CN1536033A - Ni Co Cr Al Y Si B coating layer capable of resisting thermal corrosion and its preparation method - Google Patents
Ni Co Cr Al Y Si B coating layer capable of resisting thermal corrosion and its preparation method Download PDFInfo
- Publication number
- CN1536033A CN1536033A CNA03111363XA CN03111363A CN1536033A CN 1536033 A CN1536033 A CN 1536033A CN A03111363X A CNA03111363X A CN A03111363XA CN 03111363 A CN03111363 A CN 03111363A CN 1536033 A CN1536033 A CN 1536033A
- Authority
- CN
- China
- Prior art keywords
- corrosion
- coating
- sample
- preparation
- nicocralysib
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000005260 corrosion Methods 0.000 title claims abstract description 34
- 230000007797 corrosion Effects 0.000 title claims abstract description 33
- 238000002360 preparation method Methods 0.000 title claims abstract description 18
- 229910017709 Ni Co Inorganic materials 0.000 title 1
- 239000011247 coating layer Substances 0.000 title 1
- 238000000576 coating method Methods 0.000 claims abstract description 79
- 239000011248 coating agent Substances 0.000 claims abstract description 64
- 238000000151 deposition Methods 0.000 claims abstract description 15
- 230000003647 oxidation Effects 0.000 claims description 25
- 238000007254 oxidation reaction Methods 0.000 claims description 25
- 238000002474 experimental method Methods 0.000 claims description 9
- 239000011253 protective coating Substances 0.000 claims description 8
- 238000007733 ion plating Methods 0.000 claims description 7
- 238000004140 cleaning Methods 0.000 claims description 6
- 239000011521 glass Substances 0.000 claims description 6
- 238000010438 heat treatment Methods 0.000 claims description 6
- 238000002203 pretreatment Methods 0.000 claims description 4
- 239000000470 constituent Substances 0.000 claims description 2
- 238000005488 sandblasting Methods 0.000 claims description 2
- 238000005516 engineering process Methods 0.000 abstract description 3
- 239000000203 mixture Substances 0.000 abstract description 2
- 238000010891 electric arc Methods 0.000 abstract 1
- 230000001590 oxidative effect Effects 0.000 abstract 1
- 229910045601 alloy Inorganic materials 0.000 description 21
- 239000000956 alloy Substances 0.000 description 21
- PXHVJJICTQNCMI-UHFFFAOYSA-N nickel Substances [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 description 19
- 239000007789 gas Substances 0.000 description 13
- 239000000463 material Substances 0.000 description 13
- 229910052759 nickel Inorganic materials 0.000 description 9
- 230000000694 effects Effects 0.000 description 5
- 229910000601 superalloy Inorganic materials 0.000 description 5
- 238000005137 deposition process Methods 0.000 description 4
- 239000011159 matrix material Substances 0.000 description 4
- 238000009864 tensile test Methods 0.000 description 4
- 230000004584 weight gain Effects 0.000 description 4
- 235000019786 weight gain Nutrition 0.000 description 4
- 230000004580 weight loss Effects 0.000 description 4
- 229910004298 SiO 2 Inorganic materials 0.000 description 3
- 229910008423 Si—B Inorganic materials 0.000 description 3
- 239000012267 brine Substances 0.000 description 3
- 150000001875 compounds Chemical class 0.000 description 3
- 238000005530 etching Methods 0.000 description 3
- HPALAKNZSZLMCH-UHFFFAOYSA-M sodium;chloride;hydrate Chemical compound O.[Na+].[Cl-] HPALAKNZSZLMCH-UHFFFAOYSA-M 0.000 description 3
- 230000015572 biosynthetic process Effects 0.000 description 2
- 239000003153 chemical reaction reagent Substances 0.000 description 2
- 238000002485 combustion reaction Methods 0.000 description 2
- 239000013078 crystal Substances 0.000 description 2
- 238000002844 melting Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000001681 protective effect Effects 0.000 description 2
- 238000002791 soaking Methods 0.000 description 2
- 238000005728 strengthening Methods 0.000 description 2
- 235000013619 trace mineral Nutrition 0.000 description 2
- 239000011573 trace mineral Substances 0.000 description 2
- 229910002515 CoAl Inorganic materials 0.000 description 1
- 229910000943 NiAl Inorganic materials 0.000 description 1
- NPXOKRUENSOPAO-UHFFFAOYSA-N Raney nickel Chemical compound [Al].[Ni] NPXOKRUENSOPAO-UHFFFAOYSA-N 0.000 description 1
- 239000003963 antioxidant agent Substances 0.000 description 1
- 230000003078 antioxidant effect Effects 0.000 description 1
- 235000006708 antioxidants Nutrition 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 239000003245 coal Substances 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 230000003628 erosive effect Effects 0.000 description 1
- 230000005496 eutectics Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 239000012535 impurity Substances 0.000 description 1
- 238000001755 magnetron sputter deposition Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 239000012528 membrane Substances 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 238000005240 physical vapour deposition Methods 0.000 description 1
- 238000004901 spalling Methods 0.000 description 1
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
- Physical Vapour Deposition (AREA)
Abstract
The present invention relates to coating technology, in the concrete, it discloses a NICoCrAlYSiB hot corrosion resisting high-temp. protection coating and its preparation method. Its element content composition includes: Co 28-35 wt%, Cr 17-23 wt%, Al 5-12 wt%, Y 0.1-0.6 wt%, Si 0.9-1.1 wt%, B 0.02-0.04 wt% and the rest is Ni. Said invention adopts electric arc ion deposition technique to prepare said protection coating, and as compared with existent technology said invented protection coating has highest resistance to hot corrosion and high temp. oxidative property, and its preparation process is low in cost.
Description
Technical field
The present invention relates to protective coating technique, specifically a kind of NiCoCrAlYSiB corrosion and heat resistant coating that is used for the internal combustion turbine hot-end component and preparation method thereof.
Background technology
At present, internal combustion turbine has been widely used in aircraft engine, industrial generator does, marine engine, vehicle motor etc. as the subject impetus of 21 century.Because the Working environment of gas turbine parts is quite abominable, especially high-temperature fuel gas is a kind of strong corrosive medium, impurity in fuel and the atmosphere often causes new corrosion mechanism, and significantly accelerated corrosion, therefore, require gas turbine blades when having mechanical behavior under high temperature, excellent corrosion and heat resistant and high temperature oxidation resistance also will be arranged.Adopt high-temperature protection coating on the gas turbine blades surface; can play the protection blade material and avoid oxidation and corrosive effect, wherein MCrAlY (M=Ni, Co; Ni+Co, Fe) the type coating is with its good toughness, intensity height, anti-oxidant and excellent characteristics of corrosive nature and be used widely.
Studies show that for many years, the composition of MCrAlY is in the majority with NiCrAlY, CoCrAlY and NiCoCrAlY, wherein, Ni, Co are the basic comprising elements, can and Al form compound (NiAl, Ni between stable, high-melting point metal
3Al, CoAl), in corrosive medium, Ni, Co will generate the low melting point eutectic tissue with reaction of Salmon-Saxl, but the vitriol of Co is more stable than the vitriol of Ni.Cr and Al are the elements that forms protective oxide film, and Cr can reduce and form Al
2O
3The critical content of the Al element that protective membrane is required, the Cr amount that contains in the general requirement coating is higher than 20wt.%, and the content of Al is chosen in the 5-12wt.% scope.Add Y in the coating and be in order to improve the adhesivity of oxide film, add-on is generally less than 1wt.%.Though CoCrAlY coating performance excellence because the cost of Co is higher, and has limited the use of this coating.And the NiCoCrAlY coating is more widely used with its lower cost and excellent anticorrosive, oxidation susceptibility, but the best proportioning of Ni, Co is that problem to be solved is arranged.
In addition, add micro-Si, can improve the adhesivity of oxide compound, reduce oxide growth rate, and SiO
2Corrosion stability be better than Al
2O
3, Cr
2O
3, the add-on of Si reduces with the increase of Al content.The B element can play the effect of strengthening crystal boundary, and the SiO of B and Si formation
2-B
2O
3Can improve SiO
2The antistripping ability.Though Si, B have obtained common recognition to the corrosion and heat resistant of raising MCrAlY type coating and the effect of high temperature oxidation stability,, also there is not report at present about Si, B optimal addn.
Summary of the invention
The object of the present invention is to provide a kind of NiCoCrAlYSiB corrosion and heat resistant coating and preparation method thereof, owing to dosed suitable trace element (Si and B) in the coating, and Co content is controlled at 28～35wt.%, and the present invention can further improve the corrosion and heat resistant and the high temperature oxidation resistance of NiCoCrAlY coating.
To achieve these goals, technical scheme of the present invention is: by weight percentage, constituent content is Co:28～35wt.%, Cr:17～23wt.%, Al:5～12wt.%, Y:0.1～0.6wt.%, Si:0.9～1.1wt.%, B:0.02～0.04wt.%, surplus is Ni;
The preparation method of described NiCoCrAlYSiB corrosion and heat resistant protective coating adopts arc ion plating (aip), is specially: 1) sample is carried out pre-treatment; 2) again sample is carried out sputter clean, about 2～5 minutes; 3) depositing treatment; 4) sample behind the deposited coatings is carried out vacuum heat treatment, be incubated 3～5 hours down at 900～950 ℃, heat-up rate is controlled at 6～8 ℃/min;
The described pre-treatment of step 1), to the sample that is used for oxidation and corrosion experiment grind, cleaning and sandblast pretreatment, wherein 200～300 order glass balls, wet shot are adopted in sandblasting; The sample that is used for the mechanical property experiment is only done clean; 2) described sputter clean after the sample shove charge, is evacuated to 2 * 10 with the vacuum tightness of vacuum chamber
-3～7 * 10
-3Behind the Pa, feed Ar gas, make air pressure rise to 5 * 10
-2～8 * 10
-2Pa adds-800V～-1000 high bias voltage, specimen surface is carried out sputter clean, about 2～5 minutes; 3) described depositing treatment working parameter is as follows: arc stream: 50～70A, and arc voltage: 20～25V, pulsed bias :-150～-900V, direct-current biasing :-150～-200V, dutycycle: 10～30%, depositing temperature: 300～400 ℃; The thickness of described coating is 40-50 μ m.
The present invention has the following advantages:
1. corrosion and heat resistant is excellent.The Ni-Co-Cr-Al-Y-Si-B coating of the present invention's preparation; 900 ℃ soak in the brine corrosion experiment; surrosion is minimum; can protect gas turbine blades material nickel base superalloy (as: DZ125, DSM11, M22 alloy etc.) to avoid thermal etching well and destroy, its erosion resistance is better than the Ni-20Co-20Cr-8Al-0.5Y coating.
2. oxidation-resistance is excellent.The Ni-Co-Cr-Al-Y-Si-B coating of the present invention's preparation; in 900～1100 ℃ isothermal oxidation; oxidation weight gain can protect the gas turbine blades material to avoid high temperature oxidation less than Ni-32Co-20Cr-8Al-0.5Y, Ni-20Co20-Cr-8Al-0.5Y coating well.
3. the present invention adopts the method for arc ion plating to prepare the Ni-Co-Cr-Al-Y-Si-B coating, compares with EB-PVD, magnetron sputtering, has high ionization level, high-energy-density, high efficiency, less energy-consumption, advantage cheaply.
Embodiment
Below by example the present invention is described in further detail.
Embodiment 1
Base material adopts high-pressure turbine blade material nickel base superalloy DZ125, and specimen size is 15 * 15 * 2mm
3, coated component is Ni-32Co-20Cr-8Al-0.5Y-1Si-0.03B, Ni-32Co-20Cr-8Al-0.5Y and Ni-20Co-20Cr-8Al-0.5Y.Before the preparation coating, to the base material sample grind, cleaning and sandblast (200 order glass balls, wet shot) handle; Adopt homemade MIP-8-800 type multi-arc ion plating equipment deposited coatings, after the sample shove charge, the vacuum tightness of vacuum chamber is evacuated to 7 * 10
-3Pa feeds Ar gas, makes air pressure rise to 5 * 10
-2Pa adds-the high bias voltage of 900V, and specimen surface is carried out sputter clean, about 4 minutes, adopt the processing parameter deposited coatings of table 1 then, in the deposition process, sample rotates with the matrix platform, regulates depositing time (10～12 hours), obtains the coating that thickness is 40-50 μ m; Sample behind the deposited coatings 900 ℃ of following vacuum heat treatment, is incubated 5 hours, and heat-up rate is controlled at 7 ℃/min.
Table 1 embodiment 1 processing parameter
Vacuum tightness (Pa) 7 * 10
-3
Arc stream (A) 50
Arc voltage (V) 25
Pulsed bias (V)-150
Direct-current biasing (V)-200
Dutycycle (%) 30%
Depositing temperature (℃) 300-350
1000 ℃ of following oxidations are after 100 hours, and the oxidation weight gain of DZ125 alloy is 0.513mg/cm
2, and the oxidation weight gain of three kinds of coatings can play the effect that slows down oxidation rate all less than the DZ125 alloy.Wherein, the weightening finish of Ni-32Co-20Cr-8Al-0.5Y coating is 0.441mg/cm
2, the gain in weight of Ni-20Co-20Cr-8Al-0.5Y coating is 0.348mg/cm
2, and the weightening finish of Ni-32Co-20Cr-8Al-0.5Y-1Si-0.03B coating oxidation only is 0.245mg/cm
2, be 47% of DZ125 alloy gain in weight, 55% of Ni-32Co-20Cr-8Al-0.5Y coating, 70% of Ni-20Co-20Cr-8Al-0.5Y coating.As seen, the oxidation-resistance of Ni-32Co-20Cr-8Al-0.5Y-1Si-0.03B coating is better than Ni-32Co-20Cr-8Al-0.5Y, Ni-20Co-20Cr-8Al-0.5Y coating.
In the NiCoCrAlY coating, though the corrosion and heat resistant of Co is better than Ni, the price of Co is than Ni height, and from reducing cost and improving corrosion and heat resistant and take all factors into consideration, described coating Co content is controlled in the 28-35wt.% scope.Trace element Si can improve the adhesivity of oxide compound, reduces oxide growth rate; The B element can play the effect of strengthening crystal boundary, and the SiO of B and Si formation
2-B
2O
3Can improve SiO
2The antistripping ability, therefore described coating has been added micro-Si:0.9-1.1wt.%, B:0.02-0.04wt.%.
Embodiment 2
Base material adopts gas turbine blades material nickel base superalloy DSM11, and the specimen size of carrying out oxidation and corrosion experiment is 15 * 10 * 2mm
3, the sample that carries out the mechanical property experiment is the tensile test bar of d=5mm.Coated component is: Ni-32Co-20Cr-8Al-0.5Y-1Si-0.03B and Ni-20Co-20Cr-8Al-0.5Y.Before the preparation coating, to being of a size of 15 * 10 * 2mm
3Sample grind, cleaning and sandblast (200 order glass balls, wet shot) handle, and tensile test bar is only done clean; Adopt homemade MIP-8-800 type multi-arc ion plating equipment deposited coatings, after the sample shove charge, the vacuum tightness of vacuum chamber is evacuated to 4 * 10
-3Pa feeds Ar gas, makes air pressure rise to 6 * 10
-2Pa adds-the high bias voltage of 1000V, and specimen surface is carried out sputter clean, about 2 minutes, adopt the processing parameter deposited coatings of table 2 then, in the deposition process, sample rotates with the matrix platform, regulates depositing time (10～12 hours), obtains the coating that thickness is 40-50 μ m; Sample behind the deposited coatings is carried out vacuum heat treatment, be incubated 3 hours down at 950 ℃, heat-up rate is controlled at 8 ℃/min.
Table 2 embodiment 2 processing parameters
Vacuum tightness (Pa) 4 * 10
-3
Arc stream (A) 60
Arc voltage (V) 25
Pulsed bias (V)-900
Direct-current biasing (V)-150
Dutycycle (%) 10%
Depositing temperature (℃) 350-400
Under 1100 ℃, the DSM11 alloy oxidation oxidation weight loss occurred after 5 hours, and weightlessness comes across the Ni-20Co-20Cr-8Al-0.5Y coating equally after 40 hours, and oxidation weight loss is CrO
3The result of volatilization and spalling of oxide film comprehensive action.And the Ni-32Co-20Cr-8Al-0.5Y-1Si-0.03B coating remains the trend of slow weightening finish, and it only is 1.71mg/cm that oxidation was increased weight after 100 hours
2Under 1100 ℃, the oxidation-resistance of Ni-32Co-20Cr-8Al-0.5Y-1Si-0.03B coating is better than the Ni-20Co-20Cr-8Al-0.5Y coating.
The brine corrosion of soaking that sample carries out under 900 ℃ is tested, and etching reagent is 75wt.%Na
2SO
4+ 25wt.%K
2SO
4The result shows, the DSM11 alloy is obvious corrosion weightening finish trend, corrodes that gain in weight is 0.358mg/cm after 90 hours
2The Ni-20Co-20Cr-8Al-0.5Y coating phenomenon of corrosion weight loss occurred after 10 hours.And the surrosion of Ni-32Co-20Cr-8Al-0.5Y-1Si-0.03B coating is very little, corrodes after 90 hours, and gain in weight only is 0.063mg/cm
2, have excellent corrosion and heat resistant.
Table 3, table 4 are respectively the DSM11 alloy at room temperature that contains the Ni-32Co-20Cr-8Al-0.5Y-1Si-0.03B coating and stretch and high temperature endurance performance, as can be seen, the Ni32Co20Cr8Al0.5Y1Si0.03B coating does not influence the breaking tenacity of DSM11 alloy, and the creep rupture life under the 980 ℃/190MPa condition is far above technical indicator.
Table 3 contains Ni32Co20Cr8A10.5Y1Si0.03B and is coated with DSM11 alloy at room temperature tensile property
Sample σ
0.2(Mpa) σ
b(Mpa)
DSM11 alloy 1067.0 1258.0
The DSM11 1099.3 1254.3 that vertically contains coating
DSM11 alloy 896.0 943.0
The DSM11 927.0 1047.5 that laterally contains coating
Table 4 contain Ni32Co20Cr8Al0.5Y1Si0.03B coating DSM11 alloy enduring quality (980 ℃/190MPa)
Sample creep rupture life (hour) deformation rate (δ, %)
Technical indicator＞50-
The DSM11 alloy 98.0-212.0 18.2-40.0 that contains coating
Embodiment 3
Base material adopts gas turbine blades material nickel base superalloy M22, and the specimen size of carrying out oxidation experiment is 10 * 10 * 2mm
3, the sample that carries out the enduring quality experiment is the tensile test bar of d=5mm.Coated component is: Ni-32Co-20Cr-8Al-0.5Y-1Si-0.03B and Ni-32Co-20Cr-8Al-0.5Y.Before the preparation coating, to 10 * 10 * 2mm
3Sample grind, cleaning and sandblast (200 order glass balls, wet shot) handle, and tensile test bar is only done clean; Adopt homemade MIP-8-800 type multi-arc ion plating equipment deposited coatings, after the sample shove charge, the vacuum tightness of vacuum chamber is evacuated to 2 * 10
-3Pa feeds Ar gas, makes air pressure rise to 8 * 10
-2Pa adds-the high bias voltage of 800V, and specimen surface is carried out sputter clean, about 5 minutes, adopt the processing parameter deposited coatings of table 5 then, in the deposition process, sample rotates with the matrix platform, regulates depositing time (10～12 hours), obtains the coating that thickness is 40-50 μ m; Sample behind the deposited coatings is carried out vacuum heat treatment, be incubated 4 hours down at 900 ℃, heat-up rate is controlled at 6 ℃/min.
Table 5 embodiment 3 processing parameters
Processing parameter
Vacuum tightness (Pa) 2 * 10
-3
Arc stream (A) 70
Arc voltage (V) 20
Pulsed bias (V)-200
Direct-current biasing (V)-150
Dutycycle (%) 30%
Depositing temperature (℃) 300-350
900 ℃ of following oxidations are after 100 hours, and the oxidation weight gain of M22 alloy is 0.641mg/cm
2, the gain in weight of Ni-32Co-20Cr-8Al-0.5Y coating is 0.508mg/cm
2, and the weightening finish of Ni-32Co-20Cr-8Al-0.5Y-1Si-0.03B coating oxidation only is 0.430mg/cm
2, be 67% of M22 alloy gain in weight, 85% of Ni-20Co-20Cr-8Al-0.5Y coating.As seen, the Ni-32Co-20Cr-8Al-0.5Y-1Si-0.03B coating can effectively be slowed down the oxidation rate of M22 alloy, and its oxidation-resistance is better than the Ni-32Co-20Cr-8Al-0.5Y coating.
Table 6 is for containing the M22 alloy of Ni32Co20Cr8Al0.5Y1Si0.03B coating, the enduring quality under 900 ℃/130MPa condition, and its creep rupture life＞393 hour are far above technical indicator.
Table 6 contain Ni32Co20Cr8Al0.5Y1Si0.03B coating M22 alloy enduring quality (900 ℃/130MPa)
Sample creep rupture life (hour) deformation rate (δ, %)
M22 alloy＞50-
M22 alloy＞393.0 13.1-16.5 that contain coating
Embodiment 4
Base material adopts gas turbine blades material nickel base superalloy DSM11, and specimen size is 15 * 10 * 2mm
3Coated component is: Ni-30Co-20Cr-8Al-0.5Y-1.1Si-0.02B and Ni-20Co-20Cr-8Al-0.5Y.Difference from Example 2 is: Co content is 30wt.%, and Si content is 1.1wt.%, and B content is 0.02wt.%.
Before the preparation coating, to the base material sample grind, cleaning and sandblast (300 order glass balls, wet shot) handle; Adopt homemade MIP-8-800 type multi-arc ion plating equipment deposited coatings, after the sample shove charge, the vacuum tightness of vacuum chamber is evacuated to 4 * 10
-3Pa feeds Ar gas, makes air pressure rise to 6 * 10
-2Pa adds-the high bias voltage of 1000V, and specimen surface is carried out sputter clean, about 3 minutes, adopt the processing parameter deposited coatings of table 7 then, in the deposition process, sample rotates with the matrix platform, regulates depositing time (10～12 hours), obtains the coating that thickness is 40-50 μ m; Sample behind the deposited coatings is carried out vacuum heat treatment, be incubated 3 hours down at 950 ℃, heat-up rate is controlled at 8 ℃/min.
Table 7 embodiment 4 processing parameters
Vacuum tightness (Pa) 4 * 10
-3
Arc stream (A) 60
Arc voltage (V) 25
Pulsed bias (V)-900
Direct-current biasing (V)-150
Dutycycle (%) 10%
Depositing temperature (℃) 350-400
The brine corrosion of soaking that sample carries out under 900 ℃ is tested, and etching reagent is 75wt.%Na
2SO
4+ 25wt.%K
2SO
4The result shows, the DSM11 alloy is obvious corrosion weightening finish trend, corrodes that gain in weight is 0.358mg/cm after 90 hours
2The Ni-20Co-20Cr-8Al-0.5Y coating phenomenon of corrosion weight loss occurred after 10 hours.And the surrosion of Ni-32Co-20Cr-8Al-0.5Y-1Si-0.03B coating is very little, corrodes after 90 hours, and gain in weight only is 0.073mg/cm
2, have excellent corrosion and heat resistant.
Claims (6)
1. NiCoCrAlYSiB corrosion and heat resistant protective coating, it is characterized in that: by weight percentage, constituent content is Co:28～35wt.%, Cr:17～23wt.%, Al:5～12wt.%, Y:0.1～0.6wt.%, Si:0.9～1.1wt.%, B:0.02～0.04wt.%, surplus is Ni.
2. the preparation method by the described NiCoCrAlYSiB corrosion and heat resistant of claim 1 protective coating is characterized in that: adopt arc ion plating (aip), be specially: 1) sample is carried out pre-treatment; 2) again sample is carried out sputter clean, about 2～5 minutes; 3) depositing treatment; 4) sample behind the deposited coatings is carried out vacuum heat treatment, be incubated 3～5 hours down at 900～950 ℃, heat-up rate is controlled at 6～8 ℃/min.
3. press the preparation method of the described NiCoCrAlYSiB corrosion and heat resistant of claim 2 protective coating, it is characterized in that: the described pre-treatment of step 1), to the sample that is used for oxidation and corrosion experiment grind, cleaning and sandblast pretreatment, wherein 200～300 order glass balls, wet shot are adopted in sandblasting; The sample that is used for the mechanical property experiment is only done clean.
4. by the preparation method of the described NiCoCrAlYSiB corrosion and heat resistant of claim 2 protective coating, it is characterized in that: described sputter clean after the sample shove charge, is evacuated to 2 * 10 with the vacuum tightness of vacuum chamber
-3～7 * 10
-3Behind the Pa, feed Ar gas, make air pressure rise to 5 * 10
-2～8 * 10
-2Pa adds-800V～-1000 high bias voltage, specimen surface is carried out sputter clean, about 2～5 minutes.
5. press the preparation method of the described NiCoCrAlYSiB corrosion and heat resistant of claim 2 protective coating, it is characterized in that: described depositing treatment working parameter is as follows: arc stream: 50～70A, arc voltage: 20～25V, pulsed bias :-150～-900V, direct-current biasing :-150～-200V, dutycycle: 10～30%, depositing temperature: 300～400 ℃.
6. by the preparation method of the described NiCoCrAlYSiB corrosion and heat resistant of claim 5 protective coating, it is characterized in that: the thickness of described coating is 40-50 μ m.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 03111363 CN1215129C (en) | 2003-04-04 | 2003-04-04 | Ni Co Cr Al Y Si B coating layer capable of resisting thermal corrosion and its preparation method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 03111363 CN1215129C (en) | 2003-04-04 | 2003-04-04 | Ni Co Cr Al Y Si B coating layer capable of resisting thermal corrosion and its preparation method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1536033A true CN1536033A (en) | 2004-10-13 |
| CN1215129C CN1215129C (en) | 2005-08-17 |
Family
ID=34319730
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 03111363 Expired - Fee Related CN1215129C (en) | 2003-04-04 | 2003-04-04 | Ni Co Cr Al Y Si B coating layer capable of resisting thermal corrosion and its preparation method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN1215129C (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1818419A1 (en) * | 2006-01-16 | 2007-08-15 | Siemens Aktiengesellschaft | Alloy, protective layer and component |
| CN102094163A (en) * | 2011-02-25 | 2011-06-15 | 中国科学院金属研究所 | CoNiCrAlY corrosion-resistant thermal spraying alloy powder and preparation method thereof |
| CN102115836B (en) * | 2009-12-30 | 2013-04-17 | 沈阳天贺新材料开发有限公司 | High-temperature protective coating of MCrAlY alloy system and preparation method |
| CN103770397A (en) * | 2012-10-26 | 2014-05-07 | 南昌航空大学 | A (Ti, al, si) N-Mo (S, N)2-Ag/TiAlN nano multilayer coating |
| CN105296941A (en) * | 2015-11-23 | 2016-02-03 | 沈阳黎明航空发动机(集团)有限责任公司 | Preparing of nickel base tube-shaped cathode target material and application in vacuum electric arc plating coating and plating |
| CN106148907A (en) * | 2015-04-27 | 2016-11-23 | 中国科学院金属研究所 | Do not affect high temperature resistance protective coating and the preparation thereof of high-temperature alloy base mechanics performance |
| CN107177814A (en) * | 2017-05-08 | 2017-09-19 | 哈电集团（秦皇岛）重型装备有限公司 | The anticorrosion process of temperature gas cooled reactor steam generator T22 heat exchanger tubes |
| CN108290253A (en) * | 2015-10-29 | 2018-07-17 | 赛峰航空器发动机 | The method for producing the seal member with the ontology for being made and being coated with by the superalloy of boracic |
-
2003
- 2003-04-04 CN CN 03111363 patent/CN1215129C/en not_active Expired - Fee Related
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1818419A1 (en) * | 2006-01-16 | 2007-08-15 | Siemens Aktiengesellschaft | Alloy, protective layer and component |
| CN102115836B (en) * | 2009-12-30 | 2013-04-17 | 沈阳天贺新材料开发有限公司 | High-temperature protective coating of MCrAlY alloy system and preparation method |
| CN102094163A (en) * | 2011-02-25 | 2011-06-15 | 中国科学院金属研究所 | CoNiCrAlY corrosion-resistant thermal spraying alloy powder and preparation method thereof |
| CN102094163B (en) * | 2011-02-25 | 2012-09-05 | 中国科学院金属研究所 | CoNiCrAlY corrosion-resistant thermal spraying alloy powder and preparation method thereof |
| CN103770397A (en) * | 2012-10-26 | 2014-05-07 | 南昌航空大学 | A (Ti, al, si) N-Mo (S, N)2-Ag/TiAlN nano multilayer coating |
| CN103770397B (en) * | 2012-10-26 | 2016-04-27 | 南昌航空大学 | A kind of (Ti, Al, Si) N-Mo (S, N) 2-Ag/TiAlN nano laminated coating |
| CN106148907A (en) * | 2015-04-27 | 2016-11-23 | 中国科学院金属研究所 | Do not affect high temperature resistance protective coating and the preparation thereof of high-temperature alloy base mechanics performance |
| CN108290253A (en) * | 2015-10-29 | 2018-07-17 | 赛峰航空器发动机 | The method for producing the seal member with the ontology for being made and being coated with by the superalloy of boracic |
| CN105296941A (en) * | 2015-11-23 | 2016-02-03 | 沈阳黎明航空发动机(集团)有限责任公司 | Preparing of nickel base tube-shaped cathode target material and application in vacuum electric arc plating coating and plating |
| CN105296941B (en) * | 2015-11-23 | 2017-12-19 | 沈阳黎明航空发动机(集团)有限责任公司 | The preparation and the application in vacuum arc plating coating of a kind of Ni-based sleeve cathode target |
| CN107177814A (en) * | 2017-05-08 | 2017-09-19 | 哈电集团（秦皇岛）重型装备有限公司 | The anticorrosion process of temperature gas cooled reactor steam generator T22 heat exchanger tubes |
Also Published As
| Publication number | Publication date |
|---|---|
| CN1215129C (en) | 2005-08-17 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN112064024A (en) | Diffusion-resistant high-entropy alloy coating material, high-temperature-resistant coating material, and preparation method and application thereof | |
| CN107130212B (en) | High-hardness wear-resistant thermal-shock-resistant thick tantalum coating and preparation method thereof | |
| CN1215129C (en) | Ni Co Cr Al Y Si B coating layer capable of resisting thermal corrosion and its preparation method | |
| JP5618538B2 (en) | Multilayer nitride-containing coating | |
| US4451431A (en) | Molybdenum-containing high temperature coatings for nickel- and cobalt-based superalloys | |
| CN101050515A (en) | Method for raising service life of coat layer of heat barrier by surface modification of metal binder course | |
| CN1259453C (en) | Prepn of heat shock resisting heat barrier coating | |
| CN110983257B (en) | Surface treatment method for improving corrosion resistance and anti-icing performance of titanium alloy surface | |
| CN101294284A (en) | Ablation-resistant fatigue-resistant plasma surface recombination reinforcing method | |
| CN101310969A (en) | Aluminum/aluminum oxide/Ni-base superalloy composite coating for titanium-aluminum alloy and preparation method thereof | |
| CN112663001B (en) | Titanium alloy blade protective coating and preparation method thereof | |
| CN113651619A (en) | High-entropy ceramic powder for marine diesel engine, application and application method | |
| CN107385379B (en) | A kind of preparation method of blast furnace energy recovery turbine blade surface corrosion-proof wear coating | |
| CN1219001C (en) | Oxidation-inhibited thermal barrier coating and preparing method thereof | |
| CN117107311A (en) | Pt modified blade tip protective coating and preparation method thereof | |
| CN114632949B (en) | Additive manufacturing metal part surface anticorrosion and antifouling composite treatment method | |
| CN1361308A (en) | Ionic TiALN coating for blade of air compressor in naval aircraft engine | |
| CN115679258A (en) | High-hardness wear-resistant CrAlBN-based composite coating and preparation method thereof | |
| CN1274879C (en) | Oceanic atmosphere corrosion resistant thermal barrier coating | |
| CN111254395B (en) | High-temperature-resistant corrosion-resistant multilayer composite film and preparation method thereof | |
| CN1250765C (en) | Thermal barrier coating suitable for nickel-based high-temperature alloy with high Mo content | |
| JP3281842B2 (en) | Corrosion resistant surface treatment method for gas turbine blade and its moving and stationary blade | |
| JP4764868B2 (en) | Compressor blades and gas turbine for thermal power generation | |
| CN112176298A (en) | High-wear-resistance compound coating and preparation method thereof | |
| JP4167465B2 (en) | High temperature oxidation resistant coated member and method for producing the same |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C19 | Lapse of patent right due to non-payment of the annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |