CN110747428B - Titanium alloy surface flame-retardant and sealing integrated coating and preparation method and application thereof - Google Patents
Titanium alloy surface flame-retardant and sealing integrated coating and preparation method and application thereof Download PDFInfo
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- 239000011248 coating agent Substances 0.000 title claims abstract description 64
- 238000000576 coating method Methods 0.000 title claims abstract description 64
- 229910001069 Ti alloy Inorganic materials 0.000 title claims abstract description 46
- RNFJDJUURJAICM-UHFFFAOYSA-N 2,2,4,4,6,6-hexaphenoxy-1,3,5-triaza-2$l^{5},4$l^{5},6$l^{5}-triphosphacyclohexa-1,3,5-triene Chemical compound N=1P(OC=2C=CC=CC=2)(OC=2C=CC=CC=2)=NP(OC=2C=CC=CC=2)(OC=2C=CC=CC=2)=NP=1(OC=1C=CC=CC=1)OC1=CC=CC=C1 RNFJDJUURJAICM-UHFFFAOYSA-N 0.000 title claims abstract description 38
- 239000003063 flame retardant Substances 0.000 title claims abstract description 38
- 238000007789 sealing Methods 0.000 title claims abstract description 23
- 238000002360 preparation method Methods 0.000 title claims abstract description 14
- 239000000463 material Substances 0.000 claims abstract description 37
- 229910000278 bentonite Inorganic materials 0.000 claims abstract description 20
- 239000000440 bentonite Substances 0.000 claims abstract description 20
- 229910000808 amorphous metal alloy Inorganic materials 0.000 claims abstract description 10
- 238000004381 surface treatment Methods 0.000 claims abstract description 6
- 238000005507 spraying Methods 0.000 claims description 37
- 239000000843 powder Substances 0.000 claims description 26
- 238000005488 sandblasting Methods 0.000 claims description 15
- 238000010285 flame spraying Methods 0.000 claims description 14
- PXHVJJICTQNCMI-UHFFFAOYSA-N nickel Substances [Ni] PXHVJJICTQNCMI-UHFFFAOYSA-N 0.000 claims description 11
- 229910018487 Ni—Cr Inorganic materials 0.000 claims description 10
- VNNRSPGTAMTISX-UHFFFAOYSA-N chromium nickel Chemical compound [Cr].[Ni] VNNRSPGTAMTISX-UHFFFAOYSA-N 0.000 claims description 10
- 238000000034 method Methods 0.000 claims description 9
- 238000010288 cold spraying Methods 0.000 claims description 8
- QVGXLLKOCUKJST-UHFFFAOYSA-N atomic oxygen Chemical compound [O] QVGXLLKOCUKJST-UHFFFAOYSA-N 0.000 claims description 7
- 239000001301 oxygen Substances 0.000 claims description 7
- 229910052760 oxygen Inorganic materials 0.000 claims description 7
- 239000010936 titanium Substances 0.000 claims description 7
- 238000005498 polishing Methods 0.000 claims description 6
- 239000004576 sand Substances 0.000 claims description 6
- 239000011651 chromium Substances 0.000 claims description 5
- 239000000758 substrate Substances 0.000 claims description 5
- HSFWRNGVRCDJHI-UHFFFAOYSA-N alpha-acetylene Natural products C#C HSFWRNGVRCDJHI-UHFFFAOYSA-N 0.000 claims description 4
- 229910052782 aluminium Inorganic materials 0.000 claims description 4
- SVPXDRXYRYOSEX-UHFFFAOYSA-N bentoquatam Chemical compound O.O=[Si]=O.O=[Al]O[Al]=O SVPXDRXYRYOSEX-UHFFFAOYSA-N 0.000 claims description 4
- 125000002534 ethynyl group Chemical group [H]C#C* 0.000 claims description 4
- JEIPFZHSYJVQDO-UHFFFAOYSA-N iron(III) oxide Inorganic materials O=[Fe]O[Fe]=O JEIPFZHSYJVQDO-UHFFFAOYSA-N 0.000 claims description 4
- 229910052759 nickel Inorganic materials 0.000 claims description 4
- 239000012159 carrier gas Substances 0.000 claims description 3
- 239000003350 kerosene Substances 0.000 claims description 3
- 244000137852 Petrea volubilis Species 0.000 claims description 2
- TWNQGVIAIRXVLR-UHFFFAOYSA-N oxo(oxoalumanyloxy)alumane Chemical compound O=[Al]O[Al]=O TWNQGVIAIRXVLR-UHFFFAOYSA-N 0.000 claims 1
- 239000010410 layer Substances 0.000 abstract description 25
- 239000002344 surface layer Substances 0.000 abstract description 5
- PMTRSEDNJGMXLN-UHFFFAOYSA-N titanium zirconium Chemical compound [Ti].[Zr] PMTRSEDNJGMXLN-UHFFFAOYSA-N 0.000 abstract description 3
- 238000012423 maintenance Methods 0.000 abstract description 2
- 238000004519 manufacturing process Methods 0.000 abstract description 2
- PNEYBMLMFCGWSK-UHFFFAOYSA-N aluminium oxide Inorganic materials [O-2].[O-2].[O-2].[Al+3].[Al+3] PNEYBMLMFCGWSK-UHFFFAOYSA-N 0.000 description 3
- 230000003647 oxidation Effects 0.000 description 3
- 238000007254 oxidation reaction Methods 0.000 description 3
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 description 1
- LNSPFAOULBTYBI-UHFFFAOYSA-N [O].C#C Chemical group [O].C#C LNSPFAOULBTYBI-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 229910052804 chromium Inorganic materials 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 238000005260 corrosion Methods 0.000 description 1
- 230000007797 corrosion Effects 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 239000000428 dust Substances 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 238000007750 plasma spraying Methods 0.000 description 1
- 230000002269 spontaneous effect Effects 0.000 description 1
- 230000003746 surface roughness Effects 0.000 description 1
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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
- C23C4/12—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
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22C—ALLOYS
- C22C45/00—Amorphous alloys
- C22C45/10—Amorphous alloys with molybdenum, tungsten, niobium, tantalum, titanium, or zirconium or Hf as the major constituent
-
- 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
- C23C4/02—Pretreatment of the material to be coated, e.g. for coating on selected surface areas
-
- 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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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
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Abstract
The invention discloses a titanium alloy surface flame-retardant sealing integrated coating and a preparation method and application thereof. The preparation method comprises the following steps: (1) surface treatment of the titanium alloy base material; (2) preheating the titanium alloy base material; (3) preparing a flame-retardant layer coating; (4) and (4) preparing the abradable seal coating. The invention uses the flame-retardant layer of the titanium-zirconium amorphous alloy as the bonding layer, cancels the original bonding layer, adopts the nickel-chromium-aluminum-bentonite as the abradable sealing surface layer, and has the functions of protecting the blade and the casing, simultaneously reducing the porosity between the blades and the casing, and improving the heat efficiency, thereby reducing the manufacturing cost and the maintenance cost.
Description
Technical Field
The invention relates to the technical field of titanium alloy surface treatment. In particular to a titanium alloy surface flame-retardant sealing integrated coating and a preparation method and application thereof.
Background
The titanium alloy has the characteristics of low density, high strength, excellent heat resistance and excellent corrosion resistance, and is widely applied to the fields of aerospace and the like. The casing, the rotor blade and the like of the aircraft engine compressor are made of titanium alloy. However, as engine performance continues to increase, the temperature of the compressor case also continues to increase, and the increase in ambient temperature of the equipment presents challenges to the materials themselves. The increase in temperature within the casing is also increasingly significant with respect to the expansion of the blade material. According to the data, in 1977-1988, the United states and the Soviet Union have the problem that multiple high-pressure compressor blades are broken and clamped in a casing, so that the titanium alloy is spontaneously combusted, and an engine accident is caused. In addition, due to friction between the atmospheric dust and the blades of the casing, instantaneous local temperature is overhigh, and spontaneous combustion of the titanium alloy is also caused. It was earlier proposed to increase the distance between the casing and the blade to solve the problem of blade expansion and fracture. However, the efficiency of the engine is reduced along with the increase of the clearance between the casing and the blades, and data show that the high-pressure turbine blade tip gas path clearance of a typical engine is reduced by 0.254mm, and the efficiency can be improved by about 1%; the radial clearance of the compressor is increased by 0.076mm, and the oil consumption rate can be increased by about 1%; about 2300 million RMB can be saved and 2.9 million tons of CO can be reduced every year when the working efficiency of a 530MW steam turbine is improved by 2 percent2And (4) discharging. The technical attack of flame retardance and sealing of the titanium alloy attracts a plurality of experts and scholars.
Disclosure of Invention
Therefore, the technical problem to be solved by the invention is to provide a titanium alloy sealing and flame-retardant integrated coating which can be applied to flame retardance and sealing of the inner wall of a casing of an aircraft engine compressor and a preparation method thereof.
In order to solve the technical problems, the invention provides the following technical scheme:
the flame-retardant sealing integrated coating on the surface of the titanium alloy consists of a flame-retardant layer coating and an abradable sealing coating, wherein the flame-retardant layer coating is positioned between the surface of the titanium alloy and the abradable sealing coating.
The flame-retardant and sealing integrated coating on the surface of the titanium alloy is prepared from Ti40Zr25Ni3Cu12Be20The amorphous alloy spraying powder, wherein the abradable seal coating material is NiCrAl-bentonite spraying powder.
The flame-retardant sealing integrated coating on the surface of the titanium alloy is 100-150 mu m thick; the thickness of the abradable seal coating is 1.2-2 mm.
The preparation method of the flame-retardant sealing integrated coating on the surface of the titanium alloy comprises the following steps:
(1) surface treatment of the titanium alloy base material;
(2) preheating the titanium alloy base material;
(3) preparing a flame-retardant layer coating;
(4) and (4) preparing the abradable seal coating.
In the step (1), the titanium alloy base material is subjected to surface oil removal, rust removal and polishing treatment, wherein the polishing treatment is to polish the titanium alloy base material to 800 meshes step by using sand paper so that the surface of the titanium alloy base material becomes a flat and smooth spraying surface; the surface was sandblasted by a sandblasting machine before the spraying, the sand component used for the sandblasting was alumina, and the substrate roughness Ra after the sandblasting was 1.5 μm. The purpose is to increase the surface roughness of the titanium alloy base material properly and realize the increase of the bonding force between the coating and the substrate.
In the step (2), the titanium alloy base material is preheated by adopting supersonic flame or high-pressure cold spraying, the preheating temperature is 100-130 ℃, and the preheating time is 5-30s, so that the base can generate proper expansion.
In the step (3), the flame-retardant layer coating is prepared by adopting supersonic flame spraying, and the spraying material of the flame-retardant layer coating is Ti40Zr25Ni3Cu12Be20The granularity of the amorphous alloy powder is 30-100 mu m; the technological parameters of the supersonic flame spraying are as follows: the kerosene flow is 0.38-0.44L/min, the oxygen flow is 880-980L/min, the spraying distance is 380-450mm, the powder feeding rate is 35-45g/min, and the obtained coating thickness is 100-150 mu m.
According to the preparation method of the titanium alloy surface flame-retardant sealing integrated coating, in the step (3), the flame-retardant layer coating is prepared by adopting high-pressure cold spraying; the spraying material of the flame-retardant layer coating is Ti40Zr25Ni3Cu12Be20Spraying amorphous alloy powder with the granularity of 30-100 mu m; the parameters of the high-pressure cold spraying process are as follows: the carrier gas flow is 1000-.
According to the preparation method of the flame-retardant sealing integrated coating on the surface of the titanium alloy, in the step (4), the abradable sealing coating is prepared by flame spraying; the abradable seal coating is a nickel chromium aluminum-bentonite spraying powder material, and the mass percent of each element in the nickel chromium aluminum-bentonite spraying powder material is Cr: 4%, Al: 4%, bentonite 21%, Ni: the balance; the granularity of the nickel-chromium-aluminum-bentonite powder is 88-199 mu m; the flame spraying process comprises the following steps: oxygen pressure: 0.2-0.4MPa, acetylene pressure: 0.05-0.15MPa, spraying distance: 200-250mm, powder feeding pressure: 0.4MPa, and the obtained coating thickness is 1.2-2 mm.
The application of the titanium alloy surface flame-retardant sealing integrated coating is used for the inner wall of a casing of an aircraft engine compressor.
The technical scheme of the invention achieves the following beneficial technical effects:
the coating prepared by the invention comprises a titanium-zirconium amorphous alloy flame-retardant layer with the function of a bonding layer and nickelA chromium aluminum-bentonite abradable face layer; wherein the flame-retardant layer material adopts Ti40Zr25Ni3Cu12Be20The amorphous alloy spraying powder is prepared by supersonic flame spraying or high-pressure cold spraying, and has the advantages of low porosity, compact structure and low oxidation rate; the surface layer is prepared by oxygen-acetylene flame spraying, and has good abradability, proper coating hardness and good bonding force with the flame-retardant layer.
The invention uses the titanium-zirconium amorphous alloy flame-retardant layer as the bonding layer, cancels the original bonding layer, adopts the nickel-chromium-aluminum-bentonite as the abradable sealing surface layer, and has the functions of protecting the blade and the casing, simultaneously reducing the porosity between the blades and the casing, and improving the heat efficiency, thereby reducing the manufacturing cost and the maintenance cost; meanwhile, the structure of the coating is simplified, the preparation procedures are reduced, and the preparation cost is reduced.
In the invention, the preparation of the coating by selecting the supersonic flame spraying and the high-pressure cold spraying has the following advantages: the coating is compact, the porosity is low, and the oxidation amount is small; compared with a coating prepared by an atmospheric plasma spraying mode, the coating has better performance and is more resistant to high-temperature oxidation.
Drawings
FIG. 1 is a schematic structural view of a titanium alloy surface flame-retardant sealing integrated coating of the present invention.
Detailed Description
Example 1
(1) Surface treatment of the titanium alloy base material: adopting a wafer sample of a TC4 titanium alloy sample with the diameter of 25mm and the thickness of about 3.5mm, carrying out oil and rust removal treatment on the sample before spraying, and gradually polishing the surface of the sample to 800 meshes by using abrasive paper to expose a smooth sprayed surface;
carrying out sand blasting treatment on the base material by a sand blasting machine, wherein the sand component used for sand blasting is alumina, the grain size of the sand is 30 meshes, so that the base obtains certain roughness, the binding force between the coating and the base is improved, and the roughness Ra of the base after sand blasting is 1.5 mu m;
(2) preheating the titanium alloy base material: preheating the titanium alloy by adopting supersonic flame to ensure that the substrate generates proper expansion, wherein the preheating temperature is 100-130 ℃, and the preheating time is 20S;
(3) preparing a flame-retardant layer coating: the spraying material of the flame-retardant layer coating is Ti40Zr25Ni3Cu12Be20Spraying amorphous alloy powder with the granularity of 30-100 mu m; the flame-retardant layer is prepared by adopting supersonic flame spraying, and the spraying process parameters are as follows: the flow rate of kerosene is 0.40L/min, the flow rate of oxygen is 900L/min, the spraying distance is 450mm, the powder feeding rate is 40g/min, and the thickness of the obtained coating is 120 mu m;
(4) preparing an abradable seal coating: the abradable seal coating is a nickel chromium aluminum-bentonite spraying powder material, and the mass percent of each element in the nickel chromium aluminum-bentonite spraying powder material is Cr: 4%, Al: 4%, bentonite 21%, Ni: and (4) the balance.
Preparing an abradable nickel chromium aluminum-bentonite surface layer by flame spraying, wherein the spraying process comprises the following steps: oxygen pressure: 0.4MPa, acetylene pressure: 0.15MPa, spraying distance: 220mm, powder feeding pressure: 0.4MPa, the coating thickness obtained is 1.5 mm.
Example 2
(1) Surface treatment of the titanium alloy base material: adopting a wafer sample of a TC4 titanium alloy sample with the diameter of 25mm and the thickness of about 3.5mm, carrying out oil and rust removal treatment on the sample before spraying, and gradually polishing the surface of the sample to 800 meshes by using abrasive paper to expose a smooth sprayed surface;
carrying out sand blasting treatment on the base material by a sand blasting machine, wherein the sand component used for sand blasting is alumina, the grain size of the sand is 30 meshes, so that the base obtains certain roughness, the binding force between the coating and the base is improved, and the roughness Ra of the base after sand blasting is 1.5 mu m;
(2) preheating the titanium alloy base material: preheating the titanium alloy by adopting supersonic flame to ensure that a substrate generates proper expansion, wherein the preheating temperature is between 100 and 130 ℃; the preheating time was 20S.
(3) Preparing a flame-retardant layer coating: the spraying material of the flame-retardant layer coating is Ti40Zr25Ni3Cu12Be20Spraying amorphous alloy powder with the granularity of 30-100 mu m; by high-pressure cold sprayingPreparing a flame-retardant layer, wherein the spraying process parameters are as follows: 1300L/min of carrier gas, 3MPa of nozzle pressure, 40mm of spraying distance and 60g/min of powder feeding rate, and the thickness of the obtained coating is 120 mu m;
(4) preparing an abradable seal coating: the abradable seal coating is a nickel chromium aluminum-bentonite spraying powder material, and the mass percent of each element in the nickel chromium aluminum-bentonite spraying powder material is Cr: 4%, Al: 4%, bentonite 21%, Ni: and (4) the balance.
Preparing an abradable nickel chromium aluminum-bentonite surface layer by flame spraying, wherein the spraying process comprises the following steps: oxygen pressure: 0.3MPa, acetylene pressure: 0.1MPa, spraying distance: 200mm, powder feeding pressure: 0.4MPa, the coating thickness obtained is 1.5 mm.
It should be understood that the above examples are only for clarity of illustration and are not intended to limit the embodiments. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. And obvious variations or modifications are possible which remain within the scope of the appended claims.
Claims (2)
1. A preparation method of a flame-retardant sealing integrated coating on the surface of a titanium alloy is characterized by comprising the following steps:
(1) surface treatment of the titanium alloy base material; carrying out surface oil removal, rust removal and polishing treatment on the titanium alloy base material, wherein the polishing treatment is to polish the titanium alloy base material to 800 meshes step by using sand paper so that the surface of the titanium alloy base material becomes a flat and smooth spraying surface; performing sand blasting treatment on the surface by a sand blasting machine before spraying, wherein the sand component used for sand blasting is aluminum oxide, and the roughness Ra of the substrate after sand blasting is 1.5 mu m;
(2) preheating the titanium alloy base material; preheating the titanium alloy base material by adopting supersonic flame or high-pressure cold spraying, wherein the preheating temperature is 100-130 ℃, and the preheating time is 5-30 s;
(3) preparing a flame-retardant layer coating; the flame-retardant layer coating is prepared by adopting supersonic flame spraying or high-pressure cold spraying, and the spraying material of the flame-retardant layer coating is Ti40Zr25Ni3Cu12Be20Amorphous alloy powder with the granularity of 30-100 mu m;
the technological parameters of the supersonic flame spraying are as follows: the flow rate of kerosene is 0.38-0.44L/min, the flow rate of oxygen is 880-980L/min, the spraying distance is 380-450mm, the powder feeding rate is 35-45g/min, and the thickness of the obtained coating is 100-150 mu m;
the parameters of the high-pressure cold spraying process are as follows: the carrier gas flow is 1000-
(4) Preparing an abradable seal coating; the abradable seal coating is prepared by flame spraying; the abradable seal coating is a nickel chromium aluminum-bentonite spraying powder material, and the mass percent of each element in the nickel chromium aluminum-bentonite spraying powder is Cr: 4%, Al: 4%, bentonite 21%, Ni: the balance; the granularity of the nickel-chromium-aluminum-bentonite powder is 88-199 mu m; the flame spraying process comprises the following steps: oxygen pressure: 0.2-0.4MPa, acetylene pressure: 0.05-0.15MPa, spraying distance: 200-250mm, powder feeding pressure: 0.4MPa, and the obtained coating thickness is 1.2-2 mm.
2. The application of the titanium alloy surface flame-retardant sealing integrated coating is characterized in that the titanium alloy surface flame-retardant sealing integrated coating obtained by the preparation method in the claim 1 is applied to the inner wall of a casing of an aircraft engine compressor.
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| 一种阻燃隔热复合功能涂层性能研究;王瑞军等;《热喷涂技术》;20190315;第11卷(第1期);第77-81页 * |
| 王瑞军等.一种阻燃隔热复合功能涂层性能研究.《热喷涂技术》.2019,第11卷(第1期),第77-81页. * |
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