CN108274086A - A kind of method of two-step method high temperature soldering carbon fiber reinforced carbon matrix composite material - Google Patents
A kind of method of two-step method high temperature soldering carbon fiber reinforced carbon matrix composite material Download PDFInfo
- Publication number
- CN108274086A CN108274086A CN201810068104.4A CN201810068104A CN108274086A CN 108274086 A CN108274086 A CN 108274086A CN 201810068104 A CN201810068104 A CN 201810068104A CN 108274086 A CN108274086 A CN 108274086A
- Authority
- CN
- China
- Prior art keywords
- protective atmosphere
- composite
- temperature
- fiber reinforced
- high temperature
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K1/00—Soldering, e.g. brazing, or unsoldering
- B23K1/008—Soldering within a furnace
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K1/00—Soldering, e.g. brazing, or unsoldering
- B23K1/19—Soldering, e.g. brazing, or unsoldering taking account of the properties of the materials to be soldered
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K1/00—Soldering, e.g. brazing, or unsoldering
- B23K1/20—Preliminary treatment of work or areas to be soldered, e.g. in respect of a galvanic coating
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- Ceramic Products (AREA)
Abstract
A kind of method of two-step method high temperature soldering carbon fiber reinforced carbon matrix composite material, it is related to a kind of method of soldering carbon fiber reinforced carbon matrix composite material.The present invention is to solve current CfThe technical issues of poor mechanical property of the high temperature brazing of/C composite.The present invention：One, eutectic Ti Si brazing filler metals are prepared；Two, solder piece is prepared；Three, C is preparedfThe infiltration layer of/C composite；Four, CfThe soldering of/C composite.The present invention using 14Ti 86Si eutectic solders high temperature realize carbon fiber reinforced carbon matrix composite material without pressure soldering connection, two step method for brazing are effectively improved CfThe quality of connection of/C composite.The present invention is applied to welding field.
Description
Technical field
The present invention relates to a kind of methods of soldering carbon fiber reinforced carbon matrix composite material.
Background technology
With the fast development of science and technology, the requirement to spacecraft heat structure and thermally protective materials is increasingly stringent both at home and abroad.
Carbon fiber reinforced carbon matrix composite material (Cf/ C composite) because with density is low, specific strength is high, coefficient of thermal expansion is low, high temperature resistant
The features such as function admirable, anti-yaw damper are had excellent performance has a wide range of applications in aerospace field, and the developed countries such as America and Europe have incited somebody to action
Various types of spacecrafts, solid propellant rocket superhigh temperature component use CfIt is prepared by/C composite.It is special in order to meet
Service Environment, there is an urgent need to prepare the large scale C of complicated shapef/ C composite component, but it is constrained to precast body establishment
Technology and CVI techniques, it is difficult to directly prepare large complicated C with low costf/ C composite component.In general, feasible method
It is exactly the C of secondary connection simple shapef/ C composite obtains required component.
Related CfThe connection of/C composite, including the sintering of vacuum heating-press sintering, electric field-assisted, Transient liquid phase connection, pricker
Weldering, diffusion welding (DW) and self-propagating reaction etc..Compared to other connection methods, the soldering reaction time is short, it is small to apply pressure to base material, and
The coefficient of thermal expansion of connecting material is controllable, becomes CfThe common connection method of/C composite.In existing report, Ag-Cu,
The solders such as Ag-Cu-Ti, Ti-Cu-Ni, Ti-Zr-Ni-Cu realize CfThe middle low temperature brazing of/C composite connects, and right
Actually rare in the development of high temperature brazing connection, only TiSi is respectively adopted in Dadras and Salvo et al.2Having been obtained with Si pieces can
The connector leaned on.Ti-Si based materials have been realized in CfThe methods of vacuum heating-press sintering and electric field-assisted sintering of/C composite
Connection, titanium is good to the wetability of carbon, silicon, carbon reaction generate silicon carbide and Cf/ C composite coefficient of thermal expansion is close,
Ti-Si based material high temperature conjunctions Cf/ C composite can obtain the good connector of welding quality.Therefore, using titanium silicon systems solder
Exploitation is suitble to CfThe method of/C composite high temperature brazing connection is very necessary.
Invention content
The present invention is to solve current CfThe technical issues of poor mechanical property of the high temperature brazing of/C composite, and carry
A kind of method for being brazed carbon fiber reinforced carbon matrix composite material for two-step method high temperature.
The method of the two-step method high temperature soldering carbon fiber reinforced carbon matrix composite material of the present invention carries out according to the following steps：
One, eutectic Ti-Si brazing filler metals are prepared：Grinding process scale removal is carried out to Ti pieces surface, then will go deoxygenation
The Ti pieces and Si blocks for changing skin are placed in copper pot, using vacuum arc melting equipment melt back 5 times~7 times, under vacuum
Cooled to room temperature obtains 14Ti-86Si solders；The Ti pieces of the scale removal and the atomic percentage content ratio of Si blocks
It is 7:43；
Two, solder piece is prepared：14Ti-86Si solders prepared by step 1 are cut by sheet using linear cutting equipment, into
Row grinding process scale removal is subsequently placed in ultrasonic cleaning 5min~10min in absolute ethyl alcohol, and drying obtains 14Ti-
86Si solder pieces；
Three, C is preparedfThe infiltration layer of/C composite：By C to be weldedfIt is clear that/C composite is placed in ultrasonic wave in absolute ethyl alcohol
5min~10min is washed, dries up, 14Ti-86Si solder pieces prepared by step 2 is fixed on by C to be welded using organic binderf/
On the welding surface of C composite；C to be welded is fixed with graphite jigf/ C composite is placed in vacuum brazing furnace or atmosphere furnace
In, 300 DEG C are warming up to 5 DEG C/min~10 DEG C/min under vacuum or protective atmosphere, under vacuum or protective atmosphere and temperature
10min~30min is kept the temperature under conditions of being 300 DEG C, is warming up to 5 DEG C/min~10 DEG C/min under vacuum or protective atmosphere
1380 DEG C~1440 DEG C, 10min is kept the temperature under vacuum or protective atmosphere and under conditions of temperature is 1380 DEG C~1440 DEG C, true
300 DEG C are cooled to 5 DEG C/min under empty or protective atmosphere, then room temperature is cooled to the furnace under vacuum or protective atmosphere, obtains
Welding surface has the C of infiltration layerf/ C composite；
Four, CfThe soldering of/C composite：There is the C of infiltration layer with two step 3 welding surfacesfThe conduct of/C composite
Base material is assembled into Sanming City between 14Ti-86Si solder pieces prepared by step 2 are fixed on two base materials using organic binder
Control structure；The base material that sandwich structure is fixed with graphite jig is placed in vacuum brazing furnace or atmosphere furnace, in vacuum or protection gas
300 DEG C are warming up to 5 DEG C/min~10 DEG C/min under atmosphere, is protected under vacuum or protective atmosphere and under conditions of temperature is 300 DEG C
Warm 10min~30min is warming up to 1380 DEG C~1440 DEG C, true under vacuum or protective atmosphere with 5 DEG C/min~10 DEG C/min
5min~120min is kept the temperature under conditions of being 1380 DEG C~1440 DEG C with temperature under empty or protective atmosphere, in vacuum or protective atmosphere
Under with 5 DEG C/min be cooled to 300 DEG C, then cool to room temperature with the furnace under vacuum or protective atmosphere, complete Cf/ C composite
Entire brazing process.
The invention has the advantages that：
The present invention realizes carbon fiber reinforced carbon matrix composite wood using 14Ti-86Si eutectic solders at 1380 DEG C~1440 DEG C
Expect (Cf/ C composite) without pressure soldering connection, solve existing Cf/ C composite lacks asking for high temperature brazing interconnection technique
Topic, has expanded Cf/ C composite cannot connect complicated C so as to avoid diffusion welding (DW) in the application of high-temperature fieldf/ C composite woods
Expect component and vacuum heating-press sintering to Cf/ C composite causes the problem of damage.Two step method for brazing are effectively improved Cf/C
(connector room temperature intensity is 20.5MPa~40.8MPa to the quality of connection of composite material, and connector measures under 1200 DEG C of vacuum conditions
High temperature shearing strength be 49.2MPa), on the one hand the preparation of infiltration layer realizes CfThe alloying on/C composite surface, one
Aspect is to Cf/ C base materials play the role of sealing pores, prevent solder to be excessively infiltrated up under capillary action in base material so as to cause
Connection failure.
Description of the drawings
The C of soldering is completed in the step of Fig. 1 is experiment one fourfThe entire lead solder joint microstructure photo of/C composite；
The C of soldering is completed in the step of Fig. 2 is experiment one fourfThe object of the entire soldered fitting shear fracture of/C composite
Facies analysis figure.
Specific implementation mode
Specific implementation mode one：Present embodiment is that a kind of two-step method high temperature is brazed carbon fiber reinforced carbon matrix composite material
Method specifically carries out according to the following steps：
One, eutectic Ti-Si brazing filler metals are prepared：Grinding process scale removal is carried out to Ti pieces surface, then will go deoxygenation
The Ti pieces and Si blocks for changing skin are placed in copper pot, using vacuum arc melting equipment melt back 5 times~7 times, under vacuum
Cooled to room temperature obtains 14Ti-86Si solders；The Ti pieces of the scale removal and the atomic percentage content ratio of Si blocks
It is 7:43；
Two, solder piece is prepared：14Ti-86Si solders prepared by step 1 are cut by sheet using linear cutting equipment, into
Row grinding process scale removal is subsequently placed in ultrasonic cleaning 5min~10min in absolute ethyl alcohol, and drying obtains 14Ti-
86Si solder pieces；
Three, C is preparedfThe infiltration layer of/C composite：By C to be weldedfIt is clear that/C composite is placed in ultrasonic wave in absolute ethyl alcohol
5min~10min is washed, dries up, 14Ti-86Si solder pieces prepared by step 2 is fixed on by C to be welded using organic binderf/
On the welding surface of C composite；C to be welded is fixed with graphite jigf/ C composite is placed in vacuum brazing furnace or atmosphere furnace
In, 300 DEG C are warming up to 5 DEG C/min~10 DEG C/min under vacuum or protective atmosphere, under vacuum or protective atmosphere and temperature
10min~30min is kept the temperature under conditions of being 300 DEG C, is warming up to 5 DEG C/min~10 DEG C/min under vacuum or protective atmosphere
1380 DEG C~1440 DEG C, 10min is kept the temperature under vacuum or protective atmosphere and under conditions of temperature is 1380 DEG C~1440 DEG C, true
300 DEG C are cooled to 5 DEG C/min under empty or protective atmosphere, then room temperature is cooled to the furnace under vacuum or protective atmosphere, obtains
Welding surface has the C of infiltration layerf/ C composite；
Four, CfThe soldering of/C composite：There is the C of infiltration layer with two step 3 welding surfacesfThe conduct of/C composite
Base material is assembled into Sanming City between 14Ti-86Si solder pieces prepared by step 2 are fixed on two base materials using organic binder
Control structure；The base material that sandwich structure is fixed with graphite jig is placed in vacuum brazing furnace or atmosphere furnace, in vacuum or protection gas
300 DEG C are warming up to 5 DEG C/min~10 DEG C/min under atmosphere, is protected under vacuum or protective atmosphere and under conditions of temperature is 300 DEG C
Warm 10min~30min is warming up to 1380 DEG C~1440 DEG C, true under vacuum or protective atmosphere with 5 DEG C/min~10 DEG C/min
5min~120min is kept the temperature under conditions of being 1380 DEG C~1440 DEG C with temperature under empty or protective atmosphere, in vacuum or protective atmosphere
Under with 5 DEG C/min be cooled to 300 DEG C, then cool to room temperature with the furnace under vacuum or protective atmosphere, complete Cf/ C composite
Entire brazing process.
Specific implementation mode two：The present embodiment is different from the first embodiment in that：It is organic described in step 3
Binder is 101 glue.Other are same as the specific embodiment one.
Specific implementation mode three：The present embodiment is different from the first and the second embodiment in that：Described in step 3
Organic binder is 502 glue.Other are the same as one or two specific embodiments.
Specific implementation mode four：Unlike one of present embodiment and specific implementation mode one to three：Institute in step 4
The organic binder stated is 101 glue.Other are identical as one of specific implementation mode one to three.
Specific implementation mode five：Unlike one of present embodiment and specific implementation mode one to four：Institute in step 4
The organic binder stated is 502 glue.Other are identical as one of specific implementation mode one to four.
The present invention is verified with following tests：
Experiment one：This experiment is a kind of method that two-step method high temperature is brazed carbon fiber reinforced carbon matrix composite material, specifically
It carries out according to the following steps：
One, eutectic Ti-Si brazing filler metals are prepared：Grinding process scale removal is carried out to Ti pieces surface, then will go deoxygenation
The Ti pieces and Si blocks for changing skin are placed in copper pot, using vacuum arc melting equipment melt back 5 times~7 times, under vacuum
Cooled to room temperature obtains 14Ti-86Si solders；The Ti pieces of the scale removal and the atomic percentage content ratio of Si blocks
It is 7:43；
Two, solder piece is prepared：14Ti-86Si solders prepared by step 1 are cut by sheet using linear cutting equipment, into
Row grinding process scale removal is subsequently placed in ultrasonic cleaning 10min in absolute ethyl alcohol, and drying obtains 14Ti-86Si solders
Piece；
Three, C is preparedfThe infiltration layer of/C composite：By C to be weldedfIt is clear that/C composite is placed in ultrasonic wave in absolute ethyl alcohol
10min is washed, dries up, 14Ti-86Si solder pieces prepared by step 2 is fixed on by C to be welded using organic binderf/ C is compound
On the welding surface of material；C to be welded is fixed with graphite jigf/ C composite, is placed in atmosphere furnace, under protective atmosphere with
10 DEG C/min is warming up to 300 DEG C, under protective atmosphere and temperature be 300 DEG C under conditions of keep the temperature 30min, under protective atmosphere with
10 DEG C/min is warming up to 1380 DEG C, 10min is kept the temperature under protective atmosphere and under conditions of temperature is 1380 DEG C, under protective atmosphere
300 DEG C are cooled to 5 DEG C/min, then cools to room temperature with the furnace under protective atmosphere, obtaining welding surface has infiltration layer
Cf/ C composite；
Four, CfThe soldering of/C composite：There is the C of infiltration layer with two step 3 welding surfacesfThe conduct of/C composite
Base material is assembled into Sanming City between 14Ti-86Si solder pieces prepared by step 2 are fixed on two base materials using organic binder
Control structure；The base material that sandwich structure is fixed with graphite jig, is placed in atmosphere furnace, is heated up with 10 DEG C/min under protective atmosphere
To 300 DEG C, 30min is kept the temperature under protective atmosphere and under conditions of temperature is 300 DEG C, is heated up with 10 DEG C/min under protective atmosphere
To 1400 DEG C, 5min is kept the temperature under protective atmosphere and under conditions of temperature is 1400 DEG C, is cooled down with 5 DEG C/min under protective atmosphere
To 300 DEG C, room temperature is then cooled to the furnace under protective atmosphere, complete CfThe entire brazing process of/C composite.
Its joint performance is evaluated using compression shear strength, obtained connector room temperature intensity is 20.5MPa.
Experiment two：This experiment is unlike experiment one：The item for being 1400 DEG C with temperature under protective atmosphere in step 4
10min is kept the temperature under part.Other are identical as experiment one.
Its joint performance is evaluated using compression shear strength, obtained connector room temperature intensity is 25.4MPa.
Experiment three：This experiment is unlike experiment one：The item for being 1400 DEG C with temperature under protective atmosphere in step 4
20min is kept the temperature under part.Other are identical as experiment one.
Its joint performance is evaluated using compression shear strength, obtained connector room temperature intensity is 26.7MPa.
Experiment four：This experiment is unlike experiment one：The item for being 1400 DEG C with temperature under protective atmosphere in step 4
40min is kept the temperature under part.Other are identical as experiment one.
Its joint performance is evaluated using compression shear strength, obtained connector room temperature intensity is 30.7MPa.
Experiment five：This experiment is unlike experiment one：The item for being 1400 DEG C with temperature under protective atmosphere in step 4
60min is kept the temperature under part.Other are identical as experiment one.
Its joint performance is evaluated using compression shear strength, obtained connector room temperature intensity is 32.6MPa.
Experiment six：This experiment is unlike experiment one：The item for being 1400 DEG C with temperature under protective atmosphere in step 4
90min is kept the temperature under part.Other are identical as experiment one.
Its joint performance is evaluated using compression shear strength, obtained connector room temperature intensity is 40.8MPa, and connector is 1200
The high temperature shearing strength measured under DEG C vacuum condition is 49.2MPa, the intensity obtained when higher than room temperature.
Experiment seven：This experiment is unlike experiment one：The item for being 1400 DEG C with temperature under protective atmosphere in step 4
120min is kept the temperature under part.Other are identical as experiment one.
Its joint performance is evaluated using compression shear strength, obtained connector room temperature intensity is 26.1MPa.
The C of soldering is completed in the step of Fig. 1 is experiment one fourfThe entire lead solder joint microstructure photo of/C composite, area
Domain A is base material Cf/ C composite, region B are weld seam, and as can be seen from the figure soldered fitting quality is good, and has solder leaching
It is seeped into CfIn the hole of/C composite, butt joint connection is played the role of advantageous " pinning ".In conjunction with the energy spectrum analysis in table 1,
It can be seen that brazed seam center is by eutectic structure TiSi2Mutually constituted with Si matrixes, generated between solder and base material one layer it is fine and close
SiC conversion zones.
Table 1 is the EDS analytical datas of C, D and E point in Fig. 1.
Table 1
The C of soldering is completed in the step of Fig. 2 is experiment one fourfThe object of the entire soldered fitting shear fracture of/C composite
Facies analysis figure, ● it is C, ☆ SiC, ◇ Si, ▽ TiSi2, as seen from the figure, section is by C, TiSi2, Si and SiC object phase structures
At, illustrate connector when bearing shear-type load, crackle pass through Cf/ C matrix, reaction interface and brazed seam center, this also demonstrates table 1
In material phase analysis.
Claims (5)
1. a kind of method of two-step method high temperature soldering carbon fiber reinforced carbon matrix composite material, it is characterised in that two-step method high temperature is brazed
The method of carbon fiber reinforced carbon matrix composite material carries out according to the following steps：
One, eutectic Ti-Si brazing filler metals are prepared：Grinding process scale removal is carried out to Ti pieces surface, then by scale removal
Ti pieces and Si blocks be placed in copper pot, it is natural under vacuum using vacuum arc melting equipment melt back 5 times~7 times
It is cooled to room temperature, obtains 14Ti-86Si solders；The Ti pieces of the scale removal and the atomic percentage content ratio of Si blocks are 7:
43；
Two, solder piece is prepared：14Ti-86Si solders prepared by step 1 are cut by sheet using linear cutting equipment, are beaten
Mill processing scale removal, is subsequently placed in ultrasonic cleaning 5min~10min in absolute ethyl alcohol, dries up, obtain 14Ti-86Si prickers
Tablet；
Three, C is preparedfThe infiltration layer of/C composite：By C to be weldedf/ C composite is placed in ultrasonic cleaning in absolute ethyl alcohol
5min~10min, drying, C to be welded is fixed on using organic binder by 14Ti-86Si solder pieces prepared by step 2f/C
On the welding surface of composite material；C to be welded is fixed with graphite jigf/ C composite is placed in vacuum brazing furnace or atmosphere furnace
In, 300 DEG C are warming up to 5 DEG C/min~10 DEG C/min under vacuum or protective atmosphere, under vacuum or protective atmosphere and temperature
10min~30min is kept the temperature under conditions of being 300 DEG C, is warming up to 5 DEG C/min~10 DEG C/min under vacuum or protective atmosphere
1380 DEG C~1440 DEG C, 10min is kept the temperature under vacuum or protective atmosphere and under conditions of temperature is 1380 DEG C~1440 DEG C, true
300 DEG C are cooled to 5 DEG C/min under empty or protective atmosphere, then room temperature is cooled to the furnace under vacuum or protective atmosphere, obtains
Welding surface has the C of infiltration layerf/ C composite；
Four, CfThe soldering of/C composite：There is the C of infiltration layer with two step 3 welding surfacesf/ C composite is as female
Material is assembled into sandwich between 14Ti-86Si solder pieces prepared by step 2 are fixed on two base materials using organic binder
Structure；The base material that sandwich structure is fixed with graphite jig is placed in vacuum brazing furnace or atmosphere furnace, in vacuum or protective atmosphere
Under with 5 DEG C/min~10 DEG C/min be warming up to 300 DEG C, kept the temperature under vacuum or protective atmosphere and under conditions of temperature is 300 DEG C
10min~30min is warming up to 1380 DEG C~1440 DEG C, in vacuum under vacuum or protective atmosphere with 5 DEG C/min~10 DEG C/min
Or under protective atmosphere and temperature be 1380 DEG C~1440 DEG C under conditions of keep the temperature 5min~120min, under vacuum or protective atmosphere
300 DEG C are cooled to 5 DEG C/min, then cools to room temperature with the furnace under vacuum or protective atmosphere, completes Cf/ C composite
Entire brazing process.
2. a kind of method of two-step method high temperature soldering carbon fiber reinforced carbon matrix composite material according to claim 1, special
Sign is that the organic binder described in step 3 is 101 glue.
3. a kind of method of two-step method high temperature soldering carbon fiber reinforced carbon matrix composite material according to claim 1, special
Sign is that the organic binder described in step 3 is 502 glue.
4. a kind of method of two-step method high temperature soldering carbon fiber reinforced carbon matrix composite material according to claim 1, special
Sign is that the organic binder described in step 4 is 101 glue.
5. a kind of method of two-step method high temperature soldering carbon fiber reinforced carbon matrix composite material according to claim 1, special
Sign is that the organic binder described in step 4 is 502 glue.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810068104.4A CN108274086B (en) | 2018-01-24 | 2018-01-24 | Method for brazing carbon fiber reinforced carbon-based composite material at high temperature by two-step method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810068104.4A CN108274086B (en) | 2018-01-24 | 2018-01-24 | Method for brazing carbon fiber reinforced carbon-based composite material at high temperature by two-step method |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108274086A true CN108274086A (en) | 2018-07-13 |
| CN108274086B CN108274086B (en) | 2022-03-01 |
Family
ID=62804814
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810068104.4A Active CN108274086B (en) | 2018-01-24 | 2018-01-24 | Method for brazing carbon fiber reinforced carbon-based composite material at high temperature by two-step method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108274086B (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110026634A (en) * | 2019-05-13 | 2019-07-19 | 哈尔滨工业大学 | A method of carbon fiber reinforced carbon matrix composite material is brazed using Si-Zr high-temp solder |
| CN110788511A (en) * | 2019-11-27 | 2020-02-14 | 中国航空制造技术研究院 | Preparation method of low-cost large-size fiber reinforced titanium-based composite material |
| CN115194275A (en) * | 2022-06-02 | 2022-10-18 | 哈尔滨工业大学 | Method for brazing dissimilar metals of titanium alloy and nickel-based superalloy |
| CN115365595A (en) * | 2022-09-30 | 2022-11-22 | 成都和鸿科技股份有限公司 | Brazing method for duplex guide vane |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1712167A (en) * | 2004-06-24 | 2005-12-28 | Snecma固体燃料推进器公司 | Method of brazing composite materials sealed with silicon based composition |
| CN101143397A (en) * | 2007-11-06 | 2008-03-19 | 北京有色金属研究总院 | C/C and C/SiC composite material and metal connecting method |
| CN103232257A (en) * | 2013-04-02 | 2013-08-07 | 西安交通大学 | Fast connection method of carbon/carbon composite material |
| CN105149717A (en) * | 2015-10-19 | 2015-12-16 | 哈尔滨工业大学 | Silicon-based ceramic surface metallization method |
| CN106747553A (en) * | 2017-02-21 | 2017-05-31 | 西北工业大学 | Without the method for pressure connection between a kind of C/C composites |
| CN107457499A (en) * | 2017-08-09 | 2017-12-12 | 合肥工业大学 | A kind of high-temp solder preparation method and soldering processes for silicon carbide ceramics and its composite |
-
2018
- 2018-01-24 CN CN201810068104.4A patent/CN108274086B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1712167A (en) * | 2004-06-24 | 2005-12-28 | Snecma固体燃料推进器公司 | Method of brazing composite materials sealed with silicon based composition |
| US20060006212A1 (en) * | 2004-06-24 | 2006-01-12 | Jacques Thebault | Method of brazing composite material parts sealed with a silicon-based composition |
| CN101143397A (en) * | 2007-11-06 | 2008-03-19 | 北京有色金属研究总院 | C/C and C/SiC composite material and metal connecting method |
| CN103232257A (en) * | 2013-04-02 | 2013-08-07 | 西安交通大学 | Fast connection method of carbon/carbon composite material |
| CN105149717A (en) * | 2015-10-19 | 2015-12-16 | 哈尔滨工业大学 | Silicon-based ceramic surface metallization method |
| CN106747553A (en) * | 2017-02-21 | 2017-05-31 | 西北工业大学 | Without the method for pressure connection between a kind of C/C composites |
| CN107457499A (en) * | 2017-08-09 | 2017-12-12 | 合肥工业大学 | A kind of high-temp solder preparation method and soldering processes for silicon carbide ceramics and its composite |
Non-Patent Citations (2)
| Title |
|---|
| DADRAS P等: "Joining ofcarbon-carbon composites using Boron and Titanium", 《JOURNAL OFTHEAMERICAN CERAMIC SOCIETY》 * |
| 邱东等: "C/C复合材料焊接研究现状", 《焊接》 * |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110026634A (en) * | 2019-05-13 | 2019-07-19 | 哈尔滨工业大学 | A method of carbon fiber reinforced carbon matrix composite material is brazed using Si-Zr high-temp solder |
| CN110788511A (en) * | 2019-11-27 | 2020-02-14 | 中国航空制造技术研究院 | Preparation method of low-cost large-size fiber reinforced titanium-based composite material |
| CN110788511B (en) * | 2019-11-27 | 2022-01-21 | 中国航空制造技术研究院 | Preparation method of low-cost large-size fiber reinforced titanium-based composite material |
| CN115194275A (en) * | 2022-06-02 | 2022-10-18 | 哈尔滨工业大学 | Method for brazing dissimilar metals of titanium alloy and nickel-based superalloy |
| CN115365595A (en) * | 2022-09-30 | 2022-11-22 | 成都和鸿科技股份有限公司 | Brazing method for duplex guide vane |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108274086B (en) | 2022-03-01 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108274086A (en) | A kind of method of two-step method high temperature soldering carbon fiber reinforced carbon matrix composite material | |
| US7857194B2 (en) | Method of joining metals to ceramic matrix composites | |
| Shirzadi et al. | Joining ceramics to metals using metallic foam | |
| CN112570832B (en) | Silicon carbide cladding and brazing connection method thereof | |
| Salvo et al. | One-step brazing process to join CFC composites to copper and copper alloy | |
| CN110524082B (en) | Method for quickly wetting carbon fibers in ceramic matrix composite by taking Fe as active element | |
| CN113600957A (en) | Composite interlayer and method for brazing boron carbide composite ceramic and titanium alloy | |
| CN105499833A (en) | High-temperature brazing material for brazing tungsten-copper alloy and copper or copper alloy and brazing method of high-temperature brazing material | |
| CN109047963B (en) | CfComposite brazing connection method of/C composite material and nickel-based high-temperature alloy | |
| CN103586582B (en) | A kind of laser-induced combustion self-propagating reaction assistant brazing connects C fthe method of/Al composite and TiAl | |
| CN106041350A (en) | Tungsten/copper or tungsten/steel connector and method for preparing same | |
| CN106588064B (en) | The solder and connection method of carbon/carbon compound material and nickel base superalloy | |
| CN102825354B (en) | A kind of C fcompound-the diffusion soldering method of/SiC ceramic based composites and titanium alloy | |
| CN103341675A (en) | Method for braze welding of Cf/SiC composite material and metal Nb by using Ti-Co-Nb brazing filler metal | |
| Guo et al. | Effect of Ni foam on the microstructure and properties of AlN ceramic/Cu brazed joint | |
| CN110026634B (en) | Method for brazing carbon fiber reinforced carbon-based composite material by using Si-Zr high-temperature brazing filler metal | |
| CN114131232B (en) | SiC or SiC connected by high-entropy alloy f Method for producing SiC ceramic material | |
| CN106242606A (en) | One utilizes Zr Ni base solder brazing ZrB2the method of SiC composite ceramics | |
| CN105174988A (en) | Method for connecting ceramic by adopting porous ceramic middle layer | |
| CN102825353B (en) | A kind of C fcompound-the diffusion soldering method of/SiC ceramic based composites and titanium alloy | |
| CN114749743B (en) | High-temperature connection method for soldering C/C composite material and Ni-based alloy by adopting pure Cu | |
| CN104874909A (en) | Liquid-phase diffusion bonding method for quartz composite ceramic and iron-nickel alloy | |
| CN106736030B (en) | A kind of application method of solder in welding C/SiC composite material and metal | |
| CN107043269B (en) | Method for modifying ceramic by low-temperature rapid welding | |
| Atabaki | Recent progress in joining of ceramic powder metallurgy products to metals |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |