CN105648277A - High-temperature-resistant alloy material, preparation method thereof and application thereof - Google Patents
High-temperature-resistant alloy material, preparation method thereof and application thereof Download PDFInfo
- Publication number
- CN105648277A CN105648277A CN201610172283.7A CN201610172283A CN105648277A CN 105648277 A CN105648277 A CN 105648277A CN 201610172283 A CN201610172283 A CN 201610172283A CN 105648277 A CN105648277 A CN 105648277A
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- alloy material
- resistant alloy
- temperature
- temperature resistant
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- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C19/00—Alloys based on nickel or cobalt
- C22C19/03—Alloys based on nickel or cobalt based on nickel
- C22C19/05—Alloys based on nickel or cobalt based on nickel with chromium
- C22C19/051—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W
- C22C19/055—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 20% but less than 30%
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- 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
- C22C—ALLOYS
- C22C1/00—Making non-ferrous alloys
- C22C1/02—Making non-ferrous alloys by melting
- C22C1/023—Alloys based on nickel
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C30/00—Alloys containing less than 50% by weight of each constituent
Abstract
The invention discloses a high-temperature-resistant alloy material, which belongs to the technical field of alloy materials. The high-temperature-resistant alloy material consists of the following chemical components in percentage by weight: 0.05-0.15% of C, 20.5-23.00% of Cr, 8.00-10.00% of Mo, 0.50-2.50% of Co, 0.20-1.00% of W, 17.00-20.00% of Fe, 0.001-0.010% of B and the balance Ni. The invention further discloses a preparation method and an application of the material. The alloy material disclosed by the invention has excellent high temperature resistance and mechanical properties, wherein the tensile strength sigma b at the room temperature (25 DEG C) is greater than or equal to 700N/mm<2>, the yield strength sigma 0.2 is greater than or equal to 320N/mm<2>, the elongation sigma 5 is greater than or equal to 50%, a high-temperature (816+/-3 DEG C) creep repture test is greater than or equal to 103N/mm<2>, the fracture time is greater than or equal to 25 hours, and the elongation sigma 5 is greater than or equal to 60%.
Description
Technical field
The present invention relates to alloy material, particularly relate to a kind of High-temperature resistant alloy material, its preparation method and application thereof.
Background technology
In technical field of aerospace, the requirement to using material to propose harshness of the working environment of aeroengine combustor buring room parts.
First be high temperature: aero-jet engine is from compressor to jet pipe, and each parts work at a certain temperature, some part will more than 800 DEG C when long-term work;
Next to that heavily stressed: some high-temperature components, due to vibrations, the washing away of air-flow, particularly rotate the centrifugal action caused, bigger stress will be born, if the stress of turbo blade is up to 300��409Mpa.
It is the chemical actions such as oxidation and corrosion again: combustion gas exists substantial amounts of oxygen, aqueous vapor, and there is SO2��H2The corrosive gas such as S, all play oxidation and corrosiveness to hot parts.
And, along with the development of aero gas turbine engine, the increase of thrust-weight ratio, the working environment of engine components is day by day harsh. For turbine inlet temperature (TIT), active service machine is about 1600K, reaches 1850��1950K grinding machine, and beforehand research machine will be up to 2250��2350K. Developing the gas-turbine unit of higher thrust-weight ratio, top priority is to develop the exotic material that serviceability is excellent.
Existing a lot of report about exotic material, such as application number is 201110125242.X, denomination of invention is the Chinese patent of " Ni3Al based single-crystal high-temperature alloy of high Mo that a kind of Cr is modified and preparation method thereof ", this single crystal super alloy cost performance height, long service life, antioxidant anticorrosive excellent performance, the oxide etch under resistance to 1100��1200 DEG C of high temperature; Such as application number is 201010296131.0 denominations of invention again is " a kind of nickel cobalt based high-temperature alloy containing rare earth element and preparation method thereof " Chinese patent, the alloy of this patent application has excellent processability and room temperature to high temperature tensile strength, and enduring quality is suitable with high-performance casting forging high temperature alloy TMW.
Summary of the invention
An object of the present invention, in that provide a kind of High-temperature resistant alloy material, to solve the problems referred to above.
To achieve these goals, the technical solution used in the present invention is such that a kind of High-temperature resistant alloy material, its chemical composition, is by weight percentage:
C (carbon) 0.05��0.15%
Cr (chromium) 20.5��23.00%
Mo (molybdenum) 8.00��10.00%
Co (cobalt) 0.50��2.50%
W (tungsten) 0.20��1.00%
Fe (ferrum) 17.00��20.00%
B (boron) 0.001��0.010%,
Surplus is Ni (nickel).
As preferred technical scheme: in described material, contained impurity, by mass percentage:
P��0.025%S��0.015%
Mn��1.00%Si��1.00%
Cu��0.50%.
The two of the purpose of the present invention, are in that the preparation method providing a kind of above-mentioned High-temperature resistant alloy material, and the technical scheme of employing is: comprise the following steps:
(1) weighing raw material by component ratio, then carry out melting, smelting temperature 1450��1470 DEG C, solution casting becomes consutrode;
Regulating the content of each element in fusion process so that it is weight ratio meets designing requirement, the content controlling impurity element is as far as possible low;
(2) consutrode of step (1) gained being carried out remelting refining, remelting becomes ESR ingot, its objective is to reduce further the content of impurity element so that it is meet designing requirement;
(3) ESR ingot of step (2) gained is heated to 1140��1160 DEG C, be incubated 2��3 hours, start forging, obtain rod iron; It is subsequently cooled to room temperature, then carries out surface treatment, to obtain final product.
Wherein, when carrying out surface treatment, rod iron surface is carried out car optical processing, eliminate surface defect and make rod iron size, shape, surface quality meet design requirement, prepare finished product rod iron.
As preferred technical scheme: in step (1), carry out in vaccum sensitive stove during melting.
As preferred technical scheme: step (2) carries out in electroslag furnace.
As preferred technical scheme: in step (2), the type of cooling is air cooling. Ni based high-temperature alloy cooling procedure do not have phase transformation, it is advantageous to adopt air cooling.
The three of the purpose of the present invention, are in that to provide the application of a kind of above-mentioned alloy material, are used for making aeroengine combustor buring room parts by described alloy material.
Compared with prior art, it is an advantage of the current invention that: the alloy material of the present invention has resistance to elevated temperatures and mechanical property, the tensile strength sigma of room temperature (25 DEG C) of excellenceb��700N/mm2; Yield strength ��0.2��320N/mm2; Percentage elongation ��5>=50%; High temperature (816 �� 3 DEG C) creep rupture test >=103N/mm2Rupture time >=25h percentage elongation ��5>=60%, there is good oxidation resistance, corrosion resistance simultaneously, be suitable for aeroengine combustor buring room and the after-burner parts of less than 900 DEG C life-time service, there is good welding performance and hot and cold formability.
Detailed description of the invention
Below in conjunction with embodiment, the invention will be further described.
Embodiment 1-5:
Adopting the element of different content, prepare alloy material, have employed formula 5 kinds different altogether, the composition of each element is in Table 1, in table 1, is weight/mass percentage composition value.
The composition of various elements in table 1 embodiment 1-5
Preparation method:
(1) take required chemical element according to table 1, vacuum induction furnace smelting, fusion process regulate the content of chemical element so that it is weight percent is table 1 such as:
And the content that controls impurity element is as far as possible low, solution casting becomes consutrode;
(2) by consutrode remelting refining in electroslag furnace of step (1) gained, the content of impurity element is reduced further so that it is meet following requirement:
Surplus is Ni and inevitable impurity;
After each constituent content of sample analysis is qualified, make ESR ingot.
(3) the ESR ingot heats forged of step (2) gained is made rod iron, step and technological parameter as follows;
Rod iron is heated to 1140��1160 DEG C, is incubated 2��3 hours, start forging; After rod iron forging, air cooling is to room temperature; Rod iron surface treatment, carries out car optical processing to finished product rod iron surface, eliminates surface defect and makes rod iron size, shape, surface quality meet design requirement, and prepares finished product rod iron.
Embodiment 6
Material properties test
Check mechanical property in finished product rod iron up sampling, carry out the mechanical property test of correspondence;
--sample heat treatment step and technological parameter are as follows:
Solid solution: 1150 �� 14 DEG C of time 10��30Min types of cooling of heating-up temperature: water-cooled
Finished product rod iron Progressive symmetric erythrokeratodermia obtained by embodiment 1-5 can be tested
Through tensile test at room temperature, result shows that its mechanical property is fully achieved designing requirement, and result of the test is as follows:
Room temperature tensile:
| Parameter | ��b | ��0.2 | ��5 |
| Standard | ��690 | ��275 | ��35 |
| Unit | N/mm2 | N/mm2 | % |
| Embodiment 1 result | 708 | 336 | 51 |
| Embodiment 2 result | 710 | 335 | 50 |
| Embodiment 3 result | 705 | 321 | 52 |
| Embodiment 4 result | 714 | 341 | 50 |
| Embodiment 5 result | 735 | 375 | 50 |
Creep rupture test:
It can be seen from the results above that the aviation engine components manufactured with this material, it is possible to meet the instructions for use of engine components working environment.
The foregoing is only presently preferred embodiments of the present invention, not in order to limit the present invention, all any amendment, equivalent replacement and improvement etc. made within the spirit and principles in the present invention, should be included within protection scope of the present invention.
Claims (7)
1. a High-temperature resistant alloy material, it is characterised in that: its chemical composition, be by weight percentage:
C0.05��0.15%
Cr20.5��23.00%
Mo8.00��10.00%
Co0.50��2.50%
W0.20��1.00%
Fe17.00��20.00%
B0.001��0.010%,
Surplus is Ni.
2. High-temperature resistant alloy material according to claim 1, it is characterised in that: in described material, contained impurity, by mass percentage:
P��0.025%S��0.015%
Mn��1.00%Si��1.00%
Cu��0.50%.
3. the preparation method of the High-temperature resistant alloy material described in claim 1 or 2, it is characterised in that: comprise the following steps:
(1) weighing raw material by component ratio, then carry out melting, smelting temperature 1450��1470 DEG C, solution casting becomes consutrode;
(2) consutrode of step (1) gained being carried out remelting refining, remelting becomes ESR ingot;
(3) ESR ingot of step (2) gained is heated to 1140��1160 DEG C, be incubated 2��3 hours, start forging; It is subsequently cooled to room temperature, then carries out surface treatment, to obtain final product.
4. the preparation method of High-temperature resistant alloy material according to claim 3, it is characterised in that: in step (1), carry out in vaccum sensitive stove during melting.
5. the preparation method of High-temperature resistant alloy material according to claim 3, it is characterised in that: step (2) carries out in electroslag furnace.
6. the preparation method of High-temperature resistant alloy material according to claim 3, it is characterised in that: in step (2), the type of cooling is air cooling.
7. the application of the High-temperature resistant alloy material described in claim 1 or 2, it is characterised in that be used for described alloy material making aeroengine combustor buring room parts.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610172283.7A CN105648277A (en) | 2016-03-23 | 2016-03-23 | High-temperature-resistant alloy material, preparation method thereof and application thereof |
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| CN201610172283.7A CN105648277A (en) | 2016-03-23 | 2016-03-23 | High-temperature-resistant alloy material, preparation method thereof and application thereof |
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| CN201610172283.7A Pending CN105648277A (en) | 2016-03-23 | 2016-03-23 | High-temperature-resistant alloy material, preparation method thereof and application thereof |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109988927A (en) * | 2019-03-19 | 2019-07-09 | 江苏汉青特种合金有限公司 | With the manufacturing method of excellent enduring quality alloy under a kind of high-temperature and high-pressure conditions |
| CN112095037A (en) * | 2020-11-19 | 2020-12-18 | 中国航发上海商用航空发动机制造有限责任公司 | Molded article having high-temperature durability and low anisotropy, molding method, and molded powder |
| CN113061783A (en) * | 2021-03-23 | 2021-07-02 | 江苏图南合金股份有限公司 | High-temperature alloy seamless special pipe and production method thereof |
| CN117512403A (en) * | 2024-01-04 | 2024-02-06 | 北京北冶功能材料有限公司 | Nickel-based high-temperature alloy foil easy to process and shape and preparation method thereof |
| CN117587298A (en) * | 2024-01-19 | 2024-02-23 | 北京北冶功能材料有限公司 | Nickel-based high-temperature alloy foil with low residual stress and preparation method and application thereof |
Citations (3)
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|---|---|---|---|---|
| US4673123A (en) * | 1982-10-06 | 1987-06-16 | Nippon Welding Rod Co., Ltd. | Filler for welding a heat resistant nickel-base alloy |
| CN101586203A (en) * | 2008-05-21 | 2009-11-25 | 株式会社东芝 | Nickel-base casting superalloy and cast component for steam turbine using the same as material |
| CN103924126A (en) * | 2014-04-24 | 2014-07-16 | 四川六合锻造股份有限公司 | High temperature alloy material and preparation method thereof |
-
2016
- 2016-03-23 CN CN201610172283.7A patent/CN105648277A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4673123A (en) * | 1982-10-06 | 1987-06-16 | Nippon Welding Rod Co., Ltd. | Filler for welding a heat resistant nickel-base alloy |
| CN101586203A (en) * | 2008-05-21 | 2009-11-25 | 株式会社东芝 | Nickel-base casting superalloy and cast component for steam turbine using the same as material |
| CN103924126A (en) * | 2014-04-24 | 2014-07-16 | 四川六合锻造股份有限公司 | High temperature alloy material and preparation method thereof |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109988927A (en) * | 2019-03-19 | 2019-07-09 | 江苏汉青特种合金有限公司 | With the manufacturing method of excellent enduring quality alloy under a kind of high-temperature and high-pressure conditions |
| CN112095037A (en) * | 2020-11-19 | 2020-12-18 | 中国航发上海商用航空发动机制造有限责任公司 | Molded article having high-temperature durability and low anisotropy, molding method, and molded powder |
| WO2022105529A1 (en) * | 2020-11-19 | 2022-05-27 | 中国航发上海商用航空发动机制造有限责任公司 | Formed part with high-temperature persistence and low anisotropy, forming method and forming powder |
| CN113061783A (en) * | 2021-03-23 | 2021-07-02 | 江苏图南合金股份有限公司 | High-temperature alloy seamless special pipe and production method thereof |
| CN117512403A (en) * | 2024-01-04 | 2024-02-06 | 北京北冶功能材料有限公司 | Nickel-based high-temperature alloy foil easy to process and shape and preparation method thereof |
| CN117587298A (en) * | 2024-01-19 | 2024-02-23 | 北京北冶功能材料有限公司 | Nickel-based high-temperature alloy foil with low residual stress and preparation method and application thereof |
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Application publication date: 20160608 |