Preparation method of carbon-silicon-aluminum composite material and bias plate

Abstract

The invention provides a preparation method of a carbon-silicon-aluminum composite material. The preparation method comprises the following steps: treating a carbon fiber preform in a 1100 DEG C inert gas environment for at least one hour; mixing the treated carbon fiber preform with silicon powder, and reacting for at least 6 hours in an inert gas environment of 1450 DEG C to obtain a silicon carbide fiber preform, the mass ratio of the silicon powder to the carbon fiber preform being (1-3): 1; the silicon carbide fiber prefabricated body and aluminum powder are mixed and react for at least 8 hours in the inert gas environment at the temperature of 1,100 DEG C, an aluminum-plated layer prefabricated body is obtained, and the mass ratio of the aluminum powder to the silicon carbide fiber prefabricated body is (1-4): (1-3); and reacting the aluminum-coated layer preform in an air environment at 1500 DEG C for at least 3 hours to obtain the carbon-silicon-aluminum composite material. The invention further provides the bias plate. The carbon-silicon-aluminum composite material obtained by the invention is beneficial to improving the heat conductivity coefficient and the high-temperature-resistant temperature.

Description

Technical Field

[0001] The present invention relates to the technical field of heat-conducting materials, and in particular to a preparation method of a carbon-silicon-aluminum composite material and a deflector plate. Background Art

[0002] Jet deflectors are a critical piece of equipment necessary to ensure safe and continuous takeoffs of carrier-based aircraft on aircraft carriers. Their function is to deflect the high-temperature, high-speed combustion gases ejected from the jet engines upward and outward as the aircraft prepares for takeoff. The engine's jet flame temperature can reach as high as 1300°C, requiring deflectors to possess excellent heat resistance. Furthermore, since aircraft takeoffs on aircraft carriers occur very quickly, and the deflector surface temperature cannot exceed the maximum temperature at which the aircraft tires will not be damaged, the deflector, after absorbing the heat from the jet gases of the previous aircraft, must quickly cool to a temperature within the tolerance range of the tires of the next aircraft. Therefore, high thermal conductivity is also required for the deflectors. Currently, carbon fiber materials lack both high thermal conductivity and good heat resistance. Summary of the Invention

[0003] In order to overcome the deficiencies of the prior art, the purpose of the present invention is to provide a method for preparing a carbon-silicon-aluminum composite material, and the obtained carbon-silicon-aluminum composite material is beneficial for improving thermal conductivity and high temperature resistance.

[0004] In addition, the present application also provides a deflector plate comprising the carbon-silicon-aluminum composite material.

[0005] In order to solve the above problems, the technical solutions adopted by the present invention are as follows: A method for preparing a carbon-silicon-aluminum composite material comprises the following steps: Treating the carbon fiber preform in an inert gas environment at 1100° C. for at least one hour; The treated carbon fiber preform is mixed with silicon powder and reacted in an inert gas environment at 1450° C. for at least 6 hours to obtain a silicon carbide fiber preform, wherein the mass ratio of the silicon powder to the carbon fiber preform is 1-3:1; The silicon carbide fiber preform and aluminum powder are mixed and reacted in an inert gas environment at 1100° C. for at least 8 hours to obtain an aluminum-coated preform, wherein the mass ratio of the aluminum powder to the silicon carbide fiber preform is 1-4:1-3; The aluminum-plated preform is reacted in an air environment at 1500° C. for at least 3 hours to obtain a carbon-silicon-aluminum composite material.

[0006] In some possible implementations, the mass ratio of the silicon powder to the carbon fiber preform is 1:1.

[0007] In some possible implementations, the mass ratio of the aluminum powder to the silicon carbide fiber preform is 1:1 or 4:3.

[0008] In some possible implementations, the mass ratio of the aluminum powder to the silicon carbide fiber preform is 4:3.

[0009] In some possible implementations, the carbon fiber preform is processed for 1 hour.

[0010] In some possible implementations, the reaction time of the carbon fiber preform and the silicon powder is 6 hours.

[0011] In some possible implementations, the reaction time of the silicon carbide fiber preform and the aluminum powder is 8 hours.

[0012] In some possible implementations, the processing time of the aluminum-coated preform is 3 hours.

[0013] In some possible embodiments, the heating rate of the carbon fiber preform processing process is 10°C / min, in the step of mixing the carbon fiber preform with the silicon powder, the heating rate is 5°C / min, in the step of mixing the silicon carbide fiber preform and the aluminum powder, the heating rate is 5°C / min, and in the step of obtaining the carbon-silicon-aluminum composite material, the heating rate is 10°C / min.

[0014] The present application also provides a deflector plate, characterized in that the material of the deflector plate is the carbon-silicon-aluminum composite material obtained by the preparation method.

[0015] Compared with the prior art, the present invention has the following beneficial effects: In this application, carbon fibers react with silicon powder to form silicon carbide fibers, which then react with aluminum powder to form an aluminized layer. The aluminized layer then oxidizes in air at high temperatures to form an aluminum oxide layer. The synergistic effect of the silicon carbide fibers and the aluminum oxide layer improves the thermal conductivity and high-temperature resistance of the composite material. Furthermore, the composite material of this application can be used to prepare a deflector plate, thereby meeting the requirements for rapid heat dissipation and high-temperature resistance.

[0016] The present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 A flow chart of a preparation method provided in one embodiment of the present application; Figure 2 This is an ultra-depth-of-field microscope element inspection image of the carbon-silicon-aluminum composite material obtained in an embodiment of the present application; Figure 3 This is an XRD comparison chart of the carbon-silicon-aluminum composite material obtained in Example 4 of the present application and the standard spectrum. DETAILED DESCRIPTION

[0018] The following will be combined with the drawings in the embodiments of this application to clearly and completely describe the technical solutions in the embodiments of this application. Obviously, the embodiments described are only part of the embodiments of this application, not all of the embodiments. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.

[0019] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as those commonly understood by those skilled in the art of the present invention. The terms used in this specification of the present invention are only for the purpose of describing specific embodiments and are not intended to limit the present invention.

[0020] The following embodiments of the present invention are described in detail with reference to the accompanying drawings. In the absence of conflict, the following embodiments and features in the embodiments may be combined with each other.

[0021] An embodiment of the present application provides a method for preparing a carbon-silicon-aluminum composite material, comprising the following steps.

[0022] Step S101: treating the carbon fiber preform in an inert gas environment at 1100° C. for at least one hour.

[0023] In some embodiments, the carbon fiber preform is treated in an inert gas environment at 1100° C. for one hour.

[0024] In some embodiments, the heating rate of the carbon fiber preform during the treatment process is 10° C. / min.

[0025] Step S102: The treated carbon fiber preform is mixed with silicon powder and reacted in an inert gas environment at 1450° C. for at least 6 hours to obtain a silicon carbide fiber preform. The mass ratio of the silicon powder to the carbon fiber preform is 1-3:1. In some embodiments, the reaction time of the carbon fiber preform and the silicon powder is 6 hours.

[0026] In some embodiments, the mass ratio of the silicon powder to the carbon fiber preform is 1:1. Further limiting the ratio is beneficial to further improve the thermal conductivity and the temperature tolerance.

[0027] In some embodiments, in the step of mixing the carbon fiber preform with the silicon powder, the heating rate is 5° C. / min.

[0028] Step S103: mixing the silicon carbide fiber preform and aluminum powder, and reacting them at 1100° C. in an inert gas environment for at least 8 hours to obtain an aluminum-coated preform, wherein the mass ratio of the aluminum powder to the silicon carbide fiber preform is 1-4:1-3.

[0029] In some embodiments, the mass ratio of the aluminum powder to the silicon carbide fiber preform is 1:1 or 4:3, and the ratio of aluminum to silicon carbide fiber preform is further limited to ensure the temperature resistance is 1400° C. or above.

[0030] In some embodiments, the mass ratio of the aluminum powder to the silicon carbide fiber preform is 4:3. Further limiting the ratio is conducive to ensuring the formation of α-Al2O3, thereby further improving the thermal conductivity and temperature tolerance of the composite material.

[0031] In some embodiments, the reaction time of the silicon carbide fiber preform and the aluminum powder is 8 hours.

[0032] In some embodiments, in the step of mixing the silicon carbide fiber preform and the aluminum powder, the heating rate is 5° C. / min.

[0033] Step S104: reacting the aluminum-plated preform in an air environment at 1500° C. for at least 3 hours to obtain a carbon-silicon-aluminum composite material.

[0034] In some embodiments, in the step of obtaining the carbon-silicon-aluminum composite material, the heating rate is 10° C. / min. Further reducing the heating rate of each step is beneficial to reducing thermal stress, thereby improving service life.

[0035] In some embodiments, the processing time of the aluminum-coated preform is 3 hours.

[0036] For example, the inert gas in the above steps can be argon.

[0037] The element inspection image of the carbon-silicon-aluminum composite material prepared in this application is as follows Figure 2 shown.

[0038] Another embodiment of the present application also provides a deflector plate, wherein the material of the deflector plate is a carbon-silicon-aluminum composite material obtained by the preparation method described in the above embodiment.

[0039] In this application, carbon fibers react with silicon powder to form silicon carbide fibers, which then react with aluminum powder to form an aluminized layer. The aluminized layer then oxidizes in air at high temperatures to form an aluminum oxide layer. The synergistic effect of the silicon carbide fibers and the aluminum oxide layer improves the thermal conductivity and high-temperature resistance of the composite material. Furthermore, the composite material of this application can be used to prepare a deflector plate, thereby meeting the requirements for rapid heat dissipation and high-temperature resistance.

[0040] The following describes the method in detail. Example 1

[0041] The carbon fiber preform is treated in an argon environment at 1100 degrees for one hour. The heating rate in this step is 10°C / min. The treated carbon fiber preform is then mixed with silicon powder and reacted in an argon environment at 1450 degrees for 6 hours to obtain a silicon carbide fiber preform. The mass ratio of the silicon powder to the carbon fiber preform is 1:1. In this step, the heating rate is 5°C / min. The prepared silicon carbide fiber preform is mixed with aluminum powder. The mass ratio of the aluminum powder to the silicon carbide fiber preform is 4:3. The preform is reacted in an argon environment at 1100 degrees for 8 hours to obtain an aluminum-plated preform. In this step, the heating rate is 5°C / min. The aluminum-plated preform is reacted in an air environment at 1500°C for 3 hours to obtain a carbon-silicon-aluminum composite material. In this step, the heating rate is 10°C / min. Example 2

[0042] The carbon fiber preform is treated in an argon environment at 1100 degrees for one hour. The heating rate in this step is 10°C / min. The treated carbon fiber preform is then mixed with silicon powder and reacted in an argon environment at 1450 degrees for 6 hours to obtain a silicon carbide fiber preform. The mass ratio of the silicon powder to the carbon fiber preform is 3:1. In this step, the heating rate is 5°C / min. The prepared silicon carbide fiber preform is mixed with aluminum powder. The mass ratio of the aluminum powder to the silicon carbide fiber preform is 4:3. The preform is reacted in an argon environment at 1100 degrees for 8 hours to obtain an aluminum-plated preform. In this step, the heating rate is 5°C / min. The aluminum-plated preform is reacted in an air environment at 1500°C for 3 hours to obtain a carbon-silicon-aluminum composite material. In this step, the heating rate is 10°C / min. Example 3

[0043] The carbon fiber preform is treated in an argon environment at 1100 degrees for one hour. The heating rate in this step is 10°C / min. The treated carbon fiber preform is then mixed with silicon powder and reacted in an argon environment at 1450 degrees for 6 hours to obtain a silicon carbide fiber preform. The mass ratio of the silicon powder to the carbon fiber preform is 1:1. In this step, the heating rate is 5°C / min. The prepared silicon carbide fiber preform is mixed with aluminum powder. The mass ratio of the aluminum powder to the silicon carbide fiber preform is 1:1. The preform is reacted in an argon environment at 1100 degrees for 8 hours to obtain an aluminum-plated preform. In this step, the heating rate is 5°C / min. The aluminum-plated preform is reacted in an air environment at 1500°C for 3 hours to obtain a carbon-silicon-aluminum composite material. In this step, the heating rate is 10°C / min. Example 4

[0044] The carbon fiber preform is treated in an argon environment at 1100 degrees for one hour. The heating rate in this step is 10°C / min. The treated carbon fiber preform is then mixed with silicon powder and reacted in an argon environment at 1400 degrees for 6 hours to obtain a silicon carbide fiber preform. The mass ratio of the silicon powder: the carbon fiber preform is 1:1. In this step, the heating rate is 5°C / min. The prepared silicon carbide fiber preform is mixed with aluminum powder. The mass ratio of the aluminum powder: the silicon carbide fiber preform is 4:3. The preform is reacted in an argon environment at 1100 degrees for 8 hours to obtain an aluminum-plated preform. In this step, the heating rate is 5°C / min. The aluminum-plated preform is reacted in an air environment at 1500°C for 3 hours to obtain a carbon-silicon-aluminum composite material. In this step, the heating rate is 10°C / min. Silicon carbide and α-alumina crystal forms are obtained in this embodiment. For details, see Figure 3 .

[0045] The test results of the above embodiment are shown in the following table Thermal conductivity (W / (m·K)) Temperature resistance (°C) Example 1 40 1480 Example 2 20 1300 Example 3 47 1500 Example 4 45 1600 From the analysis of the above table, it can be seen that further limiting the ratio of silicon powder, carbon fiber preform and aluminum powder is conducive to further improving the thermal conductivity and high temperature resistance of the composite material. Among them, the performance of the composite material obtained by the combination of parameters in Example 4 is the best.

[0046] For example, the thermal conductivity of the material can be tested by measuring specific heat capacity using a differential scanning calorimeter (DSC), as specified in GB / T 39862-2021. Temperature resistance can be tested using a tube furnace to determine the temperature at which the weight loss exceeds 5%, as specified in GB / T 10294-2008.

[0047] The above embodiments are only preferred embodiments of the present invention and cannot be used to limit the scope of protection of the present invention. Any non-substantial changes and replacements made by technicians in this field on the basis of the present invention fall within the scope of protection required by the present invention.

Claims

1. A method for preparing a carbon-silicon-aluminum composite material, characterized in that: The steps include: Treating the carbon fiber preform in an inert gas environment at 1100° C. for at least one hour; The treated carbon fiber preform is mixed with silicon powder and reacted in an inert gas environment at 1450° C. for at least 6 hours to obtain a silicon carbide fiber preform, wherein the mass ratio of the silicon powder to the carbon fiber preform is 1-3:1; The silicon carbide fiber preform and aluminum powder are mixed and reacted in an inert gas environment at 1100° C. for at least 8 hours to obtain an aluminum-coated preform, wherein the mass ratio of the aluminum powder to the silicon carbide fiber preform is 1-4:1-3; The aluminum-plated preform is reacted in an air environment at 1500° C. for at least 3 hours to obtain a carbon-silicon-aluminum composite material.

2. The preparation method according to claim 1, wherein The mass ratio of the silicon powder to the carbon fiber preform is 1:

1.

3. The preparation method according to claim 2, wherein The mass ratio of the aluminum powder to the silicon carbide fiber preform is 1:1 or 4:

3.

4. The preparation method according to claim 3, wherein The mass ratio of the aluminum powder to the silicon carbide fiber preform is 4:

3.

5. The preparation method according to claim 1, wherein The processing time of the carbon fiber preform is 1 hour.

6. The preparation method according to claim 5, wherein The reaction time of the carbon fiber preform and the silicon powder is 6 hours.

7. The preparation method according to claim 6, wherein The reaction time of the silicon carbide fiber preform and the aluminum powder is 8 hours.

8. The preparation method according to claim 7, wherein The processing time of the aluminum-plated preform is 3 hours.

9. The preparation method according to any one of claims 1 to 8, characterized in that The heating rate of the carbon fiber preform processing process is 10°C / min, the heating rate of the carbon fiber preform and the silicon powder mixing step is 5°C / min, the heating rate of the silicon carbide fiber preform and the aluminum powder mixing step is 5°C / min, and the heating rate of the carbon silicon aluminum composite material obtaining step is 10°C / min.

10. A deflector plate, characterized in that: The material of the deflector plate is a carbon-silicon-aluminum composite material obtained by the preparation method according to any one of claims 1 to 9.

Images