CN100448659C - Titanium-alloy special section and its production - Google Patents
Titanium-alloy special section and its production Download PDFInfo
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- CN100448659C CN100448659C CNB200610057901XA CN200610057901A CN100448659C CN 100448659 C CN100448659 C CN 100448659C CN B200610057901X A CNB200610057901X A CN B200610057901XA CN 200610057901 A CN200610057901 A CN 200610057901A CN 100448659 C CN100448659 C CN 100448659C
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- 229910001069 Ti alloy Inorganic materials 0.000 title claims abstract description 30
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 21
- 238000000034 method Methods 0.000 claims abstract description 36
- 238000001816 cooling Methods 0.000 claims abstract description 34
- 238000000465 moulding Methods 0.000 claims abstract description 34
- 239000000463 material Substances 0.000 claims abstract description 32
- 238000005516 engineering process Methods 0.000 claims abstract description 14
- 239000010410 layer Substances 0.000 claims abstract description 8
- 239000011159 matrix material Substances 0.000 claims abstract description 7
- 229910045601 alloy Inorganic materials 0.000 claims abstract description 4
- 239000000956 alloy Substances 0.000 claims abstract description 4
- 239000011229 interlayer Substances 0.000 claims abstract description 4
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 15
- 238000005520 cutting process Methods 0.000 claims description 14
- 238000009792 diffusion process Methods 0.000 claims description 10
- 238000010276 construction Methods 0.000 claims description 7
- 239000011521 glass Substances 0.000 claims description 6
- 230000015572 biosynthetic process Effects 0.000 claims description 5
- 238000004140 cleaning Methods 0.000 claims description 5
- 238000009434 installation Methods 0.000 claims description 5
- 229910052751 metal Inorganic materials 0.000 claims description 5
- 239000002184 metal Substances 0.000 claims description 5
- 229910000679 solder Inorganic materials 0.000 claims description 5
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims description 3
- 239000000314 lubricant Substances 0.000 claims description 3
- 238000005554 pickling Methods 0.000 claims description 3
- 238000004321 preservation Methods 0.000 claims description 3
- 239000003223 protective agent Substances 0.000 claims description 3
- 239000011265 semifinished product Substances 0.000 claims description 3
- 239000002195 soluble material Substances 0.000 claims description 3
- 239000010936 titanium Substances 0.000 claims description 3
- 229910052719 titanium Inorganic materials 0.000 claims description 3
- 238000001035 drying Methods 0.000 claims description 2
- 238000002360 preparation method Methods 0.000 claims description 2
- 238000005495 investment casting Methods 0.000 abstract description 3
- 230000000630 rising effect Effects 0.000 abstract 1
- 239000012809 cooling fluid Substances 0.000 description 4
- 238000009413 insulation Methods 0.000 description 3
- 239000007787 solid Substances 0.000 description 2
- 238000003466 welding Methods 0.000 description 2
- 241000896524 Sarcophaga par Species 0.000 description 1
- 239000002253 acid Substances 0.000 description 1
- 239000011538 cleaning material Substances 0.000 description 1
- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 230000002950 deficient Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 239000000047 product Substances 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 238000005201 scrubbing Methods 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
Abstract
The invention discloses a kind of titanium alloy profile wire. The related tianium alloy profile wire is a board with multilayer titanium alloy hollow structure which involves interlayer with cooling slots. It is made up of the inner scale board with the thickness from 0.3mm to 1.0mm, the outer layer's titanium alloy board with the thickness from 0.3mm to 1.0mm, and the titanium alloy interlayer board with cooling slots between the above mentioned two boards. The molecule infilterating between layers forms a homogeneous matrix with no interface with the thickness from 2.0mm to 10.00mm.The process for manufacturing the board includes following steps: the manufacture of the mould, the preparing and manufacture of the board, installing and molding of the mould with rising temperature, diffusing connection, the first molding, the second molding, cooling and incising process border. It makes use of the technology of combination of SPF and DB, makes application of the technology of the dissolveable screw-demolding core in the investment casting production process. Through twice molding, it accomplishes the processing of the titanium alloy profile wire, makes it the functional material. It provides the aircraft's cabin with the material which has the cooling function under the assurance of the intensity and stiffness. It has a good perspective for its wide application.
Description
Technical field
The present invention relates to a kind of manufacture method of titanium-alloy special section.
Background technology
Along with aircraft requires to leap more soon, the cooling of aircraft skin requires more and more higher, and the appearance and size of aircraft then requires more and more littler, and payload needs again to improve, and has higher requirement to cooling effectiveness.
Traditional aircraft skin all is a solid slab, and the difference according to functor requires in the inboard or outside increase thermal insulation layer again.And the metal solid slab is whole the heat transfer, and heat transfer rate is very rapid.
Summary of the invention
The technical issues that need to address of the present invention just are to overcome the existing dissatisfactory defective of aircraft skin cooling effect, a kind of manufacture method of titanium-alloy special section is provided, it is designed to hollow-core construction, and hollow-core construction is designed to lead to the runner of cooling fluid, can not only make volumetric heat transfer become line like this and conduct heat, it is heat insulation to increase large-area cooling fluid, considers structural strength and rigidity simultaneously, just formed when guaranteeing same intensity and rigidity, satisfied the cooling requirement to greatest extent.It has utilized the titanium alloy superplastic formation to be connected COMBINED PROCESS with diffusion, used the soluble core technology in the precision casting process dexterously, by post forming, finished the processing of titanium-alloy special section material, make it become functional material, for aircraft cabin body provides under the condition of proof strength and rigidity, have the material of refrigerating function, be with a wide range of applications.
For addressing the above problem, the present invention adopts following technical scheme:
The manufacture method of a kind of titanium-alloy special section of the present invention, it comprises the following steps: the manufacturing of water-soluble core, the sheet material preparation, the installation mold and the moulding that heats up, diffusion connects, moulding for the first time, moulding for the second time, cooling and cutting technique limit, the titanium-alloy special section that manufactures is the laminated titanium-alloy hollow-core construction sheet material of band cooling bath interlayer, it is the titanium lined alloy sheets of 0.3～1.0mm by thickness, thickness is the outer titanium alloy sheet of 0.3～1.0mm, and the titanium alloy cooling bath sandwich plate between interior lining panel and the lamina rara externa constitutes, molecule between each flaggy interpenetrates, form the matrix of the same race at no interface, sheet metal thickness is 2.0～10.0mm.
The manufacturing of water-soluble core described in the inventive method is adopted the water-soluble core post forming according to cooling bath sandwich, after finishing moulding first, water dissolves water-soluble core, carry out post forming again, select water-soluble material for use, process its profile with Digit Control Machine Tool, make it to meet the requirement of cooling bath sandwich.
Sheet material described in the inventive method is prepared as the accurate blanking of carrying out spread material with the water under high pressure cutting machine, after the pickling oven dry, be coated with solder resist, and secondary drying, make activated surface with outer activated surface and the technology limit is clear separates, lay water-soluble core, and it is spacing fixing, the titanium alloy plate of 4 layers of different-thickness stacked and the welder limit of planting makes it form seal hatch, weld suction nozzle and outlet nozzle afterwards.
The installation mold described in the inventive method and the moulding that heats up, diffusion connect, band cooling bath sandwich forming step is clean for manufactured mould is cleaned, coat lubricant and protective agent, be installed on 900 tons of superplastic formation machines, carry out cold die trial qualified after, begin to heat up, design temperature is 920 ℃; When furnace temperature and mold temperature evenly reach 920 ℃ ± 13 ℃, open fire door, the sheet material that welds the technology limit is put into mould, preheating 40 minutes, close die applies curve pressure by technological procedure afterwards, in 5 minutes, make the mould pressure-pad-force reach 650 tons, pressure-maintaining and heat-preservation 2 hours spreads the molecule that is activated fully, forms same matrix.
In the inventive method for the first time forming step for after finishing diffusion and connecting, subchannel increases air pressure, keep 940 ℃ ± 10 ℃ moulding of finishing the facade direction earlier, pressure is 200 ± 20 tons, 45 minutes dwell times, finish the moulding of plane of structure direction again, pressure is 240 ± 20 tons, 45 minutes dwell times.
After forming step was moulding for the first time for the second time in the inventive method, the sheet material after the taking-up moulding was placed on air cooling on the glass mat, after the water-soluble core stripping, and cleaning components and dry for standby; The semi-finished product that take out water-soluble core are put into 940 ± 10 ℃ mould, increase air pressure to 350 ± 20 ton, the dwell time is 40 minutes.
Cooling and cutting technique limit step described in the inventive method are the sheet material after the taking-up moulding, are placed on air cooling on the glass mat, and the sheet material behind the above-mentioned air cooling is placed on the water under high pressure cutting equipment, cut away the technology limit with water under high pressure, meet the requirements of size.
The present invention has utilized the titanium alloy superplastic formation to be connected COMBINED PROCESS with diffusion, used the soluble core technology in the precision casting process dexterously, by post forming, finished the processing of titanium-alloy special section material, make it become functional material, for aircraft cabin body provides under the condition of proof strength and rigidity, have the material of refrigerating function, be with a wide range of applications.
The present invention designs hollow-core construction, and hollow-core construction is designed to lead to the runner of cooling fluid, can not only make volumetric heat transfer become line like this conducts heat, it is heat insulation to increase large-area cooling fluid, consider structural strength and rigidity simultaneously, just formed when guaranteeing same intensity and rigidity, satisfied the cooling requirement to greatest extent.
The specific embodiment
1, mould design:
Consider the special construction of cooling duct, gas pressure can't one time-completion shaping, so need the design water-soluble core, after finishing moulding first, water dissolves water-soluble core, carries out post forming again, realizes finally design.
2, the manufacturing of core
Select water-soluble material for use, process its profile, adhere to specification with Digit Control Machine Tool.
3, blanking
The flowability of material when high temperature deformation amount by calculating the different-thickness titanium alloy plate and inflation moulding, determine scaling coefficient and blank size, and utilize the water under high pressure cutting machine carry out accurate blanking (precision of water cutting equipment for ± 0.05mm), effectively processing dimension is 2000 * 4000 * 300mm, U.S. PAR company produces), the water cutting stock mainly is to produce metal congruent melting layer for fear of when cutting, influence back operation welding quality.
4, pickling
In weak acid solution, soaked 50-60 minute, add manual auxiliary scrubbing afterwards, use the clear water rinsing afterwards again, reach the purpose on oil removing and cleaning material surface.
5, oven dry
In baking oven, dry the sheet material of above-mentioned rinsing with 120 ℃ ± 10 ℃ temperature.
6, pasting protective film
Change the sheet material after the oven dry in the clean workplace workbench, paste the coating protection film.
7, be coated with solder resist
Be coated with solder resist by technological procedure, and with its oven dry.
8, remove diaphragm
Remove diaphragm, make activated surface with outer activated surface and the technology limit is clear separates.
9, lay water-soluble core
Lay water-soluble core, and it is spacing fixing.
10, the welder limit of planting
To (contain three layers) more than 3 layers, 0.2～5.0mm, the sheet material that equal thickness or non-equal thickness have coated solder resist and removed diaphragm stacks, and the welding procedure limit makes it form seal hatch, welds suction nozzle and outlet nozzle afterwards.
11, the installation mold and the former that heats up
Manufactured mould cleaning is clean; coat lubricant and protective agent; be installed in that (this equipment is four column hydraulic structures, and effectively work area is 1500 * 2500 * 1100mm, electrothermal tube subregion heat form on 900 tons of superplastic formation machines that U.S. ACCUDYNE company produces; temperature homogeneity is ± 10 ℃; extensible formula pottery workbench, 1100 ℃ of maximum operating temperatures), carry out cold die trial qualified after; begin to heat up, design temperature is 920 ℃.
12, diffusion connects
When furnace temperature and mold temperature evenly reach 920 ℃ ± 13 ℃, open fire door, the sheet material that welds the technology limit is put into mould, preheating 40 minutes, close die applies curve pressure by technological procedure afterwards, in 5 minutes, make the mould pressure-pad-force reach 650 tons, pressure-maintaining and heat-preservation 2 hours spreads the molecule that is activated fully, forms same matrix.
13, moulding for the first time
After finishing the diffusion connection, subchannel increases air pressure, keeps 940 ℃ ± 10 ℃ moulding of finishing the facade direction earlier, and pressure is 200 ± 20 tons, 45 minutes dwell times, finish the moulding of plane of structure direction again, and pressure is 240 ± 20 tons, 45 minutes dwell times.
14, pickup and cooling
After finishing moulding, open fire door, shift out workbench, take off temperature thermocouple, the sheet material with after the overhead traveling crane taking-up moulding is placed on air cooling on the glass mat.
15, take out insoluble core
After the water-soluble core stripping, cleaning components and dry for standby.
16, moulding for the second time
The semi-finished product that take out water-soluble core are put into 940 ± 10 ℃ mould, increase air pressure to 350 ± 20 ton, the dwell time is 40 minutes.
17, pickup and cooling
After finishing moulding, open fire door, shift out workbench, take off temperature thermocouple, the sheet material with after the overhead traveling crane taking-up moulding is placed on air cooling on the glass mat.
18, cutting technique limit
Sheet material behind the above-mentioned air cooling is placed on the water under high pressure cutting equipment, cut away the technology limit, meet the requirements of size with water under high pressure.
Can produce titanium-alloy special section by above-mentioned steps, its titanium lined alloy sheets thickness be 0.3～1.0mm, outer titanium alloy sheet thickness be 0.3～1.0mm, be titanium alloy cooling bath sandwich plate between interior lining panel and the lamina rara externa, molecule between each flaggy interpenetrates, form the matrix of the same race at no interface, the titanium-alloy special section sheet metal thickness is 2.0～10.0mm.
The present invention is not limited to above-mentioned preferred forms, and other any identical with the present invention or akin products that anyone draws under enlightenment of the present invention all drop within protection scope of the present invention.
Claims (7)
1, a kind of manufacture method of titanium-alloy special section is characterized in that it comprises the following steps: manufacturing, sheet material preparation, installation mold and the moulding that heats up, diffusion connection, moulding for the first time, moulding for the second time, cooling and the cutting technique limit of water-soluble core; The titanium-alloy special section that manufactures is the laminated titanium-alloy hollow-core construction sheet material of band cooling bath interlayer, it by thickness be the titanium lined alloy sheets of 0.3～1.0mm, outer titanium alloy sheet that thickness is 0.3～1.0mm, and interior lining panel and lamina rara externa between titanium alloy cooling bath sandwich plate constitute, molecule between each flaggy interpenetrates, form the matrix of the same race at no interface, sheet metal thickness is 2.0～10.0mm.
2, manufacture method as claimed in claim 1, the water-soluble core post forming is adopted in the manufacturing that it is characterized in that described water-soluble core, after finishing moulding first, water dissolves water-soluble core, carry out post forming again, select water-soluble material for use, process its profile, make it to meet the requirement of cooling bath sandwich with Digit Control Machine Tool.
3, manufacture method as claimed in claim 1, it is characterized in that described sheet material is prepared as the accurate blanking of carrying out spread material with the water under high pressure cutting machine, after the pickling oven dry, be coated with solder resist, and secondary drying, make activated surface with outer activated surface and the technology limit is clear separates, lay water-soluble core, and it is spacing fixing, the titanium alloy plate of 4 layers of different-thickness stacked and the welder limit of planting makes it form seal hatch, weld suction nozzle and outlet nozzle afterwards.
4, manufacture method as claimed in claim 1, it is characterized in that the described installation mold and the moulding that heats up, diffusion Connection Step are for clean with manufactured mould cleaning, coat lubricant and protective agent, be installed on 900 tons of superplastic formation machines, carry out cold die trial qualified after, begin to heat up, design temperature is 920 ℃; When furnace temperature and mold temperature evenly reach 920 ℃ ± 13 ℃, open fire door, the sheet material that welds the technology limit is put into mould, preheating 40 minutes, close die applies curve pressure by technological procedure afterwards, in 5 minutes, make the mould pressure-pad-force reach 650 tons, pressure-maintaining and heat-preservation 2 hours spreads the molecule that is activated fully, forms same matrix.
5, manufacture method as claimed in claim 1, it is characterized in that described first time forming step is for after finishing diffusion and connecting, subchannel increases air pressure, keep 940 ℃ ± 10 ℃ moulding of finishing the facade direction earlier, pressure is 200 ± 20 tons, 45 minutes dwell times, finishes the moulding of plane of structure direction again, pressure is 240 ± 20 tons, 45 minutes dwell times.
6, manufacture method as claimed in claim 1, it is characterized in that described second time forming step for moulding for the first time after, take out the sheet material after the moulding, be placed on air cooling on the glass mat, after the water-soluble core stripping, cleaning components and dry for standby; The semi-finished product that take out water-soluble core are put into 940 ± 10 ℃ mould, increase air pressure to 350 ± 20 ton, the dwell time is 40 minutes.
7, manufacture method as claimed in claim 1, it is characterized in that the sheet material after described cooling and cutting technique limit step are for the taking-up moulding, be placed on air cooling on the glass mat, the sheet material behind the above-mentioned air cooling is placed on the water under high pressure cutting equipment, cut away the technology limit with water under high pressure, meet the requirements of size.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB200610057901XA CN100448659C (en) | 2006-02-27 | 2006-02-27 | Titanium-alloy special section and its production |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB200610057901XA CN100448659C (en) | 2006-02-27 | 2006-02-27 | Titanium-alloy special section and its production |
Publications (2)
| Publication Number | Publication Date |
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| CN101029703A CN101029703A (en) | 2007-09-05 |
| CN100448659C true CN100448659C (en) | 2009-01-07 |
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| CNB200610057901XA Active CN100448659C (en) | 2006-02-27 | 2006-02-27 | Titanium-alloy special section and its production |
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Families Citing this family (9)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN102335878A (en) * | 2010-07-19 | 2012-02-01 | 江海青 | Novel processing method of metal connecting rod |
| CN102990299B (en) * | 2012-11-21 | 2015-04-29 | 中国航空工业集团公司北京航空制造工程研究所 | Preparation method for X-type titanium alloy three-dimensional lattice sandwich structure |
| CN102990300B (en) * | 2012-11-21 | 2015-04-29 | 中国航空工业集团公司北京航空制造工程研究所 | Preparation method of titanium alloy three-dimensional lattice sandwich structure |
| CN102990514A (en) * | 2012-12-06 | 2013-03-27 | 无锡透平叶片有限公司 | Method for cutting flashes of blade forged piece |
| CN105290739B (en) * | 2015-11-24 | 2018-09-07 | 中国航空工业集团公司北京航空制造工程研究所 | The laying increasing material manufacturing method of abnormally-structured titanium alloy member based on diffusion connection |
| CN108372356B (en) * | 2016-12-21 | 2020-09-08 | 中国航空制造技术研究院 | Crushing method for aluminum alloy surface oxide film |
| CN108161346A (en) * | 2017-12-08 | 2018-06-15 | 北京星航机电装备有限公司 | A kind of Ti2The preparation method of AlNb/TA15 bimetallic titanium alloy composite hollow structures |
| CN113369663B (en) * | 2019-01-08 | 2022-11-01 | 浙江大学台州研究院 | Thermoplastic connection method of amorphous alloy |
| CN112775311A (en) * | 2020-12-24 | 2021-05-11 | 中航贵州飞机有限责任公司 | Low-cost pressure testing method for titanium and titanium alloy thermal forming die |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3927817A (en) * | 1974-10-03 | 1975-12-23 | Rockwell International Corp | Method for making metallic sandwich structures |
| US4217397A (en) * | 1978-04-18 | 1980-08-12 | Mcdonnell Douglas Corporation | Metallic sandwich structure and method of fabrication |
| US4916027A (en) * | 1988-01-21 | 1990-04-10 | Rockwell International Corporation | Primary structure multi-layer insulation |
| US5534354A (en) * | 1991-12-17 | 1996-07-09 | The Boeing Company | Multiple density sandwich structures |
-
2006
- 2006-02-27 CN CNB200610057901XA patent/CN100448659C/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3927817A (en) * | 1974-10-03 | 1975-12-23 | Rockwell International Corp | Method for making metallic sandwich structures |
| US4217397A (en) * | 1978-04-18 | 1980-08-12 | Mcdonnell Douglas Corporation | Metallic sandwich structure and method of fabrication |
| US4916027A (en) * | 1988-01-21 | 1990-04-10 | Rockwell International Corporation | Primary structure multi-layer insulation |
| US5534354A (en) * | 1991-12-17 | 1996-07-09 | The Boeing Company | Multiple density sandwich structures |
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| CN101029703A (en) | 2007-09-05 |
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