CN109590197A - A kind of auxiliary power unit turborotor protective coating preparation method - Google Patents
A kind of auxiliary power unit turborotor protective coating preparation method Download PDFInfo
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- CN109590197A CN109590197A CN201811291196.9A CN201811291196A CN109590197A CN 109590197 A CN109590197 A CN 109590197A CN 201811291196 A CN201811291196 A CN 201811291196A CN 109590197 A CN109590197 A CN 109590197A
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- coating
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- auxiliary power
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D—PROCESSES FOR APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D7/00—Processes, other than flocking, specially adapted for applying liquids or other fluent materials to particular surfaces or for applying particular liquids or other fluent materials
- B05D7/24—Processes, other than flocking, specially adapted for applying liquids or other fluent materials to particular surfaces or for applying particular liquids or other fluent materials for applying particular liquids or other fluent materials
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D—PROCESSES FOR APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D1/00—Processes for applying liquids or other fluent materials
- B05D1/32—Processes for applying liquids or other fluent materials using means for protecting parts of a surface not to be coated, e.g. using stencils, resists
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D—PROCESSES FOR APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D3/00—Pretreatment of surfaces to which liquids or other fluent materials are to be applied; After-treatment of applied coatings, e.g. intermediate treating of an applied coating preparatory to subsequent applications of liquids or other fluent materials
- B05D3/02—Pretreatment of surfaces to which liquids or other fluent materials are to be applied; After-treatment of applied coatings, e.g. intermediate treating of an applied coating preparatory to subsequent applications of liquids or other fluent materials by baking
- B05D3/0254—After-treatment
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B05—SPRAYING OR ATOMISING IN GENERAL; APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D—PROCESSES FOR APPLYING FLUENT MATERIALS TO SURFACES, IN GENERAL
- B05D3/00—Pretreatment of surfaces to which liquids or other fluent materials are to be applied; After-treatment of applied coatings, e.g. intermediate treating of an applied coating preparatory to subsequent applications of liquids or other fluent materials
- B05D3/02—Pretreatment of surfaces to which liquids or other fluent materials are to be applied; After-treatment of applied coatings, e.g. intermediate treating of an applied coating preparatory to subsequent applications of liquids or other fluent materials by baking
- B05D3/0254—After-treatment
- B05D3/0272—After-treatment with ovens
-
- 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
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/04—Coating on selected surface areas, e.g. using masks
- C23C14/042—Coating on selected surface areas, e.g. using masks using masks
-
- 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
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/06—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the coating material
- C23C14/14—Metallic material, boron or silicon
- C23C14/16—Metallic material, boron or silicon on metallic substrates or on substrates of boron or silicon
-
- 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
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/22—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the process of coating
- C23C14/24—Vacuum evaporation
- C23C14/32—Vacuum evaporation by explosion; by evaporation and subsequent ionisation of the vapours, e.g. ion-plating
- C23C14/325—Electric arc evaporation
-
- 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
- C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
- C23C14/58—After-treatment
- C23C14/5893—Mixing of deposited material
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Materials Engineering (AREA)
- Mechanical Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Life Sciences & Earth Sciences (AREA)
- Wood Science & Technology (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a kind of auxiliary power unit turborotor coating protection preparation methods, include the following steps；Oil removal treatment: water blast is carried out using the white fused alumina of 120 mesh, acetone soak is then used, degreases；Spraying protection bottom: silico-aluminum AlSi slurry is sprayed into the blade passage position with spray gun；Protect bottom inspection: metallographic examination protects underlayer thickness in 40~60 μ ms, should be without rarefaction defect in coating；Protective coating pre-treatment: blade and blade pelvic part position is subjected to water blast: vacuum arc plating protective coating using 280 mesh white fused aluminas, coating coating is carried out after the completion of cleaning；DIFFUSION TREATMENT: the blade is put into vacuum drying oven and is diffused processing.It is an advantage of the invention that selecting AlSi coating as bottom, the excellent CoCrAlY coating of hot corrosion resistance improves the thermophilic corrosion-resistance performance of coating compared to conventional single AlSi coating as surface layer.
Description
Technical field
The present invention relates to aircraft engine maintenance technical field, especially a kind of auxiliary power unit turborotor is applied
Layer protection preparation method.
Background technique
Turborotor is one of the core component of gas-turbine unit most critical, and major function is by high temperature height
The rectification of compression ignition gas flows to turbine rotor blade by the required method of salary distribution and direction, and turbine wheel shaft rotation is made to drive compressor acting.
Turborotor immediately combustor exit, operating temperature is high, the temperature difference is big, is subjected to the impact and erosion of high-temperature fuel gas for a long time,
Blade is not required nothing more than with enough elevated temperature strengths, also to there is good high temperature resistant property, is depended merely on alloy itself and is difficult simultaneously completely
The two requirements of foot, need high-temperature protection coating in most cases.At present usually used coating include coat of aluminide,
MCrAlY coating and thermal barrier coating.Wherein coat of aluminide due to preparation method it is simple, it is low in cost, while high temperature resistance
Can be excellent, therefore it is widely used as turbo blade high-temperature protection coating.
Auxiliary power unit (APU) is substantially a small-sized aero gas turbine engine, turbine inlet temperature about 900
℃.Turborotor is under the working environment, since the fused salts such as Na2SO4, K2SO4 are easy gradually to sink in blade and blade pelvic part position
Product, leaf pelvic part position is mainly based on High Temperature Hot-corrosion Behaviorof, while leaf basin constantly bears the impact of high-temperature high-pressure fuel gas, protective coating
It is easy to mostly use single AlSi coating to make greatly by even influence blade base performance, especially current turborotor is destroyed
In the case where protective coating, leaf basin heat erosion is particularly evident.
Summary of the invention
The purpose of the present invention is to overcome the shortcomings of the existing technology, provides a kind of auxiliary power unit turborotor painting
Layer protection preparation method selectively prepares a kind of composite coating in the blade and blade pelvic part position for being subject to heat erosion destruction, improves
The hot corrosion resistance of blade extends blade service life.
The purpose of the present invention is achieved through the following technical solutions: a kind of auxiliary power unit turborotor coating is anti-
Preparation method is protected, is included the following steps；
Oil removal treatment: the guide vane of high pressure turbine of auxiliary power unit is subjected to water blast using the white fused alumina of 120 mesh, then
It using acetone soak, degreases, and is dried for standby；
Spraying protection bottom: silico-aluminum AlSi slurry is sprayed into the blade passage position with spray gun, with a thickness of 40~60 μ
Then m carries out intermediate temperature setting and high-temperature vacuum DIFFUSION TREATMENT, form AlSi and protect bottom；
Protect bottom inspection: metallographic examination protects underlayer thickness in 40~60 μ ms, should be without rarefaction defect in coating；
Protective coating pre-treatment: blade and blade pelvic part position is subjected to water blast using 280 mesh white fused aluminas, is then placed in deionized water
20~30min of ultrasonic cleaning is carried out, then carries out 10~15min of acetone soak；
Coating protective coating: vacuum arc plating protective coating, when being evacuated to 10-2~10-3Pa, to the blade carry out from
Son cleaning, operating voltage 200V, arc current 600A, clearance time are greater than 2min, coating coating are carried out after the completion of cleaning, apply
Voltage 30V, arc current 600A, coating time 2h are plated, about 36 μm~40 μm of thickness of coating is obtained；
DIFFUSION TREATMENT: the blade being put into vacuum drying oven and is diffused processing, after furnace pressure is less than 10-2 Pa, heating
To 980 DEG C, 3h is kept the temperature, with furnace vacuum cooled to 600 DEG C hereinafter, filling 1200~1500mbar argon gas is cooled to 80 after heat preservation
DEG C or less come out of the stove；
Protective coating inspection: by coating test piece on tooling device more than 90-degree bent, check that test piece external surface coating should be without de-
It falls, chip off-falling.
Specifically, the intermediate temperature setting process is: the blade after spraying silico-aluminum slurry is heated to 80 DEG C of heat preservations
30min then heats to 300 DEG C, keeps the temperature 30min.
Specifically, the high-temperature vacuum DIFFUSION TREATMENT process is: spraying silico-aluminum slurry rear blade is placed vacuum
It is evacuated to 10Pa in furnace or is higher than 10Pa, 1000 DEG C are warming up in 2.5h, keeps the temperature 3h, vacuum furnace cooling after heat preservation
To 400 DEG C, then pours 1~2bar argon gas and be cooled to 80 DEG C or less and come out of the stove.
Specifically, further include non-coating position protection step, use shield jig by the leaf before coating protective coating
It is protected at the non-coating position of piece.
Specifically, the basis material of the auxiliary power unit is Mar-M247.
Specifically, the protective coating is CoCrAlY thermal barrier coating.
Specifically, the silico-aluminum AlSi is the dedicated silico-aluminum of aviation.The invention has the following advantages that
1, select AlSi coating as bottom, the excellent CoCrAlY coating of hot corrosion resistance is as surface layer, compared to routine
Single AlSi coating improves the thermophilic corrosion-resistance performance of coating.
2, it by applying AlSi coating in turborotor water passage surface, is selectively applied in the compound CoCrAlY of leaf basin
Layer, improves the ability of blade and blade basin corrosion and heat resistant, while guaranteeing that blade back has preferable high temperature oxidation resistance, effectively extends
Blade service life.
3, AlSi+CoCrAlY composite coating after spreading carries out bend test, without apparent disbonding phenomenon,
Anchoring strength of coating is high, is not susceptible to disbonding when vanes are impacted by high-temperature fuel gas in the operating condition.
4, the coating performance of the method for the present invention preparation is excellent, reliable in quality is stable, not only can be in military aero-engine
Upper use, and can extend on the turborotors such as domestic gas turbine and use, it prolongs its service life, has simultaneously
Significant social benefit.
Detailed description of the invention
Fig. 1 is flow chart of the invention；
Fig. 2 is that failure blade coatings damage metallographic；
Fig. 3 is the composite coating metallographic of preparation.
Specific embodiment
The present invention will be further described with reference to the accompanying drawing, but protection scope of the present invention is not limited to following institute
It states.
As shown in Fig. 1 ~ 3, a kind of auxiliary power unit turborotor coating protection preparation method, including following step
Suddenly；
Oil removal treatment: the guide vane of high pressure turbine of auxiliary power unit is subjected to water blast using the white fused alumina of 120 mesh, then
It using acetone soak, degreases, and is dried for standby；
Spraying protection bottom: silico-aluminum AlSi slurry is sprayed into the blade passage position with spray gun, with a thickness of 40~60 μ
Then m carries out intermediate temperature setting and high-temperature vacuum DIFFUSION TREATMENT, form AlSi and protect bottom；
Protect bottom inspection: metallographic examination protects underlayer thickness in 40~60 μ ms, should be without rarefaction defect in coating；
Protective coating pre-treatment: blade and blade pelvic part position is subjected to water blast using 280 mesh white fused aluminas, is then placed in deionized water
20~30min of ultrasonic cleaning is carried out, then carries out 10~15min of acetone soak；
Coating protective coating: vacuum arc plating protective coating, when being evacuated to 10-2~10-3Pa, to the blade carry out from
Son cleaning, operating voltage 200V, arc current 600A, clearance time are greater than 2min, coating coating are carried out after the completion of cleaning, apply
Voltage 30V, arc current 600A, coating time 2h are plated, about 36 μm~40 μm of thickness of coating is obtained；
DIFFUSION TREATMENT: the blade is put into vacuum drying oven and is diffused processing: after furnace pressure is less than 10-2 Pa, heating
To 980 DEG C, 3h is kept the temperature, with furnace vacuum cooled to 600 DEG C hereinafter, filling 1200~1500mbar argon gas is cooled to 80 after heat preservation
DEG C or less come out of the stove；
Protective coating inspection: by coating test piece on tooling device more than 90-degree bent, check that test piece external surface coating should be without de-
It falls, chip off-falling.
Further, the intermediate temperature setting process is: the blade after spraying silico-aluminum slurry is heated to 80 DEG C of guarantors
Warm 30min then heats to 300 DEG C, keeps the temperature 30min.
Further, the high-temperature vacuum DIFFUSION TREATMENT process is: spraying silico-aluminum slurry rear blade being placed true
It is evacuated to 10Pa in empty furnace or is higher than 10Pa, 1000 DEG C are warming up in 2.5h, keeps the temperature 3h, vacuum is cold with furnace after heat preservation
But it to 400 DEG C, then pours 1~2bar argon gas and is cooled to 80 DEG C or less and come out of the stove.
It further, further include non-coating position protection step, it will be described using shield jig before coating protective coating
It is protected at the non-coating position of blade.
Further, the basis material of the auxiliary power unit is Mar-M247.
Further, the protective coating is CoCrAlY thermal barrier coating.
Further, the silico-aluminum AlSi is the dedicated silico-aluminum of aviation.A layer in Fig. 2 is AlSi coating, and B is
CoCrAlY coating.
The above, only presently preferred embodiments of the present invention not do limitation in any form to the present invention.It is any ripe
Those skilled in the art is known, without departing from the scope of the technical proposal of the invention, all using technology contents described above
Many possible changes and modifications or equivalent example modified to equivalent change are made to technical solution of the present invention.Therefore, all
It is the content without departing from technical solution of the present invention, any change modification made to the above embodiment of technology according to the present invention,
Equivalent variations and modification belong to the protection scope of the technical program.
Claims (7)
1. a kind of aviation auxiliary power unit turborotor protective coating preparation method, it is characterised in that: including following step
Suddenly；
Oil removal treatment: the guide vane of high pressure turbine of auxiliary power unit is subjected to water blast using the white fused alumina of 120 mesh, then
It using acetone soak, degreases, and is dried for standby；
Spraying protection bottom: silico-aluminum AlSi slurry is sprayed into the blade passage position with spray gun, with a thickness of 40~60 μ
Then m carries out intermediate temperature setting and high-temperature vacuum DIFFUSION TREATMENT, form AlSi and protect bottom；
Protect bottom inspection: metallographic examination protects underlayer thickness in 40~60 μ ms, should be without rarefaction defect in coating；
Protective coating pre-treatment: blade and blade pelvic part position is subjected to water blast using 280 mesh white fused aluminas, is then placed in deionized water
20~30min of ultrasonic cleaning is carried out, then carries out 10~15min of acetone soak；
Coating protective coating: vacuum arc plating protective coating is evacuated to 10-2~10-3When Pa, ion is carried out to the blade
Cleaning, operating voltage 200V, arc current 600A, clearance time are greater than 2min, coating coating, coating are carried out after the completion of cleaning
Voltage 30V, arc current 600A, coating time 2h obtain about 36 μm~40 μm of thickness of coating；
DIFFUSION TREATMENT: the blade being put into vacuum drying oven and is diffused processing, when furnace pressure is less than 10-2After Pa, it is warming up to
980 DEG C, 3h is kept the temperature, with furnace vacuum cooled to 600 DEG C hereinafter, filling 1200~1500mbar argon gas is cooled to 80 DEG C after heat preservation
It comes out of the stove below；
Protective coating inspection: by coating test piece on tooling device more than 90-degree bent, check that test piece external surface coating should be without de-
It falls, chip off-falling.
2. a kind of auxiliary power unit turborotor protective coating preparation method according to claim 1, feature
Be: the intermediate temperature setting process is: the blade after spraying silico-aluminum slurry being heated to 80 DEG C of heat preservation 30min, then
300 DEG C are warming up to, 30min is kept the temperature.
3. a kind of auxiliary power unit turborotor protective coating preparation method according to claim 1, feature
Be: the high-temperature vacuum DIFFUSION TREATMENT process is: spraying silico-aluminum slurry rear blade being placed in vacuum drying oven and is vacuumized
To 10Pa or it is higher than 10Pa, 1000 DEG C is warming up in 2.5h, keeps the temperature 3h, vacuum cools to 400 DEG C with the furnace after heat preservation, so
After pour 1~2bar argon gas and be cooled to 80 DEG C or less and come out of the stove.
4. a kind of auxiliary power unit turborotor protective coating preparation method according to claim 1, feature
It is: further includes non-coating position protection step, use shield jig by the non-coating of the blade before coating protective coating
It is protected at position.
5. a kind of auxiliary power unit turborotor protective coating preparation method according to claim 1, feature
Be: the basis material of the auxiliary power unit is Mar-M247.
6. a kind of auxiliary power unit turborotor protective coating preparation method according to claim 1, feature
Be: the protective coating is CoCrAlY thermal barrier coating.
7. a kind of auxiliary power unit turborotor protective coating preparation method according to claim 1, feature
Be: the silico-aluminum AlSi is the dedicated silico-aluminum of aviation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811291196.9A CN109590197A (en) | 2018-10-31 | 2018-10-31 | A kind of auxiliary power unit turborotor protective coating preparation method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811291196.9A CN109590197A (en) | 2018-10-31 | 2018-10-31 | A kind of auxiliary power unit turborotor protective coating preparation method |
Publications (1)
| Publication Number | Publication Date |
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| CN109590197A true CN109590197A (en) | 2019-04-09 |
Family
ID=65958256
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811291196.9A Pending CN109590197A (en) | 2018-10-31 | 2018-10-31 | A kind of auxiliary power unit turborotor protective coating preparation method |
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6296447B1 (en) * | 1999-08-11 | 2001-10-02 | General Electric Company | Gas turbine component having location-dependent protective coatings thereon |
| CN101460708A (en) * | 2006-06-08 | 2009-06-17 | 西门子公司 | Coated turbine component and method of coating a turbine component |
| CN102936713A (en) * | 2012-11-28 | 2013-02-20 | 中国南方航空工业(集团)有限公司 | Method for seeping aluminum silicon from aluminum silicon slurry |
-
2018
- 2018-10-31 CN CN201811291196.9A patent/CN109590197A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6296447B1 (en) * | 1999-08-11 | 2001-10-02 | General Electric Company | Gas turbine component having location-dependent protective coatings thereon |
| CN101460708A (en) * | 2006-06-08 | 2009-06-17 | 西门子公司 | Coated turbine component and method of coating a turbine component |
| CN102936713A (en) * | 2012-11-28 | 2013-02-20 | 中国南方航空工业(集团)有限公司 | Method for seeping aluminum silicon from aluminum silicon slurry |
Non-Patent Citations (2)
| Title |
|---|
| 何黎明等: "AlSi+CoCrAlY复合涂层对MAR-M247合金力学性能的影响", 《航空维修与工程》 * |
| 刘劲松，蒲玉兴主编: "《航空工程材料》", 31 August 2015 * |
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Application publication date: 20190409 |