CN106435279A - Highstrength oxidationresistant hightemperature alloy and heat treatment technique and application thereof - Google Patents
Highstrength oxidationresistant hightemperature alloy and heat treatment technique and application thereof Download PDFInfo
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- CN106435279A CN106435279A CN201610924698.5A CN201610924698A CN106435279A CN 106435279 A CN106435279 A CN 106435279A CN 201610924698 A CN201610924698 A CN 201610924698A CN 106435279 A CN106435279 A CN 106435279A
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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
- C22C19/056—Alloys based on nickel or cobalt based on nickel with chromium and Mo or W with the maximum Cr content being at least 10% but less than 20%
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- 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
- C22F1/10—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
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- Organic Chemistry (AREA)
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- Thermal Sciences (AREA)
- Crystallography & Structural Chemistry (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a high-strength oxidation-resistant high-temperature alloy. The high-strength oxidation-resistant high-temperature alloy comprises, by weight, no more than 0.08% of C, no more than 0.1% of Mn, 14.0-16.0% of Cr, 4.5-6.0% of Mo, 3.35-3.65% of Ti, 4.0-6.0% of Fe, 4.4-4.8% of Al, 0.05-0.11% of B, and the balance Ni and inevitable impurities. At the room temperature (25 DEG C), the tensile strength sigma b of the alloy is equal to or higher than 950N/mm<2>, the yield strength sigma 0.2 of the alloy is equal to or higher than 790N/mm<2>, the elongation delta 5 of the alloy is equal to or higher than 4%, and the reduction of area of the alloy is equal to or higher than 9%. According to the high temperature endurance performance, the stress is 140Mpa, the temperature is 980 DEG C, the tensile strength sigma b is equal to or higher than 550N/mm<2>, the yield strength sigma 0.2 is equal to or higher than 260N/mm<2>, the elongation delta 5 is equal to or higher than 16%, and the reduction of area is equal to or higher than 32%. At the temperature of 600 DEG C and 900 DEG C, Kps of the alloy can reach 2.32*10<-20>mg<2>.cm<-4>.s<-1> and 1.23*10<-7>mg<2>.cm<-4>.s<-1>. The invention further provides the heat treatment technique for preparing the alloy and the application of the alloy used in engine parts.
Description
Technical field
The present invention relates at the manufacturing and designing of alloy material, more particularly, to a kind of high-strength, antioxidant high temperature alloy and its heat
Science and engineering skill and application.
Background technology
In technical field of aerospace, the thermal part of aero-engine, the use condition of blade material is the harshest.
Turbo blade is the critical component of gas turbine, in order to improve the efficiency of engine it is necessary to improve constantly turbine combustion
Gas inlet temperature.The temperature of general blade portion reaches more than 650 DEG C, and even as high as 980 DEG C, the temperature of leaf root part is also up to
More than 700 DEG C.And turbo blade bears the effect of aerodynamic force and centrifugal force, produce tension and bending stress, combustion gas simultaneously
The high-speed pulse of stream, makes blade produce vibrations stress.The tension average out to 140Mpa that blade portion bears, leaf root part bears
Tension reach more than 280Mpa, therefore blade material will have enough high temperature tensile strengths, creep rupture strength and creep strength, this
Also to there are good mechanical fatigue, thermal fatigue property, antioxygenic property, hot corrosion resistance and certain plasticity outward.
《The high-temperature oxidation resistant behavior of Ni-Cr-Al-Fe base alloy powder》Have studied different element proportionings to Ni-Cr-Al-
The impact of the antioxygenic property of Fe based alloy.This research finds, in the case of adding yttrium, the content of aluminium to be promoted to 9%, can
The Kp obtaining oxidation at 600 DEG C is 5.94 × 10-19mg2·cm-4·s-1Antioxygenic property.
In order to further enhance the antioxygenic property of such alloy, researcher is had to probe into the interpolation of graphite to alloy antioxygen
Change the impact of performance, find that Ni-Cr based alloy shows preferably anti-oxidant when the content of graphite increases to 6.0wt.%
Property, quality increases minimum.
The Ni-Cr-Al-Fe base alloy material that the Chinese patent of Application No. 201510579422.3 discloses its gained is same
Sample possesses preferable mechanical property.Although, preferably, yield strength is not ideal enough for the tensile strength of gained alloy.
In general, the supply of rare earth metal (as yttrium) is often restricted, price is also higher, how without rare earth metal preparation
The high-temperature alloy material of excellent performance, is one of primary study direction of those skilled in the art.
In sum, this area urgently seeks that a kind of strength character is outstanding, more preferably and preparing raw material is easy to get antioxygenic property
Can be used for prepare turbo blade preparation high-temperature alloy material.
Content of the invention
An object of the present invention is to develop use intensity performance (mainly high temperature tensile strength, high-temperature yield strength
Performance, high-temperature and durable) higher, antioxygenic property more preferably, combination property more preferably high-temperature alloy material；Another object of the present invention
It is to solve it to have the Technology for Heating Processing of more preferable serviceability；It is also an object of the present invention to provide gained alloy is starting
Application on machine part, the application especially on turbo blade.
The technical solution of the present invention is：Using Ni-Cr-Mo-Al-Ti-B steel based alloy, its chemical composition, with weight
Percentages, C≤0.08；Mn≤0.10；Cr 14.0～16.0；Mo 4.5～6.0；Ti 3.35～3.65；Fe 4.0～
6.0；Al 4.4～4.8；B 0.05～0.11；Balance of Ni and inevitable impurity.
Described inevitable impurity includes：P≤0.04；S≤0.015；Cu≤0.1；Si≤0.15.
The Technology for Heating Processing of above-mentioned alloy includes step：
(1) by the forging preparing, carry out solution treatment at 1100-1190 DEG C, be incubated 0.5-5 hour, cold afterwards
But to room temperature；
(2) carry out intermediate treatment at 1020-1100 DEG C, be incubated 0.5-5 hour, be cooled to room temperature afterwards；
(3) carry out Ageing Treatment at 800-875 DEG C, be incubated 1-10 hour, be cooled to room temperature afterwards.
Compared with the Chinese patent of Application No. 201510579422.3, alloy of the present invention does not use rare earth metal yttrium, institute
Raw material is easy to get.Meanwhile, it was found by the inventors of the present invention that being not enough to obtain outstanding antioxygenic property in the content improving aluminium
Afterwards, by the common interpolation of Ti, Mo and B, the antioxygenic property of alloy is not only made to significantly improve it is often more important that going back
Greatly improve the yield strength of alloy.
At present, what impact the addition of Ti has to the antioxygenic property of high temperature alloy, not yet forms final conclusion.As Nagelberg
The research of A S shows that Ti is unfavorable to the non-oxidizability of 310 stainless steels (Fe20Ni25Cr).
For general Fe-Cr-Ni-Al alloy, after adding Ti, the high-temperature oxidation resistance of alloy can reduce,
And the content of Ti is higher, impact is bigger.This is because, after adding Ti, alloy surface can form TiO2, thus destroy (Fe,
Cr)2O3NiO diaphragm, is that oxygen provides diffusion admittance, aggravation oxidation.
Preferably, in step (1), solid solution temperature is 1150 DEG C, and temperature retention time is 1 hour.
Preferably, in step (2), intermediate treatment temperature is 1065 DEG C, and temperature retention time is 2 hours.
Preferably, in step (3), aging temperature is 845 DEG C, and temperature retention time is 4 hours.
The mode of described cooling is air cooling or water-cooled, preferably air cooling.
Described forging be by alloy raw material after vaccum sensitive stove and vacuum consumable remelting melting and refining treatment gained.
The invention has the beneficial effects as follows：
(1) alloy material of the present invention has tensile strength sigma b under excellent resistance to elevated temperatures and mechanical property, room temperature
≥950N/mm2, yield strength σ 0.2 >=790N/mm2, percentage elongation δ 5 >=4%, reduction of area >=9%；High temperature endurance performance：Stress
980 DEG C of 140Mpa, temperature, tensile strength sigma b >=550N/mm2, yield strength σ 0.2 >=260N/mm2, percentage elongation δ 5 >=16%, face
Shrinkage >=32%；
(2) alloy material of the present invention has excellent high-temperature oxidation resistance, and at 600 DEG C, Kp is up to 2.32 × 10- 20mg2·cm-4·s-1；At 900 DEG C, Kp can be only 1.23 × 10-7mg2·cm-4·s-1；
(3) the turbo blade material of the present invention disclosure satisfy that the use requirement of high temperature complex work environment, sends out for lifting
Motivation power, has great importance, worth large-scale promotion and application, during material manufacture, carries out solution treatment, makes
Solute atoms enters in solvent lattice, makes lattice produce distortion, so that solid solution hardness and intensity is raised, strengthens turbine sheet material
Toughness and etch resistant properties, eliminate stress and softening, convenient after continue machine-shaping, finally Ageing Treatment is carried out to material,
The temperature separating out in hardening constituent heats and is incubated, and makes hardening constituent Precipitation, is hardened, and improves the strong of turbo blade material
Degree, has good economic benefit and social benefit, is suitable for promoting the use of.
Specific embodiment
Embodiment 1
(1) press following alloying components (mass percent) and prepare raw material：
C 0.08；Mn 0.1；Cr 14.0；Mo 4.5；Ti 3.35；Fe 4.0；Al 4.4；B 0.05；P≤0.04%；S
≤ 0.015%；Cu≤0.1%；Si≤0.15%；Balance of Ni.
(2) after vaccum sensitive stove and vacuum consumable remelting carry out melting and refining, obtain alloy forged piece；
(3) by the forging preparing, carry out solution treatment at 1100 DEG C, be incubated 5 hours, cooling (air cooling) afterwards is extremely
Room temperature；
(4) carry out intermediate treatment at 1020 DEG C, be incubated 5 hours, cooling (air cooling) is to room temperature afterwards；
(5) carry out Ageing Treatment at 800 DEG C, be incubated 10 hours, cooling (air cooling) is to room temperature afterwards.
(6) forming processes are carried out using forge hot or hot rolling technology.
Embodiment 2
(1) press following alloying components and prepare raw material：
C 0.05；Mn 0.08；Cr 16.0；Mo 6.0；Ti 3.65；Fe 6.0；Al 4.8；B 0.11；P≤0.04%；
S≤0.015%；Cu≤0.1%；Si≤0.15%；Balance of Ni.
(2) after vaccum sensitive stove and vacuum consumable remelting carry out melting and refining, obtain alloy forged piece；
(3) by the forging preparing, carry out solution treatment at 1190 DEG C, be incubated 0.5 hour, cool down (air cooling) afterwards
To room temperature；
(4) carry out intermediate treatment at 1100 DEG C, be incubated 0.5 hour, cooling (air cooling) is to room temperature afterwards；
(5) carry out Ageing Treatment at 875 DEG C, be incubated 1 hour, cooling (air cooling) is to room temperature afterwards.
(6) forming processes are carried out using forge hot or hot rolling technology.
Embodiment 3
(1) press following alloying components and prepare raw material：
C 0.03；Mn≤0.05；Cr 15.0；Mo 5.0；Ti 3.50；Fe 5.0；Al 4.5；B 0.06；P≤
0.04%；S≤0.015%；Cu≤0.1%；Si≤0.15%；Balance of Ni.
(2) after vaccum sensitive stove and vacuum consumable remelting carry out melting and refining, obtain alloy forged piece；
(3) by the forging preparing, carry out solution treatment at 1150 DEG C, be incubated 1 hour, cooling (air cooling) afterwards is extremely
Room temperature；
(4) carry out intermediate treatment at 1065 DEG C, be incubated 2 hours, cooling (air cooling) is to room temperature afterwards；
(5) carry out Ageing Treatment at 845 DEG C, be incubated 4 hours, cooling (air cooling) is to room temperature afterwards.
(6) forming processes are carried out using forge hot or hot rolling technology.
Experimental example 1
Mechanics properties testing is carried out to embodiment 1-3 gained alloy：
The tensile strength sigma of room temperature (25 DEG C)b≥950N/mm2, yield strength σ0.2≥790N/mm2, percentage elongation δ5>=4%,
Reduction of area >=9%；High temperature endurance performance：980 DEG C of stress 140Mpa, temperature, tensile strength sigmab≥550N/mm2, yield strength σ0.2
≥260N/mm2, percentage elongation δ5>=16%, reduction of area >=32%.
Experimental example 2
At 600 DEG C and 900 DEG C, Kp detection is carried out to embodiment 1-3 gained alloy, result is as shown in table 1：
Table 1
Experimental example 3
The content of B in the alloy of embodiment 3 is heightened to after 0.13%, gained alloy is in 980 DEG C of stress 140Mpa, temperature
Under the conditions of, tensile strength sigmabFor 378N/mm2, yield strength σ0.2For 192N/mm2.
It is obvious to a person skilled in the art that the invention is not restricted to the details of above-mentioned one exemplary embodiment, Er Qie
In the case of the spirit or essential attributes of the present invention, the present invention can be realized in other specific forms.Therefore, no matter
From the point of view of which point, embodiment all should be regarded as exemplary, and be nonrestrictive, the scope of the present invention is by appended power
Profit requires rather than described above limits, it is intended that all in the implication and scope of the equivalency of claim by falling
Change is included in the present invention.Any mark in claim should not be considered as limiting involved claim.
Moreover, it will be appreciated that although this specification is been described by according to embodiment, not each embodiment only wraps
Containing an independent technical scheme, only for clarity, those skilled in the art should for this narrating mode of specification
Using specification as an entirety, the technical scheme in each embodiment can also form those skilled in the art through appropriately combined
Understandable other embodiment.
Claims (10)
1. a kind of high-strength, antioxidant high temperature alloy it is characterised in that：Its chemical composition, by weight percentage for：
C≤0.08；
Mn≤0.10；
Cr 14.0～16.0；
Mo 4.5～6.0；
Ti 3.35～3.65；
Fe 4.0～6.0；
Al 4.4～4.8；
B 0.05～0.11；
Balance of Ni and inevitable impurity.
2. a kind of high-strength, antioxidant high temperature alloy according to claim 1 it is characterised in that：Described impurity, by quality
Percentages, including：
P≤0.04% S≤0.015%
Cu≤0.1% Si≤0.15%.
3. a kind of Technology for Heating Processing of the high-strength, antioxidant high temperature alloy described in claim 1 or 2 is it is characterised in that described
Technique includes step：
(1) by the forging preparing, carry out solution treatment at 1100-1190 DEG C, be incubated 0.5-5 hour, be cooled to afterwards
Room temperature；
(2) carry out intermediate treatment at 1020-1100 DEG C, be incubated 0.5-5 hour, be cooled to room temperature afterwards；
(3) carry out Ageing Treatment at 800-875 DEG C, be incubated 1-10 hour, be cooled to room temperature afterwards.
4. a kind of Technology for Heating Processing of high-strength, antioxidant high temperature alloy according to claim 3 is it is characterised in that step
(1) in, solid solution temperature is 1150 DEG C, and temperature retention time is 1 hour.
5. a kind of Technology for Heating Processing of high-strength, antioxidant high temperature alloy according to claim 3 is it is characterised in that step
(2) in, intermediate treatment temperature is 1065 DEG C, and temperature retention time is 2 hours.
6. a kind of Technology for Heating Processing of high-strength, antioxidant high temperature alloy according to claim 3 is it is characterised in that step
(3) in, aging temperature is 845 DEG C, and temperature retention time is 4 hours.
7. a kind of Technology for Heating Processing of high-strength, antioxidant high temperature alloy according to claim 3 is it is characterised in that described
The mode of cooling is air cooling or water-cooled, preferably air cooling.
8. a kind of Technology for Heating Processing of high-strength, antioxidant high temperature alloy according to claim 3 is it is characterised in that described
Forging be by alloy raw material after vaccum sensitive stove and vacuum consumable remelting melting and refining treatment gained.
9. application on engine components for the high-strength, antioxidant high temperature alloy described in claim 1 or 2.
10. application according to claim 9 is it is characterised in that described engine components are turbo blade.
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106702217A (en) * | 2017-03-07 | 2017-05-24 | 四川六合锻造股份有限公司 | Ni-Cr-Co-Mo-Al-Ti high-temperature alloy material and preparation method thereof |
| CN108754237A (en) * | 2018-05-15 | 2018-11-06 | 昆明理工大学 | A kind of method for preparing powder metallurgy of Ni-Cr-Al-Fe systems high temperature alloy |
| CN110468357A (en) * | 2019-08-22 | 2019-11-19 | 惠州市泰铭五金有限公司 | A kind of high life heat resistanceheat resistant difference deformable metal plate and processing method |
| CN111719057A (en) * | 2019-03-20 | 2020-09-29 | 沈阳人和机械制造有限公司 | Falling film tube and manufacturing process thereof |
| CN114934157A (en) * | 2022-07-01 | 2022-08-23 | 丹阳市金星镍材有限公司 | Heat treatment process of nickel-based high-temperature alloy for cold heading |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106702217A (en) * | 2017-03-07 | 2017-05-24 | 四川六合锻造股份有限公司 | Ni-Cr-Co-Mo-Al-Ti high-temperature alloy material and preparation method thereof |
| CN108754237A (en) * | 2018-05-15 | 2018-11-06 | 昆明理工大学 | A kind of method for preparing powder metallurgy of Ni-Cr-Al-Fe systems high temperature alloy |
| CN111719057A (en) * | 2019-03-20 | 2020-09-29 | 沈阳人和机械制造有限公司 | Falling film tube and manufacturing process thereof |
| CN110468357A (en) * | 2019-08-22 | 2019-11-19 | 惠州市泰铭五金有限公司 | A kind of high life heat resistanceheat resistant difference deformable metal plate and processing method |
| CN114934157A (en) * | 2022-07-01 | 2022-08-23 | 丹阳市金星镍材有限公司 | Heat treatment process of nickel-based high-temperature alloy for cold heading |
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Address after: 621700 West Section of Baolun Road, Henan Industrial Park, Jiangyou City, Mianyang City, Sichuan Province Patentee after: Sichuan Liuhe Special Metal Materials Co., Ltd. Address before: 621700 West Section of Baolun Road, Henan Industrial Park, Jiangyou City, Mianyang City, Sichuan Province Patentee before: Sichuan Liuhe Forging Company Ltd. |