CN100523241C - Pyrogenic oxidation resistant nickel-aluminium-dysprosium coat bond material and preparation of hot screening coating - Google Patents

Pyrogenic oxidation resistant nickel-aluminium-dysprosium coat bond material and preparation of hot screening coating Download PDF

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CN100523241C
CN100523241C CNB200810103513XA CN200810103513A CN100523241C CN 100523241 C CN100523241 C CN 100523241C CN B200810103513X A CNB200810103513X A CN B200810103513XA CN 200810103513 A CN200810103513 A CN 200810103513A CN 100523241 C CN100523241 C CN 100523241C
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dysprosium
nickel
aluminium
bonding layer
layer material
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CN101255515A (en
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郭洪波
王晓燕
宫声凯
王世兴
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Beihang University
Beijing University of Aeronautics and Astronautics
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Abstract

The invention discloses a high-temperature-oxidation-resistant nickel-aluminum-dysprosium thermal barrier coating bonding layer material, composed of 0.01 to 3 by atomic percent of dysprosium with a purity of 99.99%, 40 to 50 by atomic percent of aluminum with a purity of 99.999% and the balance nickel with a purity of 99.9999%. The dysprosium element in the melt bonding layer material mainly distributes along NiAl crystal boundary. A substrate with the nickel-aluminum-dysprosium bonding layer material is oxidized for 300 hours under 1200 DEG C, then the oxidation weight gain is about 0.5 to 1.5mg/cm<2>, the oxidation film on the surface of the substrate hardly drops off.

Description

Nickel-the aluminium of resistance to high temperature oxidation-dysprosium bonding layer material and preparation thereof
Technical field
The present invention relates to a kind of bonding layer material that is used as in the thermal barrier coating, more particularly say, be meant a kind of can being applicable under 1200 ℃ of hot environments, utilize the resistance to high temperature oxidation bonding layer material of rare earth element Dy modification NiAl.
Background technology
The development of advanced gas turbine engines constantly proposes new higher requirement to its blade.Up to more than 2000 ℃, this just requires turbine blade and turning vane long-term stable operation under temperature more than 1400 ℃ to the turbine intake temperature of thrust-weight ratio 15 above engines (Turbine inlet temperature is called for short TIT).In order to adapt to this bad working environment, satisfy the development of Aeroengines needs, except developing efficient cooling technology and high temperature alloy technology, must develop thermal barrier coating (Thermal BarrierCoatings the is called for short TBCs) technology of superhigh temperature resistant, high heat-proof quality simultaneously.
Thermal barrier coating mainly is performances such as high temperature resistant, anticorrosive and lower thermal conductivity of utilizing stupalith superior, mode with coating is compound with pottery and metallic matrix, improve the working temperature of engine and the resistance to corrosion of parts, and prolong the work-ing life of hot-end component effectively.Adopting thermofin thickness is the thermal barrier coating (adopting the air film cooling technology simultaneously) of 150~300 μ m, can effectively reduce about 150 ℃ of the working temperatures of turbine blade surface.Experimental result shows that the every reduction of blade surface temperature will make prolong about one times the creep life of blade for 15 ℃.
The basic structure of thermal barrier coating is generally bilayer structure, and bottom is a metal bonding coating, and top layer is a ceramic thermal barrier layer.Primer is generally MCrAlY (M is Ni, Co or Ni+Co), its objective is that the thermal expansivity of alleviating ceramic coating and superalloy matrix does not match, and improves the oxidation-resistance property of matrix.Under high-temperature oxidation environment, oxidation is formed the Al of one deck densification on the surface of MCrAlY layer 2O 3Protective membrane stops the further oxidation of tack coat, and then reaches the purpose of protection matrix.Studies show that to be alloy have good high temperature oxidation resistance to MCrAlY in being lower than 1150 ℃ environment.Yet when use temperature is higher than 1150 ℃, promote the oxidation will take place in coating, and cause spalling of oxide film.Therefore, MCrAlY can not be as the high-temperature protection coating of use temperature more than 1150 ℃ or the metal bonding coating of thermal barrier coating.
NiAl is a kind of intermetallic compound of long-range order, since the characteristic of metallic bond and covalent linkage coexistence, Ni 50Al 50Fusing point T mIt is 1638 ℃.Studies show that Ni 50Al 50Fusing point T mCan reach 1682 ℃, be a kind of can be at the high-temperature material of 1200 ℃ of life-time service.NiAl has good high temperature oxidation resistance, and its high temperature oxidation resistance is mainly based on the α-Al that can form the single whole with low growth velocity 2O 3Oxide film.The thermal expansivity of NiAl system all is lower than the MCrAlY system in whole temperature range, particularly the bonding force of the NiAl tie layer surface generation oxide compound of process reaction activating element modification shows its unique advantages especially, and using the NiAl coating on suitable body material can keep body material intensity and flexible improve high temperature oxidation resistance simultaneously.
Yet there are some shortcomings in NiAl: when high temperature oxidation, because the formation of oxide film causes the consumption of aluminium, thereby bring out martensitic transformation, cause oxide film that serious shrinkage takes place and peel off; On the other hand, form a large amount of cavities easily, influence the cohesiveness of oxide film, cause oxide film to come off at metal/interfacial oxide film.Based on above reason, be necessary NiAl is carried out modification.
Summary of the invention
One of purpose of the present invention provides a kind of nickel-aluminium-dysprosium bonding layer material of resistance to high temperature oxidation, and this bonding layer material is that the atomic percent of 0.01~3 dysprosium Dy, purity 99.999% is that the nickel of the surplus of 40~50 aluminium Al and purity 99.999% is formed by the atomic percent of purity 99.99%.Dy mainly distributes along the NiAl crystal boundary in the bonding layer material that melting makes.Nickel-aluminium-dysprosium bonding layer material that melting is made was 1200 ℃ of oxidations 300 hours, and oxidation weight gain is about 0.5~1.5mg/cm 2
Another object of the present invention is to propose a kind of nickel-aluminium-dysprosium target that adopts vacuum melting to prepare resistance to high temperature oxidation, and prepares the method for the thermal barrier coating that contains nickel-aluminium-dysprosium tack coat on matrix with the electron beam physical gas-phase deposite method.
The present invention adopts the preparation of electro beam physics vapour deposition method to contain the method for the thermal barrier coating of resistance to high temperature oxidation nickel-aluminium-dysprosium tack coat, includes following preparation steps:
(A) the tack coat charge bar of choosing is put into the A crucible (2) of electro beam physics vapour deposition equipment, and the nickel base superalloy matrix is installed on the substrate (5);
(B) vacuum tightness to 1 * 10 of evacuated chamber (1) -2~5 * 10 -5Pa;
(C) the speed of rotation 10~20rpm of setting rotary plate frame (6);
Adopt electron beam heated substrates (5) to 600~900 ℃, electron-beam voltage 17~19kV;
(D) deposition tack coat: prevapourising bonding layer material charge bar, and regulate electronic beam current 1.2~2.0A, charge bar climbing speed 0.8~1.0mm/min, sedimentation rate 1.5~2.0 μ m/min; Draw back baffle plate (4), the hydatogenesis tack coat begins, and takes out after deposition is finished; Put into vacuum heat treatment furnace and carry out vacuum heat treatment 2~6hrs, 1000~1100 ℃ of thermal treatment temps;
(E) deposited ceramic layer: will be installed on the substrate (5) of electro beam physics vapour deposition equipment through the nickel base superalloy matrix after (D) handles, and regulate rotary plate frame (6) to B crucible (3) top that stupalith is housed, regulate electronic beam current 1.4~1.8A, charge bar climbing speed 1.2~1.6mm/min, sedimentation rate 2.5~3.0 μ m/min; Draw back baffle plate (4), the hydatogenesis ceramic layer begins, and closed baffle plate (4) after deposition is finished takes out after deposition is finished, and promptly makes the heat barrier coat material that contains nickel-aluminium-dysprosium tack coat.
The advantage of nickel-aluminium of the present invention-dysprosium bonding layer material is: use temperature is at 1150~1200 ℃.The NiAl of Dy modification is because rate of oxidation is low, and the oxide film adhesivity is good, and is incrust, can be used as anti-ultrahigh-temperature oxidation heat barrier coating bonding layer material.The NiAl metal blocks material of Dy modification is 0.5~1.5mg/cm at 300 hours oxidation weight gains of 1200 ℃ of oxidations 2, oxide film does not almost have and peels off, and unmodified NiAl oxidation is after 50 hours, and oxide film just peels off in a large number.Compare with traditional bonding layer material MCrAlY, MCrAlY can only be used in below 1150 ℃, and when temperature surpasses 1150 ℃, oxide film thickens very fast, and causes in a large number and peel off.
Description of drawings
Fig. 1 is the structure sectional view of the heat barrier coat material for preparing of the present invention.
Fig. 2 is an electro beam physics vapour deposition equipment synoptic diagram.
Fig. 3 is bulk Ni 50Al 49.5Dy 0.5Cross section back scattering figure.
Fig. 4 is bulk Ni 50Al 49.9Dy 0.1The cross section pattern of oxidation after 305 hours.
Embodiment
The present invention is described in further detail below in conjunction with drawings and Examples.
The present invention is a kind of resistance to high temperature oxidation nickel-aluminium-dysprosium bonding layer material that utilizes rare earth element Dy modification NiAl, be low at traditional bonding layer material MCrAlY use temperature, and the NiAl oxide film is rugosity and oxide film and intermetallic form the problem that comes off in a large number that oxide film is caused in a large amount of cavities, in NiAl, add micro-reaction active element Dy, improved the adhesivity of oxide film, and the rate of oxidation that slowed down.Dy in resistance to high temperature oxidation nickel-aluminium of the present invention-dysprosium ingot casting that the employing melting method makes mainly distributes along the NiAl crystal boundary.And 1200 ℃ of oxidations 300 hours, oxidation weight gain was about 0.5~1.5mg/cm 2, demonstrating this bonding layer material has excellent oxidation-resistance and peel-ability in the time of 1200 ℃.
In the present invention, bonding layer material 11 preparations are between matrix 13 and ceramic layer material 12 (referring to shown in Figure 1), and tack coat and ceramic layer constitute thermal barrier coating.Described matrix can be a nickel base superalloy, as K3, and monocrystalline DD3, DD6, directional solidificating alloy D125.Described ceramic layer material can be that YSZ is yttrium oxide Y 2O 3Stable zirconium white ZrO 2Perhaps La 2Ce 2O 5, LaTiAlO, BaLaTiO etc.
Nickel-the aluminium of resistance to high temperature oxidation of the present invention-dysprosium bonding layer material is that the atomic percent of 0.01~3 dysprosium Dy, purity 99.999% is that the nickel of the surplus of 40~50 aluminium Al and purity 99.999% is formed by the atomic percent of purity 99.99%.The concrete composition of bonding layer material has Ni in the present invention 49.9Al 50Dy 0.01, Ni 50Al 49.95Dy 0.05, Ni 50Al 49.9Dy 0.1, Ni 55Al 44.5Dy 0.5, Ni 55Al 44Dy 1, Ni 50Al 48.5Dy 1.5, Ni 57Al 40Dy 3
The method for preparing resistance to high temperature oxidation nickel-aluminium of the present invention-dysprosium bonding layer material is: take by weighing the nickel (Ni) of purity 99.999%, the aluminium (Al) of purity 99.999% and the dysprosium (Dy) of purity 99.99% by composition proportion, and the nickel-aluminium-dysprosium that takes by weighing put into vacuum arc, in vacuum tightness 1 * 10 -3~5 * 10 -5Pa, 2500 ℃~3000 ℃ of smelting temperatures, it is that melting makes nickel-aluminium-dysprosium ingot casting that melting turns refining 3~6 times.
Electro beam physics vapour deposition equipment schematic diagram as shown in Figure 2, the technology that adopts the electro beam physics vapour deposition method to heat barrier coating on matrix is:
(A) the tack coat charge bar of choosing is put into the A crucible 2 of electro beam physics vapour deposition equipment, and the nickel base superalloy matrix is installed on the substrate 5;
(B) vacuum tightness to 1 of evacuated chamber 1 * 10 -2~5 * 10 -5Pa;
(C) the speed of rotation 10~20rpm of setting rotary plate frame 6;
Adopt 5 to 600~900 ℃ of electron beam heated substrates, electron-beam voltage 17~19kV;
(D) deposition tack coat: prevapourising bonding layer material charge bar, and regulate electronic beam current 1.2~2.0A, charge bar climbing speed 0.8~1.0mm/min, sedimentation rate 1.5~2.0 μ m/min; Draw back baffle plate 4, the hydatogenesis tack coat begins, and takes out after deposition is finished, and puts into vacuum heat treatment furnace and carries out vacuum heat treatment 2~6hrs, 1000~1100 ℃ of thermal treatment temps;
(E) deposited ceramic layer: will be installed on the substrate 4 of electro beam physics vapour deposition equipment through the nickel base superalloy matrix after (D) handles, and regulate rotary plate frame 6 to B crucible 3 tops that stupalith is housed, regulate electronic beam current 1.4~1.8A, charge bar climbing speed 1.2~1.6mm/min, sedimentation rate 2.5~3.0 μ m/min; Draw back baffle plate 4, the hydatogenesis ceramic layer begins, and closed baffle plate 4 after deposition is finished takes out after deposition is finished, and promptly makes the thermal barrier coating that contains nickel-aluminium-dysprosium tack coat.
Dy modification NiAl material is carried out performance test:
The distribution of Dy in NiAl: with the Dy modification NiAl sample sand papering that melting makes, polishing is observed under scanning electron microscope then and is found that Dy mainly distributes along the NiAl crystal boundary.
Antioxidant property test: melting ingot sample is cut out 10 * 10 * 3mm with wire cutting method 3Small pieces, with sand papering smooth, use ultrasonic 15 minutes of acetone, alcohol then respectively, again sample is dried.Sample is put into tube furnace, carry out oxidation test at 1200 ℃, the weight of the different oxidization time samples of weighing is done the oxidation kinetics curve, and weightening finish is 0.5~1.5mg/cm only 2
Cross section oxide film morphology observation:, after finding to add micro-Dy, compare with unmodified NiAl with cross section pattern after the scanning electron microscopic observation Dy modification NiAl material oxidation, spalling of oxide film seldom, oxide film is straight, and does not almost have hole between matrix, cohesiveness is fine, sees Fig. 3.
Heat barrier coat material of the present invention is carried out performance test:
Cycle life test: the Dy modification NiAl and the unmodified NiAl heat barrier coat material that prepare among the present invention are carried out the cyclic oxidation Performance Detection: sample is heated 50min in 1200 ℃ of air, forcing blast-cold 10min to carry out reciprocation cycle to room temperature then, adopt the warm recycle unit of automatic height to test, the changes in weight and the cycle index of record sample, the result shows that cyclic oxidation is after 10~20 hours, unmodified NiAl heat barrier coat material begins to lose efficacy, and Dy modification NiAl heat barrier coat material cyclic oxidation just began to lose efficacy in 200~300 hours.
Embodiment 1:System Ni 50Al 49.95Dy 0.05
According to nominal composition is Ni 50Al 49.95Dy 0.05Prepare burden, the purity of its starting material nickel and aluminium is 99.999%, and dysprosium purity is 99.99%.
Adopt vacuum arc melting Ni 50Al 49.95Dy 0.05Ingot casting, vacuum tightness are 5 * 10 -4Pa, 2500 ℃ of smelting temperatures, turn refining 4 times can melting even.
Find that with scanning electron microscopic observation Dy mainly distributes along the NiAl crystal boundary.
Sample is cut out 10 * 10 * 3mm with wire cutting method 3Small pieces, with sand papering smooth, use ultrasonic 15 minutes of acetone, alcohol then respectively, again sample is dried.1200 ℃ of oxidations 305 hours, oxidation weight gain was about 0.5mg/cm 2
With scanning electron microscopic observation oxidation rear surface and cross section pattern, find spalling of oxide film seldom, oxide film is straight, and adhesivity is fine.
The technology that (referring to shown in Figure 2) adopts the electro beam physics vapour deposition method to heat barrier coating on matrix is:
(A) with Ni 50Al 49.95Dy 0.05Ingot casting cuts into bar, and puts it in the A crucible 2 of electro beam physics vapour deposition equipment, and the nickel base superalloy matrix is installed on the substrate 5;
(B) vacuum tightness to 5 of evacuated chamber 1 * 10 -4Pa;
(C) the speed of rotation 10rpm of setting rotary plate frame 6;
Adopt 5 to 600 ℃ of electron beam heated substrates, electron-beam voltage 17kV;
(D) deposition tack coat: prevapourising bonding layer material charge bar, and regulate electronic beam current 1.2A, charge bar climbing speed 0.8mm/min, sedimentation rate 1.5 μ m/min; Draw back baffle plate 4, the hydatogenesis tack coat begins, and takes out after deposition is finished, and puts into vacuum heat treatment furnace and carries out vacuum heat treatment 2hrs, 1000 ℃ of thermal treatment temps;
(E) deposited ceramic layer: will be installed on the substrate 5 of electro beam physics vapour deposition equipment through the nickel base superalloy matrix after (D) handles, and regulate rotary plate frame 6 to stupalith (yttrium oxide Y is housed 2O 3Stable zirconium white ZrO 2) B crucible 3 tops, regulate electronic beam current 1.4A, charge bar climbing speed 1.2mm/min, sedimentation rate 2.5 μ m/min; Draw back baffle plate 4, the hydatogenesis ceramic layer begins, and closed baffle plate 4 after deposition is finished takes out after deposition is finished, and promptly contains Ni 50Al 49.95Dy 0.05The thermal barrier coating of bonding layer material.
With the above-mentioned Ni that made 50Al 49.95Dy 0.05The thermal barrier coating of bonding layer material carries out the oxidation corrosion test, in 1200 ℃ of air, heat 50min, forcing blast-cold 10min to carry out reciprocation cycle to room temperature then, adopt the warm recycle unit of automatic height to test, the changes in weight and the cycle index of record sample, Dy modification NiAl heat barrier coat material cyclic oxidation just began to lose efficacy in 300 hours.
Adopt the preparation method identical respectively to Ni with embodiment 1 49.9Al 50Dy 0.01, Ni 55Al 44Dy 1, Ni 50Al 48.5Dy 1.5, Ni 57Al 40Dy 3Bonding layer material be prepared the Ni that melting obtains 49.9Al 50Dy 0.01, Ni 55Al 44Dy 1, Ni 50Al 48.5Dy 1.5, Ni 57Al 40Dy 3Dy mainly distributes along the NiAl crystal boundary in the ingot casting material, and Ni 49.9Al 50Dy 0.01, Ni 55Al 44Dy 1, Ni 50Al 48.5Dy 1.5, Ni 57Al 40Dy 3Ingot casting oxidation 305 hours in 1200 ℃ of air, oxidation weight gain is about 1.1mg/cm 2, 0.67mg/cm 2, 1.5mg/cm 2
To contain Ni 49.9Al 50Dy 0.01, Ni 55Al 44Dy 1, Ni 50Al 48.5Dy 1.5, Ni 57Al 40Dy 3The thermal barrier coating oxidation susceptibility be respectively and just began in 230,290,200 hours to lose efficacy.
Embodiment 2: system Ni 50Al 49.9Dy 0.1
According to nominal composition is Ni 50Al 49.9Dy 0.1Prepare burden, the purity of its starting material nickel and aluminium is 99.999%, and dysprosium purity is 99.99%.
Adopt vacuum arc melting Ni 50Al 49.9Dy 0.1Ingot casting, vacuum tightness are 5 * 10 -4Pa, turn refining 4 times can melting even.
Find that with scanning electron microscopic observation Dy mainly distributes along the NiAl crystal boundary.
Sample is cut out 10 * 10 * 3mm with wire cutting method 3Small pieces, with sand papering smooth, use ultrasonic 15 minutes of acetone, alcohol then respectively, again sample is dried.1200 ℃ of oxidations 305 hours, oxidation weight gain was about 1.0mg/cm 2
With scanning electron microscopic observation oxidation rear surface and cross section pattern, find spalling of oxide film seldom, oxide film is straight, and adhesivity is fine.As accompanying drawing 4.
The technology that (referring to shown in Figure 2) adopts the electro beam physics vapour deposition method to heat barrier coating on matrix is:
(A) with Ni 50Al 49.9Dy 0.1Put into the A crucible 2 of electro beam physics vapour deposition equipment, and the nickel base superalloy matrix is installed on the substrate 5;
(B) vacuum tightness to 5 of evacuated chamber 1 * 10 -4Pa;
(C) the speed of rotation 15rpm of setting rotary plate frame 6;
Adopt 5 to 600~900 ℃ of electron beam heated substrates, electron-beam voltage 18kV;
(D) deposition tack coat: prevapourising bonding layer material charge bar, and regulate electronic beam current 1.6A, charge bar climbing speed 0.9mm/min, sedimentation rate 1.8 μ m/min; Draw back baffle plate 4, the hydatogenesis tack coat begins, and takes out after deposition is finished, and puts into vacuum heat treatment furnace and carries out vacuum heat treatment 4hrs, 1050 ℃ of thermal treatment temps;
(E) deposited ceramic layer: will be installed on the substrate 5 of electro beam physics vapour deposition equipment through the nickel base superalloy matrix after (D) handles, and regulate rotary plate frame 6 to B crucible 3 tops that stupalith is housed, regulate electronic beam current 1.6A, charge bar climbing speed 1.4mm/min, sedimentation rate 2.8 μ m/min; Draw back baffle plate 4, the hydatogenesis ceramic layer begins, and closed baffle plate 4 after deposition is finished takes out after deposition is finished, and promptly makes and contains Ni 50Al 49.9Dy 0.1The thermal barrier coating of tack coat.
Make and contain Ni 50Al 49.9Dy 0.1The oxidation susceptibility of the thermal barrier coating of tack coat is just to begin in 260 hours to lose efficacy.
Embodiment 3:System Ni 55Al 44.5Dy 0.5
According to nominal composition is Ni 55Al 44.5Dy 0.5Prepare burden, the purity of its starting material nickel and aluminium is 99.999%, and dysprosium purity is 99.99%.
Adopt vacuum arc melting Ni 55Al 44.5Dy 0.5Alloy cast ingot, vacuum tightness are 5 * 10 -4Pa, 2500 ℃ of smelting temperatures, turn refining 4 times can melting even.
Find that with scanning electron microscopic observation Dy mainly distributes along the NiAl crystal boundary.
Sample is cut out 10 * 10 * 3mm with wire cutting method 3Small pieces, with sand papering smooth, use ultrasonic 15 minutes of acetone, alcohol then respectively, again sample is dried.1200 ℃ of oxidations 305 hours, oxidation weight gain was about 1.5mg/cm 2
The technology that adopts the electro beam physics vapour deposition method to heat barrier coating on matrix is:
(A) with Ni 55Al 44.5Dy 0.5Charge bar is put into the A crucible 2 of electro beam physics vapour deposition equipment, and the nickel base superalloy matrix is installed on the substrate 5;
(B) vacuum tightness to 5 of evacuated chamber 1 * 10 -4Pa;
(C) the speed of rotation 20rpm of setting rotary plate frame 6;
Adopt 5 to 900 ℃ of electron beam heated substrates, electron-beam voltage 19kV;
(D) deposition tack coat: prevapourising bonding layer material charge bar, and regulate electronic beam current 2.0A, charge bar climbing speed 1.0mm/min, sedimentation rate 2.0 μ m/min; Draw back baffle plate 4, the hydatogenesis tack coat begins, and takes out after deposition is finished, and puts into vacuum heat treatment furnace and carries out vacuum heat treatment 6h, 1100 ℃ of thermal treatment temps;
(E) deposited ceramic layer: will be installed on the substrate 5 of electro beam physics vapour deposition equipment through the nickel base superalloy matrix after (D) handles, and regulate rotary plate frame 6 to B crucible 3 tops that stupalith is housed, regulate electronic beam current 1.8A, charge bar climbing speed 1.6mm/min, sedimentation rate 3.0 μ m/min; Draw back baffle plate 4, the hydatogenesis ceramic layer begins, and closed baffle plate 4 after deposition is finished takes out after deposition is finished, and promptly makes and contains Ni 55Al 44.5Dy 0.5The thermal barrier coating of tack coat.Make and contain Ni 55Al 44.5Dy 0.5The oxidation susceptibility of the thermal barrier coating of tack coat is just to begin in 210 hours to lose efficacy.

Claims (5)

1, a kind of nickel-aluminium of resistance to high temperature oxidation-dysprosium bonding layer material is characterized in that: this bonding layer material is that the atomic percent of 0.01~3 dysprosium Dy, purity 99.999% is that the nickel of the surplus of 40~50 aluminium Al and purity 99.999% is formed by the atomic percent of purity 99.99%.
2, nickel-aluminium according to claim 1-dysprosium bonding layer material is characterized in that: the concrete composition of bonding layer material has Ni 49.9Al 50Dy 0.01, Ni 50Al 49.95Dy 0.05, Ni 50Al 49.9Dy 0.1, Ni 55Al 44.5Dy 0.5, Ni 55Al 44Dy 1, Ni 50Al 48.5Dy 1.5Or Ni 57Al 40Dy 3
3, a kind of method for preparing the nickel-aluminium-dysprosium bonding layer material of a kind of resistance to high temperature oxidation as claimed in claim 1, it is characterized in that: take by weighing the nickel of purity 99.999%, the aluminium Al of purity 99.999% and the dysprosium Dy of purity 99.99% by composition proportion, and the nickel, aluminium, the dysprosium that take by weighing put into vacuum arc, in vacuum tightness 1 * 10 -3~5 * 10 -5Under the Pa, 2500 ℃~3000 ℃ of smelting temperatures, it is that melting makes nickel-aluminium-dysprosium ingot casting that melting turns refining 3~6 times.
4, a kind of method for preparing the nickel-aluminium-dysprosium bonding layer material of resistance to high temperature oxidation according to claim 3, it is characterized in that: the Dy in the nickel-aluminium that makes-dysprosium ingot casting mainly distributes along the NiAl crystal boundary.
5, a kind of method for preparing the nickel-aluminium-dysprosium bonding layer material of resistance to high temperature oxidation according to claim 3, it is characterized in that: the nickel-aluminium that makes-dysprosium ingot casting was 1200 ℃ of oxidations 300 hours, and oxidation weight gain is 0.5~1.5mg/cm 2
CNB200810103513XA 2008-04-08 2008-04-08 Pyrogenic oxidation resistant nickel-aluminium-dysprosium coat bond material and preparation of hot screening coating Expired - Fee Related CN100523241C (en)

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