CN108465780A - A kind of process of preparing of guided missile large titanium alloy air intake duct - Google Patents
A kind of process of preparing of guided missile large titanium alloy air intake duct Download PDFInfo
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- CN108465780A CN108465780A CN201810349766.9A CN201810349766A CN108465780A CN 108465780 A CN108465780 A CN 108465780A CN 201810349766 A CN201810349766 A CN 201810349766A CN 108465780 A CN108465780 A CN 108465780A
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- Prior art keywords
- air intake
- intake duct
- titanium alloy
- ontology
- guided missile
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C9/00—Moulds or cores; Moulding processes
- B22C9/22—Moulds for peculiarly-shaped castings
-
- 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
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
-
- C—CHEMISTRY; METALLURGY
- C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
- C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
- C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
- C22F1/16—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of other metals or alloys based thereon
- C22F1/18—High-melting or refractory metals or alloys based thereon
- C22F1/183—High-melting or refractory metals or alloys based thereon of titanium or alloys based thereon
-
- 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
- C23G1/02—Cleaning or pickling metallic material with solutions or molten salts with acid solutions
- C23G1/10—Other heavy metals
- C23G1/106—Other heavy metals refractory metals
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- Chemical & Material Sciences (AREA)
- Mechanical Engineering (AREA)
- Engineering & Computer Science (AREA)
- Organic Chemistry (AREA)
- Metallurgy (AREA)
- Materials Engineering (AREA)
- Crystallography & Structural Chemistry (AREA)
- Physics & Mathematics (AREA)
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- Chemical Kinetics & Catalysis (AREA)
- General Chemical & Material Sciences (AREA)
- Arc Welding In General (AREA)
- Welding Or Cutting Using Electron Beams (AREA)
Abstract
A kind of process of preparing of guided missile large titanium alloy air intake duct, it is produced using the conventional equipment of graphite mould titanium alloy casting, it cannot achieve using conventional titanium alloy casting technique, equadag coating scheme using the present invention, the advantages of combining titanium investment casting, guided missile casting has not only been effectively ensured fills that type is complete, so that guided missile titanium alloy casting surface roughness is reached 6.3 μm of level, the Ti alloy casting process route for realizing guided missile casting is feasible.Laser welding scheme using the present invention, realizes the feasibility of air intake duct opening casting technique route, and effectively prevents the generation of air intake duct cavity underbead crack.
Description
Technical field
The present invention relates to Ti alloy casting field, titanium alloy structure part laser welding fields, are closed more particularly, to a kind of titanium
The process of preparing of golden air intake duct.
Background technology
The large-scale air intake duct titanium casting of guided missile tends to thin-long at present, this is for Ti alloy casting, scientific research and life
Production difficulty is multiplied.There are two types of the modes of production of the current comparative maturity of titanium alloy casting, and one is precision-investment castings, another
Kind is machining graphite mold casting.The elongated feature of large-scale air intake duct casting so that the casting during precision-investment casting is easy
The titanium alloy casting of the problems such as being deformed, precision-investment casting can meet requirement of the air intake duct to surface roughness,
But wax-pattern deforms and shell processed deformation all constrains application of the investment precision casting technology route in terms of large-scale air intake duct；And machine adds
Although work graphite mold casting process route can control deformation but titanium casting surface easily forms crackle, air intake duct surface of internal cavity is split
State of the art of the line if being unable to reach requirement without removing.
Therefore, it is necessary to study a kind of guided missile process of preparing of large titanium alloy air intake duct, can not only solve
The moulding process bottleneck of large titanium alloy air intake duct, or the high-end equipment Requirement in guided missile field provides technical support.
Invention content
The purpose of the present invention is for solve in the prior art titanium alloy air intake duct due to the elongated feature of the casting of its own,
So that the problems such as casting during precision-investment casting is also easy to produce deformation, leads to the formation crackle of air intake duct surface of internal cavity, and
Since its enclosed construction can not quickly remove crackle, the problem of being unable to reach the state of the art of requirement, a kind of titanium is provided
The process of preparing of alloy air intake duct.
The deficiency of the present invention to solve above-mentioned technical problem, used technical solution are：
A kind of guided missile process of preparing of large titanium alloy air intake duct, includes the following steps：
Step 1: air intake duct separate structure designs：According to the guided missile structure feature of large titanium alloy air intake duct, by guided missile with greatly
Being divided into for Type Titanium Alloy air intake duct is divided into ontology and several sheet bodies, and ontology and sheet body are open architecture, is conducive to titanium conjunction
The realization of gold casting last handling process；
Step 2: graphite mould is processed：According to the structure snd size of the fission and sheet body divided in step 1, using CNC milling machine plus
The corresponding graphite mould mold of work, and ensure that the dimensional accuracy of graphite mould mold is ± 0.2mm；
Step 3: surface coated treatment：It is spare to take coating, coating by powder and liquid according to（6~7）:1 weight ratio mixing
It allocates, then by spray gun prepared coating even application to graphite mould surface, spray range covering connects with titanium liquid
Tactile mold cavity surface, spray range only need the mold cavity surface that covering is contacted with titanium liquid, make sprayed surface that dull surface be presented, wait doing
After dry, the place uneven to sprayed surface carries out grinding process with sand paper, and after grinding process, spraying completion is spare；
Step 4: vacuum degassing：By in step 3 after spray treatment ontology and sheet body be fitted into vacuum furnace into
Row vacuum degassing, when shove charge, should protect not collided with for mold facecoat, prevent coating shedding, be carried out at Vacuum Heat after shove charge
Reason, whether detection mold facecoat is complete, takes the complete mold of face coat spare；
Step 5: group type：The mold prepared in step 4 is subjected to assembled formation using the method for group type stage by stage, every time dress type
After percussion, the dust in mold cavity is blown away using dry compressed air, is completed rear spare；
Step 6: moulding by casting：In corresponding each mold in molten metal steps for importing five, sheet body and this will be prepared
Body handles ontology using the hot isostatic pressing mode of adopting, spare；
Step 7: pickling：By the sheet body being prepared in step 6 and ontology, just pickling removes α layers of cast(ing) surface, and pickling makes
Acid solution ingredient is HNO3, HF and water mixture, casting is uniformly moved in acid cleaning process, ensures pickling uniformity, control
It is spare after air intake duct ontology and the unilateral thinned 0.3mm of sheet body casting；
Step 8: ontology and sheet body machining：It takes sheet body and ontology in step 6 to be machined, makes ontology and sheet body group
The gap that dress is integrated the matching part under state is not more than 0.5mm, if cannot be guaranteed weld seam more than 0.5mm laser beam weldings
All fusions, welding quality cannot be protected, spare
Step 9: ontology and sheet body laser welding：Sheet body is pressed on ontology by welding tooling, passes through laser welding
Method welds together the two, and laser beam welding need to be fixed using special tooling, and processing and fabricating welding compressing sheet body is in this
Pressing plate on body, this is selected for the routine techniques of those skilled in the art, and is not belonging to the emphasis of the application, therefore is not done in detail
Thin description；
Step 10: Stress relieving annealing：Titanium alloy inlet structure after being welded in step 9 is made annealing treatment, control heating
580 DEG C ± 14 DEG C, soaking time 1h ± 10min of temperature, vacuum degree≤0.133Pa are prepared after annealing and are completed, and obtain guided missile with greatly
Type Titanium Alloy air intake duct.
Powder is the mixture of yttrium oxide and zirconium oxide in the step three and the ratio of yttrium oxide and zirconium oxide is（90
~95）:（5~10）.
Liquid is Ludox in the step three.
The heating temperature of vacuum furnace is 900 ± 30 DEG C in the step four, and soaking time is 4 ± 0.5h, vacuum
Degree≤20Pa cools to 300 DEG C or less with the furnace and comes out of the stove.
The hot isostatic pressing uses belt carcass hot isostatic pressing.
The beneficial effects of the invention are as follows：The present invention provides a kind of preparation process sides of guided missile large titanium alloy air intake duct
Method.It is produced using the conventional equipment of graphite mould titanium alloy casting, by the integrated application of a variety of new process new departures, realizes invention
Purpose.It cannot achieve using conventional titanium alloy casting technique, the casting of conventional graphite Type Titanium Alloy is big for guided missile sheet body and ontology
Area wall thickness is only that the product of 3mm cannot achieve that fill type complete.Using the equadag coating scheme of this patent, it is molten to combine titanium alloy
The advantages of die cast, be not only effectively ensured guided missile casting to fill type complete, also enable guided missile titanium alloy casting surface roughness
The level for enough reaching 6.3 μm, the Ti alloy casting process route for realizing guided missile casting are feasible.In addition for guided missile air intake duct this
The narrow elongated structure of class is once-forming by Ti alloy casting, it cannot be guaranteed that the surface quality inside cavity, if monolithic molding,
Face crack inside cavity can not be handled, it cannot be guaranteed that the reliability of air intake duct product.Using the Laser Welding of this patent
Scheme is connect, the feasibility of air intake duct opening casting technique route is realized, and effectively prevents air intake duct cavity underbead crack
It generates.A kind of guided missile research and development spy that the process of preparing of large titanium alloy air intake duct is guided missile large titanium alloy air intake duct
A kind of new production method of rope.
The present invention have the advantages that following innovative point and：1. process is novel, novelty uses a variety of new processes newly side
The integrated application of case, efficiently solves the technical bottleneck that Ti alloy casting process route is applied in terms of large-scale air intake duct.2. belt carcass
Hot isostatic pressing makes full use of the rigidity of structure of graphite core, effectively prevent titanium casting hot isostatic pressing problem on deformation,
Improve production efficiency；3. having formulated qualified laser welding interface and laser welding process scheme, sheet body and ontology are realized
The forming of a laser welding, and using the small advantage of laser welding heat input, avoid air intake duct cavity underbead crack
It generates.
Description of the drawings
Fig. 1 is inlet structure schematic diagram.
Fig. 2 is the structural schematic diagram of ontology after air intake duct segmentation.
Fig. 3 is the structural schematic diagram of sheet body after air intake duct segmentation.
Specific implementation mode
With air-to-ground guided missile large thin-wall air intake duct casting（Overall dimension：365 × 189 × 1965mm, casting about 65%
Area be 3mm thin-wall constructions, see Fig. 1）Development process for.
A kind of guided missile process of preparing of large titanium alloy air intake duct, includes the following steps：
Step 1: air intake duct separate structure designs：According to the guided missile structure feature of large titanium alloy air intake duct, by guided missile with greatly
Being divided into for Type Titanium Alloy air intake duct is divided into ontology and a sheet body, and such as Fig. 2-3, air intake duct abdomen cover board is sheet body, remaining
For ontology, ontology and sheet body are open architecture after segmentation, realize the realization of Ti alloy casting last handling process, ontology and piece
Body is open architecture, is conducive to the realization of Ti alloy casting last handling process；
Step 2: graphite mould is processed：According to the structure snd size of the fission and sheet body divided in step 1, using CNC milling machine plus
The corresponding graphite mould mold of work, and ensure that the dimensional accuracy of graphite mould mold is ± 0.2mm；
Step 3: surface coated treatment：It is spare to take coating, coating is by powder and liquid according to 7:1 weight ratio mixing preparation
It forms, then by spray gun prepared coating even application to graphite mould surface, spray range covering is contacted with titanium liquid
Mold cavity surface, spray range only need the mold cavity surface that covering is contacted with titanium liquid, make sprayed surface that dull surface be presented, to be dried
Afterwards, the place uneven to sprayed surface carries out grinding process with sand paper, and after grinding process, spraying completion is spare；
Step 4: vacuum degassing：By in step 3 after spray treatment ontology and sheet body be fitted into vacuum furnace into
Row vacuum degassing, when shove charge, should protect not collided with for mold facecoat, prevent coating shedding, be carried out at Vacuum Heat after shove charge
The heating temperature of reason, vacuum furnace is 900 ± 30 DEG C, and soaking time is 4 ± 0.5h, and vacuum degree≤20Pa cools to the furnace
300 DEG C or less are come out of the stove, and the equadag coating after being come out of the stove using this method preparation, which is had no, to fall off；
Step 5: group type：The mold prepared in step 4 is subjected to assembled formation using the method for group type stage by stage, every time dress type
After percussion, the dust in mold cavity is blown away using dry compressed air, is completed rear spare；
Step 6: moulding by casting：In corresponding each mold in molten metal steps for importing five, sheet body and this will be prepared
Body handles ontology using the hot isostatic pressing mode of adopting, spare；
Step 7: pickling：By the sheet body being prepared in step 6 and ontology, just pickling removes α layers of cast(ing) surface, and pickling makes
Acid solution ingredient is HNO3, HF and water mixture, casting is uniformly moved in acid cleaning process, ensures pickling uniformity, control
It is spare after air intake duct ontology and the unilateral thinned 0.3mm of sheet body casting；
Step 8: ontology and sheet body machining：It takes sheet body and ontology in step 6 to be machined, makes ontology and sheet body group
The gap that dress is integrated the matching part under state is not more than 0.5mm, is coordinated using ladder between air intake duct ontology and sheet body, rank
Terraced fit clearance is 0.5mm, if cannot be guaranteed that weld seam all merges more than 0.5mm laser beam weldings, welding quality cannot obtain
It is spare to guarantee
Step 9: ontology and sheet body laser welding：Sheet body is pressed on ontology by welding tooling, passes through laser welding
Method welds together the two, and laser beam welding need to be fixed using special tooling, and processing and fabricating welding compressing sheet body is in this
Pressing plate on body, this is selected for the routine techniques of those skilled in the art, and is not belonging to the emphasis of the application, therefore is not done in detail
Thin description；
Step 10: Stress relieving annealing：Titanium alloy inlet structure after being welded in step 9 is made annealing treatment, control heating
580 DEG C ± 14 DEG C, soaking time 1h ± 10min of temperature, vacuum degree≤0.133Pa are prepared after annealing and are completed, and obtain guided missile with greatly
Type Titanium Alloy air intake duct.
Powder is the mixture of yttrium oxide and zirconium oxide in the step three and the ratio of yttrium oxide and zirconium oxide is（90
~95）:（5~10）.
Liquid is Ludox in the step three
The hot isostatic pressing uses belt carcass hot isostatic pressing.
Ti alloy casting process route is successfully passed using the method for above-mentioned this patent and has developed the large-scale air intake duct of guided missile,
The method of the patent provides new approach for the development of guided missile large-scale thin-wall titanium alloy casting.
Technical solution and embodiment cited by the present invention and non-limiting, with cited by the present invention technical solution and
Embodiment is equivalent or effect same approach is all in the range of the present invention is protected.
Claims (5)
1. a kind of guided missile process of preparing of large titanium alloy air intake duct, it is characterised in that：Include the following steps：
Step 1: air intake duct separate structure designs：According to the guided missile structure feature of large titanium alloy air intake duct, by guided missile with greatly
Being divided into for Type Titanium Alloy air intake duct is divided into ontology and several sheet bodies, and ontology and sheet body are open architecture；
Step 2: graphite mould is processed：According to the structure snd size of the fission and sheet body divided in step 1, using CNC milling machine plus
The corresponding graphite mould mold of work, and ensure that the dimensional accuracy of graphite mould mold is ± 0.2mm；
Step 3: surface coated treatment：It is spare to take coating, coating by powder and liquid according to（6~7）:1 weight ratio mixing
It allocates, then by spray gun prepared coating even application to graphite mould surface, spray range covering connects with titanium liquid
Tactile mold cavity surface makes sprayed surface that dull surface be presented, and after to be dried, the place uneven to sprayed surface is polished with sand paper
It handles, after grinding process, spraying is completed spare；
Step 4: vacuum degassing：By in step 3 after spray treatment ontology and sheet body be fitted into vacuum furnace into
Row vacuum degassing, when shove charge, should protect not collided with for mold facecoat, and vacuum heat is carried out after shove charge, detect mold table
Whether finishing coat is complete, takes the complete mold of face coat spare；
Step 5: group type：The mold prepared in step 4 is subjected to assembled formation using the method for group type stage by stage, every time dress type
After percussion, the dust in mold cavity is blown away using dry compressed air, is completed rear spare；
Step 6: moulding by casting：In corresponding each mold in molten metal steps for importing five, sheet body and this will be prepared
Body handles ontology using the hot isostatic pressing mode of adopting, spare；
Step 7: pickling：By the sheet body being prepared in step 6 and ontology, just pickling removes α layers of cast(ing) surface, and pickling makes
Acid solution ingredient is HNO3, HF and water mixture, casting is uniformly moved in acid cleaning process, ensures pickling uniformity, control
It is spare after air intake duct ontology and the unilateral thinned 0.3mm of sheet body casting；
Step 8: ontology and sheet body machining：It takes sheet body and ontology in step 6 to be machined, makes ontology and sheet body group
The gap that dress is integrated the matching part under state is not more than 0.5mm, spare
Step 9: ontology and sheet body laser welding：Sheet body is pressed on ontology by welding tooling, passes through laser welding
Method welds together the two；
Step 10: Stress relieving annealing：Titanium alloy inlet structure after being welded in step 9 is made annealing treatment, control heating
580 DEG C ± 14 DEG C, soaking time 1h ± 10min of temperature, vacuum degree≤0.133Pa are prepared and are completed, obtain guided missile and closed with Large Titanium
Golden air intake duct.
2. a kind of process of preparing of guided missile large titanium alloy air intake duct according to claim 1, it is characterised in that：
Powder is the mixture of yttrium oxide and zirconium oxide in the step three and the ratio of yttrium oxide and zirconium oxide is（90~95）:（5~
10）.
3. a kind of process of preparing of guided missile large titanium alloy air intake duct according to claim 1, it is characterised in that：
Liquid is Ludox in the step three.
4. a kind of process of preparing of guided missile large titanium alloy air intake duct according to claim 1, it is characterised in that：
In the step four heating temperature of vacuum furnace be 900 ± 30 DEG C, soaking time be 4 ± 0.5h, vacuum degree≤20Pa,
300 DEG C or less are cooled to the furnace to come out of the stove.
5. a kind of process of preparing of guided missile large titanium alloy air intake duct according to claim 1, it is characterised in that：
The hot isostatic pressing uses belt carcass hot isostatic pressing.
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Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109604412A (en) * | 2018-11-08 | 2019-04-12 | 北京航星机器制造有限公司 | A kind of aluminium alloy body built-in type air intake duct superplastic forming method |
| CN110253228A (en) * | 2019-07-09 | 2019-09-20 | 南京高精船用设备有限公司 | A kind of large-scale combined thin-wall box body accuracy of manufacture ensuring method |
| CN111036855A (en) * | 2019-11-18 | 2020-04-21 | 洛阳双瑞精铸钛业有限公司 | Forming method of titanium alloy front cover shell |
| WO2020077881A1 (en) * | 2018-10-19 | 2020-04-23 | 沈阳铸造研究所有限公司 | Precision casting method for titanium alloy casting having complex cavity structure |
| CN111375731A (en) * | 2020-03-27 | 2020-07-07 | 洛阳双瑞精铸钛业有限公司 | Integral preparation process of large-scale framework high-temperature titanium alloy casting |
| CN111421108A (en) * | 2020-05-15 | 2020-07-17 | 沈阳飞机工业（集团）有限公司 | Preparation method of mold shell of thin-wall titanium alloy casting with complex structure |
| CN112355576A (en) * | 2020-10-16 | 2021-02-12 | 西安北方光电科技防务有限公司 | Machining method for high-precision wing-shaped elastic shaft part |
| CN113787311A (en) * | 2021-09-14 | 2021-12-14 | 南通市荣泰电化学设备制造有限公司 | Preparation process of titanium polar plate with firmly-adhered coating |
| CN114850784A (en) * | 2022-03-28 | 2022-08-05 | 洛阳双瑞精铸钛业有限公司 | Preparation method of titanium and titanium alloy H section bar |
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Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2020077881A1 (en) * | 2018-10-19 | 2020-04-23 | 沈阳铸造研究所有限公司 | Precision casting method for titanium alloy casting having complex cavity structure |
| CN109604412A (en) * | 2018-11-08 | 2019-04-12 | 北京航星机器制造有限公司 | A kind of aluminium alloy body built-in type air intake duct superplastic forming method |
| CN110253228A (en) * | 2019-07-09 | 2019-09-20 | 南京高精船用设备有限公司 | A kind of large-scale combined thin-wall box body accuracy of manufacture ensuring method |
| CN111036855A (en) * | 2019-11-18 | 2020-04-21 | 洛阳双瑞精铸钛业有限公司 | Forming method of titanium alloy front cover shell |
| CN111375731B (en) * | 2020-03-27 | 2021-10-26 | 洛阳双瑞精铸钛业有限公司 | Integral preparation process of large-scale framework high-temperature titanium alloy casting |
| CN111375731A (en) * | 2020-03-27 | 2020-07-07 | 洛阳双瑞精铸钛业有限公司 | Integral preparation process of large-scale framework high-temperature titanium alloy casting |
| CN111421108A (en) * | 2020-05-15 | 2020-07-17 | 沈阳飞机工业（集团）有限公司 | Preparation method of mold shell of thin-wall titanium alloy casting with complex structure |
| CN112355576A (en) * | 2020-10-16 | 2021-02-12 | 西安北方光电科技防务有限公司 | Machining method for high-precision wing-shaped elastic shaft part |
| CN112355576B (en) * | 2020-10-16 | 2022-04-12 | 西安北方光电科技防务有限公司 | Machining method for high-precision wing-shaped elastic shaft part |
| CN113787311A (en) * | 2021-09-14 | 2021-12-14 | 南通市荣泰电化学设备制造有限公司 | Preparation process of titanium polar plate with firmly-adhered coating |
| CN113787311B (en) * | 2021-09-14 | 2022-03-18 | 南通市荣泰电化学设备制造有限公司 | Preparation process of titanium polar plate with firmly-adhered coating |
| CN114850784A (en) * | 2022-03-28 | 2022-08-05 | 洛阳双瑞精铸钛业有限公司 | Preparation method of titanium and titanium alloy H section bar |
| CN114850784B (en) * | 2022-03-28 | 2023-06-02 | 洛阳双瑞精铸钛业有限公司 | Preparation method of titanium and titanium alloy H-shaped material |
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Application publication date: 20180831 |