CN104651673A - Stretch-proof nickel-aluminum alloy material and preparation method thereof - Google Patents
Stretch-proof nickel-aluminum alloy material and preparation method thereof Download PDFInfo
- Publication number
- CN104651673A CN104651673A CN201510102552.8A CN201510102552A CN104651673A CN 104651673 A CN104651673 A CN 104651673A CN 201510102552 A CN201510102552 A CN 201510102552A CN 104651673 A CN104651673 A CN 104651673A
- Authority
- CN
- China
- Prior art keywords
- vacuum melting
- stretch
- proof
- temperature
- preparation
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Classifications
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C21/00—Alloys based on aluminium
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C1/00—Making non-ferrous alloys
- C22C1/02—Making non-ferrous alloys by melting
- C22C1/026—Alloys based on aluminium
-
- 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
- C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
- Manufacture And Refinement Of Metals (AREA)
Abstract
The invention belongs to the field of aluminum alloy materials and relates to a stretch-proof nickel-aluminum alloy material and a preparation method thereof. The nickel-aluminum alloy material comprises Sb, Ti, V, Re, Rb, Nb, Er, Ni and Al, and the preparation method of the stretch-proof nickel-aluminum alloy material comprises the following steps: (1) increasing the temperature of a vacuum smelting furnace to 650-690 DEG C, adding Sb, Ti, V and Re in percentage by weight and performing vacuum smelting; (2) increasing the temperature of the vacuum smelting furnace to 790-830 DEG C, adding Rb, Nb, Er, Ni and the balance of Al and performing vacuum smelting again; (3) reducing the temperature in the vacuum smelting furnace to 560-590 DEG C at a temperature reduction speed of 30 DEG C/minute, and then insulating heat for one hour; and (4) annealing and cooling the alloy material in the vacuum smelting furnace to obtain the stretch-proof nickel-aluminum alloy material.
Description
Technical field
The invention belongs to field of alloy material, relate to a kind of alumel material and preparation method thereof, alumel material particularly relating to a kind of stretch-proof and preparation method thereof.
Background technology
The density of fine aluminium is little, and fusing point is low, and aluminium is face-centred cubic structure, therefore has very high plasticity, and be easy to processing, can be made into various section bar, sheet material, corrosion resistance is good; But the intensity of fine aluminium is very low.In order to improve the intensity of fine aluminium, alloying element can be added and use the methods such as thermal treatment to carry out the intensity of reinforced aluminum.The alloy adding the formation of certain element can also have higher intensity while the advantages such as maintenance fine aluminium light weight, become desirable structured material, therefore aluminium alloy is widely used in the aspects such as machinofacture, Transport Machinery, power machine and aircraft industry, the fuselage, pneumatic plant etc. of aircraft are normal with aluminium alloy manufacture, to alleviate deadweight.Adopt aluminium alloy to replace the welding of steel plate materials, structural weight can alleviate more than 50%, and has excellent electroconductibility, thermal conductivity.In above-mentioned purposes, the tensile property of aluminum alloy materials can affect its using state largely, therefore needs the tensile property and the elongation at break that effectively improve aluminum alloy materials.
Summary of the invention
The technical problem solved: aluminum alloy materials in use, the use of its tensile property on aluminum alloy materials has larger impact, its elongation at break is too low, easily can produce the situation of fracture in use, the purposes of restriction aluminum alloy materials, therefore the object of the invention is the elongation at break and the tensile strength that improve alumel material.
Technical scheme: for the problems referred to above, the invention discloses a kind of alumel material of stretch-proof, and the alumel material of described stretch-proof consists of the following composition:
Sb be 0.5wt% ~ 1.7wt%,
Ti be 0.3wt% ~ 1.2wt%,
V be 0.4wt% ~ 1.7wt%,
Re be 0.5wt% ~ 1.1wt%,
Rb be 0.3wt% ~ 1.0wt%,
Nb be 0.6wt% ~ 1.3wt%,
Er be 0.3wt% ~ 0.8wt%,
Ni be 8wt% ~ 14wt%,
Surplus is Al.
Preferably, the alumel material of described a kind of stretch-proof, consists of the following composition:
Sb be 0.8wt% ~ 1.3wt%,
Ti be 0.6wt% ~ 1.0wt%,
V be 0.9wt% ~ 1.4wt%,
Re be 0.7wt% ~ 1.0wt%,
Rb be 0.6wt% ~ 0.9wt%,
Nb be 0.8wt% ~ 1.2wt%,
Er be 0.4wt% ~ 0.7wt%,
Ni be 10wt% ~ 12wt%,
Surplus is Al.
A preparation method for the alumel material of stretch-proof, comprises the following steps:
(1) vacuum melting in-furnace temperature is increased to 650 ~ 690 DEG C, to add Sb be by weight percentage 0.5wt% ~ 1.7wt%, Ti be 0.3wt% ~ 1.2wt%, V be 0.4wt% ~ 1.7wt%, Re is 0.5wt% ~ 1.1wt%, vacuum melting, smelting time is 2h;
(2) vacuum melting furnace temperature is increased to 790 ~ 830 DEG C, temperature rise rate is 20 DEG C/min, after temperature-stable, in vacuum melting furnace, add Rb be again 0.3wt% ~ 1.0wt%, Nb be 0.6wt% ~ 1.3wt%, Er be 0.3wt% ~ 0.8wt%, Ni is 8wt% ~ 14wt%, surplus is Al, then vacuum melting 3h;
(3) reducing vacuum melting in-furnace temperature, is that 30 DEG C/min is reduced to 560 ~ 590 DEG C by vacuum melting in-furnace temperature according to rate of temperature fall, insulation 1h;
(4) annealed by alloy material in vacuum melting furnace, annealing temperature is after 280 ~ 330 DEG C, and insulation 90min, after cooling, prepares the alumel material of stretch-proof.
The preparation method of the alumel material of described a kind of stretch-proof, vacuum melting in-furnace temperature is increased to 670 DEG C in (1) by step.
The preparation method of the alumel material of described a kind of stretch-proof, vacuum melting furnace temperature is increased to 810 DEG C in (2) by step.
The preparation method of the alumel material of described a kind of stretch-proof, vacuum melting in-furnace temperature is reduced to 575 DEG C in (3) by step.
The preparation method of the alumel material of described a kind of stretch-proof, alloy material in vacuum melting furnace is annealed in (4) by step, and annealing temperature is 300 DEG C.
Beneficial effect: through screening the melting technology of alumel material, alloying element in alumel is also selected simultaneously, the tensile strength of alumel material and the elongation at break of preparation improve all greatly, when Sb be 0.8wt% ~ 1.3wt%,
Ti is 0.6wt% ~ 1.0wt%, V be 0.9wt% ~ 1.4wt%, Re to be 0.7wt% ~ 1.0wt%, Rb be 0.6wt% ~ 0.9wt%,
When Nb is 0.8wt% ~ 1.2wt%, Er be 0.4wt% ~ 0.7wt%, Ni is 10wt% ~ 12wt%, surplus is Al, elongation at break and the tensile strength of the alumel of preparation are better.
Embodiment
Embodiment 1
(1) vacuum melting in-furnace temperature is increased to 690 DEG C, to add Sb be by weight percentage 0.5wt%, Ti be 1.2wt%, V be 0.4wt%, Re is 1.1wt%, vacuum melting, and smelting time is 2h; (2) vacuum melting furnace temperature is increased to 830 DEG C, temperature rise rate is 20 DEG C/min, after temperature-stable, then in vacuum melting furnace, add Rb be 0.3wt%, Nb be 0.6wt%, Er be 0.8wt%, Ni is 14wt%, surplus is Al, then vacuum melting 3h; (3) reducing vacuum melting in-furnace temperature, is that 30 DEG C/min is reduced to 590 DEG C by vacuum melting in-furnace temperature according to rate of temperature fall, insulation 1h; (4) annealed by alloy material in vacuum melting furnace, annealing temperature is after 330 DEG C, and insulation 90min, after cooling, prepares the alumel material of stretch-proof.
Embodiment 2
(1) vacuum melting in-furnace temperature is increased to 650 DEG C, to add Sb be by weight percentage 1.7wt%, Ti be 0.3wt%, V be 1.7wt%, Re is 0.5wt%, vacuum melting, and smelting time is 2h; (2) vacuum melting furnace temperature is increased to 790 DEG C, temperature rise rate is 20 DEG C/min, after temperature-stable, then in vacuum melting furnace, add Rb be 1.0wt%, Nb be 1.3wt%, Er be 0.3wt%, Ni is 8wt%, surplus is Al, then vacuum melting 3h; (3) reducing vacuum melting in-furnace temperature, is that 30 DEG C/min is reduced to 560 DEG C by vacuum melting in-furnace temperature according to rate of temperature fall, insulation 1h; (4) annealed by alloy material in vacuum melting furnace, annealing temperature is after 280 DEG C, and insulation 90min, after cooling, prepares the alumel material of stretch-proof.
Embodiment 3
(1) vacuum melting in-furnace temperature is increased to 680 DEG C, to add Sb be by weight percentage 0.8wt%, Ti be 0.6wt%, V be 1.4wt%, Re is 1.0wt%, vacuum melting, and smelting time is 2h; (2) vacuum melting furnace temperature is increased to 800 DEG C, temperature rise rate is 20 DEG C/min, after temperature-stable, then in vacuum melting furnace, add Rb be 0.9wt%, Nb be 1.2wt%, Er be 0.4wt%, Ni is 12wt%, surplus is Al, then vacuum melting 3h; (3) reducing vacuum melting in-furnace temperature, is that 30 DEG C/min is reduced to 580 DEG C by vacuum melting in-furnace temperature according to rate of temperature fall, insulation 1h; (4) annealed by alloy material in vacuum melting furnace, annealing temperature is after 290 DEG C, and insulation 90min, after cooling, prepares the alumel material of stretch-proof.
Embodiment 4
(1) vacuum melting in-furnace temperature is increased to 660 DEG C, to add Sb be by weight percentage 1.3wt%, Ti be 1.0wt%, V be 0.9wt%, Re is 0.7wt%, vacuum melting, and smelting time is 2h; (2) vacuum melting furnace temperature is increased to 820 DEG C, temperature rise rate is 20 DEG C/min, after temperature-stable, then in vacuum melting furnace, add Rb be 0.6wt%, Nb be 0.8wt%, Er be 0.7wt%, Ni is 10wt%, surplus is Al, then vacuum melting 3h; (3) reducing vacuum melting in-furnace temperature, is that 30 DEG C/min is reduced to 570 DEG C by vacuum melting in-furnace temperature according to rate of temperature fall, insulation 1h; (4) annealed by alloy material in vacuum melting furnace, annealing temperature is after 310 DEG C, and insulation 90min, after cooling, prepares the alumel material of stretch-proof.
Embodiment 5
(1) vacuum melting in-furnace temperature is increased to 670 DEG C, to add Sb be by weight percentage 1.1wt%, Ti be 0.8wt%, V be 1.2wt%, Re is 0.9wt%, vacuum melting, and smelting time is 2h; (2) vacuum melting furnace temperature is increased to 810 DEG C, temperature rise rate is 20 DEG C/min, after temperature-stable, then in vacuum melting furnace, add Rb be 0.8wt%, Nb be 1.0wt%, Er be 0.6wt%, Ni is 11wt%, surplus is Al, then vacuum melting 3h; (3) reducing vacuum melting in-furnace temperature, is that 30 DEG C/min is reduced to 575 DEG C by vacuum melting in-furnace temperature according to rate of temperature fall, insulation 1h; (4) annealed by alloy material in vacuum melting furnace, annealing temperature is after 300 DEG C, and insulation 90min, after cooling, prepares the alumel material of stretch-proof.
Comparative example
(1) vacuum melting in-furnace temperature is increased to 650 DEG C, to add Sb be by weight percentage 1.7wt%, Ti be 0.3wt%, V be 1.7wt%, Re is 0.5wt%, vacuum melting, and smelting time is 2h; (2) vacuum melting furnace temperature is increased to 790 DEG C, temperature rise rate is 20 DEG C/min, and after temperature-stable, then in vacuum melting furnace, add Rb be 1.0wt%, Ni is 8wt%, surplus is Al, then vacuum melting 3h; (3) reducing vacuum melting in-furnace temperature, is that 30 DEG C/min is reduced to 560 DEG C by vacuum melting in-furnace temperature according to rate of temperature fall, insulation 1h; (4) annealed by alloy material in vacuum melting furnace, annealing temperature is after 280 DEG C, and insulation 90min, after cooling, prepares the alumel material of stretch-proof.
Determine elongation at break and the tensile strength of above-mentioned alumel material, as follows:
The alumel material of stretch-proof of the present invention has possessed good elongation at break and tensile strength.。
Claims (7)
1. an alumel material for stretch-proof, is characterized in that the alumel material of described stretch-proof consists of the following composition:
Sb be 0.5wt% ~ 1.7wt%,
Ti be 0.3wt% ~ 1.2wt%,
V be 0.4wt% ~ 1.7wt%,
Re be 0.5wt% ~ 1.1wt%,
Rb be 0.3wt% ~ 1.0wt%,
Nb be 0.6wt% ~ 1.3wt%,
Er be 0.3wt% ~ 0.8wt%,
Ni be 8wt% ~ 14wt%,
Surplus is Al.
2. the alumel material of a kind of stretch-proof according to claim 1, is characterized in that the alumel material of described stretch-proof consists of the following composition:
Sb be 0.8wt% ~ 1.3wt%,
Ti be 0.6wt% ~ 1.0wt%,
V be 0.9wt% ~ 1.4wt%,
Re be 0.7wt% ~ 1.0wt%,
Rb be 0.6wt% ~ 0.9wt%,
Nb be 0.8wt% ~ 1.2wt%,
Er be 0.4wt% ~ 0.7wt%,
Ni be 10wt% ~ 12wt%,
Surplus is Al.
3. a preparation method for the alumel material of stretch-proof, is characterized in that the preparation method of the alumel material of described stretch-proof comprises the following steps:
(1) vacuum melting in-furnace temperature is increased to 650 ~ 690 DEG C, to add Sb be by weight percentage 0.5wt% ~ 1.7wt%, Ti be 0.3wt% ~ 1.2wt%, V be 0.4wt% ~ 1.7wt%, Re is 0.5wt% ~ 1.1wt%, vacuum melting, smelting time is 2h;
(2) vacuum melting furnace temperature is increased to 790 ~ 830 DEG C, temperature rise rate is 20 DEG C/min, after temperature-stable, in vacuum melting furnace, add Rb be again 0.3wt% ~ 1.0wt%, Nb be 0.6wt% ~ 1.3wt%, Er be 0.3wt% ~ 0.8wt%, Ni is 8wt% ~ 14wt%, surplus is Al, then vacuum melting 3h;
(3) reducing vacuum melting in-furnace temperature, is that 30 DEG C/min is reduced to 560 ~ 590 DEG C by vacuum melting in-furnace temperature according to rate of temperature fall, insulation 1h;
(4) annealed by alloy material in vacuum melting furnace, annealing temperature is after 280 ~ 330 DEG C, and insulation 90min, after cooling, prepares the alumel material of stretch-proof.
4. the preparation method of the alumel material of a kind of stretch-proof according to claim 3, is characterized in that, in preparation method's step (1) of the alumel material of described stretch-proof, vacuum melting in-furnace temperature is increased to 670 DEG C.
5. the preparation method of the alumel material of a kind of stretch-proof according to claim 3, is characterized in that, in preparation method's step (2) of the alumel material of described stretch-proof, vacuum melting furnace temperature is increased to 810 DEG C.
6. the preparation method of the alumel material of a kind of stretch-proof according to claim 3, is characterized in that, in preparation method's step (3) of the alumel material of described stretch-proof, vacuum melting in-furnace temperature is reduced to 575 DEG C.
7. the preparation method of the alumel material of a kind of stretch-proof according to claim 3, it is characterized in that being annealed by alloy material in vacuum melting furnace in preparation method's step (4) of the alumel material of described stretch-proof, annealing temperature is 300 DEG C.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510102552.8A CN104651673A (en) | 2015-03-09 | 2015-03-09 | Stretch-proof nickel-aluminum alloy material and preparation method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510102552.8A CN104651673A (en) | 2015-03-09 | 2015-03-09 | Stretch-proof nickel-aluminum alloy material and preparation method thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104651673A true CN104651673A (en) | 2015-05-27 |
Family
ID=53243309
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510102552.8A Pending CN104651673A (en) | 2015-03-09 | 2015-03-09 | Stretch-proof nickel-aluminum alloy material and preparation method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104651673A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1873035A (en) * | 2005-05-31 | 2006-12-06 | 联合工艺公司 | High temperature aluminium alloys |
| EP2112242A1 (en) * | 2008-04-18 | 2009-10-28 | United Technologies Corporation | Heat treatable L12 aluminium alloys |
| CN104294091A (en) * | 2014-09-15 | 2015-01-21 | 安徽欣意电缆有限公司 | Al-Fe-Cu-Zr series aluminum alloy for cables for coal mines and aluminum alloy cable |
| CN104328315A (en) * | 2014-10-22 | 2015-02-04 | 江苏大学 | Process method for improving friction and wear properties of multi-element aluminum-silicon alloy |
| JP2015041416A (en) * | 2013-08-20 | 2015-03-02 | 株式会社豊田自動織機 | Power storage device |
-
2015
- 2015-03-09 CN CN201510102552.8A patent/CN104651673A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1873035A (en) * | 2005-05-31 | 2006-12-06 | 联合工艺公司 | High temperature aluminium alloys |
| EP2112242A1 (en) * | 2008-04-18 | 2009-10-28 | United Technologies Corporation | Heat treatable L12 aluminium alloys |
| JP2015041416A (en) * | 2013-08-20 | 2015-03-02 | 株式会社豊田自動織機 | Power storage device |
| CN104294091A (en) * | 2014-09-15 | 2015-01-21 | 安徽欣意电缆有限公司 | Al-Fe-Cu-Zr series aluminum alloy for cables for coal mines and aluminum alloy cable |
| CN104328315A (en) * | 2014-10-22 | 2015-02-04 | 江苏大学 | Process method for improving friction and wear properties of multi-element aluminum-silicon alloy |
Non-Patent Citations (1)
| Title |
|---|
| 吕伟凡: "《铸造工：初级、中级、高级》", 30 April 1996 * |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109161727B (en) | Titanium alloy for manufacturing electric arc/electron beam fuse additive and preparation method thereof | |
| CN103589903B (en) | A kind of high-strength wear-resistant copper alloy and manufacture method thereof | |
| US20150184272A1 (en) | Low cost and high strength titanium alloy and heat treatment process | |
| CN102839297A (en) | High-temperature titanium alloy and preparation method thereof | |
| CN102337429A (en) | High-strength Al-Mg-Si-Cu alloy and preparation method thereof | |
| CN105441840B (en) | A kind of hammering cogging method of high-strength heat-resistant magnesium alloy ingot casting | |
| CN106119731B (en) | A kind of gas turbine blower blade Steel material and preparation method thereof | |
| CN102676885A (en) | Aluminum alloy ingot | |
| CN106011541B (en) | A kind of Ni Cr Mo systems high-temperature alloy material and preparation method thereof | |
| CN104178711A (en) | Manufacturing method for aerospace aluminum alloy board | |
| CN104046846A (en) | Multilevel high-strength high-plasticity titanium-zirconium-based alloy and preparation method thereof | |
| CN104032195A (en) | Efficiently-extrudable low-cost high-performance heat-conducting magnesium alloy and preparation method thereof | |
| CN103952652A (en) | Manufacturing method of aluminum alloy prestretching plate for aviation | |
| CN108977689B (en) | Metastable beta titanium alloy plate and processing method thereof | |
| CN106756333A (en) | A kind of high intensity space flight manufacture method of Aluminum alloy rivet wire rod | |
| CN103131924A (en) | Sm-containing Mg-Al-Zn heat-resisting deformed magnesium alloy | |
| CN102787263A (en) | Method for manufacturing aluminum alloy rivet rod for aerospace product | |
| CN102424927A (en) | Magnesium-aluminum alloy and preparation method thereof | |
| CN107739891B (en) | A kind of nickel molybdenum intermediate alloy is preparing the application in ErNiCrMo-3 alloy | |
| CN108856614B (en) | A kind of forging method of 7000 line aluminium alloy | |
| CN105132751A (en) | Ni-Cr-Al-Fe type high temperature alloy material and preparation method and application thereof | |
| CN105583251B (en) | A kind of forging method of big specification Inconel690 alloy bar materials | |
| CN103725923B (en) | A kind of nickel-base alloy of aluminum strengthening and preparation method thereof | |
| CN106148809A (en) | A kind of high-elongation mould steel and preparation method thereof | |
| CN104878269A (en) | Method for optimizing endurance property of GH 706 alloy |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20150527 |