CN103667799B - High temperature alloy and preparation method thereof - Google Patents

High temperature alloy and preparation method thereof Download PDF

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Publication number
CN103667799B
CN103667799B CN201310682333.2A CN201310682333A CN103667799B CN 103667799 B CN103667799 B CN 103667799B CN 201310682333 A CN201310682333 A CN 201310682333A CN 103667799 B CN103667799 B CN 103667799B
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weight percent
rod iron
impurity
temperature
requirements
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CN201310682333.2A
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Chinese (zh)
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CN103667799A (en
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廖云虎
罗明
雷德江
黄志永
张华国
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四川六合锻造股份有限公司
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Abstract

The invention discloses a kind of Ni-Cr-W system high temperature alloy for Aeronautics and Astronautics and nuclear industry field and preparation method thereof, chemical constitution (weight percent) is: C0.05 ~ 0.15; Cr20.0 ~ 24.0; Mo1.00 ~ 3.00; W13.0 ~ 15.0; Si0.25 ~ 0.75; Mn0.30 ~ 1.00; Surplus Ni and impurity, its mechanical property is (under solid solution condition): tensile test at room temperature tensile strength Rm >=760Mpa; Yield strength RP0.2 >=310Mpa; Elongation A4 >=40%.

Description

High temperature alloy and preparation method thereof

Technical field

The present invention relates to high temperature alloy, particularly relate to a kind of Ni-Cr-W system high temperature alloy for Aeronautics and Astronautics and nuclear industry field and preparation method thereof.

Background technology

The Working environment of aircraft engine parts proposes harsh service requirements to material.

First be high temperature.Aero-jet engine is from pneumatic plant to jet pipe, and each component work at a certain temperature, and some part will long term operation under the condition more than 800 DEG C.

Next is heavily stressed.Some high-temperature components, due to vibrations, the washing away of air-flow, particularly rotate the centrifugation caused, will bear larger stress.Stress as turbine blade can reach 300 ~ 409Mpa.

The chemical action such as oxidation and corrosion again.There is a large amount of oxygen, aqueous vapor in combustion gas, and there is SO 2, H 2the corrosive gasess such as S, all play oxidation and corrosive nature to hot parts.

And along with the development of aero gas turbine engine, the increase of thrust-weight ratio, the Working environment of engine parts is day by day harsh.For turbine intake temperature, active service machine is about 1600K, and reach 1850 ~ 1950K grinding machine, beforehand research machine will up to 2250 ~ 2350K.Develop the gas turbine engine of higher thrust-weight ratio, top priority is the high-temperature material of development use properties excellence.

Aircraft engine is to the basic demand of high-temperature material mainly:

1, higher thermostability, anticorrosive (mainly anti-oxidant) ability namely under high temperature;

2, high hot strength;

3, good processing performance.

Summary of the invention

Instant invention overcomes the deficiencies in the prior art, a kind of high temperature alloy and preparation method thereof is provided, meet the service requirements of aircraft engine parts under its Working environment.

Consider the problems referred to above of prior art, according to an aspect disclosed by the invention, the present invention by the following technical solutions:

A kind of high temperature alloy, comprising:

C:0.05 ~ 0.15 (weight percent); Cr:20.0 ~ 24.0 (weight percent);

Mo:1.00 ~ 3.00 (weight percent); W:13.0 ~ 15.0 (weight percent);

Si:0.25 ~ 0.75 (weight percent); Mn:0.30 ~ 1.00 (weight percent);

Co:1.00 ~ 3.00 (weight percent), surplus is Ni and impurity.

In order to realize the present invention better, further technical scheme is:

According to one embodiment of the invention, described impurity comprises:

P≤0.015 (weight percent); S≤0.005 (weight percent);

Fe≤3.00 (weight percent); Ti≤0.010 (weight percent).

The present invention can also be:

Prepare a method for high temperature alloy, comprising:

(1) melting in vacuum induction furnace of required element is got, smelting temperature 1540 ~ 1560 DEG C; In fusion process, regulate the content of each element, make its weight ratio meet design requirements, the content controlling impurity element is as far as possible low, and solution casting becomes consumable electrode;

(2) by consumable electrode remelting refining in electroslag furnace, reduce the content of impurity element further, make it meet design requirements, remelting becomes ESR ingot.

According to one embodiment of the invention:

1) ESR ingot heats forged is made rod iron, step and processing parameter as follows;

Rod iron is heated to 1200 ~ 1230 DEG C, is incubated stove after 24 hours and is chilled to 1110 ~ 1130 DEG C, is incubated 2 ~ 3 hours again, start forging;

2) the rear air cooling of rod iron forging is to room temperature;

3) rod iron surface treatment, carries out car optical processing to finished product rod iron surface, eliminates surface imperfection and rod iron size, shape, surface quality are met design requirement, obtained finished product rod iron.

4) inspection by sampling mechanical property on finished product rod iron, carries out corresponding mechanical property test;

--sample heat treatment step and processing parameter as follows:

Solid solution: 1200 ~ 1240 DEG C of 1 hour times of Heating temperature

The type of cooling: water-cooled

--the technical requirements of sample tensile test at room temperature is as follows:

Tensile strength Rm >=760Mpa

Yield strength RP0.2 >=310Mpa

Elongation A4 >=40%

Compared with prior art, one of beneficial effect of the present invention is:

In technical scheme of the present invention, adopt high temperature alloy prepared by above-mentioned materials and corresponding process method, through tensile test at room temperature, result shows that its mechanical property reaches design requirements completely, and test-results is as follows:

Room temperature tensile:

Rm R p0.2 A 4 Mpa Mpa % 809 377 50 798 368 49 803 374 53 801 371 47

The aviation engine parts manufactured with this material, can meet the service requirements of engine parts Working environment, are namely provided with higher thermostability, anticorrosive (mainly anti-oxidant) ability namely under high temperature; High hot strength; Good processing performance.

Embodiment

Below in conjunction with embodiment, the present invention is described in further detail, but embodiments of the present invention are not limited thereto.

Get required chemical element, at vacuum induction furnace smelting, in fusion process, regulate the content of chemical element, make its weight percent as follows:

C Cr Co W Mo Si Mn Example 1 0.10 21.9 1.87 13.9 2.09 0.47 0.59 Example 2 0.09 21.5 1.80 13.8 2.10 0.43 0.55 Example 3 0.11 21.3 1.79 13.7 2.05 0.37 0.54 Example 4 0.105 21.0 1.89 14.0 2.03 0.39 0.60 Example 5 0.10 21.7 1.90 14.2 2.07 0.41 0.61

And the content controlling impurity element is as far as possible low, solution casting becomes consumable electrode;

(2) by consumable electrode remelting refining in electroslag furnace, reduce the content of impurity element further, make it meet following requirement:

C0.05 ~ 0.15 (weight percent) Cr20.0 ~ 24.0 (weight percent)

Mo1.00 ~ 3.00 (weight percent) W13.0 ~ 15.0 (weight percent)

Si0.25 ~ 0.75 (weight percent) Mn0.30 ~ 1.00 (weight percent)

Co1.00 ~ 3.00 (weight percent)

Surplus is Ni and inevitable impurity.

Described impurity is:

P≤0.015 (weight percent) S≤0.005 (weight percent)

Fe≤3.00 (weight percent) Ti≤0.010 (weight percent)

After each component concentration of sampling analysis is qualified, make ESR ingot.

Two, ESR ingot is made rod iron, comprises step:

(1) melting in vacuum induction furnace of required element is got, smelting temperature 1540 ~ 1560 DEG C; In fusion process, regulate the content of each element, make its weight ratio meet design requirements, the content controlling impurity element is as far as possible low, and solution casting becomes consumable electrode;

(2) by consumable electrode remelting refining in electroslag furnace, reduce the content of impurity element further, make it meet design requirements, remelting becomes ESR ingot.

The manufacture method of above-mentioned rod iron, comprises step:

1) ESR ingot heats forged is made rod iron, step and processing parameter as follows;

Rod iron is heated to 1200 ~ 1230 DEG C, is incubated stove after 24 hours and is chilled to 1110 ~ 1130 DEG C of insulations 2 ~ 3 hours, start forging;

2) the rear air cooling of rod iron forging is to room temperature;

3) rod iron surface treatment, carries out car optical processing to finished product rod iron surface, eliminates surface imperfection and rod iron size, shape, surface quality are met design requirement, obtained finished product rod iron;

4) inspection by sampling mechanical property on finished product rod iron, carries out corresponding mechanical property test;

--sample heat treatment step and processing parameter as follows:

Solid solution: 1200 ~ 1240 DEG C of 1 hour times of Heating temperature

The type of cooling: water-cooled

--the technical requirements of sample tensile test at room temperature is as follows:

Tensile strength Rm >=760Mpa

Yield strength RP0.2 >=310Mpa

Elongation A4 >=40%

Stand the test is finished product.

To sum up a kind of Ni-Cr-W system high temperature alloy for Aeronautics and Astronautics and nuclear industry field disclosed in embodiment, chemical constitution (weight percent) is: C0.05 ~ 0.15; Cr20.0 ~ 24.0; Mo1.00 ~ 3.00; W13.0 ~ 15.0; Si0.25 ~ 0.75; Mn0.30 ~ 1.00; Surplus Ni and impurity, its mechanical property is (under solid solution condition):--tensile test at room temperature tensile strength Rm >=760Mpa; Yield strength RP0.2 >=310Mpa; Elongation A4 >=40%.

Also disclose the high temperature alloy that a kind of concrete component is following in another embodiment, comprising:

C:0.1 (weight percent); Cr:22 (weight percent);

Mo:1.5 (weight percent); W:14 (weight percent);

Si:0.5 (weight percent); Mn:0.7 (weight percent);

Co:2 (weight percent), surplus is Ni and impurity.

In this specification sheets, each embodiment adopts the mode of going forward one by one to describe, and what each embodiment stressed is the difference with other embodiment, identical similar portion cross-reference between each embodiment.

Spoken of in this manual " embodiment ", " another embodiment ", " embodiment ", etc., refer to the specific features, structure or the feature that describe in conjunction with this embodiment and be included at least one embodiment of the application's generality description.Multiple place occurs that statement of the same race is not necessarily refer to same embodiment in the description.Furthermore, when describing specific features, structure or a feature in conjunction with any embodiment, what advocate is also fall within the scope of the invention to realize this feature, structure or feature in conjunction with other embodiments.

Although with reference to multiple explanatory embodiment of the present invention, invention has been described here, but, should be appreciated that, those skilled in the art can design a lot of other amendment and embodiment, these amendments and embodiment will drop within spirit disclosed in the present application and spirit.More particularly, in the scope of, claim open in the application, multiple modification and improvement can be carried out to the building block of subject combination layout and/or layout.Except the modification of carrying out building block and/or layout is with except improvement, to those skilled in the art, other purposes also will be obvious.

Claims (2)

1. a high temperature alloy, is characterized in that, comprising:
C:0.15 (weight percent); Cr:20.0 (weight percent);
Mo:3.00 (weight percent); W:15.0 (weight percent);
Si:0.75 (weight percent); Mn:1.00 (weight percent);
Co:1.00 ~ 3.00 (weight percent), surplus is Ni and impurity, and described impurity comprises:
P≤0.015 (weight percent); S≤0.005 (weight percent);
Fe≤3.00 (weight percent); Ti≤0.010 (weight percent).
2. prepare a method for high temperature alloy as claimed in claim 1, it is characterized in that, comprising:
(1) melting in vacuum induction furnace of required element is got, smelting temperature 1540 ~ 1560 DEG C; In fusion process, regulate the content of each element, make its weight ratio meet design requirements, the content controlling impurity element is as far as possible low, and solution casting becomes consumable electrode;
(2) by consumable electrode remelting refining in electroslag furnace, reduce the content of impurity element further, make it meet the design requirements of a kind of high temperature alloy described in claim 1, remelting becomes ESR ingot;
(3) ESR ingot heats forged is made rod iron, step and processing parameter as follows;
Rod iron is heated to 1200 ~ 1230 DEG C, is incubated stove after 24 hours and is chilled to 1110 ~ 1130 DEG C, is incubated 2 ~ 3 hours again, start forging;
(4) the rear air cooling of rod iron forging is to room temperature;
(5) rod iron surface treatment, carries out car optical processing to finished product rod iron surface, eliminates surface imperfection and rod iron size, shape, surface quality are met design requirement, obtained finished product rod iron;
(6) inspection by sampling mechanical property on finished product rod iron, carries out corresponding mechanical property test;
Sample heat treatment step and processing parameter as follows:
Solid solution: 1200 ~ 1240 DEG C of 1 hour times of Heating temperature
The type of cooling: water-cooled
The technical requirements of sample tensile test at room temperature is as follows:
Tensile strength Rm >=760Mpa
Yield strength RP0.2 >=310Mpa
Elongation A4 >=40%.
CN201310682333.2A 2013-12-12 2013-12-12 High temperature alloy and preparation method thereof CN103667799B (en)

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CN106498237A (en) * 2016-11-23 2017-03-15 四川六合锻造股份有限公司 A kind of Ni-Cr-Mo tungsten niobium aluminum titanium system high-temperature alloy material, preparation method and application

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CN105132751B (en) * 2015-09-14 2017-08-22 四川六合锻造股份有限公司 A kind of Ni Cr Al Fe systems high-temperature alloy material, its preparation method and application
CN105695839A (en) * 2016-02-25 2016-06-22 四川六合锻造股份有限公司 High-temperature alloy material used for manufacturing of aero-engine fastener and preparation method thereof
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CN106435278B (en) * 2016-10-24 2019-10-29 四川六合特种金属材料股份有限公司 Acting type alloy material and its heat treatment process and application when a kind of aluminium-titanium
CN107217174A (en) * 2017-05-03 2017-09-29 四川六合锻造股份有限公司 Ni Cr based high-temperature alloys and its preparation and detection method
CN108866388A (en) * 2017-05-16 2018-11-23 宋广东 Hot environment heat-resisting alloy material and its manufacturing method
CN108467973B (en) * 2018-06-11 2020-04-10 江苏银环精密钢管有限公司 Nickel-chromium-tungsten high-temperature alloy seamless tube for 700 ℃ ultra-supercritical boiler and manufacturing method thereof
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Address after: 621000 Yanghe Village, Sanhe Town, Jiangyou City, Mianyang City, Sichuan Province

Patentee after: Sichuan Liuhe Special Metal Materials Co., Ltd.

Address before: 621000 Yanghe Village, Sanhe Town, Jiangyou City, Mianyang City, Sichuan Province

Patentee before: Sichuan Liuhe Forging Company Ltd.