CN116693314A - Low-stress high-temperature-resistant connection method for C/C composite material and high-temperature alloy - Google Patents
Low-stress high-temperature-resistant connection method for C/C composite material and high-temperature alloy Download PDFInfo
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- 239000002131 composite material Substances 0.000 title claims abstract description 81
- 229910045601 alloy Inorganic materials 0.000 title claims abstract description 55
- 239000000956 alloy Substances 0.000 title claims abstract description 55
- 238000000034 method Methods 0.000 title claims abstract description 42
- 239000000843 powder Substances 0.000 claims abstract description 52
- 239000000463 material Substances 0.000 claims abstract description 47
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims abstract description 24
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- 238000002844 melting Methods 0.000 claims abstract description 14
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- 238000011065 in-situ storage Methods 0.000 claims abstract description 10
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- 239000002245 particle Substances 0.000 claims abstract description 8
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- KHYBPSFKEHXSLX-UHFFFAOYSA-N iminotitanium Chemical compound [Ti]=N KHYBPSFKEHXSLX-UHFFFAOYSA-N 0.000 claims abstract 6
- 229910001000 nickel titanium Inorganic materials 0.000 claims abstract 6
- 238000010438 heat treatment Methods 0.000 claims description 26
- 238000005219 brazing Methods 0.000 claims description 17
- 229910000601 superalloy Inorganic materials 0.000 claims description 15
- 238000001035 drying Methods 0.000 claims description 13
- 238000001816 cooling Methods 0.000 claims description 11
- LFQSCWFLJHTTHZ-UHFFFAOYSA-N Ethanol Chemical compound CCO LFQSCWFLJHTTHZ-UHFFFAOYSA-N 0.000 claims description 9
- 238000005498 polishing Methods 0.000 claims description 9
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 8
- 239000004917 carbon fiber Substances 0.000 claims description 8
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 8
- WUOACPNHFRMFPN-SECBINFHSA-N (S)-(-)-alpha-terpineol Chemical compound CC1=CC[C@@H](C(C)(C)O)CC1 WUOACPNHFRMFPN-SECBINFHSA-N 0.000 claims description 7
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- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B37/00—Joining burned ceramic articles with other burned ceramic articles or other articles by heating
- C04B37/02—Joining burned ceramic articles with other burned ceramic articles or other articles by heating with metallic articles
- C04B37/023—Joining burned ceramic articles with other burned ceramic articles or other articles by heating with metallic articles characterised by the interlayer used
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- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
- C04B2237/02—Aspects relating to interlayers, e.g. used to join ceramic articles with other articles by heating
- C04B2237/04—Ceramic interlayers
- C04B2237/08—Non-oxidic interlayers
- C04B2237/086—Carbon interlayers
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- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
- C04B2237/02—Aspects relating to interlayers, e.g. used to join ceramic articles with other articles by heating
- C04B2237/12—Metallic interlayers
- C04B2237/122—Metallic interlayers based on refractory metals
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- C—CHEMISTRY; METALLURGY
- C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
- C04B—LIME, MAGNESIA; SLAG; CEMENTS; COMPOSITIONS THEREOF, e.g. MORTARS, CONCRETE OR LIKE BUILDING MATERIALS; ARTIFICIAL STONE; CERAMICS; REFRACTORIES; TREATMENT OF NATURAL STONE
- C04B2237/00—Aspects relating to ceramic laminates or to joining of ceramic articles with other articles by heating
- C04B2237/02—Aspects relating to interlayers, e.g. used to join ceramic articles with other articles by heating
- C04B2237/12—Metallic interlayers
- C04B2237/123—Metallic interlayers based on iron group metals, e.g. steel
Abstract
The invention provides a low-stress high-temperature-resistant connection method of a C/C composite material and a high-temperature alloy, which comprises the following steps: and taking the mixed powder of the Ni-Ti alloy powder and the carbon-based powder as a connecting material, and at a lower connecting temperature, enabling liquid formed by melting the Ni-Ti alloy powder to react with the carbon-based powder in situ in a welding seam gap between the C/C composite material and the high-temperature alloy to form a TiC particle reinforced Ni-based solid solution-based composite connecting layer, thereby realizing low-stress high-temperature-resistant connection of the C/C composite material and the high-temperature alloy. The connecting material has the advantages of easy preparation, low cost, simple process and strong adaptability, and can realize connection with large gaps, unequal gaps and complex structures.
Description
Technical Field
The invention relates to the technical field of connection of composite materials and metals, in particular to a low-stress high-temperature-resistant connection method of a C/C composite material and a high-temperature alloy.
Background
The carbon fiber reinforced carbon-based composite material (C/C composite material) has the excellent performances of low density, high temperature resistance, thermal shock resistance, high strength at high temperature and the like, is an ideal material for manufacturing combustion chamber components, rocket nozzles, hypersonic aircraft thermal protection structures and the like, and has important application value on new generation strategic missiles and aerospace engines. However, C/C composites have poor ductility and impact toughness and are difficult to machine, often requiring attachment to a metal to form a composite structure in application. Along with the maturity and the improvement of the performance of the preparation process of the C/C composite material, the application of the C/C composite material in aerospace and advanced weapon systems is increasingly wide, and the research and development of the reliable connection technology of the C/C composite material and metals, particularly high-temperature alloys, has become an important subject in the development field of new-generation high-performance engines in China.
In recent years, some researches have been reported at home and abroad on the connection of a C/C composite material and a metal, and analysis is carried out from the material composition and application background of the connection, and the connection of the C/C composite material and the metal for an engine mainly has the following problems: 1) The C/C composite material is difficult to melt to form a liquid phase, has extremely poor metallurgical compatibility with metal, and cannot be directly subjected to melt welding; 2) The C/C composite material and the metal have larger thermal expansion coefficient difference, and the connection tends to form larger thermal stress, so that the joint strength is reduced and even the joint is directly cracked; 3) In an engine thrust chamber, a connection joint of a C/C composite material and metal is usually in service in a high-temperature environment, and the temperature resistance requirement is high (often above 1200 ℃). At present, two main methods for realizing the connection between the C/C composite material and the metal are diffusion welding and brazing. Although the diffusion welding method can realize the connection of the C/C composite material and metal, the connection thermal stress is large and the joint performance is unstable; and in addition, larger pressure is required to be applied in the connecting process, the structural adaptability is poor, and the connection of the actual large-size or complex components is difficult to realize. In contrast, the brazing method has simple process, no pressure and strong structural adaptability, and is the most suitable method for connecting the C/C composite material for the engine with metal. However, the traditional brazing also has the problem of thermal stress connection, and the joint has poor high temperature resistance, so that the practical application requirement of the C/C composite material and metal connection is difficult to meet. In order to relieve the thermal stress of the soldered joint and improve the high-temperature performance of the soldered joint, a composite soldering method is developed on the basis of the traditional soldering at home and abroad.
Research shows that the composite brazing can effectively relieve the connection thermal stress and improve the joint strength by adding a certain proportion of low thermal expansion coefficient reinforcing phase into the traditional brazing filler metal (such as Ag-Cu-Ti, ti-Zr-Cu-Ni, ag-Ti and the like) to adjust the thermal expansion coefficient of the connecting layer, such as SiC and the like; and the addition of the reinforcing phase can also improve the high temperature strength of the joint to some extent. However, the existing composite brazing in the form of directly externally added reinforcing phase can improve the high temperature performance of the joint to a certain extent, but can not fundamentally improve the heat resistance temperature of the joint due to the restriction of the heat resistance temperature (initial liquefaction temperature) of the low-melting metal brazing filler metal matrix. Taking Ag-Cu-Ti as a matrix solder for composite brazing as an example, the highest temperature resistance of the joint is not more than 800 ℃. In theory, the high-temperature performance and the heat-resistant temperature of the joint can be improved by adopting the brazing filler metal with high melting point, but the high brazing temperature can greatly increase the connection thermal stress, and the method is particularly unfavorable for the connection of the C/C composite material and the high-temperature alloy and other large thermal mismatch heterogeneous materials. In summary, how to reduce the thermal stress of the connection by composite brazing, and simultaneously compatibly solve the problem of high temperature resistance of the joint, so as to realize 'low stress/high temperature resistance' connection, is a bottleneck problem to be broken through when C/C composite material and high temperature alloy are connected.
Disclosure of Invention
The invention aims to compatibly solve the problems of large connection thermal stress and poor high temperature resistance of a joint existing in the connection of a C/C composite material (namely a carbon fiber reinforced carbon-based composite material) and a high-temperature alloy, and provides a low-stress high-temperature-resistant connection method for synthesizing a TiC/Ni composite connection layer based on (Ni-Ti) +C→TiC+Ni reaction in situ.
A method of low stress, high temperature resistant joining of a C/C composite to a superalloy, comprising:
and taking the mixed powder of the Ni-Ti alloy powder and the carbon-based powder as a connecting material, and reacting the liquid formed by melting the Ni-Ti alloy powder with the carbon-based powder in situ in a welding seam gap between the C/C composite material and the high-temperature alloy at a lower connecting temperature to form the TiC particle reinforced Ni-based solid solution-based composite connecting layer.
The mixed powder of the low-melting Ni-Ti alloy powder and the carbon-based powder is used as a connecting material, and at the connecting temperature, the low-melting Ni-Ti alloy powder is melted to form a liquid phase, wets a base metal to be welded (namely a C/C composite material and a high-temperature alloy) and fills a welding seam gap; and (3) reacting the carbon-based powder with the melting-reducing element Ti in the Ni-Ti liquid phase at the connecting temperature to synthesize TiC in situ, so that the connecting layer is subjected to isothermal solidification, and finally forming the TiC particle reinforced Ni-based solid solution-based composite connecting layer, namely the TiC/Ni composite connecting layer. According to the connecting method, the low thermal expansion TiC reinforcing phase is introduced into the connecting layer through the reaction of (Ni-Ti) +C→TiC+Ni to relieve the connecting thermal stress, and meanwhile, the melting-down element Ti in the Ni-Ti alloy brazing filler metal is rapidly consumed to form a Ni-based solid solution matrix with higher heat-resistant temperature, so that the low-stress high-temperature-resistant connection of the C/C composite material and the high-temperature alloy can be realized.
Optionally, the method comprises:
step S1, preparing a base material to be welded: polishing the surface to be welded of the C/C composite material and the high-temperature alloy, removing surface impurities and oxide films, cleaning the C/C composite material and the high-temperature alloy, and drying for later use;
step S2, preparing a connecting material: weighing Ni-Ti alloy powder and carbon-based powder according to a proportion, uniformly mixing to form mixed powder, then adding a proper amount of organic solvent, uniformly stirring, and preparing into paste;
step S3, presetting a connecting material: uniformly presetting the prepared pasty connecting material between the C/C composite material and a high-temperature alloy surface to be welded, and fully contacting the connecting material with two base materials to be welded (namely the C/C composite material and the high-temperature alloy) by light pressure to form a piece to be welded, wherein the connecting material is a preset layer;
step S4, vacuum connection: and placing the to-be-welded piece into a vacuum brazing furnace, vacuumizing the furnace, heating to a connecting temperature, preserving heat for a period of time, and slowly cooling the furnace to room temperature.
Optionally, in the step S1, polishing the surface to be welded by using 240-600 mesh sand paper; using alcohol and cleaning the C/C composite material and the superalloy for 2-3 times in an ultrasonic cleaner; drying in a vacuum drying oven at 40-60deg.C for 10-30min.
Optionally, in step S2, the ni—ti alloy powder has a Ti atom percentage of 15-40% and a particle size of 10-30 μm, and the ni—ti alloy powder under such conditions has a low melting point, can form a liquid phase at the joining temperature, is favorable for reacting with the carbon-based powder, and is favorable for isothermal solidification of the joining layer, and is preferably Ni62Ti38.
Optionally, in step S2, the particle size of the carbon-based powder is 2-5 μm, and the carbon-based powder is at least one selected from diamond, graphite and carbon fiber; the mass fraction of the carbon-based powder in the mixed powder is 1-6%.
Optionally, in step S2, the organic solvent is at least one selected from ethanol, α -terpineol, and gasoline-rubber, preferably α -terpineol.
Optionally, in step S3, the preset layer thickness is 0.4-0.7mm.
Optionally, in step S4, the furnace is evacuated to a vacuum of no more than 5X 10 -3 Pa。
Optionally, in step S4, the process of heating to the connection temperature is: heating to 800-1000 ℃ at a heating rate of 10-15 ℃/min; then heating to 1180-1300 ℃ at a heating rate of 50 ℃/min. The first stage adopts slow temperature rise to enable the sample to be heated stably and uniformly; the second stage adopts rapid heating to make the sample to be welded reach the connection temperature as soon as possible, so as to reduce the reaction between Ni-Ti alloy powder and C powder in the heating stage.
Optionally, in the step S4, the temperature is kept for 5-30 min; the cooling speed of the furnace is less than or equal to 5 ℃/min. The heat preservation time is selected because in the time period, the connecting material can be fully melted to fill the weld joint gap, and excessive interface reaction between the connecting layer and the C/C composite material can be avoided. But slow cooling is intended to minimize residual thermal stresses in the joint due to too fast a cooling rate.
The technical scheme provided by the invention has the beneficial effects that at least:
(1) The connecting method has the characteristic of low-temperature connection/high-temperature service, and can realize low-stress high-temperature connection of the C/C composite material and the high-temperature alloy under low-temperature and low-pressure conditions.
(2) According to the connecting method, the low thermal expansion TiC reinforcing phase is introduced into the connecting layer through the reaction of (Ni-Ti) +C→TiC+Ni to relieve the connecting thermal stress, and meanwhile, the melting reduction element Ti in the low melting Ni-Ti alloy solder is rapidly consumed to form the Ni-based solid solution-based connecting layer with higher heat resistance temperature.
(3) The connecting method adopts the mixed powder of the low-melting Ni-Ti alloy powder and the C powder as the connecting material, the connecting material is easy to prepare, the cost is low, the process is simple, the adaptability of the powdery connecting material to the joint structure is strong, and the connection with large gaps, unequal gaps and complex structures can be realized.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required for the description of the embodiments will be briefly described below, and it is apparent that the drawings in the following description are only some embodiments of the present invention, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a scanning electron microscope image of a C/C composite material based on an in-situ synthesized TiC/Ni composite connecting layer and a GH3044 superalloy connecting joint structure in the embodiment 1;
FIG. 2 is a scanning electron microscope image of an interface structure of a C/C composite material based on an in-situ synthesized TiC/Ni composite connecting layer and a GH3044 superalloy connecting joint composite material in embodiment 1 of the invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the technical solutions of the present invention will be described in detail with reference to the accompanying drawings and specific embodiments.
Example 1
The embodiment is a low-stress high-temperature-resistant connection method of a C/C composite material and GH3044 high-temperature alloy based on in-situ synthesis of a TiC/Ni composite connection layer.
The C/C composite material is a two-dimensional winding and three-dimensional perforation structure, and the density is 1.65-1.78 g/cm 3 Cut into 5X 5mm 3 Is a square of (2); by a means ofThe GH3044 superalloy is solid solution strengthening Ni-based superalloy, and the density is 8.89g/cm 3 The melting temperature ranges from 1352 to 1375 ℃ and the thermal expansion coefficient is 16.28 multiplied by 10 -6 K -1 Cut into 10X 3mm 3 Is a block of (a). The connecting material consists of Ni62Ti38 alloy powder and diamond powder, wherein the granularity of the Ni-Ti alloy powder is 10-30 mu m, the granularity of the diamond powder is 2-5 mu m, and the mass fraction of the diamond powder in the mixed powder is 3%.
The specific process of the embodiment comprises the following steps:
step 1, preparing a base material to be welded. Polishing the surface to be welded of the C/C composite material and the GH3044 superalloy with 240-600 mesh sand paper to remove surface impurities and oxide films; putting the polished composite material and the high-temperature alloy into alcohol, and repeatedly cleaning for 3 times by using an ultrasonic cleaner; and (5) placing the cleaned product into a vacuum drying oven for drying for standby, wherein the drying temperature is 40 ℃, and the drying time is 10min.
And 2, modulating the connecting material. The Ni62Ti38 alloy powder and the diamond powder are weighed according to the proportion, the powder is mechanically mixed uniformly, and then a proper amount of alpha-terpineol is added for uniform stirring, so that the paste is prepared.
And 3, presetting a connecting material. Uniformly presetting the prepared pasty connecting material between the C/C composite material and a high-temperature alloy surface to be welded, and fully contacting the C/C composite material with two base materials by light pressure; the thickness of the preset layer is controlled to be 0.5mm.
And 4, vacuum connection. Placing the weldment to be welded with preset connecting materials into a vacuum brazing furnace, closing the furnace door, and vacuumizing to 5×10 -3 pa; then heating to 1000 ℃ at a heating rate of 15 ℃/min; then heating to 1300 ℃ connection temperature at a heating rate of 50 ℃/min, preserving heat for 25min, and cooling in a furnace at a cooling rate of less than or equal to 5 ℃/min. And taking out the connection sample when the temperature in the furnace is reduced to room temperature.
And 5, joint organization and performance detection. Cutting the connecting joint along the section by using a linear cutting method, polishing the section of the joint step by using 150, 240, 400, 600, 800, 1000, 1200, 1500 and 2000-mesh sand paper, preparing a metallographic specimen, observing the microstructure of the joint by using a scanning electron microscope, and analyzing the phase components by using X-ray diffraction and energy spectrum; and (3) placing the connecting joint obtained in the step (4) into a special fixture, testing the shearing strength at room temperature and high temperature on an electronic universal testing machine, wherein the loading rate is 0.5mm/min, recording the maximum load output when the workpiece is sheared, converting the shearing strength of the joint according to the maximum load, and taking the average value of 5 samples as a final result. The resulting joint had a room temperature shear strength of 32.1MPa.
Example 2
The embodiment is a low-stress high-temperature-resistant connection method of a C/C composite material and GH4169 high-temperature alloy based on in-situ synthesis of a TiC/Ni composite connection layer.
The C/C composite material is a two-dimensional winding and three-dimensional perforation structure, and the density is 1.65-1.78 g/cm 3 Cut into 5X 5mm 3 Is a square of (2); the GH4169 superalloy is a precipitation strengthening Ni-based superalloy with a density of 8.24g/cm 3 The melting temperature is 1260-1320 ℃, and the thermal expansion coefficient is 18.7X10 -6 K -1 Cut into 10X 3mm 3 Is a block of (a). The connecting material consists of Ni62Ti38 alloy powder and graphite powder, wherein the granularity of the Ni-Ti alloy powder is 10-30 mu m, the granularity of the graphite powder is 2 mu m, and the mass fraction of the diamond powder in the mixed powder is 2%.
The specific process of the embodiment comprises the following steps:
step 1, preparing a base material to be welded. Polishing the surface to be welded of the C/C composite material and the GH4169 superalloy by using 240-600 mesh sand paper to remove surface impurities and oxide films; putting the polished composite material and the high-temperature alloy into alcohol, and repeatedly cleaning for 3 times by using an ultrasonic cleaner; and (5) placing the cleaned product into a vacuum drying oven for drying for standby, wherein the drying temperature is 40 ℃, and the drying time is 10min.
And 2, modulating the connecting material. The Ni62Ti38 alloy powder and the graphite powder are weighed according to the proportion, the powder is mechanically mixed uniformly, and then a proper amount of alpha-terpineol is added for uniform stirring, so that the paste is prepared.
And 3, presetting a connecting material. Uniformly presetting the prepared pasty connecting material between the C/C composite material and a high-temperature alloy surface to be welded, and fully contacting the C/C composite material with two base materials by light pressure; the thickness of the preset layer is controlled to be 0.5mm.
And 4, vacuum connection. Placing the weldment to be welded with preset connecting materials into a vacuum brazing furnace, closing the furnace door, and vacuumizing to 5×10 -3 pa; then heating to 1000 ℃ at a heating rate of 15 ℃/min; then heating to 1300 ℃ connection temperature at a heating rate of 50 ℃/min, preserving heat for 25min, and cooling in a furnace at a cooling rate of less than or equal to 5 ℃/min. And taking out the connection sample when the temperature in the furnace is reduced to room temperature.
And 5, joint organization and performance detection. Cutting the connecting joint along the section by using a linear cutting method, polishing the section of the joint step by using 150, 240, 400, 600, 800, 1000, 1200, 1500 and 2000-mesh sand paper, preparing a metallographic specimen, observing the microstructure of the joint by using a scanning electron microscope, and analyzing the phase components by using X-ray diffraction and energy spectrum; and (3) placing the connecting joint obtained in the step (4) into a special fixture, testing the shearing strength at room temperature and high temperature on an electronic universal testing machine, wherein the loading rate is 0.5mm/min, recording the maximum load output when the workpiece is sheared, converting the shearing strength of the joint according to the maximum load, and taking the average value of 5 samples as a final result. The resulting joint had a room temperature shear strength of 28.0MPa.
Example 3
The embodiment is a low-stress high-temperature-resistant connection method of a C/C composite material and GH4169 high-temperature alloy based on in-situ synthesis of a TiC/Ni composite connection layer.
The C/C composite material is a two-dimensional winding and three-dimensional perforation structure, and the density is 1.65-1.78 g/cm 3 Cut into 5X 5mm 3 Is a square of (2); the GH4169 superalloy is a precipitation strengthening Ni-based superalloy with a density of 8.24g/cm 3 The melting temperature is 1260-1320 ℃, and the thermal expansion coefficient is 18.7X10 -6 K -1 Cut into 10X 3mm 3 Is a block of (a). The connecting material consists of Ni62Ti38 alloy powder with granularity of 10-30 microns, carbon fiber length of 0.3mm, monofilament diameter of 6 microns and chopped carbon fiber, and the mass of the carbon fiber in the mixed powderThe fraction was 3%.
The specific process of the embodiment comprises the following steps:
step 1, preparing a base material to be welded. Polishing the surface to be welded of the C/C composite material and the GH4169 superalloy by using 240-600 mesh sand paper to remove surface impurities and oxide films; putting the polished composite material and the high-temperature alloy into alcohol, and repeatedly cleaning for 3 times by using an ultrasonic cleaner; and (5) placing the cleaned product into a vacuum drying oven for drying for standby, wherein the drying temperature is 40 ℃, and the drying time is 10min.
And 2, modulating the connecting material. The Ni62Ti38 alloy powder and the chopped carbon fiber powder are weighed according to the proportion, the powder is mechanically mixed uniformly, and then a proper amount of alpha-terpineol is added for uniform stirring, so that the paste is prepared.
And 3, presetting a connecting material. Uniformly presetting the prepared pasty connecting material between the C/C composite material and a high-temperature alloy surface to be welded, and fully contacting the C/C composite material with two base materials by light pressure; the thickness of the preset layer is controlled to be 0.7mm.
And 4, vacuum connection. Placing the weldment to be welded with preset connecting materials into a vacuum brazing furnace, closing the furnace door, and vacuumizing to 5×10 -3 pa; then heating to 1000 ℃ at a heating rate of 15 ℃/min; then heating to 1300 ℃ connection temperature at a heating rate of 50 ℃/min, preserving heat for 25min, and cooling in a furnace at a cooling rate of less than or equal to 5 ℃/min. And taking out the connection sample when the temperature in the furnace is reduced to room temperature.
And 5, joint organization and performance detection. Cutting the connecting joint along the section by using a linear cutting method, polishing the section of the joint step by using 150, 240, 400, 600, 800, 1000, 1200, 1500 and 2000-mesh sand paper, preparing a metallographic specimen, observing the microstructure of the joint by using a scanning electron microscope, and analyzing the phase components by using X-ray diffraction and energy spectrum; and (3) placing the connecting joint obtained in the step (4) into a special fixture, testing the shearing strength at room temperature and high temperature on an electronic universal testing machine, wherein the loading rate is 0.5mm/min, recording the maximum load output when the workpiece is sheared, converting the shearing strength of the joint according to the maximum load, and taking the average value of 5 samples as a final result. The resulting joint had a room temperature shear strength of 34.3MPa.
The foregoing is merely illustrative of the present invention, and the present invention is not limited thereto, and any person skilled in the art will readily recognize that variations or substitutions are within the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (10)
1. A method for low stress high temperature resistant joining of a C/C composite to a superalloy, comprising:
and taking the mixed powder of the Ni-Ti alloy powder and the carbon-based powder as a connecting material, and reacting the liquid formed by melting the Ni-Ti alloy powder with the carbon-based powder in situ in a welding seam gap between the C/C composite material and the high-temperature alloy at a lower connecting temperature to form the TiC particle reinforced Ni-based solid solution-based composite connecting layer.
2. The method according to claim 1, characterized in that the method comprises:
step S1, preparing a base material to be welded: polishing the surface to be welded of the C/C composite material and the high-temperature alloy, cleaning the C/C composite material and the high-temperature alloy, and drying for later use;
step S2, preparing a connecting material: weighing Ni-Ti alloy powder and carbon-based powder according to a proportion, uniformly mixing to form mixed powder, then adding a proper amount of organic solvent, uniformly stirring, and preparing into paste;
step S3, presetting a connecting material: uniformly presetting the prepared pasty connecting material between the C/C composite material and a high-temperature alloy surface to be welded, and fully contacting the connecting material with two base materials to be welded by light pressure to form a piece to be welded, wherein the connecting material is a preset layer;
step S4, vacuum connection: and placing the to-be-welded piece into a vacuum brazing furnace, vacuumizing the furnace, heating to a connecting temperature, preserving heat for a period of time, and slowly cooling the furnace to room temperature.
3. The method according to claim 1, wherein in step S1, the surface to be welded is sanded with 240-600 mesh sandpaper; using alcohol and cleaning the C/C composite material and the superalloy for 2-3 times in an ultrasonic cleaner; drying in a vacuum drying oven at 40-60deg.C for 10-30min.
4. The method according to claim 1, wherein in step S2 the percentage of Ti atoms in the Ni-Ti alloy powder is 15-40%, the particle size is 10-30 μm, and the alloy powder is preferably Ni62Ti38.
5. The method according to claim 1, wherein in step S2, the particle size of the carbon-based powder is 2 to 5 μm, and the carbon-based powder is at least one selected from the group consisting of diamond, graphite and carbon fiber; the mass fraction of the carbon-based powder in the mixed powder is 1-6%.
6. The method according to claim 1, wherein in step S2 the organic solvent is at least one selected from the group consisting of ethanol, α -terpineol, gasoline-rubber, preferably α -terpineol.
7. The method according to claim 1, wherein in step S3, the preset layer thickness is 0.4-0.7mm.
8. The method according to claim 1, wherein in step S4, the furnace is evacuated to a vacuum of not more than 5X 10 - 3 Pa。
9. The method according to claim 1, wherein in step S4, the heating to the joining temperature is: heating to 800-1000 ℃ at a heating rate of 10-15 ℃/min; then heating to 1180-1300 ℃ at a heating rate of 50 ℃/min.
10. The method according to claim 1, wherein in step S4, the temperature is maintained for 5 to 30 minutes; the cooling speed of the furnace is less than or equal to 5 ℃/min.
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