CN105925928A - Surface treatment method for blade of large turbine machine - Google Patents
Surface treatment method for blade of large turbine machine Download PDFInfo
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- CN105925928A CN105925928A CN201610460107.3A CN201610460107A CN105925928A CN 105925928 A CN105925928 A CN 105925928A CN 201610460107 A CN201610460107 A CN 201610460107A CN 105925928 A CN105925928 A CN 105925928A
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- spray
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- 238000000034 method Methods 0.000 title claims abstract description 47
- 238000004381 surface treatment Methods 0.000 title claims abstract description 20
- 238000005507 spraying Methods 0.000 claims abstract description 74
- 239000000843 powder Substances 0.000 claims abstract description 64
- 239000011248 coating agent Substances 0.000 claims abstract description 25
- 238000000576 coating method Methods 0.000 claims abstract description 25
- 238000007789 sealing Methods 0.000 claims abstract description 19
- 238000005498 polishing Methods 0.000 claims abstract description 10
- 239000007921 spray Substances 0.000 claims description 31
- CSCPPACGZOOCGX-UHFFFAOYSA-N Acetone Chemical compound CC(C)=O CSCPPACGZOOCGX-UHFFFAOYSA-N 0.000 claims description 18
- 238000005422 blasting Methods 0.000 claims description 18
- 238000010285 flame spraying Methods 0.000 claims description 18
- 238000010438 heat treatment Methods 0.000 claims description 18
- 238000002203 pretreatment Methods 0.000 claims description 18
- 238000004140 cleaning Methods 0.000 claims description 11
- 229910007570 Zn-Al Inorganic materials 0.000 claims description 9
- 229910045601 alloy Inorganic materials 0.000 claims description 9
- 239000000956 alloy Substances 0.000 claims description 9
- 239000003795 chemical substances by application Substances 0.000 claims description 9
- 229910052593 corundum Inorganic materials 0.000 claims description 9
- 239000010431 corundum Substances 0.000 claims description 9
- 238000000280 densification Methods 0.000 claims description 9
- 230000000873 masking effect Effects 0.000 claims description 9
- 239000002245 particle Substances 0.000 claims description 9
- 238000005488 sandblasting Methods 0.000 claims description 2
- 238000005260 corrosion Methods 0.000 abstract description 4
- 230000007797 corrosion Effects 0.000 abstract description 4
- 230000002035 prolonged effect Effects 0.000 abstract 1
- 238000009997 thermal pre-treatment Methods 0.000 abstract 1
- 238000005406 washing Methods 0.000 abstract 1
- 238000005261 decarburization Methods 0.000 description 7
- 238000004227 thermal cracking Methods 0.000 description 7
- 230000003628 erosive effect Effects 0.000 description 3
- 238000005299 abrasion Methods 0.000 description 2
- 239000008358 core component Substances 0.000 description 2
- 239000000428 dust Substances 0.000 description 2
- 239000008187 granular material Substances 0.000 description 2
- 239000002253 acid Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000004566 building material Substances 0.000 description 1
- 239000003034 coal gas Substances 0.000 description 1
- 230000009977 dual effect Effects 0.000 description 1
- 238000004134 energy conservation Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 238000005272 metallurgy Methods 0.000 description 1
- 238000003672 processing method Methods 0.000 description 1
- 238000009991 scouring Methods 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
- C23C4/02—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
Landscapes
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Plasma & Fusion (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Coating By Spraying Or Casting (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a surface treatment method for a blade of a large turbine machine. The surface treatment method comprises the steps of spraying pretreatment, thermal pretreatment, spraying of a bonding powder layer, spraying of a work layer, sealing treatment, polishing treatment and the like. By means of the surface treatment method, a coating is sprayed on a work face of the blade, washing resistance and corrosion resistance of the surface of the blade are greatly enhanced, and the service life of the blade can be prolonged by one time or above.
Description
Technical field
The present invention relates to Turbomachinery equipment technical field, particularly to the table of a kind of large-scale turbomachinery blade
Face processing method.
Background technology
Large-scale turbomachinery is the key that Beijing South Maxpower Technology Co. Ltd's consumption industries such as China's metallurgy, petrochemical industry, building materials realize energy-saving and emission-reduction
Device, blade therein is core component.Turbomachinery equipment the energy is made full use of have the heaviest
Big meaning, always China's emphasis develop one of substantial equipment with improvement.This equipment can utilize fully
The energy, does not consume coal gas, it is not required that any fuel, just can obtain energy-conservation, economical and social etc. after putting into operation
Many benefits.Therefore, advocating the society of energy-saving and emission-reduction energetically, Turbomachinery equipment has non-
The most wide market prospect.
But, due to turbomachinery work under bad environment, especially as the blade of core component, it runs
Ambient temperature is higher, and the stress born in running is very big, and long-term by dust granules in process environments
Erosion and the erosion of high-temperature vapor so that the service life of blade is short, consumption big, change
Frequently, and one of bottleneck that restriction Chinese large-sized Turbomachinery equipment is properly functioning at present is become.
In work, blade directly contacts with the corrosive gas in air and dust granules, therefore it is required that its work
Make face and should have good intensity, corrosion resistance, wearability etc., to improve its service life.
Summary of the invention
The goal of the invention of the present invention is: the problem existed for prior art, it is provided that a kind of large-scale turbine
The surface treatment method of tool blade, carries out surface process to blade, strengthens the abrasion resistance of blade surface and resistance to
Corrosivity, improves blade service life.
To achieve these goals, the technical solution used in the present invention is:
The surface treatment method of a kind of large-scale turbomachinery blade, comprises the following steps:
(1) spraying pre-treatment: cleaning blade need to spray position, then blade need to be sprayed position carry out at sandblasting
Reason；
(2) the pre-heat treatment: the blade after step (1) spraying pre-treatment is preheated to 80～150 DEG C；
(3) spraying combining powder layer: the blade base surface even application after step (2) the pre-heat treatment
One layer of combining powder, forms combining powder layer；
(4) spray coating operations layer: use the combining powder layer surface spraying work of flame-spraying normal direction step (3)
Making layer, the process conditions of flame-spraying are: flame temperature is 2300～2500 DEG C, and the speed of powder particle is
800～1000m/s, spray distance is 500～900mm, and dusty spray is Zn-Al alloy powder；
(5) sealing treatment: to the working lining surface spraying one floor height molecule hole sealing agent of step (4), then
Blade is put in baking oven and heat；
(6) polishing: coating is processed by shot blasting so that smooth surface, densification.
As the preferred technical solution of the present invention, in described step (1), acetone cleaning blade is used to need spraying
Position, and need not blade spray position masking tape protection, then need to spray to blade with brown corundum abrasive
It is coated with position and carries out blasting treatment.
As the preferred technical solution of the present invention, in described step (3), the thickness of combining powder layer is
0.2～0.3mm.
As the preferred technical solution of the present invention, in described step (4), blade base is entered by spraying process
Sector-style is cold, reduces blade base temperature.
As the preferred technical solution of the present invention, in described step (5), blade is put in baking oven and is heated to
150 DEG C, and it is incubated 3 hours.
The beneficial effects of the present invention is:
When large-scale turbomachinery blade works under severe working environment, due to for a long time by airflow scouring and
The dual function of acid medium corrosion, its surface is easily corroded and produces various etch pit；By the present invention's
Surface treatment method, at front side of vane spray-on coating, greatly strengthen abrasion resistance and the corrosion resistant of blade surface
Erosion property, can make blade increase by more than 1 times service life.
Detailed description of the invention
In order to make the object, technical solutions and advantages of the present invention clearer, preferred by the present invention below
Embodiment is described in detail.
Embodiment 1
The surface treatment method of a kind of large-scale turbomachinery blade, comprises the following steps:
(1) spraying pre-treatment: use acetone cleaning blade need to spray position, and blade be need not spraying portion
Position masking tape is protected, then with brown corundum abrasive, blade need to be sprayed position and carry out blasting treatment；
(2) the pre-heat treatment: the blade after step (1) spraying pre-treatment is preheated to 80 DEG C；
(3) spraying combining powder layer: the blade base surface even application after step (2) the pre-heat treatment
One layer of combining powder, forms combining powder layer, and the thickness of combining powder layer is 0.2mm；
(4) spray coating operations layer: use the combining powder layer surface spraying work of flame-spraying normal direction step (3)
Making layer, the process conditions of flame-spraying are: flame temperature is 2300 DEG C, and the speed of powder particle is 800m/s,
Spray distance is 500mm, and dusty spray is Zn-Al alloy powder；Spraying process carries out wind to blade base
Cold, reduce blade base temperature, in order to avoid coating crosses Thermal cracking, and the oxidized decarburization of coating can be avoided；
(5) sealing treatment: to the working lining surface spraying one floor height molecule hole sealing agent of step (4), then
Blade is put in baking oven and be heated to 150 DEG C, and be incubated 3 hours；
(6) polishing: coating is processed by shot blasting so that smooth surface, densification.
Process through the surface of the present embodiment, make blade surface occur by half former annual variation the time of etch pit
Being about 1 year, blade increases by 1 times service life.
Embodiment 2
The surface treatment method of a kind of large-scale turbomachinery blade, comprises the following steps:
(1) spraying pre-treatment: use acetone cleaning blade need to spray position, and blade be need not spraying portion
Position masking tape is protected, then with brown corundum abrasive, blade need to be sprayed position and carry out blasting treatment；
(2) the pre-heat treatment: the blade after step (1) spraying pre-treatment is preheated to 100 DEG C；
(3) spraying combining powder layer: the blade base surface even application after step (2) the pre-heat treatment
One layer of combining powder, forms combining powder layer, and the thickness of combining powder layer is 0.2mm；
(4) spray coating operations layer: use the combining powder layer surface spraying work of flame-spraying normal direction step (3)
Making layer, the process conditions of flame-spraying are: flame temperature is 2400 DEG C, and the speed of powder particle is 900m/s,
Spray distance is 600mm, and dusty spray is Zn-Al alloy powder；Spraying process carries out wind to blade base
Cold, reduce blade base temperature, in order to avoid coating crosses Thermal cracking, and the oxidized decarburization of coating can be avoided；
(5) sealing treatment: to the working lining surface spraying one floor height molecule hole sealing agent of step (4), then
Blade is put in baking oven and be heated to 150 DEG C, and be incubated 3 hours；
(6) polishing: coating is processed by shot blasting so that smooth surface, densification.
Process through the surface of the present embodiment, make blade surface occur by half former annual variation the time of etch pit
Being about 1 year, blade increases by 1.2 times service life.
Embodiment 3
The surface treatment method of a kind of large-scale turbomachinery blade, comprises the following steps:
(1) spraying pre-treatment: use acetone cleaning blade need to spray position, and blade be need not spraying portion
Position masking tape is protected, then with brown corundum abrasive, blade need to be sprayed position and carry out blasting treatment；
(2) the pre-heat treatment: the blade after step (1) spraying pre-treatment is preheated to 120 DEG C；
(3) spraying combining powder layer: the blade base surface even application after step (2) the pre-heat treatment
One layer of combining powder, forms combining powder layer, and the thickness of combining powder layer is 0.3mm；
(4) spray coating operations layer: use the combining powder layer surface spraying work of flame-spraying normal direction step (3)
Making layer, the process conditions of flame-spraying are: flame temperature is 2500 DEG C, and the speed of powder particle is 1000m/s,
Spray distance is 700mm, and dusty spray is Zn-Al alloy powder；Spraying process carries out wind to blade base
Cold, reduce blade base temperature, in order to avoid coating crosses Thermal cracking, and the oxidized decarburization of coating can be avoided；
(5) sealing treatment: to the working lining surface spraying one floor height molecule hole sealing agent of step (4), then
Blade is put in baking oven and be heated to 150 DEG C, and be incubated 3 hours；
(6) polishing: coating is processed by shot blasting so that smooth surface, densification.
Process through the surface of the present embodiment, make blade surface occur by half former annual variation the time of etch pit
Being about 1 year, blade increases by 1.3 times service life.
Embodiment 4
The surface treatment method of a kind of large-scale turbomachinery blade, comprises the following steps:
(1) spraying pre-treatment: use acetone cleaning blade need to spray position, and blade be need not spraying portion
Position masking tape is protected, then with brown corundum abrasive, blade need to be sprayed position and carry out blasting treatment；
(2) the pre-heat treatment: the blade after step (1) spraying pre-treatment is preheated to 150 DEG C；
(3) spraying combining powder layer: the blade base surface even application after step (2) the pre-heat treatment
One layer of combining powder, forms combining powder layer, and the thickness of combining powder layer is 0.2mm；
(4) spray coating operations layer: use the combining powder layer surface spraying work of flame-spraying normal direction step (3)
Making layer, the process conditions of flame-spraying are: flame temperature is 2300 DEG C, and the speed of powder particle is 900m/s,
Spray distance is 800mm, and dusty spray is Zn-Al alloy powder；Spraying process carries out wind to blade base
Cold, reduce blade base temperature, in order to avoid coating crosses Thermal cracking, and the oxidized decarburization of coating can be avoided；
(5) sealing treatment: to the working lining surface spraying one floor height molecule hole sealing agent of step (4), then
Blade is put in baking oven and be heated to 150 DEG C, and be incubated 3 hours；
(6) polishing: coating is processed by shot blasting so that smooth surface, densification.
Process through the surface of the present embodiment, make blade surface occur by half former annual variation the time of etch pit
Being about 1 year, blade increases by 1.4 times service life.
Embodiment 5
The surface treatment method of a kind of large-scale turbomachinery blade, comprises the following steps:
(1) spraying pre-treatment: use acetone cleaning blade need to spray position, and blade be need not spraying portion
Position masking tape is protected, then with brown corundum abrasive, blade need to be sprayed position and carry out blasting treatment；
(2) the pre-heat treatment: the blade after step (1) spraying pre-treatment is preheated to 90 DEG C；
(3) spraying combining powder layer: the blade base surface even application after step (2) the pre-heat treatment
One layer of combining powder, forms combining powder layer, and the thickness of combining powder layer is 0.3mm；
(4) spray coating operations layer: use the combining powder layer surface spraying work of flame-spraying normal direction step (3)
Making layer, the process conditions of flame-spraying are: flame temperature is 2500 DEG C, and the speed of powder particle is 800m/s,
Spray distance is 900mm, and dusty spray is Zn-Al alloy powder；Spraying process carries out wind to blade base
Cold, reduce blade base temperature, in order to avoid coating crosses Thermal cracking, and the oxidized decarburization of coating can be avoided；
(5) sealing treatment: to the working lining surface spraying one floor height molecule hole sealing agent of step (4), then
Blade is put in baking oven and be heated to 150 DEG C, and be incubated 3 hours；
(6) polishing: coating is processed by shot blasting so that smooth surface, densification.
Process through the surface of the present embodiment, make blade surface occur by half former annual variation the time of etch pit
Being about 1 year, blade increases by 1.2 times service life.
Embodiment 6
The surface treatment method of a kind of large-scale turbomachinery blade, comprises the following steps:
(1) spraying pre-treatment: use acetone cleaning blade need to spray position, and blade be need not spraying portion
Position masking tape is protected, then with brown corundum abrasive, blade need to be sprayed position and carry out blasting treatment；
(2) the pre-heat treatment: the blade after step (1) spraying pre-treatment is preheated to 110 DEG C；
(3) spraying combining powder layer: the blade base surface even application after step (2) the pre-heat treatment
One layer of combining powder, forms combining powder layer, and the thickness of combining powder layer is 0.2mm；
(4) spray coating operations layer: use the combining powder layer surface spraying work of flame-spraying normal direction step (3)
Making layer, the process conditions of flame-spraying are: flame temperature is 2500 DEG C, and the speed of powder particle is 1000m/s,
Spray distance is 500mm, and dusty spray is Zn-Al alloy powder；Spraying process carries out wind to blade base
Cold, reduce blade base temperature, in order to avoid coating crosses Thermal cracking, and the oxidized decarburization of coating can be avoided；
(5) sealing treatment: to the working lining surface spraying one floor height molecule hole sealing agent of step (4), then
Blade is put in baking oven and be heated to 150 DEG C, and be incubated 3 hours；
(6) polishing: coating is processed by shot blasting so that smooth surface, densification.
Process through the surface of the present embodiment, make blade surface occur by half former annual variation the time of etch pit
Being about 1 year, blade increases by 1.3 times service life.
Embodiment 7
The surface treatment method of a kind of large-scale turbomachinery blade, comprises the following steps:
(1) spraying pre-treatment: use acetone cleaning blade need to spray position, and blade be need not spraying portion
Position masking tape is protected, then with brown corundum abrasive, blade need to be sprayed position and carry out blasting treatment；
(2) the pre-heat treatment: the blade after step (1) spraying pre-treatment is preheated to 130 DEG C；
(3) spraying combining powder layer: the blade base surface even application after step (2) the pre-heat treatment
One layer of combining powder, forms combining powder layer, and the thickness of combining powder layer is 0.3mm；
(4) spray coating operations layer: use the combining powder layer surface spraying work of flame-spraying normal direction step (3)
Making layer, the process conditions of flame-spraying are: flame temperature is 2400 DEG C, and the speed of powder particle is 900m/s,
Spray distance is 600mm, and dusty spray is Zn-Al alloy powder；Spraying process carries out wind to blade base
Cold, reduce blade base temperature, in order to avoid coating crosses Thermal cracking, and the oxidized decarburization of coating can be avoided；
(5) sealing treatment: to the working lining surface spraying one floor height molecule hole sealing agent of step (4), then
Blade is put in baking oven and be heated to 150 DEG C, and be incubated 3 hours；
(6) polishing: coating is processed by shot blasting so that smooth surface, densification.
Process through the surface of the present embodiment, make blade surface occur by half former annual variation the time of etch pit
Being about 1 year, blade increases by 1.25 times service life.
Finally illustrate, above example only in order to technical scheme to be described and unrestricted, although
By referring to the preferred embodiments of the present invention, invention has been described, but the ordinary skill of this area
Personnel should be appreciated that and in the form and details it can be made various change, without departing from institute
The spirit and scope of the present invention that attached claims are limited.
Claims (5)
1. the surface treatment method of one kind large-scale turbomachinery blade, it is characterised in that: comprise the following steps:
(1) spraying pre-treatment: cleaning blade need to spray position, then blade need to be sprayed position carry out at sandblasting
Reason；
(2) the pre-heat treatment: the blade after step (1) spraying pre-treatment is preheated to 80～150 DEG C；
(3) spraying combining powder layer: the blade base surface even application after step (2) the pre-heat treatment
One layer of combining powder, forms combining powder layer；
(4) spray coating operations layer: use the combining powder layer surface spraying work of flame-spraying normal direction step (3)
Making layer, the process conditions of flame-spraying are: flame temperature is 2300～2500 DEG C, and the speed of powder particle is
800～1000m/s, spray distance is 500～900mm, and dusty spray is Zn-Al alloy powder；
(5) sealing treatment: to the working lining surface spraying one floor height molecule hole sealing agent of step (4), then
Blade is put in baking oven and heat；
(6) polishing: coating is processed by shot blasting so that smooth surface, densification.
The surface treatment method of large-scale turbomachinery blade the most according to claim 1, it is characterised in that:
In described step (1), use acetone cleaning blade need to spray position, and need not blade spray position use
Masking tape is protected, then with brown corundum abrasive, blade need to be sprayed position and carry out blasting treatment.
The surface treatment method of large-scale turbomachinery blade the most according to claim 1, it is characterised in that:
In described step (3), the thickness of combining powder layer is 0.2～0.3mm.
The surface treatment method of large-scale turbomachinery blade the most according to claim 1, it is characterised in that:
In described step (4), blade base is carried out air-cooled by spraying process, reduce blade base temperature.
The surface treatment method of large-scale turbomachinery blade the most according to claim 1, it is characterised in that:
In described step (5), blade is put into and is heated to 150 DEG C in baking oven, and is incubated 3 hours.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610460107.3A CN105925928A (en) | 2016-06-22 | 2016-06-22 | Surface treatment method for blade of large turbine machine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610460107.3A CN105925928A (en) | 2016-06-22 | 2016-06-22 | Surface treatment method for blade of large turbine machine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105925928A true CN105925928A (en) | 2016-09-07 |
Family
ID=56831974
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610460107.3A Pending CN105925928A (en) | 2016-06-22 | 2016-06-22 | Surface treatment method for blade of large turbine machine |
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| CN (1) | CN105925928A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110760782A (en) * | 2019-12-05 | 2020-02-07 | 河南科技大学 | Wear-resistant aluminum alloy and preparation method thereof |
| CN111530720A (en) * | 2020-04-26 | 2020-08-14 | 马鞍山钢铁股份有限公司 | Technology for processing return fan impeller of chain grate machine |
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| CN102041467A (en) * | 2010-12-07 | 2011-05-04 | 华中科技大学 | Hydrophobic amorphous alloy coating and preparation method thereof |
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| CN1324958A (en) * | 2000-05-18 | 2001-12-05 | 中国科学院海洋研究所 | Anticorrosion method of marine steel |
| CN101198712A (en) * | 2005-06-15 | 2008-06-11 | 马勒国际公司 | Method for coating a cylinder sleeve |
| CN101787510A (en) * | 2010-01-13 | 2010-07-28 | 西安热工研究院有限公司 | Preparation technology of turbine though-flow part coating against solid particle erosion |
| CN102041467A (en) * | 2010-12-07 | 2011-05-04 | 华中科技大学 | Hydrophobic amorphous alloy coating and preparation method thereof |
| CN102424943A (en) * | 2011-12-23 | 2012-04-25 | 安徽天一重工股份有限公司 | Preparation method of self-lubricating corrosion-resistant wear-resistant coating based on nichrome |
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| Title |
|---|
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| 戴达煌等: "《薄膜与涂层现代表面技术》", 31 July 2008, 中南大学出版社 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110760782A (en) * | 2019-12-05 | 2020-02-07 | 河南科技大学 | Wear-resistant aluminum alloy and preparation method thereof |
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| CN111530720A (en) * | 2020-04-26 | 2020-08-14 | 马鞍山钢铁股份有限公司 | Technology for processing return fan impeller of chain grate machine |
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Application publication date: 20160907 |