CN104561881A - Preparation method of high-temperature abradable seal coating - Google Patents
Preparation method of high-temperature abradable seal coating Download PDFInfo
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- CN104561881A CN104561881A CN201410820069.9A CN201410820069A CN104561881A CN 104561881 A CN104561881 A CN 104561881A CN 201410820069 A CN201410820069 A CN 201410820069A CN 104561881 A CN104561881 A CN 104561881A
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- 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
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- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention provides a preparation method of a high-temperature abradable seal coating. The preparation method comprises the following steps: preparing a high-temperature brazing material layer by a supersonic-flame spraying method; preparing a transition layer on the surface of the high-temperature brazing material layer, wherein the transition layer is obtained by performing high-energy ball milling on the high-temperature brazing material and an MCrAlY spraying material, which respectively account for 50% of the total transition layer in weight, and the transition layer is prepared under the following vacuum conditions: the temperature is 1000 DEG C-1150 DEG C, and the temperature is kept for 12 min-17 min; preparing an MCrAlY compact layer on the surface of the transition layer; preparing a porous abradable seal coating containing a pore forming agent on the surface of the compact layer, wherein the porous abradable seal coating containing the pore forming agent comprises the following raw materials in percentage by weight: 2wt%-5wt% of the pore forming agent and the MCrAlY spraying material; removing the pore forming agent, and forming a porous abradable seal coating so as to obtain the high-temperature abradable seal coating. Through the adoption of the preparation method disclosed by the invention, the bonding strength of the abradable seal coating and a base body can be enhanced, the using efficiency of brazing materials can be improved, and the cohesion strength of the abradable seal coating can be enhanced.
Description
Technical field
The present invention relates to a kind of preparation method of seal coating, particularly a kind of preparation method of high-temperature abradable seal coating, belong to coat preparing technology field.
Background technology
A new generation's aircraft engine requires that it has the features such as high-performance, high reliability, long lifetime, improves turbine intake temperature and control turbine blade and casing gap and can improve motor efficiency, reduce fuel oil consumption, increase thrust-weight ratio.The ratio of rotor tip-clearance and rotor blade length often increases by 1%, and turbine efficiency loss just increases 1-3%, and therefore, it is one of important channel of improving motor efficiency and performance that gas circuit is obturaged.
High temperature seal coating technology belongs to aircraft engine key manufacture, it is the internal surface at engine stator, suitable abradable coating is prepared near rotor side, when engine rotor extends by thermal load and centrifugal action, scraping abradable coating, form the dynamic seal being close to and being closely connected, reduce the space between engine rotor and stator, improve the efficiency of engine.The abradable seal coating of current high temperature position mainly adopts following scheme: vacuum plasma spray coating solder enhancement layer+air plasma spraying solder enhancement layer+air plasma spraying is obturaged layer, vacuum plasma spray coating enhancement layer is prepared at matrix surface, vacuum plasma spray coating enhancement layer contains solder and strengthens point, air plasma spraying solder enhancement layer is prepared on vacuum plasma spray coating enhancement layer surface, prepare air plasma spraying to obturage layer on air plasma spraying solder enhancement layer surface, air plasma spraying obturages layer inside containing hole, engine is protected by the abradable seal coating of above-mentioned high temperature position.
But along with the raising of inlet temperature before turbine, engine behaviour becomes more severe, original abradable seal coating and substrate combinating strength are not high, thermal characteristics is not mated, and easily fall block and peel off, can not meet the design requirements of advanced aero engine.The working temperature of high-temperature abradable seal coating is usually more than 1000 DEG C, also to bear high-speed fuel gas to wash away and the tip scraping of turbine blade of high speed rotating simultaneously, this just requires that high temperature seal coating has higher thermal shock resistance, antioxidant property, bonding strength, abradability energy and anti-airflow scouring performance, and its quality directly affects the power of engine, thrust, efficiency and reliability.
In sum, the seal coating providing a kind of thermal shock resistance, antioxidant property, bonding strength, abradability energy and anti-airflow scouring performance strong is this area problem demanding prompt solution.
Summary of the invention
In order to solve the problems of the technologies described above, the object of the present invention is to provide a kind of high temperature seal coating, this high temperature seal coating can improve the bonding strength of abradable seal coating and matrix, improve handiness and the production efficiency of abradable seal coating complete processing, improve the service efficiency of solder, improve the cohesive strength etc. of abradable seal coating.
In order to achieve the above object, the invention provides a kind of preparation method of high-temperature abradable seal coating, this preparation method comprises the following steps:
The high temperature brazing bed of material is prepared at matrix surface by supersonic flame spraying method;
Transition layer is prepared by supersonic flame spraying method on high temperature brazing bed of material surface, wherein, described transition layer obtains after the mixing of the MCrAlY spray material of the high-temperature brazing material of transition layer total content 50wt% and transition layer total content 50wt% through high-energy ball milling process, and the M in described MCrAlY spray material comprises W metal and/or metal Co;
Under vacuum, temperature are the condition of 1000 DEG C-1150 DEG C, insulation 12min-17min;
MCrAlY tight zone is prepared by supersonic flame spraying method on transition layer surface;
On MCrAlY tight zone surface by the porous abradable seal coating of supersonic flame spraying method preparation containing pore-forming material, wherein, the raw material composition of the porous abradable seal coating containing pore-forming material comprises pore-forming material and MCrAlY spray material, wherein, in the raw material total amount of the porous abradable seal coating containing pore-forming material for 100wt%, described Content of Pore-forming Agents is 2wt%-5wt%;
Remove containing the pore-forming material in the porous abradable seal coating of pore-forming material, form porous abradable seal coating, obtained described high-temperature abradable seal coating.
In the preparation method of high-temperature abradable seal coating provided by the invention, preferably, the thickness of the high temperature brazing bed of material of employing is 0.1mm-0.2mm.
In the preparation method of high-temperature abradable seal coating provided by the invention, preferably, the porosity of the MCrAlY tight zone of employing is 3%-5%.
In the preparation method of high-temperature abradable seal coating provided by the invention, preferably, the thickness of the MCrAlY tight zone of employing is 0.2mm-0.3mm.
In the preparation method of high-temperature abradable seal coating provided by the invention, preferably, the high-temperature brazing material preparing the employing of the high temperature brazing bed of material comprises nickel-base high-temperature braze or cobalt-based high-temperature braze.
In the preparation method of high-temperature abradable seal coating provided by the invention, preferably, the high-temperature brazing material of employing comprises BNi-1 braze or QFCo-01 braze.
In the preparation method of high-temperature abradable seal coating provided by the invention, preferably, the particle diameter of the high-temperature brazing material of employing is 5 μm-60 μm.
In the preparation method of high-temperature abradable seal coating provided by the invention, preferably, the particle diameter of the MCrAlY spray material of employing is 5 μm-40 μm.
In the preparation method of high-temperature abradable seal coating provided by the invention, preferably, the porosity of the porous abradable seal coating containing pore-forming material of employing is 35%-50%.
In the preparation method of high-temperature abradable seal coating provided by the invention, preferably, the thickness of the porous abradable seal coating containing pore-forming material of employing is 2mm-3mm.
In the preparation method of high-temperature abradable seal coating provided by the invention, preferably, the particle diameter of the pore-forming material of employing is 50 μm-100 μm; More preferably, the pore-forming material of employing comprises the polymkeric substance such as poly phenyl ester.
In the preparation method of high-temperature abradable seal coating provided by the invention, preferably, adopt chamber type electric resistance furnace to remove pore-forming material, removing temperature is 480 DEG C-530 DEG C, speed of cooling is 15 DEG C/and min-20 DEG C/min.
Preparation method's tool of high-temperature abradable seal coating provided by the invention has the following advantages:
The pure high temperature brazing bed of material used in preparation method of the present invention can improve transition layer and matrix in conjunction with effect, by high temperature brazing process can with matrix formed 100% metallurgical binding effect, avoid transition layer to ftracture the inefficacy caused;
The supersonic flame spraying method used in preparation method provided by the invention is compared with plasma spraying method, in supersonic flame spraying method, spraying particle has lower temperature and speed faster, can avoid using the vacuum chamber adopted for reducing coating oxidation, add technological flexibility, improve the production efficiency of coating; Also because particle has higher speed in supersonic flame spraying method, make to have better in conjunction with effect between the particle and distortion particle of porous coating, improve the cohesive strength of coating;
In the preparation process in accordance with the present invention by ball milling coating technology, high-temperature brazing material is made evenly to be coated on MCrAlY spray material powder surface, take full advantage of the high-temperature brazing material in mixolimnion, particle is combined more firm, avoid the coating cracking caused because high-temperature brazing material mechanically mixing is uneven and lost efficacy.
Accompanying drawing explanation
Fig. 1 is the structural representation of the high-temperature abradable seal coating of embodiment 1;
Fig. 2 is the SEM scintigram in the cross section of the high-temperature abradable seal coating of embodiment 1;
Fig. 3 is the structural representation of the matrix in embodiment 1 antithesis stretching method.
Main Reference nomenclature:
Porous abradable seal coating 6 antithesis universal stretching head 7 high-temperature abradable seal coating 8 glue line of the 1 nickel base superalloy 2 high temperature brazing bed of material 3 transition layer 4 tight zone 5 containing pore-forming material
Embodiment
In order to there be understanding clearly to technical characteristic of the present invention, object and beneficial effect, existing following detailed description is carried out to technical scheme of the present invention, but can not be interpreted as to of the present invention can the restriction of practical range.
Embodiment 1
Present embodiments provide a kind of preparation method of high-temperature abradable seal coating, this preparation method specifically comprises the following steps:
Particle diameter is adopted to be the NiCoCrAlY spray material of 10 μm-40 μm and particle diameter to be the BNi-1 high-temperature brazing material of 30 μm-80 μm to prepare high-temperature abradable seal coating;
The preparation of the high temperature brazing bed of material 2: BNi-1 high-temperature brazing material (can use more than 1000 DEG C) is sprayed to nickel base superalloy 1 surface by hypersonic flame spraying (WoKajet440 spray gun) method, prepare the high temperature brazing bed of material 2 that thickness is about 0.15mm, wherein, the concrete technology parameter of supersonic flame spraying method is: oxygen, 854 liters/min; Kerosene, 19 ls/h; Powder sending quantity, 42 gram/minute; Carrier gas, 10 liters/min; Spray distance, 280mm; The temperature of nickel base superalloy 1, is less than 120 DEG C;
The preparation of transition layer 3: BNi-1 high-temperature brazing material and NiCoCrAlY spray material powder are carried out mechanically mixing by weight for 1:1, put into ball grinder (having 100 Ф to be the large ball of 10mm and 450 Ф is the bead of 6mm), after ball-milling processing, spray to the high temperature brazing bed of material 2 surface by supersonic flame spraying method, prepare the transition layer 3 that thickness is about 0.15mm;
Wherein, the concrete technology parameter of ball-milling processing is as follows: ball milling parameter: 40Hz, 400 revs/min, rotates forward 4 hours, reverses 4 hours, takes out powder after cooling;
The processing parameter of supersonic flame spraying method is: oxygen, 870 liters/min; Kerosene, 20 ls/h; Powder sending quantity, 45 gram/minute; Carrier gas, 10 liters/min; Spray distance, 280mm; The temperature of nickel base superalloy 1, is less than 120 DEG C;
Furnace temperature is be incubated 12min-17min at 1000 DEG C-1150 DEG C under vacuum;
The preparation of tight zone 4 (porosity is 3%-5%): NiCoCrAlY spray material powder is sprayed to transition layer 3 surface by supersonic flame spraying method, prepare the tight zone 4 that thickness is about 0.25mm, wherein, the design parameter of supersonic flame spraying method is as follows: oxygen, 876 liters/min; Kerosene, 23 ls/h; Powder sending quantity, 45 gram/minute; Carrier gas, 10 liters/min; Spray distance, 280mm; The temperature of nickel base superalloy 1, is less than 150 DEG C;
Prepared by the porous abradable seal coating 5 containing pore-forming material: the polyester pore-forming material being 1:0.1 by NiCoCrAlY spray material powder and weight ratio mixes, supersonic flame spraying method is adopted to spray to tight zone 4 surface, form the porous abradable seal coating 5 (porosity is 35%-50%) containing pore-forming material of the thick 2.6mm of being about, wherein, the design parameter of supersonic flame spraying method is as follows: oxygen, 876 liters/min; Kerosene, 23 ls/h; Powder sending quantity, 40 gram/minute; Carrier gas, 10 liters/min; Spray distance, 280mm; Substrate temperature, is less than 150 DEG C;
Chamber type electric resistance furnace is adopted to remove containing the pore-forming material in the porous abradable seal coating 5 of pore-forming material, wherein, stove is chilled to 500 DEG C, speed of cooling is 15 DEG C/min-20 DEG C/min, form porous abradable seal coating, obtain the high-temperature abradable seal coating that total thickness is about 3.15mm, as shown in Figure 1, the SEM scintigram in its cross section as shown in Figure 2 for the structure of this high-temperature abradable seal coating.
The nickel base superalloy 1 of high-temperature abradable seal coating 7 is had to carry out performance test by antithesis stretching method to the preparation of the present embodiment.
Specifically comprise the following steps: have the nickel base superalloy 1 of high-temperature abradable seal coating 7 to carry out the moderate E-7 asphalt mixtures modified by epoxy resin ester gum of uniform application thickness on the unsalted surface after blast to preparation, form glue line 8, nickel base superalloy 1 upper and lower surface of high-temperature abradable seal coating 7 is had to dock with preparation respectively universal for antithesis stretching head 6, as shown in Figure 3, ensure centering, suitable pressurization 3-5 minute, sent into baking oven, 100 DEG C of insulations 3 hours.Adopt Universal hydraulic material-testing machine to be pulled by two stretching heads subsequently, calculate the bonding strength obtaining coating.
The bonding strength of conventional coatings is: 5.12MPa, 5.23MPa, 4.96MPa, 5.07MPa, 4.98MPa, and mean value is 5.072MPa; The bonding strength of the coating that preparation method of the present invention obtains is: 6.31MPa, 6.50MPa, 6.44MPa, 6.78MPa, 5.97MPa, mean value is 6.40MPa, and bonding strength improves 26.2%, and this illustrates that the cohesive strength of the high-temperature abradable seal coating that preparation method of the present invention prepares obtains effective raising.
Claims (10)
1. a preparation method for high-temperature abradable seal coating, this preparation method comprises the following steps:
The high temperature brazing bed of material is prepared at matrix surface by supersonic flame spraying method;
Transition layer is prepared by supersonic flame spraying method on high temperature brazing bed of material surface, wherein, described transition layer obtains after the mixing of the MCrAlY spray material of the high-temperature brazing material of transition layer total content 50wt% and transition layer total content 50wt% through high-energy ball milling process, and the M in described MCrAlY spray material is W metal and/or metal Co;
12min-17min is incubated at being 1000 DEG C-1150 DEG C in vacuum, temperature;
MCrAlY tight zone is prepared by supersonic flame spraying method on transition layer surface;
On MCrAlY tight zone surface by the porous abradable seal coating of supersonic flame spraying method preparation containing pore-forming material, wherein, the raw material composition of the porous abradable seal coating containing pore-forming material comprises pore-forming material and MCrAlY spray material, wherein, in the raw material total amount of the porous abradable seal coating containing pore-forming material for 100wt%, described Content of Pore-forming Agents is 2wt%-5wt%;
Remove containing the pore-forming material in the porous abradable seal coating of pore-forming material, form porous abradable seal coating, obtained described high-temperature abradable seal coating.
2. preparation method according to claim 1, wherein, the thickness of the described high temperature brazing bed of material is 0.1mm-0.2mm.
3. preparation method according to claim 1, wherein, the high-temperature brazing material that the preparation high temperature brazing bed of material adopts comprises nickel-base high-temperature braze or cobalt-based high-temperature braze.
4. preparation method according to claim 3, wherein, described high-temperature brazing material comprises BNi-1 braze or QFCo-01 braze.
5. the preparation method according to claim 3 or 4, wherein, the particle diameter of described high-temperature brazing material is 5 μm-60 μm.
6. preparation method according to claim 1, wherein, the porosity of described MCrAlY tight zone is 3%-5%; The thickness of described MCrAlY tight zone is 0.2mm-0.3mm.
7. preparation method according to claim 1, wherein, the particle diameter of described MCrAlY spray material is 5 μm-40 μm.
8. preparation method according to claim 1, wherein, the porosity of the described porous abradable seal coating containing pore-forming material is 35%-50%; The thickness of the porous abradable seal coating containing pore-forming material is 2mm-3mm.
9. preparation method according to claim 1, wherein, the particle diameter of described pore-forming material is 50 μm-100 μm; Preferably, described pore-forming material comprises poly phenyl ester.
10. preparation method according to claim 1, wherein, adopt chamber type electric resistance furnace to remove pore-forming material, removing temperature is 480 DEG C-530 DEG C, speed of cooling is 15 DEG C/min-20 DEG C/min.
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| CN104894505A (en) * | 2015-06-15 | 2015-09-09 | 中国南方航空工业(集团)有限公司 | Vacuum plasma spraying forming method for ultra-thick coating |
| EP3255172A1 (en) * | 2016-05-27 | 2017-12-13 | General Electric Company | Thermally dissipative article and method of forming a thermally dissipative article |
| CN107699840A (en) * | 2017-10-25 | 2018-02-16 | 河北工业大学 | The preparation method of porous zirconia thermal barrier coating |
| CN108179371A (en) * | 2017-12-25 | 2018-06-19 | 中国航发动力股份有限公司 | A kind of high-temperature abradable seal coating and preparation method thereof |
| CN110527940A (en) * | 2019-10-16 | 2019-12-03 | 北京矿冶科技集团有限公司 | Porous MCrAlY abradable coating of high bond strength resistance to high temperature oxidation and preparation method thereof |
| CN114136881A (en) * | 2021-11-29 | 2022-03-04 | 胜科纳米(苏州)股份有限公司 | Method for testing metal packaging bonding force of capacitive square fingerprint sensor |
| CN114774830A (en) * | 2022-06-20 | 2022-07-22 | 矿冶科技集团有限公司 | Multifunctional coating, preparation method thereof and power equipment |
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Effective date of registration: 20190612 Address after: 100024 North East military villa, eight Li bridge, Chaoyang District, Beijing Patentee after: China Institute of Aeronautical Manufacturing Technology Address before: 100024 North East military villa, eight Li bridge, Chaoyang District, Beijing Patentee before: Beijing Aviation Manufacturing Engineering Institute of China Aviation Industry Group Company |
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