CN115466875A - High-strength high-conductivity copper alloy material for rocket engine and preparation method thereof - Google Patents

High-strength high-conductivity copper alloy material for rocket engine and preparation method thereof Download PDF

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CN115466875A
CN115466875A CN202211174630.1A CN202211174630A CN115466875A CN 115466875 A CN115466875 A CN 115466875A CN 202211174630 A CN202211174630 A CN 202211174630A CN 115466875 A CN115466875 A CN 115466875A
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copper alloy
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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
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    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/02—Compacting only
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/10—Sintering only
    • 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
    • C22F1/08—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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Abstract

The invention discloses a high-strength high-conductivity copper alloy material for a rocket engine and a preparation method thereof, belongs to the technical field of alloy preparation, and is used for solving the technical problem that the existing copper alloy material is difficult to have high strength and high thermal conductivity at high temperature. The high-temperature softening resistance temperature of the copper alloy is greatly improved through the multi-element alloying of elements such as chromium, zirconium, tantalum, niobium, hafnium, vanadium, rhenium, yttrium and the like and the proper proportion, the plastic-brittle transition temperature of the copper alloy is obviously reduced, and the high-temperature strength and the high-temperature softening resistance of the alloy are greatly improved through solid solution strengthening and aging strengthening; the copper alloy material for the rocket engine prepared by the invention still has excellent performances of high strength, high toughness and the like at the temperature of 196 ℃ below zero; meanwhile, the alloy has high strength, high conductivity, high temperature resistance and excellent high temperature softening resistance; the alloy can be used for various rocket engines, and can also be widely used in the fields of high-speed rail transit, electronic communication, spot welding electrodes, lead frame materials, the inner wall of a combustion chamber of a rocket engine and the like.

Description

High-strength high-conductivity 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 high-strength copper alloy material for a rocket engine and a preparation method thereof.
Background
Copper, the metal material used for the first time in history, is pure copper widely used in various industrial fields because of its outstanding electric and thermal conductivity, but pure copper has low strength and can be greatly improved after cold hardening, but has an elongation of only about 2%, and its high-temperature softening resistance is also low. Along with the continuous improvement of the requirements of the industrial field on the performance of materials, the research and development of copper alloy materials with high strength and high conductivity are more and more attracting attention. The high-strength high-conductivity high-heat-resistance copper alloy is a copper alloy capable of stably working at the temperature of more than 300 ℃, and is mainly applied to the fields of high-speed rail transit, spot welding electrodes, electronic communication, lead frame materials, rocket engine combustion chamber inner walls and the like at present. 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-Ag alloy has excellent electric and heat conducting performance and creep deformation performance, but has low mechanical performance and high temperature softening resistance of about 400 ℃. Cu-Al 2 O 3 The alloy has excellent mechanical property, electric conduction and heat conduction performance and high temperature resistance, and the high-temperature softening temperature resistance is also higher, but the alloy is mainly prepared by a powder metallurgy method at present, the preparation process is complex, the impurity content is high, the material is not compact, and the industrial application is difficult to realize in a short time. The strength of Cu-Ni-Si alloys is high, but the electrical conductivity is low. The Cu-Cr-Zr alloy has higher strength and conductivity, but has low high-temperature mechanical property, creep resistance and high-temperature softening resistance. After decades of development, the high-strength and high-conductivity copper alloy forms a batch of products with excellent high-temperature performance in the corresponding application field. The active heat-resistant copper alloy has higher tensile strength at 500 ℃, and the tensile strength is obviously reduced at higher temperature.
With the rapid development of the fields of aerospace, microelectronics, communication, electromechanics and the like, the harsh service conditions also put new requirements on the performance of the high-strength, high-conductivity and high-heat-resistance copper alloy. The copper alloy material on the inner wall of the rocket engine combustion chamber needs to be in service at high temperature for a long time, the inner side and the outer side of the material are respectively in a high-temperature gas environment and a low-temperature environment, and the used fuel and combustion improver have corrosiveness, so that the material is extremely seriously corroded under high-temperature high-pressure and high-speed gas erosion, and therefore the copper alloy material in service needs to have higher high-temperature strength, higher thermal conductivity, higher high-temperature softening resistance temperature, high-strength and high toughness at low temperature and excellent high-temperature comprehensive performance.
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 problems that the existing copper alloy is difficult to have high strength and high toughness in a low-temperature region and high strength, high thermal conductivity and high-temperature softening resistance in a high-temperature region.
In order to achieve the above-mentioned object, the invention is realized by adopting the following technical scheme:
the invention discloses a high-strength and high-conductivity copper alloy material for a rocket engine, which comprises the following raw materials in percentage by mass: 0.2 to 1.1 percent of Cr, 0.08 to 1.0 percent of Zr, 5 to 15 percent of Ta, 0.1 to 25 percent of Nb, 0.1 to 3.5 percent of Hf, 0.05 to 0.1 percent of V, 0.05 to 0.1 percent of Re, 0.03 to 0.1 percent of Y and the balance of Cu.
The invention discloses a high-strength and high-conductivity copper alloy material for a rocket engine, which comprises the following raw materials in percentage by mass: 0.2 to 1.1 percent of Cr, 0.08 to 1.0 percent of Zr, 0.05 to 0.1 percent of V, 0.05 to 0.1 percent of Re, 0.03 to 0.1 percent of Y and the balance of Cu.
The invention discloses a high-strength and high-conductivity copper alloy material for a rocket engine, which comprises the following raw materials in percentage by mass: 0.2 to 1.1 percent of Cr, 0.08 to 1.0 percent of Zr, 5 to 15 percent of Ta, 0.1 to 25 percent of Nb and the balance of Cu.
The invention discloses a copper alloy material for a rocket engine, which comprises the following raw materials in percentage by mass: 0.2 to 1.1 percent of Cr, 0.08 to 1.0 percent of Zr, 5 to 15 percent of Ta and the balance of Cu.
The invention discloses a copper alloy material for a rocket engine, which comprises the following raw materials in percentage by mass: 0.2 to 1.1 percent of Cr, 0.08 to 1.0 percent of Zr, 0.1 to 25 percent of Nb, 0.03 to 0.1 percent of Y and the balance of Cu.
The invention discloses a copper alloy material for a rocket engine, which comprises the following raw materials in percentage by mass: 0.2 to 1.1 percent of Cr, 0.08 to 1.0 percent of Zr, 0.1 to 25 percent of Nb and the balance of Cu.
The invention discloses a copper alloy material for a rocket engine, which comprises the following raw materials in percentage by mass: 0.1 to 25 percent of Nb and the balance of Cu.
The invention discloses a copper alloy material for a rocket engine, which comprises the following raw materials in percentage by mass: 0.2 to 1.1 percent of Cr, 0.1 to 25 percent of Nb and the balance of Cu.
The invention discloses a copper alloy material for a rocket engine, which comprises the following raw materials in percentage by mass: 0.08 to 1.0 percent of Zr, 0.1 to 25 percent of Nb and the balance of Cu.
The invention discloses a copper alloy material for a rocket engine, which comprises the following raw materials in percentage by mass: 0.08 to 1.0 percent of Zr, 0.1 to 25 percent of Nb, 0.1 to 3.5 percent of Hf and the balance of Cu.
The invention also discloses a preparation method of the copper alloy material for the rocket engine, which comprises the following steps:
s1: mixing the alloy element powder of the preparation raw materials according to the mass percentage relationship, and then pressing and sintering to prepare the electrode; (ii) a
S2: placing the electrode in a vacuum consumable arc furnace in vacuumDegree less than 5 x 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 3 KA-10 KA, and the melting voltage is 25V-35V;
s3: carrying out solid solution treatment on the copper alloy cast ingot for 3-11h at the temperature of 800-1000 ℃;
s4: forging the copper alloy ingot after the solution treatment at the temperature of 750-1000 ℃ to obtain a copper alloy bar blank:
s5: making the copper alloy bar blank in vacuum degree less than 2X 10 -2 And (3) carrying out solution aging under the condition of Pa, wherein the aging temperature is 400-600 ℃, and then carrying out cold rolling to obtain the high-strength and high-conductivity copper alloy material for the rocket engine.
Compared with the prior art, the invention has the following beneficial effects:
the invention discloses a high-strength high-conductivity copper alloy material for a rocket engine, which greatly improves the high-temperature softening resistance temperature of the copper alloy, obviously reduces the plastic-brittle transition temperature of the copper alloy and greatly improves the high-temperature strength and the high-temperature softening resistance of the alloy through the multi-element alloying of elements such as chromium, zirconium, tantalum, niobium, hafnium, vanadium, rhenium, yttrium and the like and proper proportion; the copper alloy material for the rocket engine prepared by the invention still has excellent performances of high strength, high toughness and the like at the temperature of 196 ℃ below zero; meanwhile, the alloy has the advantages of high strength, high conductivity, high temperature resistance and the like; the alloy can be used for various rocket engines, and also can be widely used in the fields of high-speed rail transit, electronic communication, spot welding electrodes, lead frame materials, inner walls of combustion chambers of rocket engines and the like
The invention also discloses a preparation method of the copper alloy material for the rocket engine, compared with the prior art, the method is simple and environment-friendly, and the material prepared by the method has the advantages of high purity, uniform and fine microstructure, and wide application prospect.
Drawings
Fig. 1 is a microstructure diagram of the high-strength and high-conductivity copper alloy material for rocket power 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, "" containing, "" having, "or similar language, shall mean" consisting of … … "and" consisting essentially of … …, "e.g.," A comprises a "shall mean" A comprises a and the other "and" A comprises a only.
In this context, for the sake of brevity, not all possible combinations of features in the various embodiments or examples are described. Therefore, the respective features in the respective embodiments or examples may be arbitrarily combined as long as there is no contradiction between the combinations of the features, and all the 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.
The following examples use instrumentation conventional in the art. The experimental procedures, in which specific conditions are not noted in the following examples, are generally carried out under conventional conditions or conditions recommended by the manufacturers. The various starting materials used in the examples which follow, unless otherwise indicated, are conventional commercial products having specifications which are conventional in the art. 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 high-strength and high-conductivity copper alloy material for a rocket engine comprises the following steps:
the alloy element powder of the preparation raw material of the high-strength and high-conductivity copper alloy material for the rocket engine comprises the following components in percentage by mass: 0.2 percent of Cr0.08 percent, 0.1 percent of Zr0 percent, 0.1 percent of V, 0.1 percent of Re0.03 percent of Y and the balance of Cu;
step 1: mixing the alloy element powder of the preparation raw materials according to the mass percentage relationship, and then pressing and sintering to prepare the electrode;
and 2, step: 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 3KA, and the melting voltage is 25V;
and step 3: carrying out solid solution treatment on the copper alloy cast ingot for 3h at the temperature of 800 ℃;
and 4, step 4: forging the copper alloy cast ingot subjected to the solution treatment at the temperature of 750 ℃ to obtain a copper alloy bar blank:
and 5: making the copper alloy bar blank in vacuum degree less than 2X 10 -2 And (3) carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 400 ℃, and then carrying out cold rolling to obtain the high-strength and high-conductivity copper alloy material for the rocket engine.
The microstructure of the copper alloy material for rocket motors prepared in this example is shown in fig. 1, and it can be seen from fig. 1 that the coarse dendritic structures are completely crushed and refined. 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 in the embodiment has the room temperature tensile strength of 785-879 MPa and the elongation after fracture of 15%; the tensile strength is 1030MPa and the elongation after fracture is 10 percent under the extremely low temperature condition of-196 ℃; the tensile strength at 500 ℃ is 359MPa, and the elongation after fracture is 17%; the room temperature thermal conductivity is 260W/m.K. After softening at 970 ℃ and keeping the temperature for 30 minutes at high temperature, the strength of the copper alloy material Wen Kangla is 395MPa, the elongation after fracture is 10 percent, the tensile strength at 500 ℃ is 189MPa, the elongation after fracture is 11 percent, and the thermal conductivity is 232W/m.K.
Example 2
High-strength rocket engine a method for preparing a copper-conducting alloy material, the method comprises the following steps:
the alloy element powder of the preparation raw material of the high-strength and high-conductivity copper alloy material for the rocket engine comprises the following components in percentage by mass: 1.1 percent of Cr1.0 percent of Zr1.0 percent, 25 percent of Nb, 0.1 percent of Y and the balance of Cu;
step 1: mixing the alloy element powder of the preparation raw materials according to the mass percentage relationship, and then pressing and sintering to prepare an electrode;
step 2: 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 10KA, and the melting voltage is 35V;
and 3, step 3: carrying out solution treatment on the copper alloy cast ingot for 11h at the temperature of 1000 ℃;
and 4, step 4: forging the copper alloy cast ingot subjected to the solution treatment at the temperature of 1000 ℃ to obtain a copper alloy bar blank:
and 5: making the copper alloy bar blank in vacuum degree less than 2X 10 -2 And (3) carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 600 ℃, and then carrying out cold rolling to obtain the high-strength and high-conductivity 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 23%; the tensile strength is 1065MPa and the elongation after fracture is 15% under the condition of extremely low temperature of-196 ℃; tensile strength at 500 ℃ of 387MPa and elongation after fracture of 25%; the room temperature thermal conductivity is 278W/m.K. After softening at 970 ℃ and keeping the temperature for 30 minutes, the strength of the copper alloy material Wen Kangla is 437MPa, the elongation after fracture is 13 percent, the tensile strength at 500 ℃ is 213MPa, the elongation after fracture is 15 percent, and the heat conductivity is 261W/m.K.
Example 3
A preparation method of a high-strength and high-conductivity copper alloy material for a rocket engine comprises the following steps:
the alloy element powder of the preparation raw material of the high-strength and high-conductivity copper alloy material for the rocket engine comprises the following components in percentage by mass: 0.65% of Cr0.54% of Zr0.54% of Nb12.55% of Y, and the balance of Cu;
step 1: mixing the alloy element powder of the preparation raw materials according to the mass percentage relationship, and then pressing and sintering to prepare the electrode;
step 2: 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 6.5KA, and the melting voltage is 30V;
and step 3: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 4, step 4: forging the copper alloy cast ingot subjected to the solution treatment at the temperature of 875 ℃ to obtain a copper alloy bar blank:
and 5: making the copper alloy bar blank be less than 2X 10 vacuum degree -2 And (3) carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃, and then carrying out cold rolling to obtain the high-strength and high-conductivity 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 789MPa and the elongation after fracture of 20%; the tensile strength is 1055MPa and the elongation after fracture is 13% under the condition of extremely low temperature of-196 ℃; the tensile strength at 500 ℃ is 379MPa, and the elongation after fracture is 22%; the thermal conductivity at room temperature is 265W/m.K. After softening at 970 ℃ and keeping the temperature for 30 minutes at high temperature, the strength of the copper alloy material Wen Kangla is 403MPa, the elongation after fracture is 11 percent, the tensile strength at 500 ℃ is 206MPa, the elongation after fracture is 13 percent, and the thermal conductivity is 139W/m.K.
Example 4
A preparation method of a high-strength and high-conductivity copper alloy material for a rocket engine comprises the following steps:
the alloy element powder of the preparation raw material of the high-strength and high-conductivity copper alloy material for the rocket engine comprises the following components in percentage by mass: 0.2 percent of Cr0.08 percent of Zr0.08 percent of Ta5 percent of Nb0.1 percent of Cu;
step 1: mixing the alloy element powder of the preparation raw materials according to the mass percentage relationship, and then pressing and sintering to prepare the electrode;
step 2: 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 6.5KA, and the melting voltage is 30V;
and 3, step 3: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 4, step 4: forging the copper alloy ingot subjected to solution treatment at the temperature of 875 ℃ to obtain a copper alloy bar blank:
and 5: making the copper alloy bar blank be less than 2X 10 vacuum degree -2 And (3) carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃, and then carrying out cold rolling to obtain the high-strength and high-conductivity 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 785MPa and the elongation after fracture of 15%; the tensile strength is 1030MPa and the elongation after fracture is 10 percent under the extremely low temperature condition of-196 ℃; tensile strength at 500 ℃ of 387MPa and elongation after fracture of 25%; the room temperature thermal conductivity is 278W/m.K. After softening at 970 ℃ and keeping the temperature for 30 minutes, the strength of the copper alloy material Wen Kangla is 437MPa, the elongation after fracture is 13 percent, the tensile strength at 500 ℃ is 213MPa, the elongation after fracture is 15 percent, and the heat conductivity is 261W/m.K.
Example 5
A preparation method of a high-strength and high-conductivity copper alloy material for a rocket engine comprises the following steps:
the alloy element powder of the preparation raw material of the high-strength and high-conductivity copper alloy material for the rocket engine comprises the following components in percentage by mass: 1.1 percent of Cr1, 1.0 percent of Zr0 percent, 5 percent of Ta, 25 percent of Nb and the balance of Cu;
step 1: mixing the alloy element powder of the preparation raw materials according to the mass percentage relationship, and then pressing and sintering to prepare an electrode;
step 2: 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 6.5KA, and the melting voltage is 30V;
and step 3: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 4, step 4: forging the copper alloy ingot subjected to solution treatment at the temperature of 875 ℃ to obtain a copper alloy bar blank:
and 5: making the copper alloy bar blank in vacuum degree less than 2X 10 -2 And (3) carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃, and then carrying out cold rolling to obtain the high-strength and high-conductivity 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 23%; the tensile strength is 1065MPa and the elongation after fracture is 15% under the condition of extremely low temperature of-196 ℃; the tensile strength at 500 ℃ is 359MPa, and the elongation after fracture is 17%; the room temperature thermal conductivity is 260W/m.K. After softening at 970 ℃ for 30 minutes at high temperature, the strength of the copper alloy material Wen Kangla is 395MPa, the elongation after fracture is 10 percent, the tensile strength at 500 ℃ is 189MPa, the elongation after fracture is 11 percent, and the thermal conductivity is 232W/m.K.
Example 6
A preparation method of a high-strength and high-conductivity copper alloy material for a rocket engine comprises the following steps:
the alloy element powder of the preparation raw material of the high-strength and high-conductivity copper alloy material for the rocket engine comprises the following components in percentage by mass: cr0.65%, zr0.54%, ta10%, nb12.55%, and the balance of Cu;
step 1: mixing the alloy element powder of the preparation raw materials according to the mass percentage relationship, and then pressing and sintering to prepare the electrode;
step 2: 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 6.5KA, and the melting voltage is 30V;
and step 3: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 4, step 4: forging the copper alloy ingot subjected to solution treatment at the temperature of 875 ℃ to obtain a copper alloy bar blank:
and 5: making the copper alloy bar blank be less than 2X 10 vacuum degree -2 And (3) carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃, and then carrying out cold rolling to obtain the high-strength and high-conductivity 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 23%; the tensile strength is 1065MPa and the elongation after fracture is 15% under the condition of extremely low temperature of-196 ℃; the tensile strength at 500 ℃ is 359MPa, and the elongation after fracture is 17%; the room temperature thermal conductivity is 260W/m.K. After softening at 970 ℃ for 30 minutes at high temperature, the strength of the copper alloy material Wen Kangla is 395MPa, the elongation after fracture is 10 percent, the tensile strength at 500 ℃ is 189MPa, the elongation after fracture is 11 percent, and the thermal conductivity is 232W/m.K.
Example 7
A preparation method of a high-strength and high-conductivity copper alloy material for a rocket engine comprises the following steps:
the alloy element powder of the preparation raw material of the high-strength and high-conductivity copper alloy material for the rocket engine comprises the following components in percentage by mass: 0.2 percent of Cr0.08 percent of Zr0.08 percent of Ta5 percent, and the balance of Cu;
step 1: mixing the alloy element powder of the preparation raw materials according to the mass percentage relationship, and then pressing and sintering to prepare the electrode;
step 2: 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 6.5KA, and the melting voltage is 30V;
and step 3: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 4, step 4: forging the copper alloy cast ingot subjected to the solution treatment at the temperature of 875 ℃ to obtain a copper alloy bar blank:
and 5: making the copper alloy bar blank be less than 2X 10 vacuum degree -2 And (3) carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃, and then carrying out cold rolling to obtain the high-strength and high-conductivity 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 799MPa and the elongation after fracture of 16%; the tensile strength is 1045MPa and the elongation after fracture is 13% under the condition of extremely low temperature of-196 ℃; the tensile strength at 500 ℃ is 365MPa, and the elongation after fracture is 21%; the room temperature thermal conductivity is 266W/m.K. After softening at 970 ℃ and keeping the temperature for 30 minutes, the strength of the copper alloy material Wen Kangla is 406MPa, the elongation after fracture is 12 percent, the tensile strength at 500 ℃ is 196MPa, the elongation after fracture is 13 percent, and the thermal conductivity is 245W/m.K.
Example 8
A preparation method of a high-strength and high-conductivity copper alloy material for a rocket engine comprises the following steps:
the alloy element powder of the preparation raw material of the high-strength and high-conductivity copper alloy material for the rocket engine comprises the following components in percentage by mass: 1.1 percent of Cr1, 1.0 percent of Zr0 percent, 15 percent of Ta and the balance of Cu;
step 1: mixing the alloy element powder of the preparation raw materials according to the mass percentage relationship, and then pressing and sintering to prepare the electrode;
step 2: 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 6.5KA, and the melting voltage is 30V;
and step 3: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 4, step 4: forging the copper alloy ingot subjected to solution treatment at the temperature of 875 ℃ to obtain a copper alloy bar blank:
and 5: making the copper alloy bar blank in vacuum degree less than 2X 10 -2 And (3) carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃, and then carrying out cold rolling to obtain the high-strength and high-conductivity 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 869MPa and the elongation after fracture of 20 percent; the tensile strength is 1055MPa and the elongation after fracture is 13% under the condition of extremely low temperature of-196 ℃; the tensile strength at 500 ℃ is 367MPa, and the elongation after fracture is 22%; the room temperature thermal conductivity was 270W/m.K. After softening at 970 ℃ and keeping the temperature for 30 minutes at high temperature, the strength of the copper alloy material Wen Kangla is 425MPa, the elongation after fracture is 10 percent, the tensile strength at 500 ℃ is 200MPa, the elongation after fracture is 13 percent, and the thermal conductivity is 235W/m.K.
Example 9
A preparation method of a high-strength and high-conductivity copper alloy material for a rocket engine comprises the following steps:
the alloy element powder of the preparation raw material of the high-strength and high-conductivity copper alloy material for the rocket engine comprises the following components in percentage by mass: 0.65% of Cr0.54%, zr0.54%, 10% of Ta and the balance of Cu;
step 1: mixing the alloy element powder of the preparation raw materials according to the mass percentage relationship, and then pressing and sintering to prepare the electrode;
step 2: 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 6.5KA, and the melting voltage is 30V;
and step 3: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 4, step 4: forging the copper alloy ingot subjected to solution treatment at the temperature of 875 ℃ to obtain a copper alloy bar blank:
and 5: making the copper alloy bar blank be less than 2X 10 vacuum degree -2 And (3) carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃, and then carrying out cold rolling to obtain the high-strength and high-conductivity 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 800MPa and the elongation after fracture of 16%; the tensile strength is 1033MPa and the elongation after fracture is 11 percent under the condition of extremely low temperature of-196 ℃; the tensile strength at 500 ℃ is 367MPa, and the elongation after fracture is 20%; the room temperature thermal conductivity was 270W/m.K. After softening at 970 ℃ and keeping the temperature for 30 minutes, the strength of the copper alloy material Wen Kangla is 406MPa, the elongation after fracture is 12 percent, the tensile strength at 500 ℃ is 202MPa, the elongation after fracture is 13 percent, and the heat conductivity is 239W/m.K.
Example 10
A preparation method of a high-strength and high-conductivity copper alloy material for a rocket engine comprises the following steps:
the alloy element powder of the preparation raw material of the high-strength and high-conductivity copper alloy material for the rocket engine comprises the following components in percentage by mass: 0.2 percent of Cr0.08 percent, 0.1 percent of Zr0.08 percent of Nb0.03 percent of Y, and the balance of Cu;
step 1: mixing the alloy element powder of the preparation raw materials according to the mass percentage relationship, and then pressing and sintering to prepare the electrode;
step 2: 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 6.5KA, and the melting voltage is 30V;
and step 3: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 4, step 4: forging the copper alloy cast ingot subjected to the solution treatment at the temperature of 875 ℃ to obtain a copper alloy bar blank:
and 5: making the copper alloy bar blank in vacuum degree less than 2X 10 -2 And (3) carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃, and then carrying out cold rolling to obtain the high-strength and high-conductivity 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 799MPa and the elongation after fracture of 18 percent; the tensile strength is 1053MPa and the elongation after fracture is 13% under the condition of extremely low temperature of-196 ℃; tensile strength at 500 ℃ of 368MPa and elongation after fracture of 21%; the room temperature thermal conductivity was 270W/m.K. After softening at 970 ℃ and keeping the temperature for 30 minutes at high temperature, the strength of the copper alloy material Wen Kangla is 412MPa, the elongation after fracture is 12 percent, the tensile strength at 500 ℃ is 1197MPa, the elongation after fracture is 13 percent, and the thermal conductivity is 245W/m.K.
Example 11
A preparation method of a high-strength and high-conductivity copper alloy material for a rocket engine comprises the following steps:
the alloy element powder of the preparation raw material of the high-strength and high-conductivity copper alloy material for the rocket engine comprises the following components in percentage by mass: 1.1% of Cr1.0%, zr1.0%, 25% of Nb, 0.1% of Y and the balance of Cu;
step 1: mixing the alloy element powder of the preparation raw materials according to the mass percentage relationship, and then pressing and sintering to prepare the electrode;
step 2: 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 6.5KA, and the melting voltage is 30V;
and step 3: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 4, step 4: forging the copper alloy ingot subjected to solution treatment at the temperature of 875 ℃ to obtain a copper alloy bar blank:
and 5: making the copper alloy bar blank be less than 2X 10 vacuum degree -2 And (3) carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃, and then carrying out cold rolling to obtain the high-strength and high-conductivity 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 855MPa and the elongation after fracture of 17 percent; the tensile strength is 1053MPa and the elongation after fracture is 13% under the condition of extremely low temperature of-196 ℃; tensile strength at 500 ℃ is 375MPa, and elongation after fracture is 22%; the thermal conductivity at room temperature is 275W/m.K. After softening at 970 ℃ for 30 minutes at high temperature, the strength of the copper alloy material Wen Kangla is 405MPa, the elongation after fracture is 12 percent, the tensile strength at 500 ℃ is 205MPa, the elongation after fracture is 12 percent, and the heat conductivity is 257W/m.K.
Example 12
A preparation method of a high-strength and high-conductivity copper alloy material for a rocket engine comprises the following steps:
the alloy element powder of the preparation raw material of the high-strength and high-conductivity copper alloy material for the rocket engine comprises the following components in percentage by mass: 0.65% of Cr0.54%, 0.54% of Zr0.54%, 12.55% of Nb0.65% of Y, and the balance of Cu;
step 1: mixing the alloy element powder of the preparation raw materials according to the mass percentage relationship, and then pressing and sintering to prepare an electrode;
step 2: 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 6.5KA, and the melting voltage is 30V;
and step 3: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 4, step 4: forging the copper alloy cast ingot subjected to the solution treatment at the temperature of 875 ℃ to obtain a copper alloy bar blank:
and 5: 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 ℃, and then carrying out cold rolling to obtain the high-strength high-conductivity copper alloy material for the rocket engine.
The copper alloy material for the rocket engine prepared in the embodiment has the tensile strength at room temperature of 792MPa and the elongation after fracture of 20%; the tensile strength is 1020MPa and the elongation after fracture is 11 percent under the condition of extremely low temperature of-196 ℃; tensile strength at 500 ℃ of 377MPa and elongation after fracture of 21%; the room temperature thermal conductivity is 265W/m.K. After softening at 970 ℃ and keeping the temperature for 30 minutes at high temperature, the strength of the copper alloy material Wen Kangla is 409MPa, the elongation after fracture is 11 percent, the tensile strength at 500 ℃ is 206MPa, the elongation after fracture is 13 percent, and the thermal conductivity is 246W/m.K.
Example 13
A preparation method of a high-strength and high-conductivity copper alloy material for a rocket engine comprises the following steps:
the alloy element powder of the preparation raw material of the high-strength and high-conductivity copper alloy material for the rocket engine comprises the following components in percentage by mass: 0.2 percent of Cr0.08 percent, 0.1 percent of ZrNb0.1 percent and the balance of Cu;
step 1: mixing the alloy element powder of the preparation raw materials according to the mass percentage relationship, and then pressing and sintering to prepare the electrode;
step 2: 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 6.5KA, and the melting voltage is 30V;
and 3, step 3: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 4, step 4: forging the copper alloy ingot subjected to solution treatment at the temperature of 875 ℃ to obtain a copper alloy bar blank:
and 5: making the copper alloy bar blank in vacuum degree less than 2X 10 -2 And (3) carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃, and then carrying out cold rolling to obtain the high-strength and high-conductivity copper alloy material for the rocket engine.
The copper alloy material for the rocket engine prepared in the embodiment has tensile strength at room temperature of 836MPa and elongation after fracture of 22%; the tensile strength is 1059MPa and the elongation after fracture is 12% under the condition of extremely low temperature of-196 ℃; tensile strength at 500 ℃ of 362MPa and elongation after fracture of 19%; the room temperature thermal conductivity was 270W/m.K. After softening at 970 ℃ and keeping the temperature for 30 minutes, the strength of the copper alloy material Wen Kangla is 413MPa, the elongation after fracture is 12%, the tensile strength at 500 ℃ is 207MPa, the elongation after fracture is 13%, and the thermal conductivity is 261W/m.K.
Example 14
A preparation method of a high-strength and high-conductivity copper alloy material for a rocket engine comprises the following steps:
the alloy element powder of the preparation raw material of the high-strength and high-conductivity copper alloy material for the rocket engine comprises the following components in percentage by mass: 1.1 percent of Cr1, 1.0 percent of Zr0 percent, 25 percent of Nb and the balance of Cu;
step 1: mixing the alloy element powder of the preparation raw materials according to the mass percentage relationship, and then pressing and sintering to prepare the electrode;
step 2: the electrode is placed in a vacuum consumable arc furnace with small vacuum degreeAt 5X 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 6.5KA, and the melting voltage is 30V;
and step 3: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 4, step 4: forging the copper alloy ingot subjected to solution treatment at the temperature of 875 ℃ to obtain a copper alloy bar blank:
and 5: 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 ℃, and then carrying out cold rolling to obtain the high-strength high-conductivity 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 833MPa and the elongation after fracture of 15%; the tensile strength is 1039MPa and the elongation after fracture is 115% under the extremely low temperature condition of-196 ℃; the tensile strength at 500 ℃ is 385MPa, and the elongation after fracture is 22 percent; the room temperature thermal conductivity was 270W/m.K. After softening at 970 ℃ for 30 minutes at high temperature, the strength of the copper alloy material Wen Kangla is 425MPa, the elongation after fracture is 12 percent, the tensile strength at 500 ℃ is 199MPa, the elongation after fracture is 13 percent, and the heat conductivity coefficient is 237W/m.K.
Example 15
A preparation method of a high-strength and high-conductivity copper alloy material for a rocket engine comprises the following steps:
the alloy element powder of the preparation raw material of the high-strength and high-conductivity copper alloy material for the rocket engine comprises the following components in percentage by mass: 0.65% of Cr0.54%, 0.54% of Zr0.55%, 12.55% of Nbs, and the balance of Cu;
step 1: mixing the alloy element powder of the preparation raw materials according to the mass percentage relationship, and then pressing and sintering to prepare the electrode;
step 2: 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 6.5KA, and the melting voltage is 30V;
and step 3: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 4, step 4: forging the copper alloy ingot subjected to solution treatment at the temperature of 875 ℃ to obtain a copper alloy bar blank:
and 5: making the copper alloy bar blank in vacuum degree less than 2X 10 -2 And (3) carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃, and then carrying out cold rolling to obtain the high-strength and high-conductivity 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 839MPa and the elongation after fracture of 20%; the tensile strength is 1051MPa and the elongation after fracture is 12% under the condition of extremely low temperature of-196 ℃; the tensile strength at 500 ℃ is 379MPa, and the elongation after fracture is 20%; the room temperature thermal conductivity was 270W/m.K. After softening at 970 ℃ and keeping the temperature for 30 minutes, the strength of the copper alloy material Wen Kangla is 412MPa, the elongation after fracture is 11 percent, the tensile strength at 500 ℃ is 205MPa, the elongation after fracture is 12 percent, and the thermal conductivity is 247W/m.K.
Example 16
A preparation method of a high-strength and high-conductivity copper alloy material for a rocket engine comprises the following steps:
the alloy element powder of the preparation raw material of the high-strength and high-conductivity copper alloy material for the rocket engine comprises the following components in percentage by mass: 0.65% of Cr0.55% of Zr0.55% of Nb0.1% of Cu in balance;
step 1: mixing the alloy element powder of the preparation raw materials according to the mass percentage relationship, and then pressing and sintering to prepare the electrode;
and 2, step: 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 6.5KA, and the melting voltage is 30V;
and step 3: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 4, step 4: forging the copper alloy ingot subjected to solution treatment at the temperature of 875 ℃ to obtain a copper alloy bar blank:
and 5: making the copper alloy bar blank in vacuum degree less than 2X 10 -2 The solution aging is carried out under the condition of Pa,the aging temperature is 500 ℃, and then the high-strength and high-conductivity copper alloy material for the rocket engine is obtained by cold rolling.
The copper alloy material for the rocket engine prepared in the embodiment has the room-temperature tensile strength of 786MPa and the elongation after fracture of 23%; the tensile strength is 1033MPa and the elongation after fracture is 13 percent under the condition of extremely low temperature of-196 ℃; the tensile strength at 500 ℃ is 360MPa, and the elongation after fracture is 25%; the thermal conductivity at room temperature is 275W/m.K. After softening at 970 ℃ for 30 minutes at high temperature, the strength of the copper alloy material Wen Kangla is 397MPa, the elongation after fracture is 13%, the tensile strength at 500 ℃ is 189MPa, the elongation after fracture is 15%, and the heat conductivity coefficient is 259W/m.K.
Example 17
A preparation method of a high-strength and high-conductivity copper alloy material for a rocket engine comprises the following steps:
the alloy element powder of the preparation raw material of the high-strength and high-conductivity copper alloy material for the rocket engine comprises the following components in percentage by mass: nb25%, and the balance being Cu;
step 1: mixing the alloy element powder of the preparation raw materials according to the mass percentage relationship, and then pressing and sintering to prepare the electrode;
step 2: 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 6.5KA, and the melting voltage is 30V;
and step 3: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 4, step 4: forging the copper alloy cast ingot subjected to the solution treatment at the temperature of 875 ℃ to obtain a copper alloy bar blank:
and 5: making the copper alloy bar blank in vacuum degree less than 2X 10 -2 And (3) carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃, and then carrying out cold rolling to obtain the high-strength and high-conductivity 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 870MPa and the elongation after fracture of 20 percent; the tensile strength is 1060MPa and the elongation after fracture is 13 percent under the condition of extremely low temperature of-196 ℃; tensile strength at 500 ℃ of 382MPa and elongation after fracture of 23%; the thermal conductivity at room temperature is 2669W/m.K. After softening at 970 ℃ and keeping the temperature for 30 minutes, the strength of the copper alloy material Wen Kangla is 430MPa, the elongation after fracture is 12%, the tensile strength at 500 ℃ is 210MPa, the elongation after fracture is 13%, and the thermal conductivity is 249W/m.K.
Example 18
A preparation method of a high-strength and high-conductivity copper alloy material for a rocket engine comprises the following steps:
the alloy element powder of the preparation raw material of the high-strength and high-conductivity copper alloy material for the rocket engine comprises the following components in percentage by mass: nb12.55%, the balance being Cu;
step 1: mixing the alloy element powder of the preparation raw materials according to the mass percentage relationship, and then pressing and sintering to prepare the electrode;
step 2: 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 6.5KA, and the melting voltage is 30V;
and step 3: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 4, step 4: forging the copper alloy ingot subjected to solution treatment at the temperature of 875 ℃ to obtain a copper alloy bar blank:
and 5: making the copper alloy bar blank in vacuum degree less than 2X 10 -2 And (3) carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃, and then carrying out cold rolling to obtain the high-strength and high-conductivity 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 799MPa and the elongation after fracture of 21%; the tensile strength is 1037MPa and the elongation after fracture is 11 percent under the condition of extremely low temperature of-196 ℃; the tensile strength at 500 ℃ is 379MPa, and the elongation after fracture is 21%; the room temperature thermal conductivity was 270W/m.K. After softening at 970 ℃ and keeping the temperature for 30 minutes, the strength of the copper alloy material Wen Kangla is 399MPa, the elongation after fracture is 12 percent, the tensile strength at 500 ℃ is 198MPa, the elongation after fracture is 12 percent, and the heat conductivity coefficient is 239W/m.K.
Example 19
A preparation method of a high-strength and high-conductivity copper alloy material for a rocket engine comprises the following steps:
the alloy element powder of the preparation raw material of the high-strength and high-conductivity copper alloy material for the rocket engine comprises the following components in percentage by mass: 0.2 percent of Cr0.2 percent, 0.1 percent of Nb0.1 percent and the balance of Cu;
step 1: mixing the alloy element powder of the preparation raw materials according to the mass percentage relationship, and then pressing and sintering to prepare the electrode;
step 2: 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 6.5KA, and the melting voltage is 30V;
and step 3: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 4, step 4: forging the copper alloy ingot subjected to solution treatment at the temperature of 875 ℃ to obtain a copper alloy bar blank:
and 5: making the copper alloy bar blank in vacuum degree less than 2X 10 -2 And (3) carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃, and then carrying out cold rolling to obtain the high-strength and high-conductivity 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 17%; the tensile strength is 1039MPa and the elongation after fracture is 13 percent under the condition of extremely low temperature of-196 ℃; the tensile strength at 500 ℃ is 379MPa, and the elongation after fracture is 19%; the room temperature thermal conductivity is 270W/m.K. After softening at 970 ℃ and keeping the temperature for 30 minutes, the strength of the copper alloy material Wen Kangla is 425MPa, the elongation after fracture is 11%, the tensile strength at 500 ℃ is 195MPa, the elongation after fracture is 12%, and the heat conductivity is 256W/m.K.
Example 20
A preparation method of a high-strength and high-conductivity copper alloy material for a rocket engine comprises the following steps:
the alloy element powder of the preparation raw material of the high-strength and high-conductivity copper alloy material for the rocket engine comprises the following components in percentage by mass: 1.1 percent of Cr1, 25 percent of Nb and the balance of Cu;
step 1: mixing the alloy element powder of the preparation raw materials according to the mass percentage relationship, and then pressing and sintering to prepare the electrode;
and 2, step: 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 6.5KA, and the melting voltage is 30V;
and step 3: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 4, step 4: forging the copper alloy ingot subjected to solution treatment at the temperature of 875 ℃ to obtain a copper alloy bar blank:
and 5: making the copper alloy bar blank in vacuum degree less than 2X 10 -2 And (3) carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃, and then carrying out cold rolling to obtain the high-strength and high-conductivity 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 822MPa and the elongation after fracture of 21 percent; the tensile strength is 1039MPa and the elongation after fracture is 12 percent under the condition of extremely low temperature of-196 ℃; the tensile strength at 500 ℃ is 365MPa, and the elongation after fracture is 20%; the room temperature thermal conductivity is 270W/m.K. After softening at 970 ℃ and keeping the temperature for 30 minutes, the strength of the copper alloy material Wen Kangla is 435MPa, the elongation after fracture is 12 percent, the tensile strength at 500 ℃ is 206MPa, the elongation after fracture is 13 percent, and the heat conductivity is 257W/m.K.
Example 21
A preparation method of a high-strength and high-conductivity copper alloy material for a rocket engine comprises the following steps:
the alloy element powder of the preparation raw material of the high-strength and high-conductivity copper alloy material for the rocket engine comprises the following components in percentage by mass: 0.65% of Cr0, 12.55% of Nbs, and the balance of Cu;
step 1: mixing the alloy element powder of the preparation raw materials according to the mass percentage relationship, and then pressing and sintering to prepare the electrode;
step 2: 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 6.5KA, and the melting voltage is 30V;
and step 3: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 4, step 4: forging the copper alloy ingot subjected to solution treatment at the temperature of 875 ℃ to obtain a copper alloy bar blank:
and 5: making the copper alloy bar blank in vacuum degree less than 2X 10 -2 And (3) carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃, and then carrying out cold rolling to obtain the high-strength and high-conductivity 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 799MPa and the elongation after fracture of 19 percent; the tensile strength is 1053MPa and the elongation after fracture is 12% under the condition of extremely low temperature of-196 ℃; the tensile strength at 500 ℃ is 375MPa, and the elongation after fracture is 20%; the room temperature thermal conductivity was 270W/m.K. After softening at 970 ℃ and keeping the temperature for 30 minutes, the strength of the copper alloy material Wen Kangla is 425MPa, the elongation after fracture is 12 percent, the tensile strength at 500 ℃ is 203MPa, the elongation after fracture is 13 percent, and the heat conductivity coefficient is 260W/m.K.
Example 22
A preparation method of a high-strength and high-conductivity copper alloy material for a rocket engine comprises the following steps:
the alloy element powder of the preparation raw material of the high-strength and high-conductivity copper alloy material for the rocket engine comprises the following components in percentage by mass: zr0.08%, nb0.1%, and the balance of Cu;
step 1: mixing the alloy element powder of the preparation raw materials according to the mass percentage relationship, and then pressing and sintering to prepare an electrode;
and 2, step: 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 6.5KA, and the melting voltage is 30V;
and 3, step 3: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 4, step 4: forging the copper alloy ingot subjected to solution treatment at the temperature of 875 ℃ to obtain a copper alloy bar blank:
and 5: 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 ℃, and then carrying out cold rolling to obtain the high-strength high-conductivity 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 805MPa and the elongation after fracture of 15%; the tensile strength is 1036MPa and the elongation after fracture is 12% under the extremely low temperature condition of-196 ℃; tensile strength at 500 ℃ of 373MPa and elongation after fracture of 19%; the room temperature thermal conductivity is 269W/m.K. After softening at 970 ℃ and keeping the temperature for 30 minutes, the strength of the copper alloy material Wen Kangla is 415MPa, the elongation after fracture is 12 percent, the tensile strength at 500 ℃ is 210MPa, the elongation after fracture is 13 percent, and the thermal conductivity is 235W/m.K.
Example 23
A preparation method of a high-strength and high-conductivity copper alloy material for a rocket engine comprises the following steps:
the alloy element powder of the preparation raw material of the high-strength and high-conductivity copper alloy material for the rocket engine comprises the following components in percentage by mass: zr1.0%, nb25%, and the balance of Cu;
step 1: mixing the alloy element powder of the preparation raw materials according to the mass percentage relationship, and then pressing and sintering to prepare the electrode;
step 2: 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 6.5KA, and the melting voltage is 30V;
and step 3: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 4, step 4: forging the copper alloy ingot subjected to solution treatment at the temperature of 875 ℃ to obtain a copper alloy bar blank:
and 5: the copper alloy bar billet is subjected to small vacuum degreeAt 2X 10 -2 And (3) carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃, and then carrying out cold rolling to obtain the high-strength and high-conductivity 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 873MPa and elongation after fracture of 22%; the tensile strength is 1049MPa and the elongation after fracture is 12% under the condition of extremely low temperature of-196 ℃; tensile strength at 500 ℃ of 366MPa and elongation after fracture of 23%; the room temperature thermal conductivity was 270W/m.K. After softening at 970 ℃ and keeping the temperature for 30 minutes, the strength of the copper alloy material Wen Kangla is 425MPa, the elongation after fracture is 12%, the tensile strength at 500 ℃ is 209MPa, the elongation after fracture is 13%, and the heat conductivity is 256W/m.K.
Example 24
A preparation method of a high-strength and high-conductivity copper alloy material for a rocket engine comprises the following steps:
the alloy element powder of the preparation raw material of the high-strength and high-conductivity copper alloy material for the rocket engine comprises the following components in percentage by mass: zr0.54%, nb12.55%, and the balance of Cu;
step 1: mixing the alloy element powder of the preparation raw materials according to the mass percentage relationship, and then pressing and sintering to prepare the electrode;
and 2, step: 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 6.5KA, and the melting voltage is 30V;
and step 3: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 4, step 4: forging the copper alloy ingot subjected to solution treatment at the temperature of 875 ℃ to obtain a copper alloy bar blank:
and 5: 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 ℃, and then carrying out cold rolling to obtain the high-strength high-conductivity 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 799MPa and the elongation after fracture of 22%; the tensile strength is 1049MPa and the elongation after fracture is 13% under the condition of extremely low temperature of-196 ℃; tensile strength at 500 ℃ is 377MPa, and elongation after fracture is 22%; the room temperature thermal conductivity is 272W/m.K. After softening at 970 ℃ and keeping the temperature for 30 minutes, the strength of the copper alloy material Wen Kangla is 417MPa, the elongation after fracture is 12 percent, the tensile strength at 500 ℃ is 197MPa, the elongation after fracture is 13 percent, and the thermal conductivity is 239W/m.K.
Example 25
A preparation method of a high-strength and high-conductivity copper alloy material for a rocket engine comprises the following steps:
the alloy element powder of the preparation raw material of the high-strength and high-conductivity copper alloy material for the rocket engine comprises the following components in percentage by mass: zr0.08%, nb0.1%, hf0.1%, and the balance of Cu;
step 1: mixing the alloy element powder of the preparation raw materials according to the mass percentage relationship, and then pressing and sintering to prepare an electrode;
step 2: 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 6.5KA, and the melting voltage is 30V;
and step 3: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 4, step 4: forging the copper alloy cast ingot subjected to the solution treatment at the temperature of 875 ℃ to obtain a copper alloy bar blank:
and 5: making the copper alloy bar blank in vacuum degree less than 2X 10 -2 And (3) carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃, and then carrying out cold rolling to obtain the high-strength and high-conductivity 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 803MPa and the elongation after fracture of 19 percent; the tensile strength is 1042MPa and the elongation after fracture is 11% under the extremely low temperature condition of-196 ℃; the tensile strength at 500 ℃ is 376MPa, and the elongation after fracture is 25%; the room temperature thermal conductivity was 270W/m.K. After softening at 970 ℃ and keeping the temperature for 30 minutes, the strength of the copper alloy material Wen Kangla is 425MPa, the elongation after fracture is 12 percent, the tensile strength at 500 ℃ is 203MPa, the elongation after fracture is 13 percent, and the heat conductivity is 256W/m.K.
Example 26
A preparation method of a high-strength and high-conductivity copper alloy material for a rocket engine comprises the following steps:
the alloy element powder of the preparation raw material of the high-strength and high-conductivity copper alloy material for the rocket engine comprises the following components in percentage by mass: zr1.0%, nb25%, hf3.5%, and the balance of Cu;
step 1: mixing the alloy element powder of the preparation raw materials according to the mass percentage relationship, and then pressing and sintering to prepare the electrode;
step 2: 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 6.5KA, and the melting voltage is 30V;
and step 3: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 4, step 4: forging the copper alloy ingot subjected to solution treatment at the temperature of 875 ℃ to obtain a copper alloy bar blank:
and 5: making the copper alloy bar blank in vacuum degree less than 2X 10 -2 And (3) carrying out solid solution aging under the condition of Pa, wherein the aging temperature is 500 ℃, and then carrying out cold rolling to obtain the high-strength and high-conductivity 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 785MPa and the elongation after fracture of 16%; the tensile strength is 1039MPa and the elongation after fracture is 12 percent under the condition of extremely low temperature of-196 ℃; the tensile strength at 500 ℃ is 363MPa, and the elongation after fracture is 22%; the room temperature thermal conductivity is 269W/m.K. After softening at 970 ℃ and keeping the temperature for 30 minutes, the strength of the copper alloy material Wen Kangla is 399MPa, the elongation after fracture is 13 percent, the tensile strength at 500 ℃ is 196MPa, the elongation after fracture is 13 percent, and the heat conductivity coefficient is 260W/m.K.
Example 27
Unlike in example 26, the alloying element powder of the raw material for preparing the high-strength and high-conductivity copper alloy material for rocket motors in this example includes: zr0.54%, nb12.55%, hf1.8%, and the balance Cu, the same as in example 26 except that the above steps were carried out, whereby a high-strength high-conductivity copper alloy material for rocket engines was obtained.
The copper alloy material for the rocket engine prepared in the embodiment has the room-temperature tensile strength of 826MPa and the elongation after fracture of 21 percent; the tensile strength is 1049MPa and the elongation after fracture is 13% under the condition of extremely low temperature of-196 ℃; the tensile strength at 500 ℃ is 365MPa, and the elongation after fracture is 20%; the thermal conductivity at room temperature is 273W/m.K. After softening at 970 ℃ and keeping the temperature for 30 minutes, the strength of the copper alloy material Wen Kangla is 421MPa, the elongation after fracture is 11%, the tensile strength at 500 ℃ is 201MPa, the elongation after fracture is 12%, and the heat conductivity is 237W/m.K.
Example 28
Different from the embodiment 1, the alloying element powder of the raw material for preparing the high-strength and high-conductivity copper alloy material for the rocket engine in the embodiment comprises: cr1.1%, zr1.0%, V0.05%, re0.05% and Y-0.1%, and the balance of Cu, and the rest steps are the same as in example 1, so that the high-strength and high-conductivity copper alloy material for the rocket engine is obtained.
Example 29
Different from embodiment 4, the alloying element powder of the raw material for preparing the high-strength and high-conductivity copper alloy material for the rocket engine in the embodiment comprises: cr0.2%, zr0.09%, ta15%, nb12.55%, and the balance of Cu, all the other steps being the same as in example 4, to obtain a high-strength and high-conductivity copper alloy material for rocket engines.
Example 30
A preparation method of a high-strength and high-conductivity copper alloy material for a rocket engine comprises the following steps:
the alloy element powder of the preparation raw material of the high-strength and high-conductivity copper alloy material for the rocket engine comprises the following components in percentage by mass: 0.2 percent of Cr0.55 percent of Zr0.55 percent of Ta5 percent of Nb25 percent of Hf0.1 percent of V0.1 percent of Re0.08 percent of Y0.1 percent of Zr, the balance being Cu;
step 1: mixing the alloy element powder of the preparation raw materials according to the mass percentage relationship, and then pressing and sintering to prepare the electrode;
and 2, step: 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 10KA, and the melting voltage is 25V;
and step 3: carrying out solid solution treatment on the copper alloy cast ingot for 7h at the temperature of 900 ℃;
and 4, step 4: forging the copper alloy cast ingot subjected to the solution treatment at the temperature of 875 ℃ to obtain a copper alloy bar blank:
and 5: 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 ℃, and then carrying out cold rolling to obtain the high-strength high-conductivity copper alloy material for the rocket engine.
Example 31
A preparation method of a high-strength and high-conductivity copper alloy material for a rocket engine comprises the following steps:
the alloy element powder of the preparation raw material of the high-strength and high-conductivity copper alloy material for the rocket engine comprises the following components in percentage by mass: cr1.0%, zr0.08%, ta10%, nb18%, hf3.0%, V0.08%, re0.05%, Y0.1%, and the balance of Cu;
step 1: mixing the alloy element powder of the preparation raw materials according to the mass percentage relationship, and then pressing and sintering to prepare an electrode;
and 2, step: 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 10KA, and the melting voltage is 25V;
and step 3: carrying out solution treatment on the copper alloy cast ingot for 10 hours at the temperature of 900 ℃;
and 4, step 4: forging the copper alloy ingot after the solution treatment at the temperature of 950 ℃ to obtain a copper alloy bar blank:
and 5: making the copper alloy bar blank in vacuum degree less than 2X 10 -2 Pa, the aging temperature is 600 ℃, and then the high-strength and high-conductivity copper alloy material for the rocket engine is obtained by cold rollingAnd (5) feeding.
Example 31
Unlike in example 30, the alloying element powder of the raw material for preparing the high-strength and high-conductivity copper alloy material for the rocket engine includes: cr1.1%, zr1.0%, ta15%, nb0.1%, hf3.5%, V0.05%, re0.1%, Y0.03%, and the balance Cu, and the remaining preparation steps were the same as in example 30, whereby a high-strength, high-conductivity copper alloy material for rocket engines was obtained.
The high-strength and high-conductivity copper alloy material for the rocket engine prepared by the invention still has excellent performances of high strength, high toughness and the like at the temperature of 196 ℃ below zero; meanwhile, the alloy has high strength, high conductivity, high temperature resistance and excellent high temperature softening resistance; the alloy can be used for various rocket engines, and can also be widely used in the fields of high-speed rail transit, electronic communication, spot welding electrodes, lead frame materials, the inner wall of a combustion chamber of a rocket engine and the like.
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 high-strength high-conductivity copper alloy material for the rocket engine is characterized by comprising the following raw materials in percentage by mass: 0.2 to 1.1 percent of Cr, 0.08 to 1.0 percent of Zr, 5 to 15 percent of Ta, 0.1 to 25 percent of Nb, 0.1 to 3.5 percent of Hf, 0.05 to 0.1 percent of V, 0.05 to 0.1 percent of Re, 0.03 to 0.1 percent of Y and the balance of Cu.
2. The high-strength high-conductivity copper alloy material for the rocket engine is characterized by comprising the following raw materials in percentage by mass: 0.2 to 1.1 percent of Cr, 0.08 to 1.0 percent of Zr, 0.05 to 0.1 percent of V, 0.05 to 0.1 percent of Re, 0.03 to 0.1 percent of Y and the balance of Cu.
3. The high-strength high-conductivity copper alloy material for the rocket engine is characterized by comprising the following raw materials in percentage by mass: 0.2 to 1.1 percent of Cr, 0.08 to 1.0 percent of Zr, 5 to 15 percent of Ta, 0.1 to 25 percent of Nb and the balance of Cu.
4. The high-strength high-conductivity copper alloy material for the rocket engine is characterized by comprising the following raw materials in percentage by mass: 0.2 to 1.1 percent of Cr, 0.08 to 1.0 percent of Zr, 5 to 15 percent of Ta and the balance of Cu.
5. The high-strength high-conductivity copper alloy material for the rocket engine is characterized by comprising the following raw materials in percentage by mass: 0.2 to 1.1 percent of Cr, 0.08 to 1.0 percent of Zr, 0.1 to 25 percent of Nb, 0.03 to 0.1 percent of Y and the balance of Cu.
6. The high-strength high-conductivity copper alloy material for the rocket engine is characterized by comprising the following raw materials in percentage by mass: 0.2 to 1.1 percent of Cr, 0.08 to 1.0 percent of Zr, 0.1 to 25 percent of Nb and the balance of Cu.
7. The high-strength high-conductivity copper alloy material for the rocket engine is characterized by comprising the following raw materials in percentage by mass: 0.1 to 25% of Nb and the balance of Cu.
8. The high-strength high-conductivity copper alloy material for the rocket engine is characterized by comprising the following raw materials in percentage by mass: 0.2 to 1.1 percent of Cr, 0.1 to 25 percent of Nb and the balance of Cu or 0.08 to 1.0 percent of Zr, 0.1 to 25 percent of Nb and the balance of Cu.
9. The high-strength high-conductivity copper alloy material for the rocket engine is characterized by comprising the following raw materials in percentage by mass: 0.08 to 1.0 percent of Zr, 0.1 to 25 percent of Nb, 0.1 to 3.5 percent of Hf and the balance of Cu.
10. A method for producing a 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 and sintering to prepare an electrode;
s2: 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 3 KA-10 KA, and the voltage is 25V-35V;
s3: carrying out solution treatment on the copper alloy cast ingot for 3-11h at the temperature of 800-1000 ℃;
s4: forging the copper alloy ingot after the solution treatment at the temperature of 750-1000 ℃ to obtain a copper alloy bar blank:
s5: making the copper alloy bar blank in vacuum degree less than 2X 10 -2 Carrying out solid solution aging treatment at 400-600 ℃ under Pa, and then carrying out cold rolling to obtain the high-strength high-conductivity copper alloy material for the rocket engine.
CN202211174630.1A 2022-09-26 2022-09-26 High-strength high-conductivity copper alloy material for rocket engine and preparation method thereof Pending CN115466875A (en)

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