CN108103484A - A kind of engine titanium alloy component local size restorative procedure - Google Patents
A kind of engine titanium alloy component local size restorative procedure Download PDFInfo
- Publication number
- CN108103484A CN108103484A CN201711223926.7A CN201711223926A CN108103484A CN 108103484 A CN108103484 A CN 108103484A CN 201711223926 A CN201711223926 A CN 201711223926A CN 108103484 A CN108103484 A CN 108103484A
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- China
- Prior art keywords
- titanium alloy
- alloy component
- restorative procedure
- local size
- component local
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Classifications
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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
- C23C18/00—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating
- C23C18/16—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating by reduction or substitution, e.g. electroless plating
- C23C18/31—Coating with metals
- C23C18/32—Coating with nickel, cobalt or mixtures thereof with phosphorus or boron
- C23C18/34—Coating with nickel, cobalt or mixtures thereof with phosphorus or boron using reducing agents
- C23C18/36—Coating with nickel, cobalt or mixtures thereof with phosphorus or boron using reducing agents using hypophosphites
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P6/00—Restoring or reconditioning objects
-
- 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
- C23C18/00—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating
- C23C18/16—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating by reduction or substitution, e.g. electroless plating
- C23C18/18—Pretreatment of the material to be coated
- C23C18/1851—Pretreatment of the material to be coated of surfaces of non-metallic or semiconducting in organic material
- C23C18/1872—Pretreatment of the material to be coated of surfaces of non-metallic or semiconducting in organic material by chemical pretreatment
- C23C18/1886—Multistep pretreatment
- C23C18/1889—Multistep pretreatment with use of metal first
-
- 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
- C23C18/00—Chemical coating by decomposition of either liquid compounds or solutions of the coating forming compounds, without leaving reaction products of surface material in the coating; Contact plating
- C23C18/54—Contact plating, i.e. electroless electrochemical plating
-
- 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
- C23G—CLEANING OR DE-GREASING OF METALLIC MATERIAL BY CHEMICAL METHODS OTHER THAN ELECTROLYSIS
- C23G1/00—Cleaning or pickling metallic material with solutions or molten salts
- C23G1/14—Cleaning or pickling metallic material with solutions or molten salts with alkaline solutions
- C23G1/20—Other heavy metals
- C23G1/205—Other heavy metals refractory metals
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- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical Kinetics & Catalysis (AREA)
- General Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- Metallurgy (AREA)
- Organic Chemistry (AREA)
- Electrochemistry (AREA)
- Electroplating And Plating Baths Therefor (AREA)
- Electroplating Methods And Accessories (AREA)
- Chemically Coating (AREA)
Abstract
It is an object of the invention to provide a kind of engine titanium alloy component local size restorative procedures, which is characterized in that carries out repairing sizes using chemical nickel plating method, technological process is：Oil removing → non-plated surface protection → blast → corrosion → activation process → nickel preplating → chemical nickel plating → heat treatment.The method of the invention can solve the problems, such as the reparation of the overproof and old coating of accessory size, extend the service life of part, meet engine production and repair requirement, reduce repair cost, have significant economic and social benefit.
Description
Technical field
The present invention relates to the repairing sizes method of aero-engine titanium alloy component, more particularly to a kind of titanium alloy chemical plating
The process of nickel.
Background technology
Titanium alloy has many good characteristics, such as very high corrosion resistance, heat-resisting quantity, is aerospace chemical industry and oil work
Indispensable material in industry, however, the alloy such as wears no resistance, surface easily abrades, and easily occurs each other there are some defects
Adhesion, the engine after military service occur zero often due to relative motion abrasion, corrosion of Service Environment etc. between part in overhaul
There is scuffing, wear phenomenon in part surface, after mechanical grinding is modified, size beyond design drawing requirement, influences normally to fill again
Machine uses.The built-up welding of routine, changing the modes such as part, not only the cycle is long and of high cost.For this reason, it may be necessary to find a kind of fast and low-cost
Repair method.Usually adoptable chemical method repairing has chromium plating and chemical nickel plating.Since each position of eligible for repair part is overproof
Size it is different, and structure is more complicated, and because of the limitation of chrome-plated process characteristic, repairing sizes are carried out more using chemical nickel plating
It is effective.
The content of the invention
It is an object of the invention to provide a kind of engine titanium alloy component local size restorative procedures, are closed by using titanium
The method of golden chemical nickel plating completes the reparation to parts locally size, has not only met the technical indicator of design requirement, but also has extended
The service life of part.
Technical solution of the present invention is as follows：
Repairing sizes are carried out using chemical nickel plating method, technological process is：Oil removing → non-plated surface protection → blast → corruption
Erosion → activation process → nickel preplating → chemical nickel plating → heat treatment.
The present invention improves the wearability of titanium alloy surface and case hardness by coating, for dimension overproof after military service zero
Part is repaired, and extends its service life.Since titanium alloy component surface is easily in passive state, so will before chemical nickel plating
The bond strength of coating and matrix is improved by special surface activation process process.Based on this, the present invention develops satisfaction
Titanium alloy plating pre-processing technique and nickel chemical plating technology, using the technique prepare coating heat under the conditions of 250 DEG C 1h without
Bubble, coating microhardness are more than HV500, and the microhardness after 350 DEG C handle 1h is more than more than HV700, and single slot thickness is in 40 μ
More than m.
Main craft procedure explanation：
(1), the requirement of plating titanium alloy component
The titanium alloy component of chemical nickel plating to be carried out should be the semi-finished product by full annealing, the low power of wrought titanium alloy
Tissue is not to be exceeded 6 grades in 10 grades of standard judge pictures.Part answers chamfering, and R cannot be less than 0.2mm, and surface cannot have load mould,
The defects of scuffing, scratch.
(2), oil removing
Part in organic solvent and alkaline salt solution is subjected to electrochemical deoiling successively, forbids to contact halogen.Alkalescence
The ingredient and content of salting liquid be：
Except oil temperature is 70-90 DEG C, until cleared.
(3), activate
Activation process is that titanium alloy carries out hydrogenation treatment in the solution, and hydrogenation treatment make use of titanium alloy to have strong suction
The characteristics of Hydrogen Energy power, processing, which makes surface obtain one layer, in strongly acidic solution has certain active hydrogenation film, and the present invention is exactly
Titanium alloy surface is activated using this principle.The processing is the key that ensure titanium alloy surface chemical Ni-plating layer combination power work
Sequence, specific formula are as follows：
Color after part hydrogenation treatment is grey to black, and a small amount of sediment occurred on part need not be removed before plating,
It does not interfere with the combination power of coating and matrix.
The preparation of hydrogenation treatment solution is that sulfuric acid is slowly added into hydrochloric acid in the case where being stirred continuously and cooling down.
(4), nickel preplating
Contact nickel plating bath ingredient and content：
(5), chemical nickel plating
Chemical nickel plating tank liquor ingredient and content：
Temperature： 85℃-90℃
10-15 μm of deposition velocity/h
The preferred vulcanized lead PbS of stabilizer.
Following annex solution can be used while plating to be added：
After the present invention carries out engineering application at the scene, onsite application effect is fine, part performance and in stable condition.It can
Meet the requirement of aero-engine titanium alloy component quality control standards (QCS) acceptance criteria, solve the overproof and old coating of accessory size
Reparation problem extends the service life of part, meets engine production and repairs requirement, reduce repair cost, has notable
Economic and social benefit.Part after chemical nickel plating repairs size, can extend at least one life cycle, make part
Working life improved by original 300h to more than 600h.50 component parts for assembly of a machine engine overhaul tasks, 50 component parts for assembly of a machine systems are completed at present
Forging piece is processed, and 100% qualification is sent.Every about 150,000 yuan of component output value such as by producing per year based on 100, then can be created straight every year
Connect 15,000,000 yuan of economic benefit.
Specific embodiment
The method further illustrated the present invention by the following examples.
Embodiment 1
Technological process is：Oil removing → non-plated surface protection → blast → corrosion → activation process → nickel preplating → chemical nickel plating
→ heat treatment；Wherein：
Oil removal process is that part is carried out electrochemical deoiling in organic solvent and alkaline salt solution successively, alkaline salt solution
Ingredient and content are：
Activation process：
Activate tank liquor ingredient and content：
The preparation of activation process solution is that sulfuric acid is slowly added into hydrochloric acid (following implementation in the case where being stirred continuously and cooling down
Example uses the method).Color after part activation process is grey, has a small amount of sediment on part.
Nickel preplating：
Contact nickel plating bath ingredient and content：
One layer of layers of copper of piece surface uniform deposition after processing.
Chemical nickel plating：
Chemical nickel plating tank liquor ingredient and content：
Temperature：85℃
The coating prepared using above-mentioned technique heats 1h without blistering, coating microhardness HV550, warp under the conditions of 250 DEG C
Microhardness after 350 DEG C of processing 1h is more than HV750,10 μm/h of deposition velocity.
Embodiment 2
Activation process：
Activate tank liquor ingredient and content：
Color after part activation process is grey, without sediment on part.Nickel preplating：
Contact nickel plating bath ingredient and content：
One layer of layers of copper of piece surface uniform deposition after processing.
Chemical nickel plating：
Chemical nickel plating tank liquor ingredient and content：
Temperature： 90℃
The coating prepared using above-mentioned technique heats 1h without blistering, coating microhardness HV650, warp under the conditions of 250 DEG C
Microhardness after 350 DEG C of processing 1h is more than HV850,15 μm/h of deposition velocity.
Embodiment 3
Activation process：
Activate tank liquor ingredient and content：
Color after part activation process is grey, has a small amount of sediment on part.
Nickel preplating：
Contact nickel plating bath ingredient and content：
One layer of layers of copper of piece surface uniform deposition after processing.
Chemical nickel plating：
Chemical nickel plating tank liquor ingredient and content：
Temperature：88℃
The coating prepared using above-mentioned technique heats 1h without blistering, coating microhardness HV590, warp under the conditions of 250 DEG C
Microhardness after 350 DEG C of processing 1h is more than HV800,13 μm/h of deposition velocity.
The above embodiments merely illustrate the technical concept and features of the present invention, and its object is to allow person skilled in the art
Scholar can understand present disclosure and implement according to this, and it is not intended to limit the scope of the present invention.It is all according to the present invention
The equivalent change or modification that Spirit Essence is made, should be covered by the protection scope of the present invention.
Claims (10)
1. a kind of engine titanium alloy component local size restorative procedure, which is characterized in that ruler is carried out using chemical nickel plating method
Very little reparation, technological process are：Oil removing → non-plated surface protection → blast → corrosion → activation process → nickel preplating → chemical nickel plating
→ heat treatment.
2. according to engine titanium alloy component local size restorative procedure described in claim 1, it is characterised in that：Oil removal process is
Part is subjected to electrochemical deoiling in organic solvent and alkaline salt solution successively, the ingredient and content of alkaline salt solution are：
Except oil temperature is 70-90 DEG C.
3. according to engine titanium alloy component local size restorative procedure described in claim 1, it is characterised in that：Activation process is
Titanium alloy is placed in solution and carries out hydrogenation treatment, the ingredient and content of tank liquor used are：Sulfuric acid 250-300ml/l, ρ=
1.84；Hydrochloric acid 650-700ml/l, ρ=1.19；Activation temperature is 18 DEG C -25 DEG C, soak time 60-90min.
4. according to engine titanium alloy component local size restorative procedure described in claim 3, it is characterised in that：The tank liquor
Ingredient and content are：Sulfuric acid 260-280ml/l, ρ=1.84；Hydrochloric acid 680-690ml/l, ρ=1.19.
5. according to engine titanium alloy component local size restorative procedure described in claim 1, which is characterized in that in nickel preplating,
Contact nickel plating bath ingredient and content are：
Nickel chloride 220-240g/l
Hydrochloric acid 180-200g/l
Nickel preplating parameter is：
Temperature room temperature
Current density 5-8A/dm2
Time 3-5min.
6. according to engine titanium alloy component local size restorative procedure described in claim 5, which is characterized in that in nickel preplating,
Contact nickel plating bath ingredient and content are：Nickel chloride 220-230g/l, hydrochloric acid 180-190g/l.
7. according to engine titanium alloy component local size restorative procedure described in claim 1, it is characterised in that：Chemical nickel plating
In, chemical nickel plating tank liquor ingredient and content are：
8. according to engine titanium alloy component local size restorative procedure described in claim 7, it is characterised in that：The stabilizer
For vulcanized lead.
9. according to the engine titanium alloy component local size restorative procedure of claim 7 or 8, it is characterised in that：Chemical plating
Nickel carries out at 85 DEG C -90 DEG C, and deposition velocity is 10-15 μm/h.
10. according to the engine titanium alloy component local size restorative procedure of claim 1 or 7, which is characterized in that plating is same
The following annex solutions of Shi Caiyong are added：
Annex solution ingredient：Nickel sulfate 180-230g/l, sodium acetate 2g/l, lactic acid 25ml/l；1 liter is diluted to after mixing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711223926.7A CN108103484A (en) | 2017-11-29 | 2017-11-29 | A kind of engine titanium alloy component local size restorative procedure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711223926.7A CN108103484A (en) | 2017-11-29 | 2017-11-29 | A kind of engine titanium alloy component local size restorative procedure |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115110073A (en) * | 2022-06-16 | 2022-09-27 | 中国航发贵州黎阳航空动力有限公司 | Chemical nickel plating method for nickel-based superalloy |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1439741A (en) * | 2002-10-23 | 2003-09-03 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for chemically electroplating thick nickle on titanium alloy |
| CN102392233A (en) * | 2011-11-02 | 2012-03-28 | 沈阳飞机工业（集团）有限公司 | Method for adopting hydrogenating treatment as pretreatment of chemical nickel plating of titanium alloy |
| CN106637156A (en) * | 2016-12-23 | 2017-05-10 | 贵州黎阳航空动力有限公司 | Local chemical nickel-plating method for complex titanium alloy part |
-
2017
- 2017-11-29 CN CN201711223926.7A patent/CN108103484A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1439741A (en) * | 2002-10-23 | 2003-09-03 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for chemically electroplating thick nickle on titanium alloy |
| CN102392233A (en) * | 2011-11-02 | 2012-03-28 | 沈阳飞机工业（集团）有限公司 | Method for adopting hydrogenating treatment as pretreatment of chemical nickel plating of titanium alloy |
| CN106637156A (en) * | 2016-12-23 | 2017-05-10 | 贵州黎阳航空动力有限公司 | Local chemical nickel-plating method for complex titanium alloy part |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115110073A (en) * | 2022-06-16 | 2022-09-27 | 中国航发贵州黎阳航空动力有限公司 | Chemical nickel plating method for nickel-based superalloy |
| CN115110073B (en) * | 2022-06-16 | 2024-02-27 | 中国航发贵州黎阳航空动力有限公司 | Nickel-based superalloy chemical nickel plating method |
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Application publication date: 20180601 |