CN108754386A - Thermal shock resistant MCrAlY coating and preparation method thereof - Google Patents
Thermal shock resistant MCrAlY coating and preparation method thereof Download PDFInfo
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- CN108754386A CN108754386A CN201810845113.XA CN201810845113A CN108754386A CN 108754386 A CN108754386 A CN 108754386A CN 201810845113 A CN201810845113 A CN 201810845113A CN 108754386 A CN108754386 A CN 108754386A
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- 238000000576 coating method Methods 0.000 title claims abstract description 116
- 239000011248 coating agent Substances 0.000 title claims abstract description 74
- 230000035939 shock Effects 0.000 title claims abstract description 40
- 238000002360 preparation method Methods 0.000 title claims abstract description 14
- 239000000956 alloy Substances 0.000 claims abstract description 30
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 30
- 239000000843 powder Substances 0.000 claims abstract description 18
- 238000007254 oxidation reaction Methods 0.000 claims abstract description 6
- 230000003647 oxidation Effects 0.000 claims abstract description 5
- 229910052742 iron Inorganic materials 0.000 claims abstract description 3
- 229910052759 nickel Inorganic materials 0.000 claims abstract description 3
- 239000013078 crystal Substances 0.000 claims description 77
- 238000010276 construction Methods 0.000 claims description 26
- 238000000034 method Methods 0.000 claims description 17
- 229910052761 rare earth metal Inorganic materials 0.000 claims description 10
- 238000009792 diffusion process Methods 0.000 claims description 8
- 239000007789 gas Substances 0.000 claims description 8
- 239000000126 substance Substances 0.000 claims description 8
- 229910052751 metal Inorganic materials 0.000 claims description 7
- 238000005507 spraying Methods 0.000 claims description 7
- 230000007547 defect Effects 0.000 claims description 6
- 239000004615 ingredient Substances 0.000 claims description 6
- 238000012360 testing method Methods 0.000 claims description 6
- 229910052727 yttrium Inorganic materials 0.000 claims description 6
- 239000002184 metal Substances 0.000 claims description 5
- 239000003961 penetration enhancing agent Substances 0.000 claims description 5
- 238000010791 quenching Methods 0.000 claims description 5
- 230000000171 quenching effect Effects 0.000 claims description 5
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 5
- 229910052782 aluminium Inorganic materials 0.000 claims description 4
- 229910052804 chromium Inorganic materials 0.000 claims description 4
- 239000011247 coating layer Substances 0.000 claims description 4
- 239000000567 combustion gas Substances 0.000 claims description 4
- 239000010410 layer Substances 0.000 claims description 4
- 239000002994 raw material Substances 0.000 claims description 4
- 238000007750 plasma spraying Methods 0.000 claims description 3
- 229910052684 Cerium Inorganic materials 0.000 claims description 2
- 239000003963 antioxidant agent Substances 0.000 claims description 2
- 230000003078 antioxidant effect Effects 0.000 claims description 2
- 235000006708 antioxidants Nutrition 0.000 claims description 2
- 238000002485 combustion reaction Methods 0.000 claims description 2
- 238000010285 flame spraying Methods 0.000 claims description 2
- 239000011261 inert gas Substances 0.000 claims description 2
- 229910052746 lanthanum Inorganic materials 0.000 claims description 2
- 238000010422 painting Methods 0.000 claims description 2
- 238000001291 vacuum drying Methods 0.000 claims description 2
- 239000000463 material Substances 0.000 abstract description 16
- 230000007797 corrosion Effects 0.000 abstract description 9
- 238000005260 corrosion Methods 0.000 abstract description 9
- 230000006399 behavior Effects 0.000 abstract description 5
- 238000005336 cracking Methods 0.000 abstract description 5
- 238000009826 distribution Methods 0.000 abstract description 5
- 238000005272 metallurgy Methods 0.000 abstract description 3
- 239000002131 composite material Substances 0.000 abstract 1
- 208000037656 Respiratory Sounds Diseases 0.000 description 6
- 229910000765 intermetallic Inorganic materials 0.000 description 5
- XKRFYHLGVUSROY-UHFFFAOYSA-N Argon Chemical compound [Ar] XKRFYHLGVUSROY-UHFFFAOYSA-N 0.000 description 4
- 238000010438 heat treatment Methods 0.000 description 4
- 239000011253 protective coating Substances 0.000 description 4
- 150000002910 rare earth metals Chemical class 0.000 description 4
- 238000005275 alloying Methods 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 239000011159 matrix material Substances 0.000 description 3
- 239000000203 mixture Substances 0.000 description 3
- 229910000838 Al alloy Inorganic materials 0.000 description 2
- 238000004873 anchoring Methods 0.000 description 2
- 229910052786 argon Inorganic materials 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 2
- 230000007812 deficiency Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000006698 induction Effects 0.000 description 2
- 230000003993 interaction Effects 0.000 description 2
- 229910052702 rhenium Inorganic materials 0.000 description 2
- 101000718623 Bacillus subtilis (strain 168) RNA polymerase sigma-K factor Proteins 0.000 description 1
- 101001062993 Escherichia coli (strain K12) RNA polymerase sigma factor FliA Proteins 0.000 description 1
- 101001023209 Vibrio parahaemolyticus serotype O3:K6 (strain RIMD 2210633) RNA polymerase sigma factor for flagellar operon Proteins 0.000 description 1
- 238000009825 accumulation Methods 0.000 description 1
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 description 1
- 230000003026 anti-oxygenic effect Effects 0.000 description 1
- 238000013459 approach Methods 0.000 description 1
- 229910000422 cerium(IV) oxide Inorganic materials 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 229910052593 corundum Inorganic materials 0.000 description 1
- 230000001351 cycling effect Effects 0.000 description 1
- 230000006378 damage Effects 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000000945 filler Substances 0.000 description 1
- 238000009689 gas atomisation Methods 0.000 description 1
- 239000000320 mechanical mixture Substances 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 239000003595 mist Substances 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 229910021420 polycrystalline silicon Inorganic materials 0.000 description 1
- 229920005591 polysilicon Polymers 0.000 description 1
- 230000008092 positive effect Effects 0.000 description 1
- 230000002265 prevention Effects 0.000 description 1
- -1 rare earth Rare earth Chemical class 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- WUAPFZMCVAUBPE-UHFFFAOYSA-N rhenium atom Chemical compound [Re] WUAPFZMCVAUBPE-UHFFFAOYSA-N 0.000 description 1
- 238000002791 soaking Methods 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
- 229910001845 yogo sapphire Inorganic materials 0.000 description 1
Classifications
-
- 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
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
- C23C4/06—Metallic material
- C23C4/073—Metallic material containing MCrAl or MCrAlY alloys, where M is nickel, cobalt or iron, with or without non-metal elements
-
- 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
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
- C23C4/129—Flame spraying
-
- 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
- C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
- C23C4/12—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the method of spraying
- C23C4/134—Plasma spraying
Abstract
The invention discloses a thermal shock resistant MCrAlY coating and a preparation method thereof, belonging to the technical field of surface engineering. The MCrAlY coating has heat shock resistance, M is one or more of Ni, Co or Fe, the grain boundary of the coating consists of a special structure grain boundary and a random grain boundary, the coating contains a grain boundary characteristic element RE to optimize the characteristic distribution of the grain boundary, and the proportion of the special structure grain boundary in the coating is more than or equal to 80 percent. By adding grain boundary characteristic element RE into MCrAlY alloy powder or diffusing RE into MCrAlY coating, the proportion of special structure grain boundary is obviously improved, especially sigma 3nThe proportion of (A) is that the grain boundary failure resistance of the material is obviously improved, and the corrosion and cracking behaviors are effectively prevented from continuously proceeding. Coating layerThe high-temperature-resistant composite material has the characteristics of high bonding strength, excellent high-temperature oxidation resistance and thermal shock resistance, long service life and the like, and can be widely used for protecting high-temperature hot end components of engines in the fields of aviation, ships, electric power, metallurgy and the like.
Description
Technical field
The invention belongs to field of surface engineering technique, it is related to a kind of heat shock resistance MCrAlY coatings and preparation method thereof, especially
It is related to a kind of by improving method of the special construction crystal boundary accounting to improve its thermal shock resistance in MCrAlY coatings.
Background technology
Blade, turbine outer ring, combustion chamber, the burner inner liner etc. of weight (big) type equipment turbogenerator such as aviation, naval vessel, electric power
The high-temperature oxydation and corrosion failure of crucial hot-end component be influence machine life, reliability and safety in operation principal element,
MCrA1Y high-temperature protection coatings are prepared on hot-end component surface, are to solve the problems, such as one of this most efficient method.
MCrAlY coating grain boundaries, Y form M with matrix elementxY types (X=1,2,3 ...) intermetallic compound, such as Ni5Y、
Co5Y etc..Intermetallic compound (IMC) is the atom chemical combination by a certain percentage of metal, is formed different with the lattice of original the two
Composition of alloy object, new orderly superstructure can be formed, there is the heat resistance better than high temperature alloy, specific strength, compare the service life
The advantages that, antioxygenic property with good stability and outstanding under high temperature, but intermetallic compound brittleness at room temperature is big, such as
M5There is Y IMC hcp (close-packed hexagonal) structure, brittlement phase easily to be cracked in cold cycling in grain boundaries accumulation, thermal stress
Mismatch reduces thermal shock performance of coatings, accelerates coating failure, reduces the service life of coating and part.
In polycrystal, since the orientation of crystal grain is different, there are crystal boundaries for intercrystalline.The performance of polycrystalline material is micro- with it
Tissue and grain boundary features have contact closely, due to grain boundaries often exist it is larger distort, more defect and miscellaneous
Matter, surface-active is higher than intra-die, the destruction of conventional polysilicon body metal material, either mechanics form or chemical attack
Crystal boundary is all originated from, the raising of crystal boundary failure drag can significantly improve the performance of material." bounding engineering " is exactly to pass through alloying
The modes such as element, deformation and heat treatment increase the ratio of special grain boundary in polycrystalline material, to optimize the Grain Boundary Character of material
Distribution so that significantly improve with the relevant a certain or multiple performance of grain boundaries.Grain boundary design has become with control to be changed
The effective means of kind polycrystalline material performance.
According to coincidence site lattice (coincidence site lattice, CSL) theory, crystal boundary can be divided into special construction crystal boundary
(low Σ values CSL crystal boundaries, 3≤Σ≤27) and random grain boundary (Σ>27), special construction crystal boundary pair and the relevant properties of crystal boundary
Optimization play positive effect, pass through improve special grain boundary proportion in entire crystal boundary approach, improve material corrosion resistance
Substantially it is the continuity for controlling crystal boundary with the basic principle of toughness, i.e. a large amount of distributions of special grain boundary interrupt random grain boundary
Connectivity, and then significantly improve material crystal boundary failure drag.It therefore, will be notable by improving the ratio of low Σ CSL crystal boundaries
Interface sensibility is reduced, to effectively prevent crystal boundary and material internal corrosion and cracking behaviors from being carried out continuously.
By improving special construction crystal boundary ratio, so as to adjust polycrystalline boundaries network, material and crystalline substance can significantly improve
The related performance in boundary.The CSL crystal boundaries of this 3 angles of special construction crystal boundary, especially Σ 3, Σ 9 and Σ 27 have unique category
Property, belong to Σ 3n(n=1,2 or 3), are low energy crystal boundaries to crystal boundary, and the random grain boundary of periphery is high energy crystal boundary, low energy crystal boundary
Feature is stable structure, has lower energy, compared with random grain boundary, has higher mistake to Grain Boundary Sliding and crack propagation
Imitate drag.Therefore, the ratio that low Σ CSL crystal boundaries in material account for all CSL crystal boundaries is improved, Σ 3 is especially improvednRatio, then
It hinders crackle stronger along random grain boundary extended capability, material thermal shock resistance will be significantly improved.
Invention content
In order to solve in the prior art, MCrAlY coating grain boundaries intermetallic compound brittleness is big, reduces coating thermal shock
Performance leads to coating service life and reliability deficiency problem, the present invention provides a kind of heat shock resistance MCrAlY coatings and its
Preparation method specifically includes a kind of ratio improving special construction crystal boundary in coating using the micro grain boundary features elements RE of addition,
And the method for using the technology to prepare MCrAlY protective coatings.Stable with coating performance using the coating of technology preparation,
Bond strength is high, high temperature oxidation resisting and good in thermal shock, the features such as service life is long.
The present inventor has found by a lot of research work, adds micro grain boundary features elements RE (rare earth
Rare earth), by the formation of crystal grain thinning and the low Σ values CSL crystal boundaries of promotion, improve special construction crystal boundary ratio, especially Σ 3n
Crystal boundary (n=1,2 or ratio 3), reduce interface sensibility, so as to effectively prevent corrosion and cracking behaviors it is continuous into
Row is the effective ways for preparing excellent MCrAlY protective coatings, improving gas turbine high temperature hot-end component service life.
Rare earth elements RE atomic radius is big, and has special electronic structure, in high temperature alloy after rare earth doped elements RE,
The result of calculation of crystal boundary electronic structure shows that rare earth can provide more polyelectron for bonding in crystal boundary area.I.e. in MCrAlY crystal boundaries
Place, the atom of matrix M obtain more electronics so that the interaction between RE M atoms adjacent with crystal boundary area is bonded to ion
Variation is closed, also reinforces the bonding of crystal boundary atom and the M atoms of crystal boundary both sides, and then improves crystal boundary failure drag, improves crystal boundary
Intensity.Meanwhile the result of calculation of the local density of state shows, after RE is added, and is had occurred between M atoms outermosts track in system
More strong interaction, while making crystal boundary M in the density of states proportion increase at keypad, reduce the total energy of system
Amount, keeps grain boundary structure more stable, therefore rare earth elements RE, promotes the formation of low Σ values CSL crystal boundaries, especially Σ 3nCrystal boundary (n
=1,2 or ratio 3), special construction crystal boundary ratio is improved, interface sensibility is reduced, so as to effectively prevent to corrode
With being carried out continuously for cracking behaviors, MCrAlY coating thermal shock resistances are improved.
The present invention provides a kind of heat shock resistance MCrAlY coatings, and specific technical solution is as follows.
Heat shock resistance MCrAlY coatings, M are one or more of Ni, Co or Fe, and coating crystal boundary is by special construction crystal boundary
It is constituted with random grain boundary, coating contains grain boundary features elements RE and is distributed with optimizing Grain Boundary Character, and special construction crystal boundary accounts in coating
Than >=80%.
Further, special construction crystal boundary refers to the crystal boundary of CSL≤27 3≤Σ, and random grain boundary refers to Σ CSL>27 crystalline substance
Boundary.
Further, 3 ΣnCrystal boundary (n=1,2 or 3) quantity accounts for special construction crystal boundary ratio >=70%.
Further, grain boundary features elements RE is one or more of La, Ce, Re (rhenium) rare earth element, and RE contents are
0.1-5wt%.
Further, coating layer thickness 0.05-0.2mm, 900 combustion gas thermal shock tests of (60~904 DEG C) ± 20 DEG C of progress,
Coating is without falling off, detach, peeling, crack defect；Water quenching thermal shock resistance (according to HB7269-96 methods) is carried out at 1200 DEG C,
Thermal shock number >=150 time；2000h constant temperature oxidations testing coating reaches complete anti-oxidant rank at 1200 DEG C.
Further, the coating is for aero-engine or thereof for ground gas turbine blade, turbine outer ring or burning
The protection of room high temperature hot-end component.
Further, it is protected for aero-turbine outer shroud using the coating, coating service life is promoted to 800h
More than, improve 2 times or more than traditional MCrAlY coatings；Vessel personnel blade shields are used for using the coating, coating uses
Service life is more than 18000h, and 1.5 times or more are improved than traditional MCrAlY coatings.
The present invention also provides a kind of preparation methods of heat shock resistance MCrAlY coatings, include the following steps：
(1) dispensing：It requires to prepare M, Cr, Al, Y metal simple-substance or alloy raw material according to MCrAlY alloy powdered ingredients,
Prepare grain boundary features elements RE, RE contents are 0.1-5wt%；
(2) prepared by powder：Prepare MCrAlY alloy powder；
(3) prepared by coating：Prepare MCrAlY (RE) alloy coat.
Further, the method for preparing MCrAlY alloy powder is mechanical mixture or inert gas atomizer method.
Further, the method for preparing MCrAlY alloy coating is supersonic flame spraying, vacuum plasma spray coating or big
Gas plasma spraying.
The present invention also provides a kind of preparation methods of heat shock resistance MCrAlY coatings, include the following steps：
(1) dispensing：It requires to prepare M, Cr, Al, Y metal simple-substance or alloy raw material according to MCrAlY alloy powdered ingredients；
(2) prepared by powder：Prepare MCrAlY alloy powder；
(3) prepared by coating：Prepare MCrAlY alloy coating；
(4) RE is oozed in coating diffusion：Prepare penetration enhancer according to coating RE content requirements, by the portion of penetration enhancer and spraying MCrAlY coatings
Part is put into vacuum drying oven, is carried out High temperature diffusion and is oozed, prepares MCrAlY coatings.
The present inventor is prepared for MCrAlYRE alloy powders and coating by well known method, and coating has heat-resisting
The features such as impact property is excellent, service life is long can be widely used for the fields such as aviation, naval vessel, electric power, metallurgy engine high-temperature heat
The protection of end pieces.
The present invention has following remarkable advantage：Special construction crystal boundary ratio is significantly improved by adding grain boundary features elements RE
Example, especially Σ 3nRatio, the connectivity of random grain boundary has been interrupted by a large amount of distributions of special grain boundary, the crystal boundary of material loses
Effect drag is significantly improved, and effective prevention corrosion is carried out continuously with cracking behaviors, solves prior art MCrAlY painting layer crystals
Intermetallic compound brittleness is big at boundary, reduces coating thermal shock resistance properties, leads to coating service life and reliability deficiency problem.It applies
Layer have the characteristics that bond strength height, high temperature oxidation resisting and good in thermal shock, service life it is long, can be widely used for aviation,
The protection of the fields such as naval vessel, electric power, metallurgy engine high-temperature hot-end component.MCrAlY alloy coating provided by the present invention is used
Protected in aero-turbine outer shroud, coating service life is promoted to 800h or more, than traditional MCrAlY coatings improve 2 times with
On；Vessel personnel blade shields are used for using the coating, coating service life is more than 18000h, than traditional MCrAlY coatings
Improve 1.5 times or more.
Description of the drawings
Fig. 1 is low Σ CSL crystal boundaries Anticrack schematic diagram.
Coincidence site lattice profiles versus schemes in coating before and after Fig. 2 is addition Ce.
Specific implementation mode
Below in conjunction with attached drawing, the present invention will be further described.
Embodiment 1
Fig. 1 is low Σ CSL crystal boundaries Anticrack schematic diagram, wherein a：The corrosion occurred along crystal boundary；b：After adding RE,
Along the corrosion of random grain boundary；c-e：Corrosion and crackle are along Σ 3nCrystal boundary extended mode, arrow represent direction.As can be seen that with
It low Σ CSL crystal boundary ratios to improve, high energy wide-angle random grain boundary network will be interrupted, and hinder crackle along the continuation of random grain boundary
Extension, significantly improves material thermal-shock resistance.
Metallic element is according to following ingredient composition：Al, 7wt%；Cr, 22wt%, Y, 1.5wt%；Ni：Surplus.It will be above-mentioned
Material is put into vacuum atomizing equipment, using Frequency Induction Heating, is obtained using argon gas atomization after the abundant alloying of aluminium alloy
NiCrAlY alloy powders.
Using low-voltage plasma spraying NiCrAlY alloy powders, the Gas Turbine outer portion after surface preparation
Part surface prepares protective coating.Spraying parameter is：Arc current 600A；Arc voltage 65V；Powder feed rate 65g/min；Spraying away from
From 220mm.Special construction crystal boundary (CSL≤27 3≤Σ) accounting 70%, wherein Σ 3 in NiCrAlY coatingsnCrystal boundary (n=1,2 or
3) it is 62% that quantity, which accounts for special construction crystal boundary ratio,.600 combustion gas thermal shock tests of (60~904 DEG C) ± 20 DEG C of progress, coating
There is the defects of peeling, crackle；Water quenching thermal shock resistance (according to HB7269-96 methods) is carried out at 1200 DEG C, coating after 80 times
There is peeling and local shedding.
NiCrAlYCe coatings introduce Ce elements using diffusion cementation process.Rare earth diffusion penetration enhancer is formulated as follows：Using
5% CeO2Powder, 10% NaF, surplus are filler Al2O3Powder, the specific steps are：It is true in high temperature that reaction is oozed in rare earth diffusion
It is carried out in empty stove, heating rate is about 20 DEG C/min, and permeation temperature is 1100 DEG C, soaking time 3h.
After diffusion is oozed, Ce contents are 0.8% in NiCrAlYCe coatings, coating layer thickness 0.10mm, anchoring strength of coating
55MPa, porosity 0.4%.Special construction crystal boundary (CSL≤27 3≤Σ) accounting 88%, wherein Σ 3 in coatingnCrystal boundary (n=1,
2 or 3) quantity accounts for special construction crystal boundary ratio is 83%, compared to NiCrAlY coatings, special construction is brilliant in NiCrAlYCe coatings
Boundary's ratio improves 26%, Σ 3nCrystal boundary improves 32% in special construction crystal boundary accounting.± 20 DEG C of (60~904 DEG C) are fired
Gas thermal shock test, there is the defects of peeling, crackle compared to NiCrAlY coatings in coating after 925 times, improves 54%；?
1200 DEG C carry out water quenching thermal shock resistance (according to HB7269-96 methods), and peeling and local shedding occurs in coating after 150 times.
Coincidence site lattice profiles versus figure in coating is added before and after Ce as shown in Fig. 2, a) being wherein weight position in NiCrAlY coatings
Dot matrix is distributed, b) it is that coincidence site lattice is distributed in NiCrAlYCe coatings after adding Ce.As can be seen that special construction is brilliant after addition Ce
Boundary (CSL≤27 3≤Σ) distribution is substantially improved.
It is protected for aero-engine two-stage turbine outer shroud using the coating, coating service life is promoted to 820h or more,
2.5 times are improved than traditional MCrAlY coatings.
Embodiment 2
Metallic element is according to following ingredient composition：Al, 7wt%；Cr, 30wt%, Y, 1.5wt%；Re, 1%；Co：Surplus.
Above-mentioned material is put into vacuum atomizing equipment, using Frequency Induction Heating, argon gas mist is utilized after the abundant alloying of aluminium alloy
Change and obtains CoCrAlYRe alloy powders.
CoCrAlYRe alloy coats, the gas turbine blades surface after surface preparation are prepared using supersonic spray coating
Prepare protective coating.In CoCrAlYRe coatings Re contents be 0.9%, coating layer thickness 0.12mm, anchoring strength of coating 50MPa,
Porosity 0.5%, special construction crystal boundary (CSL≤27 3≤Σ) accounting 87% in coating, wherein Σ 3nCrystal boundary (n=1,2 or 3)
It is 78% that quantity, which accounts for special construction crystal boundary ratio, compared to CoCrAlY coatings, special construction crystal boundary ratio in CoCrAlY Re coatings
Example improves 24%, Σ 3nCrystal boundary accounting improves 30%.(60~904 DEG C) ± 20 DEG C of progress combustion gas thermal shock tests, 980 times
There is the defects of peeling, crackle compared to CoCrAlY coatings in coating afterwards, improves 50%；Water quenching anti-thermal shock is carried out at 1200 DEG C
Performance (according to HB7269-96 methods), there is peeling and local shedding in coating after 150 times.
Vessel personnel blade shields are used for using the coating, coating service life 21000h is applied than traditional MCrAlY
Layer improves 1.5 times or more.
Claims (11)
1. heat shock resistance MCrAlY coatings, M is one or more of Ni, Co or Fe, coating crystal boundary by special construction crystal boundary and
Random grain boundary is constituted, which is characterized in that coating contains grain boundary features elements RE and is distributed with optimizing Grain Boundary Character, special knot in coating
Structure crystal boundary accounting >=80%.
2. heat shock resistance MCrAlY coatings according to claim 1, which is characterized in that special construction crystal boundary refers to 3≤Σ
The crystal boundary of CSL≤27, random grain boundary refer to Σ CSL>27 crystal boundary.
3. heat shock resistance MCrAlY coatings according to claim 2, which is characterized in that Σ 3nCrystal boundary (n=1,2 or 3) quantity
Account for special construction crystal boundary ratio >=70%.
4. heat shock resistance MCrAlY coatings according to claim 1, which is characterized in that grain boundary features elements RE is La, Ce
One or more of rare earth element, RE contents are 0.1-5wt%.
5. heat shock resistance MCrAlY coatings according to claim 1, which is characterized in that coating layer thickness 0.05-0.2mm, (60
~904 DEG C)+20 DEG C carry out 900 combustion gas thermal shock tests, coating is without falling off, detach, peeling, crack defect；1200 DEG C into
Row water quenching thermal shock resistance (according to HB7269-96 methods), thermal shock number >=150 time；2000h constant temperature oxidations are surveyed at 1200 DEG C
Examination coating reaches complete anti-oxidant rank.
6. the heat shock resistance MCrAlY coatings according to Claims 1 to 5 any claim, which is characterized in that the painting
Protection of the layer for aero-engine or thereof for ground gas turbine blade, turbine outer ring or combustion chamber high temperature hot-end component.
7. heat shock resistance MCrAlY coatings according to claim 6, which is characterized in that be used for aeroplane engine using the coating
Machine turbine outer ring protects, and coating service life is promoted to 800h or more, and 2 times or more is improved than traditional MCrAlY coatings；Using this
Coating is used for Vessel personnel blade shields, and coating service life is more than 18000h, and 1.5 times are improved than traditional MCrAlY coatings
More than.
8. the preparation method of the heat shock resistance MCrAlY coatings according to Claims 1 to 5 any claim, feature exist
In including the following steps：
(1) dispensing：It requires to prepare M, Cr, Al, Y metal simple-substance or alloy raw material according to MCrAlY alloy powdered ingredients, prepare
Grain boundary features elements RE, RE contents are 0.1-5wt%；
(2) prepared by powder：Prepare MCrAlY alloy powder；
(3) prepared by coating：Prepare MCrAlY alloy coating.
9. preparation method according to claim 8, which is characterized in that the method for preparing MCrAlY alloy powder is that machinery is mixed
Conjunction or inert gas atomizer method.
10. preparation method according to claim 8, which is characterized in that the method for preparing MCrAlY alloy coating is Supersonic
Fast flame-spraying, vacuum plasma spray coating or air plasma spraying.
11. the preparation method of the heat shock resistance MCrAlY coatings according to Claims 1 to 5 any claim, feature
It is, includes the following steps：
(1) dispensing：It requires to prepare M, Cr, Al, Y metal simple-substance or alloy raw material according to MCrAlY alloy powdered ingredients；
(2) prepared by powder：Prepare MCrAlY alloy powder；
(3) prepared by coating：Prepare MCrAlY alloy coating；
(4) RE is oozed in coating diffusion：Prepare penetration enhancer according to coating RE content requirements, the component of penetration enhancer and spraying MCrAlY coatings is put
Enter in vacuum drying oven, carries out High temperature diffusion and ooze, prepare MCrAlY coatings.
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