WO2023124269A1 - High-temperature-resistant carbon-carbon composite body and production method therefor, and carbon fiber prefab - Google Patents

Abstract

A high-temperature-resistant carbon-carbon composite body and a production method therefor, and a carbon fiber prefab, relating to the technical field of solar photovoltaics. The method comprises: laying at least one layer of carbon fiber web on the surface of a carbon fiber assembly having few weave points, and then needle punching to form a composite cloth; providing a carbon fiber structure on the outer surface of a mold to obtain a carbon fiber prefab; the carbon fiber structure comprises: a stacked machined layer and a first prefab body; at least one machined layer comprises a mesh structure; the mesh structure is formed by laying at least one layer of multi-weave point carbon fiber fabric; removing the mold from the carbon fiber prefab and performing densification, obtaining a machined precursor; and removing the machined layer from the machined precursor. The carbon fibers are arranged straight and evenly to maximize the tensile properties of carbon fibers. The composite cloth reduces the intrusion channels of high-temperature steam and prolongs the life of the high-temperature-resistant carbon-carbon composite body. The machined layer facilitates vapor deposition and can prevent surface crusting.

Description

A high-temperature-resistant carbon-carbon composite body, its production method, and carbon fiber prefabricated body

This application claims the priority of the Chinese patent application submitted to the China Patent Office on December 30, 2021, with the application number 202111680622.X and the title of the invention "a high temperature resistant carbon-carbon composite body and its production method, and carbon fiber prefabricated body" , the entire contents of which are incorporated in this application by reference.

technical field

The invention relates to the field of solar photovoltaic technology, in particular to a high-temperature-resistant carbon-carbon composite body, a production method thereof, and a carbon fiber prefabricated body.

Background technique

High-temperature resistant carbon-carbon composites are widely used in the fields of aerospace, friction resistance, and furnace heat field. At present, the production method of high-temperature-resistant carbon-carbon composites is mainly: adopting two-way plain weave structure and carbon fiber mesh tires to be alternately laminated and needled, and then undergoing densification and removal of machine-added layers.

In the process of studying the above-mentioned prior art, the inventor found that: the high-temperature-resistant carbon-carbon composite prepared by the existing production method of the high-temperature-resistant carbon-carbon composite has a short service life.

Contents of the invention

The invention provides a high-temperature-resistant carbon-carbon composite body, a production method thereof, and a carbon fiber prefabricated body, aiming at solving the problem that the prepared high-temperature-resistant carbon-carbon composite body has a short service life.

The first aspect of the present invention provides a high temperature resistant carbon-carbon composite and its production method, the method comprising:

Lay at least one layer of carbon fiber net tire on the surface of the carbon fiber assembly with few weaving points, and then needle punch to form a composite cloth; the carbon fiber assembly with few weaving points includes: no weft cloth, and/or, at least one bundle arranged in parallel in a plane a first carbon fiber filament tow;

A carbon fiber structure is arranged on the outer surface of the mold to obtain a carbon fiber preform; the carbon fiber structure includes: a machine-added layer and a first preform body stacked; the machine-added layer is located between the mold and the first preform Between the bodies, and/or, the machine-added layer is located on the side of the first preform body away from the mold; at least one machine-added layer contains a mesh structure; the mesh structure consists of at least one layer and more Weave point carbon fiber fabric is laid and formed; the first prefabricated body is formed by at least one layer of unit layers stacked and needled; thorn formation;

removing the mold from the carbon fiber preform and performing a densification treatment to obtain a machined precursor;

The machining layer is removed from the machining precursor.

In the embodiment of the present invention, at least one layer of carbon fiber mesh is laid on the surface of the carbon fiber aggregate with few weaving points, and then needle punched to form a composite cloth. The range makes the carbon fibers arranged as straight and even as possible, maximizes the tensile properties of the carbon fibers, increases the load-bearing limit of the composite cloth, and can increase the life of the high-temperature-resistant carbon-carbon composite. Moreover, in the composite cloth, the carbon fibers are more likely to be arranged straight and evenly, with fewer weaving points, which reduces the intrusion channel of high-temperature steam in the high-temperature-resistant carbon-carbon composite, and greatly reduces the degree of corrosion of hot high-temperature steam. Further prolonging the life of the high temperature resistant carbon-carbon composite. At the same time, the multi-weave carbon fiber fabric in at least one machine-added layer makes the porosity of the machine-added layer higher, which is beneficial to the vapor deposition in the densification process, and can prevent surface crusting, and the machine-added layer is made It is removed before the finished product and will not affect the service life of the finished product. There are fewer weaving points in the carbon fiber aggregate with less weaving points, and there are fewer weaving points in the above-mentioned high-temperature-resistant carbon-carbon composite body, so that the thickness or surface density of the high-temperature-resistant carbon-carbon composite body is less restricted, and it can be obtained The high-temperature-resistant carbon-carbon composite body with thicker thickness and larger surface density can increase the application range of the high-temperature-resistant carbon-carbon composite body.

Optionally, in the case where the mold is a crucible mold or an insulated cylinder mold, the machine-added layer is only located between the mold and the first preform body;

In the case that the mold is a heat shield outer bladder mold, the machine-added layer is only located on the side of the first preform body away from the mold.

Optionally, at least one of the machine-added layers includes: a surplus portion formed by stacking needle punching of at least one of the unit layers.

Optionally, when one layer of machine-added layer includes both the mesh structure and the margin part, the margin part is located between the mesh structure and the first preform body , the margin part and the first preform body are integrally formed; the thickness of the margin part is 1-3 mm; the thickness of the margin part is: the margin part is along the mesh structure and The size of the stacking direction of the first preform body.

Optionally, the mold includes a straight arm part parallel to the axial direction thereof, a bottom perpendicular to the straight arm part, and an arc connecting the straight arm part and the bottom;

When the thickness of the arc portion is greater than the thickness of the straight arm, and the difference between the two thicknesses is greater than or equal to 5 mm, the carbon fiber structure further includes: located on the outer surface of the unit layer, and connected to the arc portion The second preform body oppositely arranged; the second preform body is formed by winding the composite cloth; the thickness of the straight arm is: the dimension of the straight arm in a direction perpendicular to the axial direction of the mould.

Optionally, the areal density of the machined layer is less than or equal to the areal density of the first preform body, and/or, the areal density of the machined layer is less than or equal to the areal density of the second preform body.

Optionally, the areal density of the machine-added layer is less than or equal to 350g/m ² ; and/or, the areal density of the first preform body is greater than or equal to 400g/m ² ; and/or, the areal density of the second preform body Greater than or equal to 400g/m ² .

Optionally, the step of winding the composite cloth includes: first obliquely winding the composite cloth with the second carbon fiber filament bundle, and then hooping the composite cloth; wherein, during the hoop winding process, The second carbon fiber filament bundle is perpendicular to the axial direction of the mold.

The second aspect of the present invention provides a carbon fiber prefabricated body, including: a first prefabricated body and a machine-added layer stacked; in the stacking direction of the first prefabricated body and the machine-added layer, the machine-added layer is located at least one side of the first preform body;

The first prefabricated body is formed by laminating at least one unit layer; the unit layer is formed by laminating at least one layer of carbon fiber mesh after the composite cloth is wound;

The composite cloth is composed of at least one layer of carbon fiber net tires stacked on the plane of a carbon fiber aggregate with few weaving points; the carbon fiber aggregate with few weaving points includes: no weft fabric, and/or at least one bundle of first bundles arranged in parallel in a plane Carbon fiber filament tow;

At least one machine-added layer includes a mesh structure; the mesh structure is formed by laminating at least one layer of multi-weave carbon fiber fabric.

Optionally, when the number of unit layers in the first preform body is greater than 1, the included angle between the first carbon fiber filament bundles in adjacent unit layers is greater than 0.

Optionally, when the number of unit layers in the first preform body is greater than or equal to 4, the first preform body includes at least one first unit layer, at least one second unit layer, at least one a third unit layer, at least one fourth unit layer;

Wherein, the first carbon fiber filament bundle in the first unit layer is perpendicular to the axial direction of the mold, the first carbon fiber filament bundle in the second unit layer is parallel to the axial direction of the mold, and the first carbon fiber filament bundle in the third unit layer is parallel to the axial direction of the mold. The included angle between the axial directions of the molds is +45°, and the included angle between the first carbon fiber filament bundles in the fourth unit layer and the axial directions of the molds is -45°.

The above-mentioned carbon fiber prefabricated body has the same or similar beneficial effects as the above-mentioned production method of the high-temperature-resistant carbon-carbon composite body, and in order to avoid repetition, details are not repeated here.

In a third aspect of the present invention, a high temperature resistant carbon-carbon composite body is provided, comprising:

At least one unit layer; when the number of unit layers is greater than 1, each unit layer is stacked;

The unit layer is composed of at least one layer of carbon fiber mesh after the composite cloth is wound;

The composite cloth is composed of at least one layer of carbon fiber net tires stacked on the plane of a carbon fiber aggregate with few weaving points; the carbon fiber aggregate with few weaving points includes: no weft fabric, and/or at least one bundle of first bundles arranged in parallel in a plane Carbon fiber filament tow.

The above-mentioned high-temperature-resistant carbon-carbon composite has the same or similar beneficial effects as the above-mentioned production method of the high-temperature-resistant carbon-carbon composite, and in order to avoid repetition, details are not repeated here.

Description of drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following will briefly introduce the accompanying drawings that need to be used in the description of the embodiments of the present invention. Obviously, the accompanying drawings in the following description are only some embodiments of the present invention , for those skilled in the art, other drawings can also be obtained according to these drawings without paying creative labor.

Fig. 1 shows the step flow chart of the production method of a kind of high temperature resistant carbon-carbon composite body in the embodiment of the present invention;

Fig. 2 shows a schematic structural view of a first carbon fiber filament bundle arranged parallel to a plane in an embodiment of the present invention;

Fig. 3 shows a schematic structural view of a carbon fiber preform in an embodiment of the present invention;

Fig. 4 shows a schematic structural view of an oblique winding wire in an embodiment of the present invention;

Fig. 5 shows a schematic structural view of a hoop-wrapped wire in an embodiment of the present invention.

Explanation of attached drawing numbers:

101-the first carbon fiber filament bundle, 102-the machine-added layer, 103-the first preform body, 104-needling buffer layer, 105-the second carbon fiber filament bundle, 200-the mold, 201-the arc portion of the mold.

specific embodiment

The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are some of the embodiments of the present invention, but not all of them. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without creative efforts fall within the protection scope of the present invention.

Fig. 1 shows a flow chart of steps of a production method of a high-temperature-resistant carbon-carbon composite in an embodiment of the present invention. Referring to Fig. 1, the production method of the high-temperature-resistant carbon-carbon composite includes the following steps:

Step S1, laying at least one layer of carbon fiber mesh on the surface of the carbon fiber assembly with few weaving points, and then needle punching to form a composite cloth; the carbon fiber assembly with few weaving points includes: no weft cloth, and/or, arranged in parallel to form a plane At least one bundle of first carbon fiber filament bundles.

There are fewer weaving points in the non-woven fabric, and the interweaving and bending range of carbon fibers is small. The carbon fibers are arranged as straight and even as possible to maximize the tensile properties of carbon fibers. At least one layer of carbon fiber mesh is laid on the surface of the non-weft fabric, and then acupuncture A composite cloth is formed, and the composite cloth has a better bearing capacity, which can increase the life of the high-temperature-resistant carbon-carbon composite body. Moreover, in the non-weft fabric, the carbon fibers are more likely to be arranged straight and evenly, with fewer weaving points, which reduces the intrusion channel of high-temperature steam in the high-temperature-resistant carbon-carbon composite, and greatly reduces the degree of corrosion of hot high-temperature steam , Further prolonging the life of the high temperature resistant carbon-carbon composite.

It should be noted that the carbon fiber aggregates with few weaving points may include carbon fiber aggregates with a floating length greater than or equal to 5, or carbon fiber aggregates without weaving points. Specifically, the floating length includes warp floating length or weft floating length, wherein, the warp floating length refers to the warp length continuously floating on the weft yarn in the fabric, and the weft floating length refers to the weft yarn continuously floating on the warp yarn in the fabric length. Fig. 2 shows a schematic structural view of a first carbon fiber filament bundle arranged parallel to a plane in an embodiment of the present invention. Referring to FIG. 2 , multiple bundles of first carbon fiber filament bundles 101 are arranged in parallel to form a plane. At least one bundle of first carbon fiber filament bundles arranged in parallel in a plane has no weaving point at all, and the carbon fibers are not interwoven and bent. The carbon fibers are all straight and evenly arranged to maximize the tensile performance of carbon fibers. At least one layer of carbon fiber mesh tire is laid on the surface of a carbon fiber filament bundle, and then needle-punched to form a composite cloth. The composite cloth has a better bearing capacity and can increase the life of the high-temperature-resistant carbon-carbon composite. Moreover, in at least one bundle of first carbon fiber filament bundles arranged parallel to a plane, the carbon fibers are arranged straight and evenly with the greatest probability, and there are no weaving points at all, which reduces the intrusion channel of high-temperature steam in the high-temperature-resistant carbon-carbon composite body, and greatly The degree of corrosion of hot high-temperature steam is reduced to a certain extent, and the life of high-temperature-resistant carbon-carbon composites is further extended.

Step S2, setting a carbon fiber structure on the outer surface of the mold to obtain a carbon fiber preform; the carbon fiber structure includes: a stacked machine-added layer and a first preform body; the machine-added layer is located between the mold and the second Between a preform body, and/or, the machine-added layer is located on the side of the first preform body away from the mold; at least one machine-added layer includes a mesh structure; the mesh structure consists of at least A layer of multi-weave carbon fiber fabric is laid; the first prefabricated body is formed by at least one layer of unit layers stacked and needled; the unit layer is: after winding the composite cloth, laying at least one layer of carbon fiber mesh Acupuncture formation after the fetus.

The shape and size of the mold can be correspondingly matched with the shape and size of the high-temperature resistant carbon-carbon composite body, which is not specifically limited in the embodiment of the present invention. A carbon fiber structure is provided on the outer surface of the mold to obtain a carbon fiber preform. The carbon fiber structure includes: a stacked machine-added layer and a first prefabricated body. The machine-added layer is located between the mold and the first preform body, and/or the machine-added layer is located on a side of the first preform body away from the mold. That is to say, there are three situations in which the machine-added layer exists: in one case, the machine-added layer is only located between the mold and the first prefabricated body; in the other case, the machine-added layer is only located between the first preformed body The side away from the mold; in another case, the machine-added layer is located between the mold and the first preform body, and at the same time, the machine-added layer is also located on the side of the first preform body away from the mold. As for the specific location of the machine-added layer, it is set according to actual needs, and is not specifically limited in this embodiment of the present invention.

Fig. 3 shows a schematic structural view of a carbon fiber preform in an embodiment of the present invention. 200 in FIG. 3 is a mold, and the carbon fiber structure includes: a machine-added layer 102 and a first prefabricated body 103 that are stacked. In FIG. 3 , the machine-added layer 102 is located between the mold 200 and the first preform body 103 , and the machine-added layer 102 is also located on the side of the first preform body 103 away from the mold 200 . 104 in FIG. 3 may be a needle-punched buffer layer. The function of the acupuncture buffer layer 104 is mainly to provide a buffer for the needle during the acupuncture process. The material of the needle-punched buffer layer 104 may be a PVC board or the like, which is not specifically limited in this embodiment of the present invention.

At least one machine-added layer contains a mesh structure, and the mesh structure is formed by laying at least one layer of multi-weaving point carbon fiber fabric. Specifically, if the machine-added layer is only located on the side of the first preform body away from the mold, then the machine-added layer contains the aforementioned mesh structure. If the machine-added layer is only located between the first preform body and the mould, then the machine-added layer contains the aforementioned mesh structure. If the machine-added layer is located between the mold and the first preform body, and at the same time, the machine-added layer is also located on the side of the first preform body away from the mold, then only the machine layer located between the mold and the first preform body may be The added layer contains the above-mentioned mesh structure; it can also be that only the machine-added layer located on the side of the first preform body away from the mold contains the above-mentioned mesh structure; it can also be a machine-added layer located between the mold and the first preform body The layer and the machine-added layer located on the side of the first preform body away from the mold all include the above-mentioned mesh structure, which is not specifically limited in the embodiment of the present invention. The above-mentioned multi-weave carbon fiber fabric may be a carbon fiber fabric with more weaving points than the non-weaving fabric. For example, the multi-weave carbon fiber fabric may be a carbon fiber plain weave or a carbon fiber twill weave, which is not specifically limited in this embodiment of the present invention. In the mesh structure, when the number of layers of the multi-weaving point carbon fiber fabric is greater than 1, needle punching can be performed on the laid multi-weaving point carbon fiber fabric. The mesh structure may also include a carbon fiber mesh tire, for example, a carbon fiber mesh tire and a multi-weave carbon fiber fabric are laminated and laid, and the mesh structure is formed by needle punching.

It should be noted that the multi-weave carbon fiber fabric may include a carbon fiber fabric with a floating length of less than 5, wherein the floating length includes a warp floating length or a weft floating length, and the warp floating length refers to continuous floating on the weft yarn in the fabric. The length of the warp yarn, the weft float length refers to the length of the weft yarn that floats continuously on the warp yarn in the fabric.

At least one machine-added layer contains the above-mentioned mesh structure, and the mesh structure is formed by laying multi-weave carbon fiber fabrics. Multi-weave points mean higher porosity, so the higher porosity of the machine-added layer is conducive to densification treatment The vapor deposition in the machine can prevent surface crusting, and the machine-added layer is removed before it is made into a finished product. Even if there are multi-woven carbon fiber fabrics in the machine-added layer, it will not be added to Introducing the intrusion channel of high-temperature steam into the finished product will not affect the service life of the finished product. In addition, the above-mentioned mesh structure does not require wire winding, and the production method is simple.

Optionally, the porosity of the mesh structure is greater than the porosity of the first prefabricated body, which is beneficial to the vapor deposition in the densification process, and can prevent surface crusting, and the machine-added layer is removed before it is made into a finished product, so it will not Introducing the intrusion channel of high-temperature steam into the finished product will not affect the service life of the finished product.

Optionally, the areal density of the mesh structure is less than the areal density of the first preform body, and/or, the strength of the carbon fibers in the mesh structure is less than the strength of the carbon fibers in the first preform body, and/or, the strength of the carbon fibers in the mesh structure is The modulus of the carbon fiber is smaller than that of the carbon fiber in the first prefabricated body. On the one hand, it is beneficial to the vapor deposition in the densification process, and can prevent the surface crusting, and the machine-added layer is removed before it is made into a finished product. Introducing the intrusion channel of high-temperature steam into the finished product will not affect the service life of the finished product. On the other hand, it can also reduce costs and facilitate processing.

Optionally, at least one machine layer may include: a surplus portion formed by stacking needle punching of at least one of the above-mentioned unit layers. Specifically, if the machine-added layer is only located on the side of the first preform body away from the mold, the machine-added layer may contain the aforementioned mesh structure and surplus. If the machine-added layer is only located between the first preform body and the mould, the machine-added layer may contain the aforementioned mesh structure and surplus. If the machine-added layer is located between the mold and the first preform body, and at the same time, the machine-added layer is also located on the side of the first preform body away from the mold, then the above-mentioned surplus part can be located in at least one of the two machine-added layers In the embodiment of the present invention, there is no specific limitation on whether the margin part and the above-mentioned mesh structure are located in the same machine-added layer. For example, the machine-added layer located between the mold and the first preform body only contains the mesh structure, that is to say the mesh structure directly serves as the machine-added layer; the machine-added layer located on the side of the first preform body away from the mold only contains The margin part, that is to say, the margin part is directly used as a machine-added layer. The preparation method of the above-mentioned surplus part is the same as that of the first preform body, and the processing method is simple.

Optionally, in the case where a machine-added layer includes both the above-mentioned mesh structure and the margin part, the margin part is located between the mesh structure and the first prefabricated body, that is to say, the needles are stacked by the above-mentioned unit layers. The remaining part of the thorn is close to the first prefabricated body. During the preparation process, the first preformed body and the remaining part are integrally formed or prepared at one time. The production method is simple. At the same time, the mesh structure is far away from the first preformed body. That is, the mesh structure is located on the outside of the carbon fiber preform, which is more conducive to vapor deposition and prevents surface crusting. In this case, this margin can exist as a machined margin.

Optionally, when one layer of machine-added layer includes the above-mentioned mesh structure and the margin part, the thickness of the margin part is 1-3mm, and the thickness of the margin part is: the margin part is along the mesh structure and the dimension in the stacking direction of the first prefabricated body, the thickness of the remaining part is small, which is beneficial to cost saving.

After wrapping the above-mentioned composite cloth, at least one layer of carbon fiber net tire is laid and needled to form a unit layer, and at least one layer of unit layers is stacked and needled to form the first prefabricated body. There is no specific limitation on how many layers of carbon fiber mesh tires are laid during the process of forming the unit layer. There is also no specific limitation on how many layers of the first preform body are formed by stacking and needling. The above-mentioned first prefabricated body is a high-temperature-resistant carbon-carbon composite body after subsequent processing. Then, in the high-temperature-resistant carbon-carbon composite body, the degree of interweaving and bending of carbon fibers is small or even almost non-existent, so that the carbon fibers are arranged as straight and even as possible. , to maximize the tensile properties of carbon fibers, improve the load-bearing limit of composite cloth, and improve the life of high-temperature-resistant carbon-carbon composites. Moreover, in the composite cloth, the carbon fibers are more likely to be arranged straight and evenly, with fewer weaving points, which reduces the intrusion channel of high-temperature steam in the high-temperature-resistant carbon-carbon composite, and greatly reduces the degree of corrosion of hot high-temperature steam. Further prolonging the life of the high temperature resistant carbon-carbon composite. There are fewer weaving points in the carbon fiber aggregate with less weaving points, and then there are fewer weaving points in the above-mentioned high-temperature-resistant carbon-carbon composite body, so that the thickness or surface density of the first prefabricated body or the high-temperature-resistant carbon-carbon composite body is limited. Less, high temperature resistant carbon-carbon composites with thicker thickness and larger surface density can be produced, and the applicable range of high temperature resistant carbon carbon composites can be increased.

Optionally, the above-mentioned step of winding the composite cloth may include: first obliquely winding the composite cloth with the second carbon fiber filament bundle, and then circumferentially winding the composite cloth; wherein, during the circumferential winding process, The second carbon fiber filament bundle is perpendicular to the axial direction of the mold. Fig. 4 shows a schematic structural view of an oblique winding wire in an embodiment of the present invention. In FIG. 4 , the second carbon fiber filament bundle 105 is not perpendicular to the axis L of the mold, and the angle between the second carbon fiber filament bundle 105 and the axis L of the mold is not specifically limited. Fig. 5 shows a schematic structural view of a hoop-wrapped wire in an embodiment of the present invention. In FIG. 5 , the second carbon fiber filament bundle 105 is perpendicular to the axis L of the mold. The oblique wire winding mainly reinforces the seam, and the hoop wire winding can enhance the hoop strength. It should be noted that the strength, modulus, etc. of the second carbon fiber filament bundle may be equal to or different from the aforementioned first carbon fiber filament bundle, which is not specifically limited in this embodiment of the present invention.

Optionally, in the case where the mold is a crucible mold or an insulating tube mold, the machine-added layer is only located between the mold and the first preform body, that is, the machine-added layer is only located on the inner side of the first preform body, and the machine-added layer is only located on the inner side of the first preform body. The inner surface of the obtained crucible and insulation cylinder is smoother. The inner surfaces of the crucible and the heat-insulating cylinder need to be used as assembly surfaces, and the inner surfaces of the crucible and the heat-insulating cylinder are smoother, which is beneficial to assembly. However, in the actual application process of the crucible and the heat preservation cylinder, the smoothness of the outer surface is not required to be high, and the machine-added layer may not be provided, so there is no material waste, the cost can be reduced, and the production method is simple.

Optionally, in the case where the mold is a heat shield outer mold, the machine-added layer is only located on the side of the first preform body away from the mold, that is, the machine-added layer is only located on the outside of the first preform body, and the machine-added layer is only located on the outside of the first preform body. The outer surface of the obtained heat shield outer bladder is smoother. The outer surface of the heat shield outer tube needs to be used as an assembly surface, and the outer surface of the heat shield outer tube is smoother, which is convenient for assembly. However, in the actual application process of the heat shield outer tube, the smoothness of the inner surface is not high, there is no machine-added layer, there is no material waste, the cost can be reduced, and the production method is simple.

Optionally, as shown in FIG. 3 , the mold 200 includes a straight arm part parallel to the axial direction L thereof, a bottom perpendicular to the straight arm part, and an arc part 201 connecting the straight arm part and the bottom. In the case where the thickness of the arc portion 201 is greater than the thickness of the straight arm, and the thickness of the arc portion 201 and the thickness of the straight arm have a thickness difference greater than or equal to 5mm, the carbon fiber structure also includes: the outer surface of the unit layer, and The arc portion 201 is opposite to the second preform body. The second preform body is formed by winding composite cloth. The thickness of the straight arm is: the dimension of the straight arm in a direction perpendicular to the axial direction L of the mold 200 . In the case where the difference between the two thicknesses is greater than or equal to 5 mm, the curvature of the carbon fibers in the prepared high-temperature-resistant carbon-carbon composite body is small by arranging the second preform body, and the preparation method is simple.

Optionally, the areal density of the machined layer is less than or equal to the areal density of the first preform body, and/or, the areal density of the machined layer is less than or equal to the areal density of the second preform body. The machine-added layer needs to be removed before forming the finished product. Therefore, setting its surface density lower can reduce production costs, and the preparation method is simple. At the same time, it can also facilitate the vapor deposition in the densification process and prevent surface crusting. Will affect the service life of the finished product.

Optionally, the areal density of the machine-added layer is less than or equal to 350g/m ² ; and/or, the areal density of the first preform body is greater than or equal to 400g/m ² ; and/or, the areal density of the second preform body The production cost greater than or equal to 400g/m ² can be reduced, and the preparation method is simple, and at the same time, it can also facilitate the vapor deposition in the densification process, prevent surface crusting, and will not affect the service life of the finished product.

Optionally, in step S2, in the process of forming the first preform body, when the unit layers are stacked, the angle between the first carbon fiber filament bundles in adjacent unit layers is greater than 0, that is, adjacent unit layers In the unit layer, the first carbon fiber filament bundles can be non-parallel, which can increase the anti-extrusion strength of the high-temperature-resistant carbon-carbon composite in different directions, greatly improve its overall mechanical properties, and prolong its service life. It should be noted that, in adjacent unit layers, the angle between the first carbon fiber filament bundles is not specifically limited. For example, in adjacent unit layers, the included angles between the first carbon fiber filament bundles can be equal, and then the angle between the first carbon fiber filament bundles in the adjacent unit layers in the formed first preform body or finished product and its axial direction The included angle can be increased or decreased successively, which is convenient for the preparation, and the anti-extrusion strength in different directions is approximately equal.

Optionally, in step S2, when the number of unit layers in the first preform body is greater than or equal to 4, the first preform body includes at least one first unit layer, at least one second unit layer, at least one A third unit layer, at least one fourth unit layer. Wherein, the first carbon fiber filament bundle in the first unit layer is perpendicular to the axial direction of the mold, the first carbon fiber filament bundle in the second unit layer is parallel to the axial direction of the mold, and the first carbon fiber filament bundle in the third unit layer is parallel to the axial direction of the mold. The included angle between the axial directions of the molds is +45°, and the included angle between the first carbon fiber filament bundles in the fourth unit layer and the axial directions of the molds is -45°. Whether the first unit layer, the second unit layer, the third unit layer, and the fourth unit layer are adjacent to each other is not specifically limited. The arrangement of the above-mentioned unit layers can further increase the anti-extrusion strength of the high-temperature-resistant carbon-carbon composite in different directions, greatly improve its overall mechanical properties, and prolong its service life. For example, the bending strength can reach more than 140Mpa.

For example, one layer of the first unit layer, one layer of the second unit layer, one layer of the third unit layer, and one layer of the fourth unit layer that are adjacently distributed can be used as a cycle, and the first prefabricated layer is laid and needle-punched in this cycle. body body.

Optionally, the areal density of the composite cloth can be 300-500g/m ² , the oblique winding angle of carbon fiber is 45°, and the areal density of the carbon fiber mesh tire can be 50-120g/m ² . The needling depth in step S2 can be 10-16 mm, the needling density is 24-45 needles/cm ² , and the density of the first preform body can be 0.5-0.7 g/cm ³ , the resulting high temperature resistant carbon-carbon composite The body has a longer lifespan.

Step S3, removing the mold from the carbon fiber preform, and performing densification treatment to obtain a machined precursor.

The process of densification can be densification of deposition, such as vapor deposition. In this embodiment of the present invention, this step is not specifically limited.

Step S4, removing the machined layer from the machined precursor.

This step is mainly through machine processing to remove the machine layer. This step may also include surface treatment, etc., which are not specifically limited in this embodiment of the present invention.

It should be noted that, in the case where the machine-added layer includes a margin part formed by stacking and needling of at least one unit layer, since the unit layer of stacked needle punching in the margin part is added by machine as a margin part, therefore, The number of unit layers in the high temperature resistant carbon-carbon composite will be less than the number of unit layers in the carbon fiber prefabricated body. For example, if the number of unit layers in the carbon fiber preform is m, and the number of unit layers in the remaining part is n, then the number of unit layers in the high temperature resistant carbon-carbon composite can be m-n layers. In the case that the machine-added layer does not include the residual part, the number of unit layers in the high-temperature-resistant carbon-carbon composite body and the number of unit layers in the carbon fiber prefabricated body can be equal.

The embodiment of the present invention also provides a carbon fiber preform, which includes: a first preform body and a machine-added layer arranged in layers. In the stacking direction of the first preform body and the machine-added layer, the machine-added layer is located on at least one side of the first preform body. For example, in the lamination direction, the machine-added layers are located only on either side of the first preform. Alternatively, in the stacking direction, the machine-added layers are located on both sides of the first preform.

The first preform body is formed by stacking at least one unit layer. The unit layer is composed of composite cloth wound with filaments, and then laminated with at least one layer of carbon fiber mesh. The composite cloth is composed of at least one layer of carbon fiber net tires stacked on the plane of a carbon fiber aggregate with few weaving points; the carbon fiber aggregate with few weaving points includes: no weft cloth, and/or, at least one bundle of first carbon fiber lengths arranged in parallel in a plane tow.

In the carbon fiber prefabricated body, at least one machine-added layer contains a mesh structure; the mesh structure is formed by laminating at least one layer of multi-weave carbon fiber fabric.

In the carbon fiber preform, when the number of unit layers in the first preform body is greater than 1, the included angle between the first carbon fiber filament bundles in adjacent unit layers is greater than 0.

In the carbon fiber preform, when the number of unit layers in the first preform body is greater than or equal to 4, the first preform body includes at least one first unit layer, at least one second unit layer, and at least one third unit layer, at least one fourth unit layer. Wherein, the first carbon fiber filament bundle in the first unit layer is perpendicular to the axial direction of the mold, the first carbon fiber filament bundle in the second unit layer is parallel to the axial direction of the mold, and the first carbon fiber filament bundle in the third unit layer is parallel to the axial direction of the mold. The included angle between the axial directions of the molds is +45°, and the included angle between the first carbon fiber filament bundles in the fourth unit layer and the axial directions of the molds is -45°.

Regarding the carbon fiber prefabricated body, reference can be made to the relevant records about the carbon fiber prefabricated body in the production method of the aforementioned high-temperature-resistant carbon-carbon composite body, and the same or similar effects can be achieved. In order to avoid repetition, details are not repeated here. It should be noted that the carbon fiber preform can be prepared by step S1 and step S2 of the production method of the aforementioned high-temperature-resistant carbon-carbon composite. There are no specific limitations on other production and preparation methods of the carbon fiber preform.

An embodiment of the present invention also provides a high temperature resistant carbon-carbon composite body, comprising: at least one unit layer; when the number of unit layers is greater than 1, each unit layer is stacked. The unit layer is composed of composite cloth wound with filaments, and then laminated with at least one layer of carbon fiber mesh. The composite fabric is composed of at least one layer of carbon fiber net tires laminated with a plane of carbon fiber aggregates with few weaving points. The carbon fiber assembly with few weaving points includes: no weft fabric, and/or at least one bundle of first carbon fiber filament bundles arranged in parallel in a plane.

Regarding the high-temperature-resistant carbon-carbon composite, you can refer to the relevant records about the high-temperature-resistant carbon-carbon composite in the production method of the aforementioned high-temperature-resistant carbon-carbon composite, and can achieve the same or similar effects. In order to avoid repetition, no more details are given here. . The high-temperature-resistant carbon-carbon composite can be prepared by the above-mentioned production method 2 of the high-temperature-resistant carbon-carbon composite. As for other production and preparation methods of the high-temperature-resistant carbon-carbon composite body, no specific limitation is made.

It should be noted that, for the method embodiment, for the sake of simple description, it is expressed as a series of action combinations, but those skilled in the art should know that the embodiment of the present application is not limited by the described action sequence, because According to the embodiment of the present application, certain steps may be performed in other orders or simultaneously. Secondly, those skilled in the art should also know that the embodiments described in the specification belong to preferred embodiments, and the actions involved are not necessarily required by the embodiments of the present application.

It should be noted that, in this document, the term "comprising", "comprising" or any other variation thereof is intended to cover a non-exclusive inclusion such that a process, method, article or apparatus comprising a set of elements includes not only those elements, It also includes other elements not expressly listed, or elements inherent in the process, method, article, or device. Without further limitations, an element defined by the phrase "comprising a ..." does not preclude the presence of additional identical elements in the process, method, article, or apparatus comprising that element.

Through the description of the above embodiments, those skilled in the art can clearly understand that the methods of the above embodiments can be implemented by means of software plus a necessary general-purpose hardware platform, and of course also by hardware, but in many cases the former is better implementation. Based on such an understanding, the essence of the technical solution of the present invention or the part that contributes to the prior art can be embodied in the form of software products, and the computer software products are stored in a storage medium (such as ROM/RAM, disk, CD) contains several instructions to make a terminal (which may be a mobile phone, a computer, a server, an air conditioner, or a network device, etc.) execute the methods described in various embodiments of the present invention.

Embodiments of the present invention have been described above in conjunction with the accompanying drawings, but the present invention is not limited to the above-mentioned specific implementations, and the above-mentioned specific implementations are only illustrative, rather than restrictive, and those of ordinary skill in the art will Under the enlightenment of the present invention, many forms can also be made without departing from the gist of the present invention and the protection scope of the claims, and these all belong to the protection of the present invention.

Claims (12)

A method for producing a high temperature resistant carbon-carbon composite body, characterized in that the method comprises: Lay at least one layer of carbon fiber net tire on the surface of the carbon fiber assembly with few weaving points, and then needle punch to form a composite cloth; the carbon fiber assembly with few weaving points includes: no weft cloth, and/or, at least one bundle arranged in parallel in a plane a first carbon fiber filament tow; A carbon fiber structure is arranged on the outer surface of the mold to obtain a carbon fiber preform; the carbon fiber structure includes: a machine-added layer and a first preform body stacked; the machine-added layer is located between the mold and the first preform Between the bodies, and/or, the machine-added layer is located on the side of the first preform body away from the mold; at least one machine-added layer contains a mesh structure; the mesh structure consists of at least one layer and more Weave point carbon fiber fabric is laid and formed; the first prefabricated body is formed by at least one layer of unit layers stacked and needled; thorn formation; removing the mold from the carbon fiber preform and performing a densification treatment to obtain a machined precursor; The machining layer is removed from the machining precursor. The method for producing a high-temperature-resistant carbon-carbon composite according to claim 1, wherein, when the mold is a crucible mold or an insulation cylinder mold, the machine-added layer is only located between the mold and the second Between a prefabricated body; In the case that the mold is a heat shield outer bladder mold, the machine-added layer is only located on the side of the first preform body away from the mold. The method for producing a high-temperature-resistant carbon-carbon composite according to claim 1, wherein at least one of the machine-added layers includes: a surplus portion formed by stacking needle punching of at least one of the unit layers. The method for producing a high-temperature resistant carbon-carbon composite according to claim 3, characterized in that, when one layer of the machine-added layer includes the mesh structure and the margin part, the margin A part is located between the mesh structure and the first preform body, and the margin part is integrally formed with the first preform body; the thickness of the margin part is 1-3mm; the margin The thickness of the part is: the size of the surplus part along the stacking direction of the mesh structure and the first preform body. The method for producing a high-temperature-resistant carbon-carbon composite according to claim 1, wherein the mold includes a straight arm portion parallel to its axial direction, a bottom perpendicular to the straight arm portion, and connecting the straight arm part and arc of said bottom; When the thickness of the arc portion is greater than the thickness of the straight arm, and the difference between the two thicknesses is greater than or equal to 5 mm, the carbon fiber structure further includes: located on the outer surface of the unit layer, and connected to the arc portion The second preform body oppositely arranged; the second preform body is formed by winding the composite cloth; the thickness of the straight arm is: the dimension of the straight arm in a direction perpendicular to the axial direction of the mould. The method for producing a high-temperature-resistant carbon-carbon composite according to claim 5, wherein the surface density of the machine-added layer is less than or equal to the surface density of the first preform body, and/or the surface density of the machine-added layer is less than Or equal to the areal density of the second preform body. The method for producing a high-temperature-resistant carbon-carbon composite according to claim 5 or 6, wherein the areal density of the machine-added layer is less than or equal to 350g/m ² ; and/or, the areal density of the first preform body is greater than or equal to 400g/m ² ; and/or, the areal density of the second preform body is greater than or equal to 400g/m ² . The method for producing a high-temperature-resistant carbon-carbon composite according to any one of claims 1-6, wherein the step of winding the composite cloth comprises: first obliquely wrapping the composite cloth with the second carbon fiber filament bundle Winding the filaments, and then wrapping the composite cloth in a circumferential direction; wherein, in the process of circumferential winding, the second carbon fiber filament bundle is perpendicular to the axial direction of the mold. A carbon fiber prefabricated body, characterized in that it includes: a first prefabricated body and a machine-added layer stacked; in the stacking direction of the first prefabricated body and the machine-added layer, the machine-added layer is located at the first at least one side of the body of the preform; The first prefabricated body is formed by laminating at least one unit layer; the unit layer is formed by laminating at least one layer of carbon fiber mesh after the composite cloth is wound; The composite cloth is composed of at least one layer of carbon fiber net tires stacked on the plane of a carbon fiber aggregate with few weaving points; the carbon fiber aggregate with few weaving points includes: no weft fabric, and/or at least one bundle of first bundles arranged in parallel in a plane Carbon fiber filament tow; At least one machine-added layer includes a mesh structure; the mesh structure is formed by laminating at least one layer of multi-weave carbon fiber fabric. The carbon fiber preform according to claim 9, wherein, when the number of unit layers in the first preform body is greater than 1, in adjacent unit layers, between the first carbon fiber filament bundles The included angle is greater than 0. The carbon fiber preform according to claim 9 or 10, characterized in that, In the case where the number of unit layers in the first preform body is greater than or equal to 4, the first preform body includes at least one first unit layer, at least one second unit layer, and at least one third unit layer , at least one fourth unit layer; Wherein, the first carbon fiber filament bundle in the first unit layer is perpendicular to the axial direction of the mold, the first carbon fiber filament bundle in the second unit layer is parallel to the axial direction of the mold, and the first carbon fiber filament bundle in the third unit layer is parallel to the axial direction of the mold. The included angle between the axial directions of the molds is +45°, and the included angle between the first carbon fiber filament bundles in the fourth unit layer and the axial directions of the molds is -45°. A high temperature resistant carbon-carbon composite body, characterized in that it comprises: At least one unit layer; when the number of unit layers is greater than 1, each unit layer is stacked; The unit layer is composed of at least one layer of carbon fiber mesh after the composite cloth is wound; The composite cloth is composed of at least one layer of carbon fiber net tires stacked on the plane of a carbon fiber aggregate with few weaving points; the carbon fiber aggregate with few weaving points includes: no weft fabric, and/or at least one bundle of first bundles arranged in parallel in a plane Carbon fiber filament tow.

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