CN109536819A - A kind of blade of aviation engine bonding coat MCrAlY target - Google Patents
A kind of blade of aviation engine bonding coat MCrAlY target Download PDFInfo
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- CN109536819A CN109536819A CN201811576175.1A CN201811576175A CN109536819A CN 109536819 A CN109536819 A CN 109536819A CN 201811576175 A CN201811576175 A CN 201811576175A CN 109536819 A CN109536819 A CN 109536819A
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- block
- target
- mcraly
- crucible
- blade
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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
- C22C19/058—Alloys based on nickel or cobalt based on nickel with chromium without Mo and W
-
- 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
-
- C—CHEMISTRY; METALLURGY
- C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
- C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/22—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the process of coating
- C23C14/34—Sputtering
- C23C14/3407—Cathode assembly for sputtering apparatus, e.g. Target
- C23C14/3414—Metallurgical or chemical aspects of target preparation, e.g. casting, powder metallurgy
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Manufacture And Refinement Of Metals (AREA)
Abstract
A kind of blade of aviation engine bonding coat MCrAlY target, it is characterized by: the MCrAlY target carries out ingredient: M 40~70% by nominal composition by weight percentage, Cr 19~35%, Al 10~25%, Y 0.1~1.5%, the M refers to that metal, M are at least one of Ni and Co.The present invention passes through the optimization of component and the synergistic effect with vacuum induction melting matching technique, a kind of high-purity MCrAlY target of blade of aviation engine bonding coat is obtained, the mass percentage of oxygen element is less than 6ppm in the target alloy, the mass percentage of element sulphur is less than 6ppm, and the mass percentage of nitrogen is less than 5ppm.
Description
Technical field
The present invention relates to aeronautical material fields, and in particular to a kind of blade of aviation engine bonding coat MCrAlY target
Material.
Background technique
With the fast development of aircraft industry, engine thermal end pieces operating temperature is gradually risen, with the leaf of gas turbine
For piece and combustion chamber, by the oxidation and corrosiveness of high-temperature fuel gas, the temperature that they are born is up to 1100 DEG C, has surpassed
The ultimate-use (limiting service) temperature (1075 DEG C) of nickel-base alloy is gone out.Currently advanced ceramic heat-barrier coating can be in the work environment
Leaf temperature is further reduced about 90~150 DEG C or so.The most common thermal barrier coating system is that metal bonding coating and ceramics are protected
Duplex coating system composed by sheath.Metal bonding coating main function is to mitigate thermal expansion coefficient between ceramic layer and matrix not
The problem of matching, improves the high temperature protection performance of matrix.
As the bonding layer material of thermal barrier coating, MCrAlY adhesive layer at being grouped as in Thermal Cycling to adhesive layer
The behavior of peeling off of the growth rate of oxide layer, ingredient, the binding force between integrality and matrix and thermal oxide layer rise and determine
Effect.Therefore, alloy bonding layer is extremely important at service life of the component selections for thermal barrier coating.Contain in MCrAlY alloy
Certain density Al and Cr is to form Al in matrix surface in oxidation process2O3And Cr2O3Continuous protective film, protectiveness
The change film of oxygen is being the oxidation resistant key point of thermal barrier coating.Wherein, Y mainly rises in MCrAlY and improves Al2O3And Cr2O3's
Adhesion strength between continuous protective film and matrix alloy.
Purity is the first requirement of MCrAlY alloy, and the metallurgical quality of MCrAlY alloy directly affects making for thermal barrier coating
With performance, purity is higher, and performance is better.O, N, S are objectionable impurities elements in nickel base superalloy, they usually segregate to oxidation
Object-alloy interface, weaken oxide and it is Ni-based between interface adhesion.In addition, O, N, S can be with the alloys in nickel-base alloy
Element interacts, and forms non-metallic inclusion with oxide, sulfide, nitride form, they are all that stress is concentrated
Area of origin, deteriorate the comprehensive performance of MCrAlY alloy.
Vacuum induction melting (VIM) is a kind of gold using the principle smelting metal under vacuum conditions of electromagnetic induction heating
Belong to preparation process, fire-clay crucible formula vacuum induction melting there are two big outstanding advantages, i.e., without Forced water cooling system, low energy consumption.Secondly,
Vaccum sensitive stove has strong electromagnetic agitation, can keep the very high degree of superheat (150 ~ 200 DEG C), facilitate in fusion process
Alloying component is eliminated to be segregated and obtain the higher material of metallurgical quality.Y element is a kind of strong due to its lower formation free energy
Oxide sulfide formation element, alloy refining period yttrium have very strong deoxidation and desulphurizing ability, on the other hand, very
Empty induction furnace has strong electromagnetic agitation, can keep the very high degree of superheat (150 ~ 200 DEG C), facilitate in fusion process to disappear
Except alloying component is segregated and obtains the higher material of metallurgical quality.Its deoxidation and desulfurization product are under the action of electromagnetic agitation by band
To bath surface, dross is formed to purify alloy melt.Therefore, it is necessary to which root is returned to trace to the source, go out from MCrAlY alloy melting angle
Hair controls micro objectionable impurities elements (O, N, S) content in master alloy to greatest extent, and obtain high purification is suitable for aviation
Engine blade bonding coat becomes one of current urgent problem to be solved with MCrAlY target.
Summary of the invention
It is an object of the present invention to provide a kind of blade of aviation engine bonding coat MCrAlY target, which is
The target of high-purity, the mass percentage of oxygen element is less than 5ppm in alloy, and the mass percentage of element sulphur is less than 5ppm,
The mass percentage of nitrogen is less than 4ppm.
In order to achieve the above objectives, the technical solution adopted by the present invention is that: a kind of blade of aviation engine bonding coat is used
MCrAlY target carries out ingredient by nominal composition by weight percentage:
M 40~70%,
Cr 19~35%,
Al 10~25%,
Y 0.1~1.5%,
The M refers to that metal, M are at least one of Ni and Co.
Further, preferable scheme is that the MCrAlY target by nominal composition carries out ingredient by weight percentage:
M 45~65%,
Cr 20~32%,
Al 14~22%,
Y 0.2~1%.
Further, the MCrAlY target the preparation method is as follows:
1) pretreatment of raw material: after Ni block, Co block, Cr block, Al block and Y block carry out surface scale polishing, using acetone in frequency
Under conditions of 20~30KHz, it is cleaned by ultrasonic 2 times, 5 min, is put in baking oven after cleaning and dries 10 under the conditions of 373K every time
~30 min obtain pretreated target source material；
2) crucible and ingot mould pretreatment: by the graphite ingot mould of vacuum induction melting and the graphite ingot after molding flask moulding
Mould is put into resistance furnace when being warming up to 1173K, keeps the temperature 2~4h；
3) crucible and ingot mould installation: crucible and the ingot mould being fully warmed-up are mounted in vacuum induction melting furnace, crucible is cleared up
And ingot mould, and install foam ceramic filter additional on sprue cup；
4) ingredient and charging: being first added the Ni block, Co block and Cr block prepared after having pre-processed by alloy nominal composition in crucible,
And Al block and Y block are added in charging hopper, close vacuum induction melting furnace fire door；
5) it vacuumizes: vacuum induction melting furnace is vacuumized, so that vacuum degree reaches 0.032Pa in furnace；
6) melt: starting power transmission after the completion of vacuumizing, to be at this time that 5~10 KW heat 10~15min with small-power, increase function
After rate continues 5~10min of heating to 10~15 KW, increase power to 20 KW until furnace charge is all melting down；
7) add aluminium block: step 6 furnace charge is all melting down, when being heated to charge-temperature is 1773K~1823K, by charging hopper
In Al block be added in crucible melt；
8) it skims: after Al block in step 7 furnace charge all fusing, taking the oxidizing slag of melt composition off；
9) lead to argon gas: step 8 being skimmed, high-purity argon gas protective atmosphere is passed through；
10) add yttrium block: when being heated to charge-temperature is 1773K~1823K, the Al block in charging hopper being added to crucible
In melt；
11) it refines: when being heated to charge-temperature is 1873K~2073K, starting to refine, refining time is 10~30min；
12) it casts: after refining, stopping 3~5 min of power transmission, then with 3~5KW of power to electricity, measuring charge-temperature is
At 1673 DEG C~1773 DEG C, cast molding is carried out；
13) feeding: surface is handled to meet requirement.
Vacuum induction melting blade of aviation engine bonding coat uses crucible type fire resisting with MCrAlY target in the present invention
CaO crucible, MgO crucible, Y can be used in material melting2O3Any one in crucible.
The present invention is due to using above-mentioned process, firstly, raw material used in master alloy are high pure metal Ni
(99.98%), Co(99.50%), Cr(99%), Al(99.99%) and Y(99.9%).On the one hand, then pass through abrasive machine pair
Raw material is handled in advance, is removed Ni block, Co block, Cr block, Al block and Y block and is carried out surface scale, is further reduced due to former material
Expect introduced impurity content, using acetone under conditions of frequency is 20~30KHz, be cleaned by ultrasonic 2 times, every time 5 min,
It is put in after cleaning in baking oven and dries 10~30 min under the conditions of 373K, obtain pretreated target source material.On the other hand,
Crucible for vacuum induction melting and casting are handled with graphite ingot mould, are put into resistance furnace when being warming up to 1173K, heat preservation 2
The temperature of crucible and graphite ingot mould is warming up to 1173K by~4h in advance, when avoiding power transmission early period and casting, the two and alloy
Temperature difference is excessive between melt, causes crucible and graphite ingot mould to rupture impaired, is then exactly by crucible and the ingot mould being fully warmed-up
It is mounted in vacuum induction melting furnace, and clearing furnace, crucible and ingot mould inner wall, the interference due to external environment is avoided to cause to close
The pollution of gold, and install aluminium oxide ceramics filter screen additional on sprue cup, play the role of filtering slag in melt casting.With
Afterwards, match honest material, reload by alloy nominal composition.Then, vacuum induction melting furnace is vacuumized, so that vacuum degree in furnace
Reach 0.032Pa, start power transmission, to be at this time that 5~10 KW heat 10~15min with small-power, increase power to 10~15
After KW continues 5~10min of heating, increase power to 20 KW is all melting down up to furnace charge, adds aluminium block, skims, and leads to argon gas,
Under high-purity argon gas protective atmosphere, wherein O2, N2, H2, H2O and CH4All it is not more than 2ppm, using vacuum induction melting furnace by raw material
It is smelted into master alloy.After refining, stop 3~5 min of power transmission, then with 3~5KW of power to electricity, measuring charge-temperature is
At 1673 DEG C~1773 DEG C, cast molding is carried out.By being analyzed above it is found that production technology of the invention is gone from raw material selection
It descales, the control optimization of ingredient, crucible and ingot mould cleaning, each process such as protective atmosphere melting control stringent, each process
It can avoid the introducing of impurity element.
In short, the present invention is obtained by the optimization of component and the synergistic effect with vacuum induction melting matching technique
A kind of high-purity MCrAlY target of blade of aviation engine bonding coat, the mass percentage of oxygen element is small in the target alloy
In 6ppm, the mass percentage of element sulphur is less than 6ppm, and the mass percentage of nitrogen is less than 5ppm.
Specific embodiment
A specific embodiment of the invention is briefly described as below
Embodiment 1: the NiCrAlY target carries out ingredient according to nominal composition weight percent (wt%):
Ni 46.6%,
Co 23%,
Cr 20%,
Al 10%,
Y 0.4%,
The preparation method of the NiCrAlY target:
1) pretreatment of raw material: after Ni block, Co block, Cr block, Al block and Y block carry out surface scale polishing, using acetone in frequency
Under conditions of 20~30KHz, it is cleaned by ultrasonic 2 times, 5 min, is put in baking oven after cleaning and dries 10 under the conditions of 373K every time
~30 min obtain pretreated target source material；
2) crucible and ingot mould pretreatment: by the graphite ingot mould of vacuum induction melting and the graphite ingot after molding flask moulding
Mould is put into resistance furnace when being warming up to 1173K, keeps the temperature 2~4h；
3) crucible and ingot mould installation: crucible and the ingot mould being fully warmed-up are mounted in vacuum induction melting furnace, crucible is cleared up
And ingot mould, and install foam ceramic filter additional on sprue cup；
4) ingredient and charging: being first added the Ni block, Co block and Cr block prepared after having pre-processed by alloy nominal composition in crucible,
And Al block and Y block are added in charging hopper, close vacuum induction melting furnace fire door；
5) it vacuumizes: vacuum induction melting furnace is vacuumized, so that vacuum degree reaches 0.032Pa in furnace；
6) melt: starting power transmission after the completion of vacuumizing, to be at this time that 5~10 KW heat 10~15min with small-power, increase function
After rate continues 5~10min of heating to 10~15 KW, increase power to 20 KW until furnace charge is all melting down；
7) add aluminium block: step 6 furnace charge is all melting down, when being heated to charge-temperature is 1773K~1823K, by charging hopper
In Al block be added in crucible melt；
8) it skims: after Al block in step 7 furnace charge all fusing, taking the oxidizing slag of melt composition off；
9) lead to argon gas: step 8 being skimmed, high-purity argon gas protective atmosphere is passed through；
10) add yttrium block: when being heated to charge-temperature is 1773K~1823K, the Al block in charging hopper being added to crucible
In melt；
11) it refines: when being heated to charge-temperature is 1873K~2073K, starting to refine, refining time is 10~30min；
12) it casts: after refining, stopping 3~5 min of power transmission, then with 3~5KW of power to electricity, measuring charge-temperature is
At 1673 DEG C~1773 DEG C, cast molding is carried out；
13) feeding: surface is handled to meet requirement.
Through examining: the MCrAlY target finished product impurity content that step 12 obtains is respectively O:4ppm；S:3ppm；N:
3ppm。
Embodiment 2: the NiCrAlY target carries out ingredient according to nominal composition weight percent (wt%):
Ni 39.2%,
Co 15%,
Cr 25%,
Al 20%,
Y 0.8%,
The preparation method of the NiCrAlY target:
1) pretreatment of raw material: after Ni block, Co block, Cr block, Al block and Y block carry out surface scale polishing, using acetone in frequency
Under conditions of 20~30KHz, it is cleaned by ultrasonic 2 times, 5 min, is put in baking oven after cleaning and dries 10 under the conditions of 373K every time
~30 min obtain pretreated target source material；
2) crucible and ingot mould pretreatment: by the graphite ingot mould of vacuum induction melting and the graphite ingot after molding flask moulding
Mould is put into resistance furnace when being warming up to 1173K, keeps the temperature 2~4h；
3) crucible and ingot mould installation: crucible and the ingot mould being fully warmed-up are mounted in vacuum induction melting furnace, crucible is cleared up
And ingot mould, and install foam ceramic filter additional on sprue cup；
4) ingredient and charging: being first added the Ni block, Co block and Cr block prepared after having pre-processed by alloy nominal composition in crucible,
And Al block and Y block are added in charging hopper, close vacuum induction melting furnace fire door；
5) it vacuumizes: vacuum induction melting furnace is vacuumized, so that vacuum degree reaches 0.032Pa in furnace；
6) melt: starting power transmission after the completion of vacuumizing, to be at this time that 5~10 KW heat 10~15min with small-power, increase function
After rate continues 5~10min of heating to 10~15 KW, increase power to 20 KW until furnace charge is all melting down；
7) add aluminium block: step 6 furnace charge is all melting down, when being heated to charge-temperature is 1773K~1823K, by charging hopper
In Al block be added in crucible melt；
8) it skims: after Al block in step 7 furnace charge all fusing, taking the oxidizing slag of melt composition off；
9) lead to argon gas: step 8 being skimmed, high-purity argon gas protective atmosphere is passed through；
10) add yttrium block: when being heated to charge-temperature is 1773K~1823K, the Al block in charging hopper being added to crucible
In melt；
11) it refines: when being heated to charge-temperature is 1873K~1923K, starting to refine, refining time is 10~30min；
12) it casts: after refining, stopping 3~5 min of power transmission, then with 3~5KW of power to electricity, measuring charge-temperature is
At 1673 DEG C~1773 DEG C, cast molding is carried out；
13) feeding: surface is handled to meet requirement.
Through examining: the MCrAlY target finished product impurity content that step 12 obtains is respectively O:3ppm；S:3ppm；N:
4ppm。
Embodiment 3: the NiCrAlY target carries out ingredient according to nominal composition weight percent (wt%):
Ni 40.5%,
Co 20%,
Cr 25%,
Al 13%,
Y 1.5%,
The preparation method of the NiCrAlY target:
1) pretreatment of raw material: after Ni block, Co block, Cr block, Al block and Y block carry out surface scale polishing, using acetone in frequency
Under conditions of 20~30KHz, it is cleaned by ultrasonic 2 times, 5 min, is put in baking oven after cleaning and dries 10 under the conditions of 373K every time
~30 min obtain pretreated target source material；
2) crucible and ingot mould pretreatment: by the graphite ingot mould of vacuum induction melting and the graphite ingot after molding flask moulding
Mould is put into resistance furnace when being warming up to 1173K, keeps the temperature 2~4h；
3) crucible and ingot mould installation: crucible and the ingot mould being fully warmed-up are mounted in vacuum induction melting furnace, crucible is cleared up
And ingot mould, and install foam ceramic filter additional on sprue cup；
4) ingredient and charging: being first added the Ni block, Co block and Cr block prepared after having pre-processed by alloy nominal composition in crucible,
And Al block and Y block are added in charging hopper, close vacuum induction melting furnace fire door；
5) it vacuumizes: vacuum induction melting furnace is vacuumized, so that vacuum degree reaches 0.032Pa in furnace；
6) melt: starting power transmission after the completion of vacuumizing, to be at this time that 5~10 KW heat 10~15min with small-power, increase function
After rate continues 5~10min of heating to 10~15 KW, increase power to 20 KW until furnace charge is all melting down；
7) add aluminium block: step 6 furnace charge is all melting down, when being heated to charge-temperature is 1773K~1823K, by charging hopper
In Al block be added in crucible melt；
8) it skims: after Al block in step 7 furnace charge all fusing, taking the oxidizing slag of melt composition off；
9) lead to argon gas: step 8 being skimmed, high-purity argon gas protective atmosphere is passed through；
10) add yttrium block: when being heated to charge-temperature is 1773K~1823K, the Al block in charging hopper being added to crucible
In melt；
11) it refines: when being heated to charge-temperature is 1873K~1923K, starting to refine, refining time is 10~30min；
12) it casts: after refining, stopping 3~5 min of power transmission, then with 3~5KW of power to electricity, measuring charge-temperature is
At 1673 DEG C~1773 DEG C, cast molding is carried out；
13) feeding: surface is handled to meet requirement.
Through examining: the MCrAlY target finished product impurity content that step 12 obtains is respectively O:4ppm；S:3ppm；N:
3ppm。
The above embodiments merely illustrate the technical concept and features of the present invention, and its object is to allow person skilled in the art
Scholar cans understand the content of the present invention and implement it accordingly, and it is not intended to limit the scope of the present invention.It is all according to the present invention
Equivalent change or modification made by Spirit Essence should all cover in protection scope of the present invention.
Claims (2)
1. a kind of blade of aviation engine bonding coat MCrAlY target, it is characterised in that: the MCrAlY target is by name
Ingredient carries out ingredient by weight percentage:
M 40~70%,
Cr 19~35%,
Al 10~25%,
Y 0.1~1.5%,
The M refers to that metal, M are any one or two kinds in Ni and Co.
2. blade of aviation engine bonding coat MCrAlY target according to claim 1, it is characterised in that: described
MCrAlY target carries out ingredient by nominal composition by weight percentage:
M 45~65%,
Cr 20~32%,
Al 14~22%,
Y 0.2~1%.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811576175.1A CN109536819A (en) | 2018-12-22 | 2018-12-22 | A kind of blade of aviation engine bonding coat MCrAlY target |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811576175.1A CN109536819A (en) | 2018-12-22 | 2018-12-22 | A kind of blade of aviation engine bonding coat MCrAlY target |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109536819A true CN109536819A (en) | 2019-03-29 |
Family
ID=65856578
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| Application Number | Title | Priority Date | Filing Date |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110918976A (en) * | 2019-10-30 | 2020-03-27 | 哈尔滨工业大学 | Forming method of NiAl-based alloy component |
| CN114107775A (en) * | 2021-11-17 | 2022-03-01 | 内蒙古科技大学 | Bonding layer alloy for turbine blade of aircraft engine and preparation method thereof |
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| CN102212786A (en) * | 2011-05-27 | 2011-10-12 | 中国航空工业集团公司北京航空制造工程研究所 | Method for preparing thermal barrier coating |
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| CN103556117A (en) * | 2013-11-19 | 2014-02-05 | 中国科学院金属研究所 | MCrAlY ion plating negative material and preparation method of casting of MCrAlY ion plating negative material |
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| CN102094170A (en) * | 2009-12-15 | 2011-06-15 | 沈阳天贺新材料开发有限公司 | Zirconium oxide thermal barrier coating for turbine buckets of gas turbine and preparation method thereof |
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| CN110918976A (en) * | 2019-10-30 | 2020-03-27 | 哈尔滨工业大学 | Forming method of NiAl-based alloy component |
| CN110918976B (en) * | 2019-10-30 | 2022-03-08 | 哈尔滨工业大学 | Forming method of NiAl-based alloy component |
| CN114107775A (en) * | 2021-11-17 | 2022-03-01 | 内蒙古科技大学 | Bonding layer alloy for turbine blade of aircraft engine and preparation method thereof |
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