CN106975748A - A kind of preparation method of Wear-resistant, high-temperature resistant nickel-base alloy turbo blade - Google Patents
A kind of preparation method of Wear-resistant, high-temperature resistant nickel-base alloy turbo blade Download PDFInfo
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Abstract
The invention discloses a kind of preparation method of Wear-resistant, high-temperature resistant nickel-base alloy turbo blade, comprise the following steps：Gas-atomized powder technique is used first, Co-based alloy powder is made stand-by；Then electron beam quick shaping process is used, turbo blade is made, and be heat-treated obtained turbine blade surface, then dried after the deposition layer of metal tack coat of its surface, finally using supersonic spray coating technique in one layer of thermal barrier coating of metal bonding coating surface spraying, Wear-resistant, high-temperature resistant turbo blade is made after drying.The preparation method is simple to operate, and more preferably, anti-wear performance is more excellent for obtained turbo blade resistance to elevated temperatures, and long, mechanical property is good for service life.
Description
Technical field：
The present invention relates to alloy surface modifying field, a kind of Wear-resistant, high-temperature resistant nickel-base alloy turbo blade is specifically related to
Preparation method.
Background technology：
Nickel base superalloy typically bears to work under conditions of certain stress more than 600 DEG C, and it not only has good height
Warm anti-oxidant and resistance to corrosion, and have higher elevated temperature strength, creep strength and creep rupture strength, and well antifatigue
Performance.It is mainly used in the structure member worked under field of aerospace hot conditions, working-blade, the turbine of such as aero-engine
Disk, combustion chamber etc..
As aero-engine is to energy efficiency and the requirement more and more higher of thrust so that the upper raising speed of turbine inlet temperature (TIT)
Degree (15 DEG C/year) has exceeded well over the speedup (5 DEG C/year) of high temperature alloy heat resistance.At present, only by air film cooling technology and alloy sheet
Body performance can not meet the design needs of aero-engine.
In order that the reliability and life-span of engine and Gas Turbine part effectively improve, can be on its surface
Apply protective coating, high temperature, hyperbaric environment and engine and the isolation of Gas Turbine part alloy substrate are opened, turbine is reduced
The harm that part is oxidized and corroded.The power of each aviation at present in order to maintain an edge, all how to turbine part especially
It is that turbo blade carries out effectively protection as research emphasis and core technology secret.Wherein turbo blade as aero-engine with
And the core part of gas turbine, local environment is extremely complex and severe, and is in the state that runs at high speed.This requires coating
Not only there are preferably tissue and chemical heat endurance, and its physical property and mechanical performance will be with preferable with matrix alloy
Matching.
Chinese Master's thesis (" grind by Crystal Nickel-based Superalloy surface NiCrAlYSi Coatings in Vacuum electric arc depositing process and high-temperature behavior
Study carefully；Gong Yingyong, Harbin Institute of Technology, in December, 2015) prepared using vacuum arc coating technology on Crystal Nickel-based Superalloy surface
NiCrAlYSi protective coatings.It has studied influence of the coating electric current to coating structure and thickness.It was found that when arc current is 620
During ± 10A, electric arc can be caused unstable and blow-out phenomenon, make coating texture uneven, inside has hole, cavity etc. and lacked
Fall into.When arc current is 720 ± 10A, target can be by slight damage.Only when arc current is in 670 ± 10A, coating
Coating process be in metastable working condition, coating structure even compact.When the coating time is no more than 150min,
NiCrAlYSi coating layer thicknesses and coating time proportional relation, and uniform coating thickness, diverse location thickness disparity are no more than 3 μ
m.Show through 760 DEG C of high temperature tension test results, the tensile strength of the Crystal Nickel-based Superalloy of the coating containing NiCrAlYSi, surrender are strong
Degree, elongation percentage and the contraction percentage of area are respectively 1115MPa, 922MPa, 14.5% and 21.5%.The nickel of the coating containing NiCrAlYSi
Testing Tensile Strength at Elevated Temperature, yield strength, elongation percentage and the contraction percentage of area of the base single crystal alloy at 980 DEG C be respectively 885.0MPa,
822.5MPa, 31.5% and 37.3%.With Crystal Nickel-based Superalloy matrix phase ratio, NiCrAlYSi coatings are significantly improved 1100
Anti- constant temperature oxidation performance at DEG C and the anti-cyclic oxidation performance at 1000 DEG C.The constant temperature oxidation in 1100 DEG C of still airs
After 100h, the average oxidation speed of coating sample is about 0.087g/m2H (is less than 0.1g/m2H), complete grade of oxidation resistance is reached.But
It is that the resistance to elevated temperatures and antioxygenic property of the coating stills need further to improve and can meet turbo blade and be adapted to badly
The requirement of environment.
The content of the invention：
It is an object of the invention to provide a kind of preparation method of Wear-resistant, high-temperature resistant nickel-base alloy turbo blade, this method is made
Turbo blade thermal conductivity it is low, resistance to elevated temperatures is good, and anti-wear performance is excellent, and service life is long.
To achieve the above object, the present invention uses following technical scheme：
A kind of preparation method of Wear-resistant, high-temperature resistant nickel-base alloy turbo blade, comprises the following steps：
(1) gas-atomized powder technique is used, Co-based alloy powder is made, it is stand-by；
(2) threedimensional model of turbo blade is set up, discretization layering is then carried out to it along in short transverse, thickness is formed
Uniform section, section file is imported into the metal dust former of electron beam constituency；
(3) Co-based alloy powder obtained above is loaded in the metal dust former of electron beam constituency, and will shaping
Substrate is positioned in the forming cavity of electron beam constituency metal dust former on liftable platform, and forming cavity is vacuumized,
And shaping substrate is preheated, tile one layer of Co-based alloy powder after the completion of preheating on substrate, then the electricity by being pre-designed
Beamlet scans alloy powder, obtains sedimentary, layer upon layer is realized successively, until turbo blade is machined, after machining,
Cooling gas is passed through, blade cooling is treated to less than 80 DEG C, takes out and is cooled to room temperature, obtain pending turbo blade；
(4) it is put into after pending turbo blade obtained above is cleaned and dried in graphite heater furnace, after processing 1-4h
Taken out after furnace cooling；
(5) dried after turbine blade surface deposition layer of metal tack coat after the treatment, then using supersonic speed
Spraying coating process obtains Wear-resistant, high-temperature resistant nickel-base alloy turbine leaf in one layer of thermal barrier coating of metal bonding coating surface spraying after drying
Piece；
Wherein, the material of the thermal barrier coating includes rare earth niobates and its solid solution, wherein the rare earth niobates
Learning composition is：Ln3NbO7, Ln include La, Pr, Nd, Sm, Eu, Gd, Tb, Dy, Ho, Er, Tm, Yb, Lu, Y and Sc in one kind or
Multiple combinations；The solid solution chemical composition is Ln3(Nb1-xTax)O7(0≤x ＜ 1).
As the preferred of above-mentioned technical proposal, in step (1), the condition of the gas-atomized powder is：Using vacuum atomizing
Technology, nitrogen pressure is 3.5-4MPa, and the liquation degree of superheat is 120-180 DEG C, caliber is 5mm, and extension elongation is used when being 11mm
Close coupling confined type nozzle is atomized.
As the preferred of above-mentioned technical proposal, in step (1), the composition of the Co-based alloy powder is Al 4-5.5%,
Nb 5-8%, Ti 1-3.2%, Cr 0.5-3.5%, remaining is Ni.
As the preferred of above-mentioned technical proposal, in step (2), the thickness of the section is 0.02-0.08mm.
As the preferred of above-mentioned technical proposal, in step (3), thickness and step (2) described section of every layer of sedimentary
Thickness is identical, and the vacuum in sedimentary preparation process in forming cavity is 10-2Pa。
As the preferred of above-mentioned technical proposal, in step (3), the condition of the basal plate preheating is：Beam scan velocity
For 10000-11500mm/s, electronic beam current is 40mA, and sweep span is 0.03-0.15mm.
As the preferred of above-mentioned technical proposal, in step (4), the condition of the processing is that furnace temperature is 1100-1200 DEG C, pressure
Power is 8-12MPa.
As the preferred of above-mentioned technical proposal, in step (5), the metal bonding coating is MCrAlY alloy, and wherein M is
One or more combinations in Ni, Co, Fe, Y is one kind in Y, La, Hf, and the thickness of metal bonding coating is 150-300 μm.
As the preferred of above-mentioned technical proposal, in step (5), the thickness of the thermal barrier coating is 200-300 μm.
Chromium can be effectively increased the anti-oxidant and anti-corrosion capability of matrix in ni-base wrought superalloy；Nb, Al, Ti's
Add, it can be with matrix formation Ni3 (Nb, Al, Ti) phase, and it can effectively improve the yield strength of material as hardening constituent.
The invention has the advantages that：
Thermal barrier coating produced by the present invention, 1000 DEG C of intrinsic thermal conductivities of compact block are 1.1-1.4W/mk, compared to current
Commercial YSZ is greatly reduced, and the material is from room temperature to 1600 DEG C of holding phase stabilities and excellent resistance oxygen ability.
And present invention layer of metal tack coat of turbine blade surface spraying now before spraying thermal barrier coating, effectively change
It has been apt to the adhesion between coating,
Embodiment：
In order to be better understood from the present invention, below by embodiment, the present invention is further described, and embodiment is served only for solution
The present invention is released, any restriction will not be constituted to the present invention.
Embodiment 1
A kind of preparation method of Wear-resistant, high-temperature resistant nickel-base alloy turbo blade, comprises the following steps：
(1) gas-atomized powder technique is used, Co-based alloy powder is made, it is stand-by, wherein, the process conditions of gas-atomized powder
For：Using vacuum atomizing technology, nitrogen pressure is 3.5MPa, and the liquation degree of superheat is 120 DEG C, caliber is 5mm, and extension elongation is
It is atomized during 11mm using close coupling confined type nozzle, the composition of Co-based alloy powder is Al 4%, Nb 5%, Ti 1%, Cr
0.5%, remaining is Ni；
(2) threedimensional model of turbo blade is set up, discretization layering is then carried out to it along in short transverse, thickness is formed
Uniform section, slice thickness is 0.02mm, and section file is imported into the metal dust former of electron beam constituency；
(3) Co-based alloy powder obtained above is loaded in the metal dust former of electron beam constituency, and will shaping
Substrate is positioned in the forming cavity of electron beam constituency metal dust former on liftable platform, and forming cavity is evacuated to
10-2Pa, and shaping substrate is preheated, tile one layer of Co-based alloy powder after the completion of preheating on substrate, then by setting in advance
The electron beam scanning alloy powder of meter, obtains sedimentary, and its thickness is identical with above-mentioned slice thickness, and heap layer by layer is then realized successively
Product, until turbo blade is machined, after machining, is passed through cooling gas, treats blade cooling to less than 80 DEG C, takes out and cold
But to room temperature, pending turbo blade is obtained, wherein, the condition of basal plate preheating is：Beam scan velocity is 10000mm/
S, electronic beam current is 40mA, and sweep span is 0.03mm；
(4) it is put into after pending turbo blade obtained above is cleaned and dried in graphite heater furnace, lower 1100 DEG C, pressure
Power is that 8MPa handles taking-up after furnace cooling after 1h；
(5) dried after turbine blade surface deposition layer of metal tack coat after the treatment, then using supersonic speed
Spraying coating process obtains Wear-resistant, high-temperature resistant nickel-base alloy turbine leaf in one layer of thermal barrier coating of metal bonding coating surface spraying after drying
Piece；
Wherein, the thickness of the thermal barrier coating is 200 microns, and the material of thermal barrier coating includes rare earth niobates, wherein institute
Stating rare earth niobates chemical composition is：Y3NbO7；The metal bonding coating is CoCrAlY alloys, and the thickness of metal bonding coating is
150μm。
Embodiment 2
A kind of preparation method of Wear-resistant, high-temperature resistant nickel-base alloy turbo blade, comprises the following steps：
(1) gas-atomized powder technique is used, Co-based alloy powder is made, it is stand-by, wherein, the process conditions of gas-atomized powder
For：Using vacuum atomizing technology, nitrogen pressure is 4MPa, and the liquation degree of superheat is 180 DEG C, caliber is 5mm, and extension elongation is 11mm
Shi Caiyong close coupling confined type nozzle is atomized, and the composition of Co-based alloy powder is Al 5.5%, Nb 8%, Ti 3.2%, Cr
3.5%, remaining is Ni；
(2) threedimensional model of turbo blade is set up, discretization layering is then carried out to it along in short transverse, thickness is formed
Uniform section, slice thickness is 0.08mm, and section file is imported into the metal dust former of electron beam constituency；
(3) Co-based alloy powder obtained above is loaded in the metal dust former of electron beam constituency, and will shaping
Substrate is positioned in the forming cavity of electron beam constituency metal dust former on liftable platform, and forming cavity is evacuated to
10-2Pa, and shaping substrate is preheated, tile one layer of Co-based alloy powder after the completion of preheating on substrate, then by setting in advance
The electron beam scanning alloy powder of meter, obtains sedimentary, and its thickness is identical with above-mentioned slice thickness, and heap layer by layer is then realized successively
Product, until turbo blade is machined, after machining, is passed through cooling gas, treats blade cooling to less than 80 DEG C, takes out and cold
But to room temperature, pending turbo blade is obtained, wherein, the condition of basal plate preheating is：Beam scan velocity is 11500mm/
S, electronic beam current is 40mA, and sweep span is 0.15mm；
(4) it is put into after pending turbo blade obtained above is cleaned and dried in graphite heater furnace, lower 1200 DEG C, pressure
Power is that 12MPa handles taking-up after furnace cooling after 4h；
(5) dried after turbine blade surface deposition layer of metal tack coat after the treatment, then using supersonic speed
Spraying coating process obtains Wear-resistant, high-temperature resistant nickel-base alloy turbine leaf in one layer of thermal barrier coating of metal bonding coating surface spraying after drying
Piece；
Wherein, the thickness of the thermal barrier coating is 300 microns, and the material of thermal barrier coating includes rare earth niobates, wherein institute
Stating rare earth niobates chemical composition is：Yb3NbO7；
The metal bonding coating is NiCrAlY alloys, and the thickness of metal bonding coating is 300 μm.
Embodiment 3
A kind of preparation method of Wear-resistant, high-temperature resistant nickel-base alloy turbo blade, comprises the following steps：
(1) gas-atomized powder technique is used, Co-based alloy powder is made, it is stand-by, wherein, the process conditions of gas-atomized powder
For：Using vacuum atomizing technology, nitrogen pressure is 3.6MPa, and the liquation degree of superheat is 130 DEG C, caliber is 5mm, and extension elongation is
It is atomized during 11mm using close coupling confined type nozzle, the composition of Co-based alloy powder is Al 4.5%, Nb 6%, Ti 1-
3.2%th, Cr 1%, remaining is Ni；
(2) threedimensional model of turbo blade is set up, discretization layering is then carried out to it along in short transverse, thickness is formed
Uniform section, slice thickness is 0.04mm, and section file is imported into the metal dust former of electron beam constituency；
(3) Co-based alloy powder obtained above is loaded in the metal dust former of electron beam constituency, and will shaping
Substrate is positioned in the forming cavity of electron beam constituency metal dust former on liftable platform, and forming cavity is evacuated to
10-2Pa, and shaping substrate is preheated, tile one layer of Co-based alloy powder after the completion of preheating on substrate, then by setting in advance
The electron beam scanning alloy powder of meter, obtains sedimentary, and its thickness is identical with above-mentioned slice thickness, and heap layer by layer is then realized successively
Product, until turbo blade is machined, after machining, is passed through cooling gas, treats blade cooling to less than 80 DEG C, takes out and cold
But to room temperature, pending turbo blade is obtained, wherein, the condition of basal plate preheating is：Beam scan velocity is 10500mm/
S, electronic beam current is 40mA, and sweep span is 0.05mm；
(4) it is put into after pending turbo blade obtained above is cleaned and dried in graphite heater furnace, lower 1120 DEG C, pressure
Power is that 9MPa handles taking-up after furnace cooling after 2h；
(5) dried after turbine blade surface deposition layer of metal tack coat after the treatment, then using supersonic speed
Spraying coating process obtains Wear-resistant, high-temperature resistant nickel-base alloy turbine leaf in one layer of thermal barrier coating of metal bonding coating surface spraying after drying
Piece；
Wherein, the thickness of the thermal barrier coating is 200 microns, and the material of thermal barrier coating includes rare earth niobates, wherein institute
Stating rare earth niobates chemical composition is：Cd3NbO7；The metal bonding coating is FeCrAlY alloys, and the thickness of metal bonding coating is
300μm。
Embodiment 4
A kind of preparation method of Wear-resistant, high-temperature resistant nickel-base alloy turbo blade, comprises the following steps：
(1) gas-atomized powder technique is used, Co-based alloy powder is made, it is stand-by, wherein, the process conditions of gas-atomized powder
For：Using vacuum atomizing technology, nitrogen pressure is 3.57MPa, and the liquation degree of superheat is 150 DEG C, caliber is 5mm, and extension elongation is
It is atomized during 11mm using close coupling confined type nozzle, the composition of Co-based alloy powder is Al 5%, Nb 7%, Ti 2.5%, Cr
2%, remaining is Ni；
(2) threedimensional model of turbo blade is set up, discretization layering is then carried out to it along in short transverse, thickness is formed
Uniform section, slice thickness is 0.06mm, and section file is imported into the metal dust former of electron beam constituency；
(3) Co-based alloy powder obtained above is loaded in the metal dust former of electron beam constituency, and will shaping
Substrate is positioned in the forming cavity of electron beam constituency metal dust former on liftable platform, and forming cavity is evacuated to
10-2Pa, and shaping substrate is preheated, tile one layer of Co-based alloy powder after the completion of preheating on substrate, then by setting in advance
The electron beam scanning alloy powder of meter, obtains sedimentary, and its thickness is identical with above-mentioned slice thickness, and heap layer by layer is then realized successively
Product, until turbo blade is machined, after machining, is passed through cooling gas, treats blade cooling to less than 80 DEG C, takes out and cold
But to room temperature, pending turbo blade is obtained, wherein, the condition of basal plate preheating is：Beam scan velocity is 11000mm/
S, electronic beam current is 40mA, and sweep span is 0.08mm；
(4) it is put into after pending turbo blade obtained above is cleaned and dried in graphite heater furnace, lower 1140 DEG C, pressure
Power is that 10MPa handles taking-up after furnace cooling after 3h；
(5) dried after turbine blade surface deposition layer of metal tack coat after the treatment, then using supersonic speed
Spraying coating process obtains Wear-resistant, high-temperature resistant nickel-base alloy turbine leaf in one layer of thermal barrier coating of metal bonding coating surface spraying after drying
Piece；
Wherein, the thickness of the thermal barrier coating is 200 microns, and the material of thermal barrier coating includes rare earth niobates, wherein institute
Rare earth niobates chemical composition is stated for (La0.7Y0.3)3NbO7；
The metal bonding coating is FeCrAlY alloys, and the thickness of metal bonding coating is 150 μm.
Embodiment 5
A kind of preparation method of Wear-resistant, high-temperature resistant nickel-base alloy turbo blade, comprises the following steps：
(1) gas-atomized powder technique is used, Co-based alloy powder is made, it is stand-by, wherein, the process conditions of gas-atomized powder
For：Using vacuum atomizing technology, nitrogen pressure is 3.8MPa, and the liquation degree of superheat is 160 DEG C, caliber is 5mm, and extension elongation is
It is atomized during 11mm using close coupling confined type nozzle, the composition of Co-based alloy powder is Al 5%, Nb 7.5%, Ti 3%, Cr
3%, remaining is Ni；
(2) threedimensional model of turbo blade is set up, discretization layering is then carried out to it along in short transverse, thickness is formed
Uniform section, slice thickness is 0.07mm, and section file is imported into the metal dust former of electron beam constituency；
(3) Co-based alloy powder obtained above is loaded in the metal dust former of electron beam constituency, and will shaping
Substrate is positioned in the forming cavity of electron beam constituency metal dust former on liftable platform, and forming cavity is evacuated to
10-2Pa, and shaping substrate is preheated, tile one layer of Co-based alloy powder after the completion of preheating on substrate, then by setting in advance
The electron beam scanning alloy powder of meter, obtains sedimentary, and its thickness is identical with above-mentioned slice thickness, and heap layer by layer is then realized successively
Product, until turbo blade is machined, after machining, is passed through cooling gas, treats blade cooling to less than 80 DEG C, takes out and cold
But to room temperature, pending turbo blade is obtained, wherein, the condition of basal plate preheating is：Beam scan velocity is 11200mm/
S, electronic beam current is 40mA, and sweep span is 0.12mm；
(4) it is put into after pending turbo blade obtained above is cleaned and dried in graphite heater furnace, lower 1180 DEG C, pressure
Power is that 11MPa handles taking-up after furnace cooling after 3h；
(5) dried after turbine blade surface deposition layer of metal tack coat after the treatment, then using supersonic speed
Spraying coating process obtains Wear-resistant, high-temperature resistant nickel-base alloy turbine leaf in one layer of thermal barrier coating of metal bonding coating surface spraying after drying
Piece；
Wherein, the thickness of the thermal barrier coating is 300 microns, and the material of thermal barrier coating includes rare earth niobates solid solution,
Wherein described rare earth niobates solid solution chemical composition is Y3(Nb0.3Ta0.7)O7；
The metal bonding coating is CoCrAlY alloys, and the thickness of metal bonding coating is 150 μm.
Comparative example 1
The heat barrier coat material of turbine blade surface replaces with YSZ materials, and other preparation conditions and embodiment 5 are identical.
Comparative example 2
Turbine blade surface only sprays thermal barrier coating, does not have deposited metal tack coat, other preparation conditions and the phase of embodiment 5
Together.
Comparative example 3
Turbine blade surface does not spray thermal barrier coating, and only deposition has metal bonding coating, other preparation conditions and embodiment 5
It is identical.
Performance test is carried out to turbo blade obtained above below；
1st, hardness test
Hardness determination is carried out to four kinds of samples respectively using WILSOWWOLPERT450SVD types Vickers.
Test result shows that embodiment 1-5 turbine blade surface hardness is up to 412HV, and the hardness of comparative example 1 is
205HV, the hardness of comparative example 2 is 322HV, and the hardness of comparative example 3 is 274HV.
2nd, coating performance is tested
Thermal shock resistance：By the sample prepared during thermal shock test, it is put into heating furnace, is heated to 1000 DEG C of temperature, protects
Taken out after warm 10min balances, in 25 DEG C of cold water of input, 20 times repeatedly.
Test result is shown：Embodiment 1-5 turbo blade is not all applied after 20 1000 DEG C of thermal shocks test
Layer peels off, bubbled and cracking phenomena, illustrates the excellent bonding performance of coating and matrix；And there is a small amount of rise in the coating of documents 1
Steep phenomenon；There is substantial amounts of peeling, foaming and cracking phenomena in the coating of comparative example 2；There is a small amount of coating in the coating of comparative example 3
Cracking phenomena.
Drawing by high temperature mechanical property：Test is carried out on the accurate universal testing machine of German ZWICK companies Z100 types, is entered respectively
Test at 760 DEG C and 980 DEG C of row.Test is carried out using displacement method, and rate of extension is 3mm/s, surrender after-drawing speed before surrender
Rate is 5mm/s.
Test result：The tensile strength of embodiment 1-5 turbo blade is 1228MPa-1305MPa, the whirlpool of comparative example 1
The tensile strength of impeller blade is 961MPa, and comparative example 2-3 tensile strength is only 806-812MPa.
Thermal cycle oxidation test is carried out on Thermal cycle oxidation device, and sample is first in 1000 DEG C of stove internal oxiditions
60min, then air natural cooling 10min is 1 circulation outside stove, is weighed once every several circulations.When weighing, peeling
Oxide-film is not counted in total gain in weight.
Test result：After 1000 DEG C of constant temperature oxidation 200h, the oxidation weight gain of embodiment 1-5 turbine blade coating is only
0.012-0.015mg/cm2, and the weightening of the coating oxidation of comparative example 1 is 3.15mg/cm2, the coating oxidation of comparative example 2, which increases weight, is
3.00mg/cm2, the coating oxidation weightening of comparative example 3 is 3.89mg/cm2。
Turbo blade produced by the present invention has more preferable mechanical performance it can be seen from above-mentioned test result, anti-oxidant
Excellent performance, anti-wear performance is good, and resistance to elevated temperatures is good.
Claims (9)
1. a kind of preparation method of Wear-resistant, high-temperature resistant nickel-base alloy turbo blade, it is characterised in that comprise the following steps：
(1) gas-atomized powder technique is used, Co-based alloy powder is made, it is stand-by；
(2) threedimensional model of turbo blade is set up, discretization layering is then carried out to it along in short transverse, thickness is formed uniform
Section, will section file imported into the metal dust former of electron beam constituency；
(3) Co-based alloy powder obtained above is loaded in the metal dust former of electron beam constituency, and by shaping substrate
It is positioned in the forming cavity of electron beam constituency metal dust former on liftable platform, forming cavity is vacuumized, and it is right
Shaping substrate is preheated, and tile one layer of Co-based alloy powder after the completion of preheating on substrate, then the electron beam by being pre-designed
Alloy powder is scanned, sedimentary is obtained, layer upon layer is realized successively, until turbo blade is machined, after machining, is passed through
Cooling gas, treats blade cooling to less than 80 DEG C, takes out and is cooled to room temperature, obtains pending turbo blade；
(4) it is put into after pending turbo blade obtained above is cleaned and dried in graphite heater furnace, with stove after processing 1-4h
Taken out after cooling；
(5) dried after turbine blade surface deposition layer of metal tack coat after the treatment, then using supersonic spray coating
Technique obtains Wear-resistant, high-temperature resistant nickel-base alloy turbo blade in one layer of thermal barrier coating of metal bonding coating surface spraying after drying；
Wherein, the material of the thermal barrier coating includes rare earth niobates and its solid solution, wherein the rare earth niobates chemical group
Turn into：Ln3NbO7, Ln include La, Pr, Nd, Sm, Eu, Gd, Tb, Dy, Ho, Er, Tm, Yb, Lu, Y and Sc in one or more
Combination；The solid solution chemical composition is Ln3(Nb1-xTax)O7(0≤x ＜ 1).
2. a kind of preparation method of Wear-resistant, high-temperature resistant nickel-base alloy turbo blade as claimed in claim 1, it is characterised in that：Step
Suddenly in (1), the condition of the gas-atomized powder is：Using vacuum atomizing technology, nitrogen pressure is 3.5-4MPa, the liquation degree of superheat
It is 5mm for 120-180 DEG C, caliber, using the atomization of close coupling confined type nozzle when extension elongation is 11mm.
3. a kind of preparation method of Wear-resistant, high-temperature resistant nickel-base alloy turbo blade as claimed in claim 1, it is characterised in that：Step
Suddenly in (1), the composition of the Co-based alloy powder is Al4-5.5%, Nb 5-8%, Ti 1-3.2%, Cr 0.5-3.5%, its
Remaining is Ni.
4. a kind of preparation method of Wear-resistant, high-temperature resistant nickel-base alloy turbo blade as claimed in claim 1, it is characterised in that：Step
Suddenly in (2), the thickness of the section is 0.02-0.08mm.
5. a kind of preparation method of Wear-resistant, high-temperature resistant nickel-base alloy turbo blade as claimed in claim 1, it is characterised in that：Step
Suddenly in (3), the thickness of every layer of sedimentary is identical with the thickness of step (2) described section, in sedimentary preparation process in forming cavity
Vacuum be 10-2Pa。
6. a kind of preparation method of Wear-resistant, high-temperature resistant nickel-base alloy turbo blade as claimed in claim 1, it is characterised in that：Step
Suddenly in (3), the condition of the basal plate preheating is：Beam scan velocity is 10000-11500mm/s, and electronic beam current is 40mA,
Sweep span is 0.03-0.15mm.
7. a kind of preparation method of Wear-resistant, high-temperature resistant nickel-base alloy turbo blade as claimed in claim 1, it is characterised in that：Step
Suddenly in (4), the condition of the processing is that furnace temperature is 1100-1200 DEG C, and pressure is 8-12MPa.
8. a kind of preparation method of Wear-resistant, high-temperature resistant nickel-base alloy turbo blade as claimed in claim 1, it is characterised in that：Step
Suddenly in (5), the metal bonding coating is MCrAlY alloy, and wherein M is one or more combinations in Ni, Co, Fe, Y be Y, La,
One kind in Hf, the thickness of metal bonding coating is 150-300 μm.
9. a kind of preparation method of Wear-resistant, high-temperature resistant nickel-base alloy turbo blade as claimed in claim 1, it is characterised in that：Step
Suddenly in (5), the thickness of the thermal barrier coating is 200-300 μm.
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