CN106881561A - A kind of preparation method of titanium alloy thin wall multilayer hollow structure - Google Patents
A kind of preparation method of titanium alloy thin wall multilayer hollow structure Download PDFInfo
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- CN106881561A CN106881561A CN201510940511.6A CN201510940511A CN106881561A CN 106881561 A CN106881561 A CN 106881561A CN 201510940511 A CN201510940511 A CN 201510940511A CN 106881561 A CN106881561 A CN 106881561A
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- hollow structure
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- 229910001069 Ti alloy Inorganic materials 0.000 title claims abstract description 34
- 238000002360 preparation method Methods 0.000 title claims abstract description 13
- 238000009792 diffusion process Methods 0.000 claims abstract description 82
- 239000000463 material Substances 0.000 claims abstract description 20
- 238000000034 method Methods 0.000 claims description 20
- 238000012360 testing method Methods 0.000 claims description 16
- 239000011162 core material Substances 0.000 claims description 12
- 238000010276 construction Methods 0.000 claims description 7
- 238000003466 welding Methods 0.000 claims description 7
- 238000009413 insulation Methods 0.000 claims description 4
- 238000013461 design Methods 0.000 abstract description 6
- 238000007493 shaping process Methods 0.000 abstract description 6
- 230000007812 deficiency Effects 0.000 abstract description 2
- 238000012372 quality testing Methods 0.000 abstract 1
- 239000010410 layer Substances 0.000 description 31
- 238000005516 engineering process Methods 0.000 description 6
- 239000000956 alloy Substances 0.000 description 4
- 238000012545 processing Methods 0.000 description 4
- 229910045601 alloy Inorganic materials 0.000 description 2
- 238000007689 inspection Methods 0.000 description 2
- 238000003754 machining Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 238000005554 pickling Methods 0.000 description 2
- 239000002356 single layer Substances 0.000 description 2
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004140 cleaning Methods 0.000 description 1
- 239000013078 crystal Substances 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000001514 detection method Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000001125 extrusion Methods 0.000 description 1
- 238000007731 hot pressing Methods 0.000 description 1
- 239000002648 laminated material Substances 0.000 description 1
- 239000011159 matrix material Substances 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 238000003825 pressing Methods 0.000 description 1
- 238000003892 spreading Methods 0.000 description 1
- 239000000758 substrate Substances 0.000 description 1
- 239000010936 titanium Substances 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
Classifications
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B1/00—Layered products having a non-planar shape
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B15/00—Layered products comprising a layer of metal
- B32B15/01—Layered products comprising a layer of metal all layers being exclusively metallic
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
- B32B3/26—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer
- B32B3/30—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids ; characterised by an apertured layer characterised by a layer formed with recesses or projections, e.g. hollows, grooves, protuberances, ribs
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Pressure Welding/Diffusion-Bonding (AREA)
- Shaping Metal By Deep-Drawing, Or The Like (AREA)
Abstract
The present invention provides a kind of preparation method of titanium alloy thin wall multilayer hollow structure, and titanium alloy thin wall multilayer hollow structure is obtained by steps such as the independent hot-forming, assembling of panel sandwich layer, overall diffusion connections.Panel of the present invention and sandwich layer are separately formed, with inner chamber forming accuracy is high, design freedom big, materials'use scope is wide, inner chamber Accurate Shaping problem, the quality testing problem of internal structure of multilayer hollow structure are avoided, and inside and outside Rotating fields can not be using the deficiency of foreign material.
Description
Technical field
The present invention relates to a kind of preparation method of titanium alloy thin wall multilayer hollow structure, more particularly to xenogenesis titanium is closed
The preparation method of golden multilayer hollow structure, belongs to titanic alloy machining technical field.
Background technology
Titanium alloy, can be with superior decay resistance with excellent fatigue resistance used as high specific strength metal material, its
Operating temperature range, up to 650 DEG C, is that Aero-Space engine system and high Mach flight device structural member are preferable
Candidate materials.However, resistance of deformation is big under titanium alloy normal temperature, plasticity is poor, resilience is serious, using cold forming work
Skill flexible extrusion molding technique difficulty is larger.
Superplasticforming/the Diffusion bonding techniques of titanium alloy are using excellent deformation of the material under superplastic state
Performance and a kind of new technology for spreading switching performance and growing up.When titanium alloy is in superplastic state, its
Good flowing properties, it is easy to fill, so as to be easily formed out complex-shaped constitutional detail.
Since titanium alloy superplastic forming/diffusion connection (SPF/ has invented in Rockwell International of the U.S. in 1970
DB) after group technology, technique rapidly becomes manufacture titanium alloy structure part and looks steadily throughout the world with its unique superiority
Purpose new technology.The method is the superplasticity and the diffusion connection performance in same thermal gauge model for utilizing material,
Realize not only having shaped but also having connected in one cycle, make the different entirety for being difficult to prepare using common process and tie
Component.Integrated, functional product, weight saving, cost reduction can be made by this technique.
The structure type of common superplastic forming/diffusion connection is multi-layer hollow structure type, multi-layer hollow structure
Form uses three ply board, and its technical process is as shown in figure 1, be that gas is first loaded in mold cavity so that three layers
There is diffusion connection between plate, air inlet pastes three ply board superplastic forming between three ply board after the completion of diffusion connection
Film, obtains product as shown in Figure 2, realizes that the diffusion connection of sandwich layer only has pattern tool to seal at high temperature, right
Mould and die accuracy requirement is high, and the loading accuracy of equipment also requires that height, and the forming accuracy of its inner chamber depends on centre
The Free Transform coordination degree of two-layer, control difficulty is big, and forming quality and diffusion defect are difficult detection.
At present, in order to improve the purpose of temperature in use and reduces cost, wish to realize in multiple layers in hollow structure
Using high-temperature titanium alloy, sandwich layer uses common alloy of titanium to panel, and existing superplastic forming/diffusion connecting process
Also the processing between xenogenesis titanium alloy cannot be realized.
The content of the invention
It is an object of the invention to overcome prior art not enough, there is provided a kind of inner chamber forming quality is high and easy inspection
Survey, the preparation method that xenogenesis titanium alloy thin wall multilayer hollow structure can be realized.
Technical solution of the invention：A kind of preparation method of titanium alloy thin wall multilayer hollow structure, by with
Lower step is realized：
The first step, single sheathing and sandwich layer are hot-forming；
The shape manufacture heat pressing and molding mold of panel and sandwich layer according to the multilayer hollow structure to be prepared, hot pressing work
Skill is selected according to the material of panel and sandwich layer.Because panel of the present invention and sandwich layer are individually to be hot pressed into
Type, therefore the design of its shape can be with more flexible, it is to avoid in traditional superplastic forming/diffusion connecting process, panel
The design limitations caused because superplastic forming pastes mould with core shape.
Second step, sandwich construction assembling,
The panel and sandwich layer that the first step is processed are overlapped and are assembled together；
Can be assembled by frock, the sandwich construction after assembling is positioned to accurately, prevent from being misplaced between each layer.
3rd step, overall diffusion connection,
The sandwich construction that second step is assembled in a vacuum furnace, carries out overall diffusion welding (DW), obtains titanium alloy thin wall many
Layer hollow structure, diffusion welding craft is, in TXBAt ± 10 DEG C, heat-insulation pressure keeping is not less than 1h, then in TMB±10℃
Under, heat-insulation pressure keeping is not less than 1h, wherein TXBIt is the optimal diffusion temperature of core material, TMBFor panel material is optimal
Diffusion temperature.
Processing parameter setting needed for other diffusion welding (DW)s is this area diffusion welding (DW) universal means, and those skilled in the art can
To be selected as needed.
The optimal diffusion temperature T of core materialXBDetermine that method is as follows：
A3.1, the diffusion connection temperature range [T in core materialXmin,TXmax] in, select different diffusion temperatures to enter
The diffusion connection of row sandwich layer test specimen；Wherein TXmin、TXmaxFor core material can be diffused the minimum of connection and most
High-temperature, the selection of diffusion temperature will cover diffusion connection temperature range, be typically chosen adjacent diffusion temperature poor
It is 10~15 DEG C.
Sandwich layer test specimen under A3.2, the different diffusion temperatures obtained to step A3.1 carries out tension test, obtains
Sandwich layer test specimen tensile strength under different diffusion temperatures；Tension test is specifically shown in GB228.1-2010.
A3.3, according to the sandwich layer test specimen tensile strength under different diffusion temperatures, fitting obtains the diffusion temperature of sandwich layer
- tensile strength curve；
A3.4, the diffusion temperature-tensile strength curve according to sandwich layer, obtain the corresponding diffusion of maximum pulling strength
Temperature is the optimal diffusion temperature T of core materialXB。
The optimal diffusion temperature T of panel materialMBDetermination method with the optimal diffusion temperature T of core materialXBIt is determined that side
Method, does not just repeat one by one herein.
From T within 2 hours in the overall diffusion connectionXBRise to TMB, can otherwise be grown up influence material because of crystal grain
Material substrate performance and the welding quality of overall diffusion connection.
Present invention beneficial effect compared with prior art：
(1) panel of the present invention and sandwich layer are separately formed, with inner chamber forming accuracy is high, design freedom big,
Materials'use scope is wide, it is to avoid the inner chamber Accurate Shaping problem of multilayer hollow structure, the inspection of the quality of internal structure
Problem is surveyed, and inside and outside Rotating fields can not be using the deficiency of foreign material；
(2) present invention can prepare the panel gradient-structure different with core material, and such as panel uses high temperature titanium
Alloy and sandwich layer uses common alloy of titanium, the purpose of temperature in use and reduces cost is improved so as to reach；
(3) present invention determine that the technique of overall diffusion connection, it is ensured that connection matter between xenogenesis titanium alloy
Amount, by alternating temperature diffusion connecting process may be such that the tensile strength of jointing reach weaker matrix material 80~
95%；
(4) present invention has flexible designability and changeable environmental suitability, and forming quality is reliable, raw
The product cycle is shorter, and technology, economic benefit are obvious.
Figure of description
Fig. 1 is superplastic forming/diffusion connection diagram；
Fig. 2 is titanium alloy thin wall multilayer hollow structural representation；
Fig. 3 prepares titanium alloy thin wall multilayer hollow structure flow chart for the present invention.
Specific embodiment
Below in conjunction with accompanying drawing and instantiation, the present invention is described in detail.
Using Ti55, TC4 titanium alloy plate for meeting air standard, sheet metal thickness is 1.2mm.
This example by following steps as shown in figure 3, realized：
1st, panel, sandwich layer are individually hot-forming
Mold design and processing：It is QTRSi4Mo to select mold materials according to use condition.According to individual layer part
Appearance profile, while considering the linear expansion coefficient design mold cavity of product and mould.
Plate cutting：According to panel and sandwich layer measure, in this embodiment, covering and sandwich layer need blanking 4 altogether
Laminate material, specification 1500*500*1.2mm.
Single layer structure shapes：Upper and lower panel and upper and lower the sandwich layer independent hot forming of totally 4 Rotating fields, such as upper and lower panel
1 mold symmetrically then can be respectively shared with upper and lower sandwich layer, is 1 mold shaping upper and lower panel in embodiment,
1 mold shapes upper and lower sandwich layer.Wherein upper and lower panel is Ti55 titanium alloy materials, hot forming temperature 850
± 10 DEG C, shaping feed rate 0.03Mpa/ minutes；Upper and lower sandwich layer is TC4 titanium alloy materials, hot forming
800 ± 10 DEG C of temperature, shaping feed rate 0.01Mpa/ minutes.
Part pickling：Panel after shaping and sandwich layer part are machined by matching requirements, are pressed after processing
Standard carries out pickling, holding surface cleaning.
2nd, sandwich construction assembling
Single layer structure is accurately positioned using frock, is superimposed, assembled.
3rd, overall diffusion connection
The sandwich construction that will be assembled enters diffusion in vacuum stove, carries out overall diffusion connection；
It is determined that optimal diffusion temperature, the optimal diffusion temperature of panel Ti55 titanium alloys is 925 DEG C, sandwich layer TC4 titaniums
The optimal diffusion temperature of alloy is 850 DEG C, it is determined that the technique of overall diffusion connection is 850 ± 10 DEG C, is incubated 1h,
925 ± 10 DEG C are risen in 1h again, 1h is incubated, vacuum is maintained at 10 in diffusion process-2Pa, forming pressure
It is 2MPa.
4th, side removes to form final products more than technique, using machining removal technique more than side, reach size will
Ask, form final products.
Tensile strength actual measurement is 950MPa wherein at Diffusion Bonding Joint, is the 95% of the TC4 strengths of materials, and
Due to panel use Ti55 titanium alloys so that its temperature in use improve 100 DEG C (in 1 hour), achieve compared with
Good technique effect.
Unspecified part of the present invention is known to the skilled person technology.
Claims (6)
1. a kind of preparation method of titanium alloy thin wall multilayer hollow structure, it is characterised in that by following steps
Realize：
The first step, single sheathing and sandwich layer are hot-forming；
Second step, sandwich construction assembling,
The panel and sandwich layer that the first step is processed are overlapped and are assembled together；
3rd step, overall diffusion connection,
The sandwich construction that second step is assembled in a vacuum furnace, carries out overall diffusion welding (DW), obtains titanium alloy thin wall many
Layer hollow structure, diffusion welding craft is, in TXBAt ± 10 DEG C, heat-insulation pressure keeping is not less than 1h, then in TMB±10℃
Under, heat-insulation pressure keeping is not less than 1h, wherein TXBIt is the optimal diffusion temperature of core material, TMBFor panel material is optimal
Diffusion temperature.
2. the preparation method of a kind of titanium alloy thin wall multilayer hollow structure according to claim 1, it is special
Levy and be：The optimal diffusion temperature T of 3rd step SMIS layer materialXBDetermine that method is as follows：
A3.1, the diffusion connection temperature range [T in core materialX min,TX max] in, select different diffusion temperatures to enter
The diffusion connection of row sandwich layer test specimen, wherein TX min、TX maxFor core material can be diffused the minimum of connection and most
High-temperature；
Sandwich layer test specimen under A3.2, the different diffusion temperatures obtained to step A3.1 carries out tension test, obtains
Sandwich layer test specimen tensile strength under different diffusion temperatures；
A3.3, according to the sandwich layer test specimen tensile strength under different diffusion temperatures, fitting obtains the diffusion temperature of sandwich layer
- tensile strength curve；
A3.4, the diffusion temperature-tensile strength curve according to sandwich layer, obtain the corresponding diffusion of maximum pulling strength
Temperature is the optimal diffusion temperature T of core materialXB。
3. the preparation method of a kind of titanium alloy thin wall multilayer hollow structure according to claim 1, it is special
Levy and be：The optimal diffusion temperature T of panel material in 3rd stepMBDetermine that method is as follows：
B3.1, the diffusion connection temperature range [T in panel materialM min,TM max] in, select different diffusion temperatures to enter
The diffusion connection of row panel test specimen, wherein TM min、TM maxFor panel material can be diffused the minimum of connection and most
High-temperature；
Panel test specimen under B3.2, the different diffusion temperatures obtained to step B3.1 carries out tension test, obtains
Panel test specimen tensile strength under different diffusion temperatures；
B3.3, according to the panel test specimen tensile strength under different diffusion temperatures, fitting obtains the diffusion temperature of panel
- tensile strength curve；
B3.4, the diffusion temperature-tensile strength curve according to panel, obtain the corresponding diffusion of maximum pulling strength
Temperature is the optimal diffusion temperature T of panel materialMB。
4. the preparation method of a kind of titanium alloy thin wall multilayer hollow structure according to claim 1, it is special
Levy and be：From T within 2 hours during integrally diffusion is connected in 3rd stepXBRise to TMB。
5. the preparation method of a kind of titanium alloy thin wall multilayer hollow structure according to claim 2, it is special
Levy and be：The selection of diffusion temperature will cover diffusion connection temperature range in the step A3.1, select adjacent
Diffusion temperature difference be 10~15 DEG C.
6. the preparation method of a kind of titanium alloy thin wall multilayer hollow structure according to claim 3, it is special
Levy and be：The selection of diffusion temperature will cover diffusion connection temperature range in the step B3.1, select adjacent
Diffusion temperature difference be 10~15 DEG C.
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN109604410A (en) * | 2018-11-09 | 2019-04-12 | 南京航空航天大学 | A kind of titanium alloy multilayer plates fast shaping apptss and its manufacturing process |
| CN109955041A (en) * | 2019-03-28 | 2019-07-02 | 中国航空制造技术研究院 | Titanium alloy hollow structure without molding Preparation Method |
| CN110340244A (en) * | 2019-07-22 | 2019-10-18 | 北京航星机器制造有限公司 | A kind of four-layer structure substep superplastic forming-diffusion connection method |
| CN110743957A (en) * | 2019-11-01 | 2020-02-04 | 哈尔滨工业大学 | Integrated forming method for low-temperature forming/high-temperature reaction diffusion connection of magnesium alloy hollow four-layer structure |
| CN112846643A (en) * | 2020-12-08 | 2021-05-28 | 北京星航机电装备有限公司 | Forming method and forming device for titanium alloy thin-wall hollow structure |
| CN113996906A (en) * | 2021-11-09 | 2022-02-01 | 南京航空航天大学 | Preparation method of multilayer board hollow structure containing layered composite material |
| CN114012235A (en) * | 2021-11-02 | 2022-02-08 | 贵州永红航空机械有限责任公司 | Diffusion welding method for TA2 material microchannel radiator |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0893342A2 (en) * | 1997-07-24 | 1999-01-27 | Fuji Jukogyo Kabushiki Kaisha | Leading edge structure of aircraft airfoil and method of fabricating the same |
| US5881459A (en) * | 1996-09-27 | 1999-03-16 | Mcdonnell Douglas Corporation | Pressure communication for superplastically formed, diffusion bonded panels and method of manufacture |
| EP1455965B1 (en) * | 2001-12-21 | 2007-01-10 | BAE Systems PLC | Superplastic forming and diffusion bonding process |
| CN101148000A (en) * | 2006-09-21 | 2008-03-26 | 航天材料及工艺研究所 | High temperature alloy complex groove structure panel and flange liquid phase diffusion connecting method |
| CN103862233A (en) * | 2014-02-12 | 2014-06-18 | 江苏呈飞精密合金股份有限公司 | Preparation method of composite plate with corrugated sandwich layer structure |
| CN104228310A (en) * | 2014-10-10 | 2014-12-24 | 哈尔滨工业大学 | Method for preparing Ti2AlNb alloy light three-layer hollow structure |
| CN105032980A (en) * | 2015-09-09 | 2015-11-11 | 航天海鹰(哈尔滨)钛业有限公司 | Thin-wall titanium alloy complex variable-cross-section pipe forming method and application |
-
2015
- 2015-12-15 CN CN201510940511.6A patent/CN106881561A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5881459A (en) * | 1996-09-27 | 1999-03-16 | Mcdonnell Douglas Corporation | Pressure communication for superplastically formed, diffusion bonded panels and method of manufacture |
| EP0893342A2 (en) * | 1997-07-24 | 1999-01-27 | Fuji Jukogyo Kabushiki Kaisha | Leading edge structure of aircraft airfoil and method of fabricating the same |
| EP1455965B1 (en) * | 2001-12-21 | 2007-01-10 | BAE Systems PLC | Superplastic forming and diffusion bonding process |
| CN101148000A (en) * | 2006-09-21 | 2008-03-26 | 航天材料及工艺研究所 | High temperature alloy complex groove structure panel and flange liquid phase diffusion connecting method |
| CN103862233A (en) * | 2014-02-12 | 2014-06-18 | 江苏呈飞精密合金股份有限公司 | Preparation method of composite plate with corrugated sandwich layer structure |
| CN104228310A (en) * | 2014-10-10 | 2014-12-24 | 哈尔滨工业大学 | Method for preparing Ti2AlNb alloy light three-layer hollow structure |
| CN105032980A (en) * | 2015-09-09 | 2015-11-11 | 航天海鹰(哈尔滨)钛业有限公司 | Thin-wall titanium alloy complex variable-cross-section pipe forming method and application |
Non-Patent Citations (4)
| Title |
|---|
| 中国机械工程学会焊接学会编: "《焊接手册 第2卷 材料的焊接》", 31 October 2014 * |
| 王清江 等: "《高温钛合金的现状与前景》", 《航空材料学报》 * |
| 许鹏宇: "《Ti2AlNb基合金的高温拉伸性能》", 《中国优秀硕士学位论文全文数据库工程科技I辑》 * |
| 高卫明主: "《焊接方法与操作》", 31 August 2012 * |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN109604410A (en) * | 2018-11-09 | 2019-04-12 | 南京航空航天大学 | A kind of titanium alloy multilayer plates fast shaping apptss and its manufacturing process |
| CN109955041A (en) * | 2019-03-28 | 2019-07-02 | 中国航空制造技术研究院 | Titanium alloy hollow structure without molding Preparation Method |
| CN110340244A (en) * | 2019-07-22 | 2019-10-18 | 北京航星机器制造有限公司 | A kind of four-layer structure substep superplastic forming-diffusion connection method |
| CN110743957A (en) * | 2019-11-01 | 2020-02-04 | 哈尔滨工业大学 | Integrated forming method for low-temperature forming/high-temperature reaction diffusion connection of magnesium alloy hollow four-layer structure |
| CN112846643A (en) * | 2020-12-08 | 2021-05-28 | 北京星航机电装备有限公司 | Forming method and forming device for titanium alloy thin-wall hollow structure |
| CN114012235A (en) * | 2021-11-02 | 2022-02-08 | 贵州永红航空机械有限责任公司 | Diffusion welding method for TA2 material microchannel radiator |
| CN113996906A (en) * | 2021-11-09 | 2022-02-01 | 南京航空航天大学 | Preparation method of multilayer board hollow structure containing layered composite material |
| CN113996906B (en) * | 2021-11-09 | 2022-07-26 | 南京航空航天大学 | Preparation method of multilayer board hollow structure containing layered composite material |
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Application publication date: 20170623 |