermal conductivity is 235W/m.K.
Example 19
A preparation method of a thermal shock resistant copper alloy material for a rocket engine comprises the following steps:
the preparation raw materials of the thermal shock resistant copper alloy material for the rocket engine comprise: zr0.06%, ta0.1%, nb2%, hf0.1%, and the balance of Cu;
step 1: mixing the alloy elements of the preparation raw materials according to the mass percentage relationship, and then pressing into an electrode; step 2: placing the electrode in a vacuum electron beam melting furnace under vacuum degree of less than 3 × 10 -2 Smelting for 2 times under the condition of Pa to obtain a semi-finished product ingot; the current of the vacuum electron beam melting electron beam gun is 2.5A, and the melting speed is 20mm/min;
and 3, step 3: placing the electrode in a vacuum consumable arc furnace under vacuum degree of less than 5 × 10 -2 Smelting under Pa for 2 timesObtaining a copper alloy ingot; the current of the vacuum consumable arc melting is 5KA, and the melting voltage is 30V; and 4, step 4: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 5: forging the copper alloy cast ingot subjected to the solution treatment at the temperature of 800 ℃ to obtain a copper alloy bar blank; and 6: making the copper alloy bar blank be less than 2X 10 vacuum degree -2 Carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃; forging the copper alloy bar blank subjected to the aging treatment at the temperature of 700 ℃ to obtain a copper alloy forging blank;
and 7: the copper alloy forging stock is processed in vacuum degree less than 2 x 10 -2 And (3) carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃, and obtaining the heat-resistant and impact-resistant copper alloy material for the rocket engine. The copper alloy material for the rocket engine prepared by the embodiment has the room temperature tensile strength of 852-915 MPa and the elongation after fracture of 20 percent; the tensile strength at 500 ℃ is 370MPa, and the elongation after fracture is 21%; the room temperature thermal conductivity is 265W/m.K. After 10 thermal cycles (196 ℃ below zero to 500 ℃), the copper alloy material has the temperature tensile strength of 397MPa, the elongation after fracture of 17 percent, the tensile strength of 216MPa at 500 ℃, the elongation after fracture of 13 percent and the thermal conductivity of 235W/m.K.
Example 20
A preparation method of a thermal shock resistant copper alloy material for a rocket engine comprises the following steps:
the preparation raw materials of the thermal shock resistant copper alloy material for the rocket engine comprise: zr0.6%, ta0.9%, nb30%, hf0.5%, and the balance of Cu;
step 1: mixing the alloy elements of the preparation raw materials according to the mass percentage relationship, and then pressing into an electrode; step 2: placing the electrode in a vacuum electron beam melting furnace under the vacuum degree of less than 3 x 10 -2 Smelting for 2 times under the condition of Pa to obtain a semi-finished product ingot; the current of the vacuum electron beam melting electron beam gun is 2.5A, and the melting speed is 20mm/min;
and step 3: placing the electrode in a vacuum consumable arc furnace at a vacuum degree of less than 5 × 10 -2 Smelting for 2 times under the condition of Pa to obtain a copper alloy ingot; the vacuum is fromThe current of the consumable arc melting is 5KA, and the melting voltage is 30V; and 4, step 4: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 5: forging the copper alloy cast ingot subjected to the solution treatment at the temperature of 800 ℃ to obtain a copper alloy bar blank; step 6: making the copper alloy bar blank in vacuum degree less than 2X 10 -2 Carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃; forging the copper alloy bar blank subjected to the aging treatment at the temperature of 700 ℃ to obtain a copper alloy forging blank; and 7: the copper alloy forging stock is processed in vacuum degree less than 2 x 10 -2 Pa, and carrying out solid solution aging at the aging temperature of 500 ℃ to obtain the heat-resistant impact-resistant copper alloy material for the rocket engine.
The copper alloy material for the rocket engine prepared in the embodiment has the room temperature tensile strength of 875MPa and the elongation after fracture of 20%; the tensile strength at 500 ℃ is 355MPa, and the elongation after fracture is 20%; the room temperature thermal conductivity is 271W/m.K. After 10 thermal cycles (196 ℃ below zero to 500 ℃), the copper alloy material has the temperature tensile strength of 435MPa, the elongation after fracture of 15 percent, the tensile strength of 210MPa at 500 ℃ and the elongation after fracture of 13 percent, and the thermal conductivity of 236W/m.K.
Example 21
A preparation method of a thermal shock resistant copper alloy material for a rocket engine comprises the following steps:
the preparation raw materials of the thermal shock resistant copper alloy material for the rocket engine comprise: zr0.33%, ta0.5%, nb16%, hf0.3%, and the balance of Cu;
step 1: mixing the alloy elements of the preparation raw materials according to the mass percentage relationship, and then pressing into an electrode; and 2, step: placing the electrode in a vacuum electron beam melting furnace under vacuum degree of less than 3 × 10 -2 Smelting for 2 times under the condition of Pa to obtain a semi-finished product ingot; the current of the vacuum electron beam melting electron beam gun is 2.5A, and the melting speed is 20mm/min;
and step 3: placing the electrode in a vacuum consumable arc furnace at a vacuum degree of less than 5 × 10 -2 Smelting for 2 times under the condition of Pa to obtain a copper alloy ingot; the current of the vacuum consumable arc melting is 5KA, and the melting voltage isIs 30V; and 4, step 4: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 5: forging the copper alloy cast ingot subjected to the solution treatment at the temperature of 800 ℃ to obtain a copper alloy bar blank; and 6: making the copper alloy bar blank in vacuum degree less than 2X 10 -2 Carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃; forging the copper alloy bar blank subjected to the aging treatment at the temperature of 700 ℃ to obtain a copper alloy forging blank;
and 7: the copper alloy forging stock is processed under the vacuum degree of less than 2 multiplied by 10 -2 And (3) carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃, and obtaining the heat-resistant and impact-resistant copper alloy material for the rocket engine. The copper alloy material for the rocket engine prepared in the embodiment has room temperature tensile strength of 876MPa and elongation after fracture of 18%; a tensile strength of 355MPa at 500 ℃ and an elongation after fracture of 19%; the room temperature thermal conductivity is 269W/m.K. After 10 thermal cycles (-196 ℃ -500 ℃), the copper alloy material has 457MPa of warm tensile strength, 10-19% of elongation after fracture, 211MPa of tensile strength at 500 ℃, 13% of elongation after fracture and 235W/m.K of thermal conductivity coefficient.
Example 22
A preparation method of a thermal shock resistant copper alloy material for a rocket engine comprises the following steps:
the preparation raw materials of the thermal shock resistant copper alloy material for the rocket engine comprise: ta0.1%, nb2%, hf0.1%, and the balance of Cu;
step 1: mixing the alloy elements of the preparation raw materials according to the relation of mass percentage, and then pressing into an electrode; and 2, step: placing the electrode in a vacuum electron beam melting furnace under the vacuum degree of less than 3 x 10 -2 Smelting for 2 times under the condition of Pa to obtain a semi-finished product ingot; the current of the vacuum electron beam melting electron beam gun is 2.5A, and the melting speed is 20mm/min;
and 3, step 3: placing the electrode in a vacuum consumable arc furnace at a vacuum degree of less than 5 × 10 -2 Smelting for 2 times under the condition of Pa to obtain a copper alloy ingot; the current of the vacuum consumable arc melting is 5KA, and the melting voltage is 30V; and 4, step 4: strip of copper alloy ingot at 900 deg.CCarrying out solution treatment for 7h under the condition;
and 5: forging the copper alloy cast ingot subjected to the solution treatment at the temperature of 800 ℃ to obtain a copper alloy bar blank; step 6: making the copper alloy bar blank in vacuum degree less than 2X 10 -2 Carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃; forging the copper alloy bar blank subjected to the aging treatment at the temperature of 700 ℃ to obtain a copper alloy forging blank;
and 7: the copper alloy forging stock is processed in vacuum degree less than 2 x 10 -2 And (3) carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃, and obtaining the heat-resistant and impact-resistant copper alloy material for the rocket engine. The copper alloy material for the rocket engine prepared by the embodiment has the room temperature tensile strength of 900MPa and the elongation after fracture of 20 percent; the tensile strength at 500 ℃ is 365MPa, and the elongation after fracture is 22%; the room temperature thermal conductivity is 271W/m.K. After 10 thermal cycles (196 ℃ below zero to 500 ℃), the tensile strength of the copper alloy material at the temperature of 459MPa, the elongation after fracture of 10 to 19 percent, the tensile strength of 199MPa at the temperature of 500 ℃, the elongation after fracture of 15 percent and the heat conductivity coefficient of 237W/m.K.
Example 23
A preparation method of a thermal shock resistant copper alloy material for a rocket engine comprises the following steps:
the preparation raw materials of the thermal shock resistant copper alloy material for the rocket engine comprise: ta0.9%, nb30%, hf0.5%, and the balance of Cu;
step 1: mixing the alloy elements of the preparation raw materials according to the mass percentage relationship, and then pressing into an electrode; and 2, step: placing the electrode in a vacuum electron beam melting furnace under the vacuum degree of less than 3 x 10 -2 Smelting for 2 times under the condition of Pa to obtain a semi-finished product ingot; the current of the vacuum electron beam melting electron beam gun is 2.5A, and the melting speed is 20mm/min;
and step 3: placing the electrode in a vacuum consumable arc furnace under vacuum degree of less than 5 × 10 -2 Smelting for 2 times under the condition of Pa to obtain a copper alloy ingot; the current of the vacuum consumable arc melting is 5KA, and the melting voltage is 30V; and 4, step 4: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 5: forging the copper alloy cast ingot subjected to the solution treatment at the temperature of 800 ℃ to obtain a copper alloy bar blank; step 6: making the copper alloy bar blank be less than 2X 10 vacuum degree -2 Pa, and carrying out solid solution aging at the aging temperature of 500 ℃; forging the copper alloy bar blank subjected to the aging treatment at the temperature of 700 ℃ to obtain a copper alloy forging blank;
and 7: the copper alloy forging stock is processed under the vacuum degree of less than 2 multiplied by 10 -2 And (3) carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃, and obtaining the heat-resistant and impact-resistant copper alloy material for the rocket engine. The copper alloy material for the rocket engine prepared in the embodiment has the room temperature tensile strength of 906MPa and the elongation after fracture of 21%; tensile strength at 500 ℃ of 377MPa and elongation after fracture of 23%; the room temperature thermal conductivity is 269W/m.K. After 10 thermal cycles (196 ℃ below zero to 500 ℃), the copper alloy material has the warm tensile strength of 482MPa, the elongation after fracture of 18 percent, the tensile strength of 236MPa, the elongation after fracture of 16 percent and the thermal conductivity of 242W/m.K at 500 ℃.
Example 24
A preparation method of a thermal shock resistant copper alloy material for a rocket engine comprises the following steps:
the preparation raw materials of the thermal shock resistant copper alloy material for the rocket engine comprise: ta0.5%, nb16%, hf0.3%, and the balance of Cu;
step 1: mixing the alloy elements of the preparation raw materials according to the mass percentage relationship, and then pressing into an electrode; step 2: placing the electrode in a vacuum electron beam melting furnace under vacuum degree of less than 3 × 10 -2 Smelting for 2 times under the condition of Pa to obtain a semi-finished product ingot; the current of the vacuum electron beam melting electron beam gun is 2.5A, and the melting speed is 20mm/min;
and 3, step 3: placing the electrode in a vacuum consumable arc furnace at a vacuum degree of less than 5 × 10 -2 Smelting for 2 times under the condition of Pa to obtain a copper alloy ingot; the current of the vacuum consumable arc melting is 5KA, and the melting voltage is 30V; and 4, step 4: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 5: casting the copper alloy ingot after the solution treatmentForging at the temperature of 800 ℃ to obtain a copper alloy bar blank; step 6: making the copper alloy bar blank in vacuum degree less than 2X 10 -2 Carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃; forging the copper alloy bar blank subjected to the aging treatment at the temperature of 700 ℃ to obtain a copper alloy forging blank;
and 7: the copper alloy forging stock is processed under the vacuum degree of less than 2 multiplied by 10 -2 And (3) carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃, and obtaining the heat-resistant and impact-resistant copper alloy material for the rocket engine. The copper alloy material for the rocket engine prepared in the embodiment has the room-temperature tensile strength of 899MPa and the elongation after fracture of 19 percent; tensile strength of 370MPa at 500 ℃ and elongation after fracture of 22%; the room temperature thermal conductivity is 269W/m.K. After 10 thermal cycles (196 ℃ below zero to 500 ℃), the tensile strength of the copper alloy material at room temperature is 408MPa, the elongation after fracture is 17%, the tensile strength at 500 ℃ is 229MPa, the elongation after fracture is 15%, and the thermal conductivity is 231W/m.K.
Example 25
A preparation method of a thermal shock resistant copper alloy material for a rocket engine comprises the following steps:
the preparation raw materials of the thermal shock resistant copper alloy material for the rocket engine comprise: zr0.33%, ta0.5%, nb16%, and the balance of Cu;
step 1: mixing the alloy elements of the preparation raw materials according to the relation of mass percentage, and then pressing into an electrode; step 2: placing the electrode in a vacuum electron beam melting furnace under the vacuum degree of less than 3 x 10 -2 Smelting for 2 times under the condition of Pa to obtain a semi-finished product ingot; the current of the vacuum electron beam melting electron beam gun is 2.5A, and the melting speed is 20mm/min;
and step 3: placing the electrode in a vacuum consumable arc furnace at a vacuum degree of less than 5 × 10 -2 Smelting for 2 times under the condition of Pa to obtain a copper alloy ingot; the current of the vacuum consumable arc melting is 5KA, and the melting voltage is 30V; and 4, step 4: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 5: forging the copper alloy ingot after the solution treatment at the temperature of 800 ℃ to obtain a copper alloyA gold bar blank; step 6: making the copper alloy bar blank in vacuum degree less than 2X 10 -2 Carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃; forging the copper alloy bar blank subjected to the aging treatment at the temperature of 700 ℃ to obtain a copper alloy forging blank;
and 7: the copper alloy forging stock is processed in vacuum degree less than 2 x 10 -2 Pa, and carrying out solid solution aging at the aging temperature of 500 ℃ to obtain the heat-resistant impact-resistant copper alloy material for the rocket engine. The copper alloy material for the rocket engine prepared by the embodiment has the room-temperature tensile strength of 875MPa and the elongation after fracture of 17 percent; the tensile strength at 500 ℃ is 375MPa, and the elongation after fracture is 22%; the room temperature thermal conductivity is 267W/m.K. After 10 thermal cycles (196 ℃ below zero to 500 ℃), the copper alloy material has 395MPa of warm tensile strength, 17 percent of elongation after fracture, 199MPa of tensile strength at 500 ℃, 13 percent of elongation after fracture and 241W/m.K of thermal conductivity.
Example 26
A preparation method of a thermal shock resistant copper alloy material for a rocket engine comprises the following steps:
the preparation raw materials of the thermal shock resistant copper alloy material for the rocket engine comprise: zr0.6%, ta0.9%, nb30%, and the balance of Cu;
step 1: mixing the alloy elements of the preparation raw materials according to the mass percentage relationship, and then pressing into an electrode; step 2: placing the electrode in a vacuum electron beam melting furnace under the vacuum degree of less than 3 x 10 -2 Smelting for 2 times under the condition of Pa to obtain a semi-finished product ingot; the current of the vacuum electron beam melting electron beam gun is 2.5A, and the melting speed is 20mm/min;
and 3, step 3: placing the electrode in a vacuum consumable arc furnace under vacuum degree of less than 5 × 10 -2 Smelting for 2 times under the condition of Pa to obtain a copper alloy ingot; the current of the vacuum consumable arc melting is 5KA, and the melting voltage is 30V; and 4, step 4: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 5: forging the copper alloy cast ingot subjected to the solution treatment at the temperature of 800 ℃ to obtain a copper alloy bar blank; step 6: making the copper alloy bar blank in the vacuum degree less than2×10 -2 Carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃; forging the copper alloy bar blank subjected to the aging treatment at the temperature of 700 ℃ to obtain a copper alloy forging blank;
and 7: the copper alloy forging stock is processed in vacuum degree less than 2 x 10 -2 And (3) carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃, and obtaining the heat-resistant and impact-resistant copper alloy material for the rocket engine. The copper alloy material for the rocket engine prepared in the embodiment has the room temperature tensile strength of 909MPa and the elongation after fracture of 20%; tensile strength at 500 ℃ of 339MPa and elongation after fracture of 20 percent; the room temperature thermal conductivity is 269W/m.K. After 10 thermal cycles (196 ℃ below zero to 500 ℃), the copper alloy material has the temperature tensile strength of 399MPa, the elongation after fracture of 15 percent, the tensile strength of 205MPa at 500 ℃, the elongation after fracture of 13 percent and the thermal conductivity of 236W/m.K.
Example 27
A preparation method of a thermal shock resistant copper alloy material for a rocket engine comprises the following steps:
the preparation raw materials of the thermal shock resistant copper alloy material for the rocket engine comprise: zr0.33%, ta0.5%, nb16%, and the balance of Cu;
step 1: mixing the alloy elements of the preparation raw materials according to the mass percentage relationship, and then pressing into an electrode; step 2: placing the electrode in a vacuum electron beam melting furnace under the vacuum degree of less than 3 x 10 -2 Smelting for 2 times under the condition of Pa to obtain a semi-finished product ingot; the current of the vacuum electron beam melting electron beam gun is 2.5A, and the melting speed is 20mm/min;
and step 3: placing the electrode in a vacuum consumable arc furnace under vacuum degree of less than 5 × 10 -2 Smelting for 2 times under the condition of Pa to obtain a copper alloy ingot; the current of the vacuum consumable arc melting is 5KA, and the melting voltage is 30V; and 4, step 4: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 5: forging the copper alloy cast ingot subjected to the solution treatment at the temperature of 800 ℃ to obtain a copper alloy bar blank; and 6: making the copper alloy bar blank in vacuum degree less than 2X 10 -2 Solution aging under Pa condition and aging temperatureIs 500 ℃; forging the copper alloy bar blank subjected to the aging treatment at the temperature of 700 ℃ to obtain a copper alloy forging blank;
and 7: the copper alloy forging stock is processed in vacuum degree less than 2 x 10 -2 And (3) carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃, and obtaining the heat-resistant and impact-resistant copper alloy material for the rocket engine. The copper alloy material for the rocket engine prepared in the embodiment has room temperature tensile strength of 879MPa and elongation after fracture of 17%; the tensile strength at 500 ℃ is 359MPa, and the elongation after fracture is 21%; the thermal conductivity at room temperature is 265W/m.K. After 10 thermal cycles (196 ℃ below zero to 500 ℃), the copper alloy material has the warm tensile strength of 459MPa, the elongation after fracture of 17 percent, the tensile strength of 199MPa, the elongation after fracture of 15 percent and the thermal conductivity of 235W/m.K at 500 ℃.
Example 27
Different from the embodiment 26, the preparation raw materials of the thermal shock resistant copper alloy material for the rocket engine comprise: zr0.06%, ta0.1%, nb2% and the balance of Cu; the other preparation methods are the same as the examples, and the heat-resistant and impact-resistant copper alloy material for the rocket engine is obtained.
Example 28
A preparation method of a thermal shock resistant copper alloy material for a rocket engine comprises the following steps:
the preparation raw materials of the thermal shock resistant copper alloy material for the rocket engine comprise: 0.1% of Ti0.1%, 1.0% of Cr0%, 0.08% of Zr0, 0.9% of Ta0, 25% of Nb, 0.5% of Hf0, 0.09% of La0 and the balance of Cu;
step 1: mixing the alloy elements of the preparation raw materials according to the relation of mass percentage, and then pressing into an electrode; step 2: placing the electrode in a vacuum electron beam melting furnace under the vacuum degree of less than 3 x 10 -2 Smelting for 1 time under the condition of Pa to obtain a semi-finished product ingot; the current of the vacuum electron beam melting electron beam gun is 2.5A, and the melting speed is 20mm/min;
and step 3: placing the electrode in a vacuum consumable arc furnace at a vacuum degree of less than 5 × 10 -2 Smelting for 2 times under the condition of Pa to obtain a copper alloy ingot; the current of the vacuum consumable arc melting is 5KA, and the melting voltage is 30V; step (ii) of4: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 5: forging the copper alloy cast ingot subjected to the solution treatment at the temperature of 800 ℃ to obtain a copper alloy bar blank; and 6: making the copper alloy bar blank in vacuum degree less than 2X 10 -2 Carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃; forging the copper alloy bar blank subjected to the aging treatment at the temperature of 700 ℃ to obtain a copper alloy forging blank; and 7: the copper alloy forging stock is processed under the vacuum degree of less than 2 multiplied by 10 -2 And (3) carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃, and obtaining the heat-resistant and impact-resistant copper alloy material for the rocket engine.
Example 29
A preparation method of a thermal shock resistant copper alloy material for a rocket engine comprises the following steps:
the preparation raw materials of the thermal shock resistant copper alloy material for the rocket engine comprise: 0.68% of Ti0.68%, 0.19% of Cr0.06%, 0.1% of Zr0.06%, 30% of Nb, 0.2% of Hf0.08%, and the balance of Cu;
step 1: mixing the alloy elements of the preparation raw materials according to the mass percentage relationship, and then pressing into an electrode; and 2, step: placing the electrode in a vacuum electron beam melting furnace, and melting for 2 times under the condition that the vacuum degree is less than 3 multiplied by 10 < -2 > Pa to obtain a semi-finished product ingot; the current of the vacuum electron beam melting electron beam gun is 2.5A, and the melting speed is 20mm/min;
and step 3: placing the electrode in a vacuum consumable arc furnace at a vacuum degree of less than 5 × 10 -2 Smelting for 2 times under the condition of Pa to obtain a copper alloy ingot; the current of the vacuum consumable arc melting is 5KA, and the melting voltage is 30V; and 4, step 4: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 5: forging the copper alloy cast ingot subjected to the solution treatment at the temperature of 800 ℃ to obtain a copper alloy bar blank; and 6: making the copper alloy bar blank be less than 2X 10 vacuum degree -2 Carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃; forging the copper alloy bar blank subjected to the aging treatment at the temperature of 700 ℃ to obtain a copper alloy forging blank; step (ii) of7: the copper alloy forging stock is processed in vacuum degree less than 2 x 10 -2 And (3) carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃, and obtaining the heat-resistant and impact-resistant copper alloy material for the rocket engine.
Example 30
Unlike example 29, the starting materials for producing the thermal shock resistant copper alloy material for rocket engines included: ti0.7%, cr0.1%, zr0.6%, ta0.7%, nb2%, hf0.1%, la0.01%, and the balance Cu, and the remaining preparation methods were the same as in example 29, to obtain a heat-and impact-resistant copper alloy material for rocket engines. The above-mentioned contents are only for illustrating the technical idea of the present invention, and the protection scope of the present invention is not limited thereby, and any modification made on the basis of the technical idea of the present invention falls within the protection scope of the claims of the present invention.

Claims (10)

1. The thermal shock resistant copper alloy material for the rocket engine is characterized by comprising the following preparation raw materials in percentage by mass: 0.1 to 0.7 percent of Ti,0.1 to 1.0 percent of Cr, 0.06 to 0.6 percent of Zr, 0.1 to 0.9 percent of Ta, 2 to 30 percent of Nb, 0.1 to 0.5 percent of Hf, 0.01 to 0.09 percent of La and the balance of Cu.
2. The thermal shock resistant copper alloy material for the rocket engine is characterized by comprising the following preparation raw materials in percentage by mass: 0.1 to 0.7 percent of Ti,0.1 to 1.0 percent of Cr, 2 to 30 percent of Nb, 0.1 to 0.5 percent of Hf, 0.01 to 0.09 percent of La and the balance of Cu.
3. The thermal shock resistant copper alloy material for the rocket engine is characterized by comprising the following preparation raw materials in percentage by mass: 0.1 to 0.7 percent of Ti,0.1 to 1.0 percent of Cr, 2 to 30 percent of Nb, 0.1 to 0.5 percent of Hf and the balance of Cu.
4. The thermal shock resistant copper alloy material for the rocket engine is characterized by comprising the following preparation raw materials in percentage by mass: 0.1 to 1.0 percent of Cr, 2 to 30 percent of Nb, 0.1 to 0.5 percent of Hf and the balance of Cu.
5. The thermal shock resistant copper alloy material for the rocket engine is characterized by comprising the following raw materials in percentage by mass: 2 to 30 percent of Nb, 0.1 to 0.5 percent of Hf and the balance of Cu.
6. The thermal shock resistant copper alloy material for the rocket engine is characterized by comprising the following preparation raw materials in percentage by mass: 0.06-0.6% of Zr, 2-30% of Nb, 0.1-0.5% of Hf and the balance of Cu.
7. The thermal shock resistant copper alloy material for the rocket engine is characterized by comprising the following raw materials in percentage by mass: 0.06-0.6% of Zr, 2-30% of Nb and the balance of Cu.
8. The thermal shock resistant copper alloy material for the rocket engine is characterized by comprising the following raw materials in percentage by mass: 0.06-0.6% of Zr, 0.1-0.9% of Ta, 2-30% of Nb, 0.1-0.5% of Hf and the balance of Cu or 0.1-0.9% of Ta, 2-30% of Nb, 0.1-0.5% of Hf and the balance of Cu.
9. The thermal shock resistant copper alloy material for the rocket engine is characterized by comprising the following preparation raw materials in percentage by mass: 0.06-0.6% of Zr, 0.1-0.9% of Ta, 2-30% of Nb and the balance of Cu.
10. A method for producing a thermal shock resistant copper alloy material for a rocket engine as recited in any one of claims 1 to 9, comprising the steps of:
s1: mixing the alloy elements of the preparation raw materials according to the relation of mass percentage, and then pressing into an electrode;
s2: placing the electrode in a vacuum electron beam melting furnace under the vacuum degree of less than 3 x 10 -2 Smelting for 1-3 times under the condition of Pa to obtain a semi-finished product ingot; the current of an electron beam gun of the vacuum electron beam melting furnace is 2.0A-3.0A, and the melting speed is 10 mm/min-30 mm/min;
s3: placing the semi-finished cast ingot in a vacuum consumable arc furnace, and keeping the vacuum degree less than 5 multiplied by 10 -2 Smelting for 1-3 times under the condition of Pa to obtain a copper alloy ingot; the current of the vacuum consumable arc melting is 2 KA-8 KA, and the melting voltage is 25V-35V;
s4: carrying out solution treatment on the copper alloy cast ingot for 4-10h at the temperature of 800-1000 ℃;
s5: forging the copper alloy ingot after the solution treatment at the temperature of 700-900 ℃ to obtain a copper alloy bar blank:
s6: making the copper alloy bar blank in vacuum degree less than 2X 10 -2 Carrying out solid solution aging treatment at 400-600 ℃ under the condition of Pa; then forging the copper alloy bar blank subjected to aging treatment at the temperature of 600-800 ℃ to obtain a copper alloy forging blank:
s7: the copper alloy forging stock is processed in vacuum degree less than 2 x 10 -2 And (3) carrying out solution aging under the condition of Pa, wherein the aging temperature is 400-600 ℃, and obtaining the heat-resistant and impact-resistant copper alloy material for the rocket engine.
CN202211174627.XA 2022-09-26 2022-09-26 Thermal shock resistant copper alloy material for rocket engine and preparation method thereof Pending CN115612888A (en)

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TW200702458A (en) * 2005-03-28 2007-01-16 Sumitomo Metal Ind Copper alloy and process for producing the same
JP2008163439A (en) * 2007-01-05 2008-07-17 Sumitomo Light Metal Ind Ltd Copper alloy material and method for producing the same, and electrode member of welding equipment
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