Composite cylindrical part and manufacturing method thereof

Abstract

The invention provides a composite material cylindrical part and a manufacturing method thereof, and the manufacturing method of the composite material cylindrical part comprises the following steps: sleeving a composite material prefabricated body to form a cylindrical structure; wherein the composite material prefabricated body is a tubular part and is provided with a starting end and a tail end which are opposite to each other; the core mold is installed in the inner hole of the cylindrical structure, the outer side of the cylindrical structure is wrapped with the outer mold, and therefore a cavity is formed between the core mold and the outer mold; wherein the cylindrical structure is positioned in the cavity; and filling liquid into the cavity, and manufacturing the composite material cylindrical part by adopting a liquid forming process. According to the manufacturing method of the composite material barrel-shaped part, the barrel-shaped structure is formed by sleeving the composite material prefabricated body and is only provided with the free end formed at the tail end of the composite material prefabricated body, so that the debonding probability is effectively reduced, the tail end is annularly wrapped outside the inner layer and can be more restrained, and the service life of the barrel-shaped structure is prolonged. And even if the tail end part is debonded, the large-area debonding condition is difficult to occur.

Description

Technical Field

[0001] The invention relates to the technical field of composite material cylindrical component manufacturing, and in particular to a composite material cylindrical component and a manufacturing method thereof. Background Art

[0002] The casing is one of the important parts in aircraft engines and gas turbines, such as the fan containment casing, which surrounds the outside of the blades. There are a large number of high-speed rotating blades in aircraft engines and gas turbines. In the case of foreign impact, process defects, etc., the rotating blades may fall off. Therefore, the fan containment casing is required to have good containment to ensure that high-speed and high-energy fragments do not penetrate the casing, thereby preventing the fragments from causing kidney damage to equipment and personnel. In addition, the engine rotor has a huge unbalanced load after the blades fly off, which will cause the engine to vibrate continuously before stopping. During this period, the casing is still required to maintain a certain structural integrity and not disintegrate.

[0003] At the same time, the size of the containment casing is large, and its weight will have a significant impact on the total weight of the engine, thereby affecting the engine efficiency. The low-temperature end casings in the new generation of commercial engines generally use carbon fiber composite materials. Patent EP1674244 proposes the use of a triaxial woven preform and a resin liquid molding process to manufacture a fan containment casing of equal thickness. Patent EP1674671 proposes a variable thickness fan containment casing, in which the reinforcement phase of the casing composite core is a circumferentially aligned, multi-layered braid, and the other composite layers are obtained by a spirally wound braid. Patent US8322971B2 proposes a composite material containment casing, which first uses a three-dimensional weaving method to process a variable thickness fiber preform, then winds it on a core shaft to obtain a casing preform, and then obtains the casing through resin liquid molding.

[0004] However, in the above-mentioned method of preparing the containment casing by laying preforms on the core shaft, for example, the composite material containment casing provided in patent US8322971B2, the first and tail ends of the wound preforms on the inside and outside of the containment casing are free ends, and the ends of the preforms at both ends of the circumferential direction of the containment casing are also free ends. During use, the free ends are prone to detachment problems, which in turn cause large-scale interlayer debonding. Moreover, after the blades fall off, the engine will experience severe vibration for a period of time, causing the impact range of interface failure and debonding to continue to increase, and ultimately leading to a serious decrease in the stiffness of the containment casing, or even the disintegration of the containment casing, posing a huge threat to human and machine safety. Summary of the invention

[0005] The purpose of the present invention is to provide a method for manufacturing a composite material cylindrical part, which can improve the technical problem that the composite material cylindrical part manufactured by the existing winding method is prone to large-area debonding.

[0006] Another object of the present invention is to provide a composite material cylindrical part, which can improve the technical problem that the existing composite material cylindrical parts manufactured by winding are prone to large-area debonding.

[0007] The embodiments of the present invention can be implemented in the following ways:

[0008] A method for manufacturing a composite material cylindrical component, the method comprising:

[0009] The composite material preform is encircled to form a cylindrical structure; wherein the composite material preform is a tubular member having a starting end and a tail end opposite to each other;

[0010] Installing the core mold in the inner hole of the cylindrical structure and wrapping the outer mold on the outer side of the cylindrical structure, thereby forming a cavity between the core mold and the outer mold; wherein the cylindrical structure is located in the cavity;

[0011] The cavity is filled with liquid, and a composite material cylindrical part is manufactured by adopting a liquid molding process.

[0012] Optionally, the step of enclosing the composite material preform to form a cylindrical structure comprises:

[0013] Inserting the tail end of the composite material preform into the annular body from the circumferential opening of the annular body, and pulling the tail end until the starting end of the composite material preform is sleeved on the annular body;

[0014] The composite material preform is sleeved on the starting end from the circumferential opening, and the tail end is pulled to move circumferentially along the annular body until the composite material preform is completely encircled on the annular body to form the cylindrical structure.

[0015] Optionally, the annular body is made of a material that can be melted by heating.

[0016] Optionally, after the step of forming a cavity between the core mold and the outer mold, the method for manufacturing a composite material cylindrical member further comprises:

[0017] The cylindrical structure and the mold are heated until the temperature reaches the melting temperature of the annular body; wherein the mold comprises a core mold and an outer mold;

[0018] The molten liquid formed by melting the annular body is discharged from the mold through the outlet gate of the mold.

[0020] Optionally, in the composite material preform, the thickness of the starting end decreases gradually in a direction away from the tail end.

[0021] Optionally, the length of the starting end is greater than or equal to the arc length corresponding to 10° of the outer circumference of the composite cylindrical member.

[0022] Optionally, in the composite material preform, the thickness of the tail end decreases gradually in a direction away from the starting end.

[0023] Optionally, the length of the tail end is greater than or equal to the arc length corresponding to 10° of the outer circumference of the composite cylindrical member.

[0024] Optionally, the starting end of the composite material preform is closed, and the tail end of the composite material preform is open.

[0025] Optionally, the composite material preform has a plurality of preform sections distributed from the starting end to the tail end, each of the preform sections being used to form a loop layer structure of the cylindrical structure; the starting end is an end portion of a preform section located at one end of the composite material preform, and the tail end is an end portion of a preform section located at the other end of the composite material preform; along the starting end to the tail end, the inner diameters of the plurality of preform sections increase successively to adapt to the radial length changes of different loop layers of the cylindrical structure.

[0026] Optionally, the composite material preform is a fabric made by weaving, and the warp direction of the fabric is the length direction of the composite material preform, and the weft direction of the fabric is the circumferential direction of the composite material preform.

[0027] Optionally, the composite material preform is made of at least one of carbon fiber, glass fiber, Kevlar fiber, polyimide fiber or SiC fiber.

[0028] A composite material cylindrical component is manufactured by adopting the composite material cylindrical component manufacturing method.

[0029] A composite cylindrical part has a cylindrical structure formed by a composite preform loop. The composite preform is a tubular part having a relative starting end and a tail end. The tail end is wrapped around the outside of the loop layer where the starting end is located.

[0030] The composite cylindrical member and the manufacturing method thereof provided by the embodiments of the present invention have the following beneficial effects:

[0031] The embodiment of the present invention provides a composite material cylindrical part manufacturing method, which includes forming a cylindrical structure by entrapping a composite material preform; wherein the composite material preform is a tubular part and has a relative starting end and a tail end; installing a core mold in the inner hole of the cylindrical structure, and wrapping an outer mold on the outer side of the cylindrical structure, so as to form a cavity between the core mold and the outer mold; wherein the cylindrical structure is located in the cavity; filling the cavity with liquid, and using a liquid molding process to form a composite material cylindrical part. Since in the composite material cylindrical part manufacturing method, the cylindrical structure is formed by entrapping the composite material preform, it only has a free end formed by the tail end of the composite material preform, thereby effectively reducing the probability of debonding, and since the composite material preform is tubular, correspondingly, the tail end is annularly wrapped outside the inner layer, it can be subject to more constraints, even if the tail end part debonds, it is difficult to have a large-area debonding situation, thereby ensuring the reliability of the composite material cylindrical part, and it is not easy to have the problem of stiffness reduction or even disintegration due to large-area debonding during use.

[0032] An embodiment of the present invention also provides a composite material cylindrical part, which is manufactured using the above-mentioned composite material cylindrical part manufacturing method. Therefore, it also has a low probability of debonding. Even if debonding occurs in the tail end, it is difficult to have large-area debonding, thereby ensuring the reliability of the composite material cylindrical part. It is not easy to have the beneficial effect of reducing stiffness or even disintegrating due to large-area debonding during use.

[0033] An embodiment of the present invention also provides a composite material cylindrical part, which has a cylindrical structure formed by a composite material preform loop, the composite material preform is a tubular part, and has a relative starting end and a tail end; the tail end is wrapped on the outside of the loop layer where the starting end is located, so that there is only one free end, namely the tail end, which effectively reduces the probability of debonding. Moreover, since the composite material preform is tubular, the tail end is wrapped in a ring shape outside the inner layer accordingly, and it can be subject to more constraints. Even if part of the tail end debonds, it is difficult for large-area debonding to occur, thereby ensuring the reliability of the composite material cylindrical part, and it is not easy to have the problem of reduced stiffness or even disintegration due to large-area debonding during use. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] The above features and advantages of the present invention can be better understood after reading the detailed description of the embodiments of the present disclosure in conjunction with the following drawings. In the drawings, the components are not necessarily drawn to scale, and components with similar related properties or features may have the same or similar reference numerals.

[0035] Figure 1 A step diagram showing a method for manufacturing a composite material cylindrical member according to one aspect of the present invention is shown;

[0036] Figure 2 A schematic structural diagram of a housing casing provided according to one aspect of the present invention is shown;

[0037] Figure 3 A schematic diagram of the main structure of a composite material preform provided according to one aspect of the present invention is shown;

[0038] Figure 4 A left-side structural schematic diagram of a composite material preform provided according to one aspect of the present invention is shown;

[0039] Figure 5 A schematic structural diagram of an annular body provided according to one aspect of the present invention is shown;

[0040] Figure 6 It shows a structural schematic diagram of executing step S11 in the method for manufacturing a composite material cylindrical member according to one aspect of the present invention;

[0041] Figure 7 It shows a schematic structural diagram of executing step S12 in the method for manufacturing a composite material cylindrical member according to one aspect of the present invention;

[0042] Figure 8 A schematic structural diagram of a manufactured cylindrical structure provided according to one aspect of the present invention is shown;

[0043] Fig. 9 Shows Figure 8 The enlarged structural diagram of position Ⅰ in the middle;

[0044] Fig.10 A schematic diagram of the main structure of a composite material preform provided according to another aspect of the present invention is shown.

[0045] Reference numerals:

[0046] 100-cylindrical structure; 110-composite material preform; 111-starting end; 112-tailing end; 113-preform section; 114-first preform section; 115-second preform section; 121-inner layer structure; 122-outer layer structure; 130-annular body; 131-circumferential opening; 132-first free end; 133-second free end; 140-inner hole; 200-enclosing casing. DETAILED DESCRIPTION

[0047] The present invention is described in detail below in conjunction with the accompanying drawings and specific embodiments. Note that the aspects described below in conjunction with the accompanying drawings and specific embodiments are only exemplary and should not be construed as limiting the scope of protection of the present invention in any way.

[0048] In the description of the present invention, it should be noted that if the terms "upper", "lower", "inside", "outside", "vertical" and the like appear, the orientation or position relationship indicated is based on the orientation or position relationship shown in the drawings, or is the orientation or position relationship in which the product of the invention is usually placed when used, rather than indicating or implying that the device or element referred to must have a specific orientation or be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present invention.

[0049] At the same time, it should be noted that the terms "first", "second", etc. are only used for distinguishing descriptions and cannot be understood as indicating or implying relative importance.

[0050] In the description of the present invention, it is also necessary to explain that, unless otherwise clearly specified or limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, an integral connection, or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, or the internal communication of two components, etc. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0051] In the description of this embodiment, the cylindrical member is a shell-like structural member that is hollow and circumferentially closed or has an opening.

[0052] Figure 1 The steps of the method for manufacturing a composite cylindrical member provided in this embodiment are shown. Figure 1 This embodiment provides a composite material cylindrical member manufacturing method, and accordingly, also provides a composite material cylindrical member, such as Figure 2 A structural schematic diagram of a specific example of a composite material cylindrical part provided in the present embodiment is shown, that is, in the present embodiment, the composite material cylindrical part is a housing casing 200. It can be understood that in some other embodiments, the composite material cylindrical part manufacturing method provided in the present embodiment can also be used to manufacture other types of composite material cylindrical parts.

[0053] In this embodiment, the method for manufacturing a composite material cylindrical member comprises the following steps:

[0054] S01: Encircling a composite material preform 110 to form a cylindrical structure 100 .

[0055] Figure 3 FIG. 1 shows a schematic diagram of the main structure of the composite material preform 110 provided in this embodiment. Figure 4 FIG. 1 shows a left-side structural schematic diagram of a composite material preform 110 provided in this embodiment. Figure 3 and Figure 4As shown, the composite material preform 110 is a hollow tubular member, and the composite material has a relative starting end 111 and a tail end 112. The composite material cylindrical member manufacturing method may also include a step of manufacturing the composite material preform 110 before executing step S01. In the present embodiment, the composite material preform 110 is a fabric formed by weaving a composite material, and the fabric may be a three-dimensional fabric, or a two-dimensional fabric formed into a hollow tubular shape by stitching. Specifically, the composite material preform 110 can be obtained by weaving at least one of carbon fiber, glass fiber, Kevlar fiber, polyimide fiber or SiC fiber (silicon carbide fiber) through a three-dimensional loom process.

[0056] Furthermore, the warp direction of the fabric is the length direction of the composite material preform 110 (eg Figure 3 The weft direction of the fabric is the circumferential direction of the composite material preform 110 (as shown in the A direction in FIG. Figure 4 It should be noted that, since the composite material preform 110 is a composite material fabric, it has certain deformability and flexibility. Figure 4 The circular tube structure shown is a shape maintained under the action of external forces.

[0057] Furthermore, during the weaving process, the thickness of each part of the composite material preform 110 can be manufactured according to the design of the composite material cylindrical part to be manufactured, thereby realizing a square preform that imitates the profile and thickness distribution of the composite material cylindrical part to be manufactured. Specifically, the thickness of each part of the composite material preform 110 can be changed by adjusting the number of layers of yarn during weaving.

[0058] Specifically, the steps of enclosing the composite material preform 110 to form the cylindrical structure 100 include:

[0059] S11 : inserting the tail end 112 of the composite material preform 110 into the annular body 130 from the circumferential opening 131 of the annular body 130 , and pulling the tail end 112 until the starting end 111 of the composite material preform 110 is sleeved on the annular body 130 .

[0060] Figure 5 FIG. 1 shows a schematic structural diagram of the annular body 130 provided in this embodiment. Figure 6 The schematic diagram of the structure of the composite material cylindrical member manufacturing method provided in this embodiment is shown. Figure 5 and Figure 6In this embodiment, the composite material preform 110 is pre-deformed during the entrapment process by the annular body 130 having the circumferential opening 131, thereby improving the accuracy of the entrapment and deformation of the composite material preform 110 and simplifying the molding process and process. Since the annular body 130 has the circumferential opening 131, the annular body 130 has two free ends forming the circumferential opening 131, and the two free ends are the first free end 132 and the second free end 133. Furthermore, in order to ensure the positioning of the composite material preform 110 on the annular body 130 during the entrapment operation, the starting end 111 of the composite material preform 110 is closed, and the tail end 112 of the composite material preform 110 is open, so that the entrapment can be performed from the tail end 112 of the composite material preform 110.

[0061] When performing the entrapment operation, firstly, the tail end 112 of the composite material preform 110 is opened, and the tail end 112 of the composite material preform 110 is inserted into the first free end 132, and then the tail end 112 is pulled to move toward the second free end 133 until the closed part of the starting end 111 of the composite material preform 110 abuts against the first free end 132. Figure 6 As shown, at this time, the starting end 111 is sleeved on the first free end 132 of the ring body 130, and the tail end 112 is separated from the ring body 130 from the second free end 133. Figure 6 The portion of the composite material preform 110 that is sleeved on the annular body 130 forms the innermost loop layer structure of the cylindrical structure 100 .

[0062] S12: The tail end 112 of the composite material preform 110 is sleeved on the starting end 111 from the circumferential opening 131 , and the tail end 112 is pulled to move circumferentially along the annular body 130 until the composite material preform 110 is completely encircled on the annular body 130 , forming a cylindrical structure 100 .

[0063] Figure 7 The schematic diagram of the structure when executing step S12 in the method for manufacturing a composite material cylindrical member provided in this embodiment is shown. Figure 8 1 shows a schematic structural diagram of the manufactured cylindrical structure 100. Fig. 9 for Figure 8 The enlarged structural diagram of the part Ⅰ in the middle. Please refer to Figure 5-Figure 9 , through the opening of the tail end 112 of the composite material preform 110, the tail end 112 of the composite material preform 110 is inserted into the first free end 132. At this time, the starting end 111 of the composite material preform 110 is sleeved on the first free end 132 to form a part of the innermost trap layer structure of the cylindrical structure 100. Therefore, when the tail end 112 is inserted into the first free end 132, the tail end 112 is wrapped around the outer periphery of the starting end 111 of the composite material preform 110 (such as Figure 7At this time, the circumferential opening 131 of the annular body 130 is covered by the composite material preform 110, and the circumferential direction of the annular structure formed by the composite material preform 110 is closed. Then, the tail end 112 of the composite material preform 110 is pulled to move along the circumference of the annular body 130 until the composite material preform 110 is completely trapped on the annular body 130, forming a Figure 8 The cylindrical structure 100 shown in the figure. In this embodiment, the manufactured cylindrical structure 100 includes an annular body 130 in addition to the composite material preform 110 , and the annular body 130 is completely wrapped inside the composite material preform 110 .

[0064] Furthermore, in order to facilitate the removal of the annular body 130 so that the final composite cylindrical member does not have the inner core of the annular body 130, the annular body 130 can be made of a heat-meltable material, such as a resin that can be melted at low temperature. Alternatively, in some other embodiments, an inflatable form can also be used.

[0065] Optionally, in the composite material preform 110 provided in this embodiment, the thickness of the starting end 111 decreases in the direction away from the tail end 112, that is, the closer to the end of the composite material preform 110, the smaller the thickness of the starting end 111, which helps to reduce the step height formed at the end, thereby reducing the possibility of interface failure caused by stress concentration at this location. Further, the length of the starting end 111 is greater than or equal to the arc length corresponding to 10° of the outer circumference of the composite material cylindrical member, that is, the length of the starting end 111 is greater than or equal to 1 / 36 of the outer circumference of the composite material cylindrical member.

[0066] Similarly, in the composite material preform 110 provided in this embodiment, the thickness of the tail end 112 decreases in the direction away from the starting end 111, that is, the closer to the end of the composite material preform 110, the smaller the thickness of the tail end 112, which helps to reduce the step height of the end, thereby reducing the possibility of interface failure caused by stress concentration at this location. Further, the length of the tail end 112 is greater than or equal to the arc length corresponding to 10° of the outer circumference of the cylindrical member, that is, the length of the tail end 112 is greater than or equal to 1 / 36 of the outer circumference of the composite material cylindrical member.

[0067] It is understandable that the thickness of the starting end 111 and the tail end 112 can also be set to be equal, for example, Fig. 9 In the structure shown, the starting end 111 is a structure of uniform thickness, and the tail end 112 is a structure of gradually decreasing thickness.

[0068] Furthermore, the composite material preform 110 has a plurality of preform sections 113 distributed from the starting end 111 to the tail end 112, each preform section 113 is used to form a trap layer structure of the cylindrical structure 100, the starting end 111 is the end portion of a preform section 113 located at one end of the composite material preform 110, and the tail end 112 is the end portion of a preform section 113 located at the other end of the composite material preform 110. In this way, the preform section 113 where the tail end 112 is located is wrapped in the outer layer, and the preform section 113 where the starting end 111 is located is closer to the annular body 130 than the preform section 113 where the tail end 112 is located. In order to avoid quality problems caused by excessive deformation of the composite material preform 110, the composite material preform 110 is configured such that the inner diameters of the plurality of preform sections 113 increase in sequence from the starting end 111 to the tail end 112 to adapt to the radial length changes of different trap layers of the cylindrical structure 100.

[0069] like Fig. 9 As shown, in the cylindrical structure 100 formed in this embodiment, the cylindrical structure 100 has two trap layer structures, which are an inner layer structure 121 and an outer layer structure 122. Figure 5 The composite preform 110 shown has two preform sections 113, which are respectively a first preform section 114 and a second preform section 115, the starting end 111 is the end portion of the first preform section 114 away from the second preform section 115, and the first preform section 114 is used to form an inner layer structure 121; the tail end 112 is the end portion of the second preform section 115 away from the first preform section 114, and the second preform section 115 is used to form an outer layer structure 122.

[0070] In other words, in the manufactured cylindrical structure 100, the second preform section 115 is wrapped outside the first preform section 114, and the first preform section 114 is in contact with the outer surface of the annular body 130, so that the inner diameter of the first preform section 114 is equal to the axial length of the annular body 130 (if there is a flange, the flange length must also be included), and the inner diameter of the second preform section 115 is equal to the sum of the inner diameter of the first preform section 114 and twice the thickness of the first preform section 114. If the composite cylindrical part to be manufactured is a variable thickness structure, then correspondingly, the thickness of each preform section 113 is also set to be different according to the requirements. At this time, the inner diameter of the second preform section 115 wrapped outside the first preform section 114 can be set to the sum of the inner diameter of the first preform section 114 and twice the maximum thickness of the first preform section 114.

[0071] It should be noted that the number of the trap layer structures included in the cylindrical structure 100 is not limited here. It is understandable that in some other embodiments, the number of the trap layer structures included in the cylindrical structure 100 can also be set to other values ​​greater than or equal to 1, such as 1.5 or 4, etc., according to needs. Accordingly, when the number of the trap layer structures included in the cylindrical structure 100 is 1.5, the composite material preform 110 has two preform sections 113, and the length of the preform section 113 where the tail end 112 is located is shorter than the length of the preform section 113 where the starting end 111 is located; when the number of the trap layers included in the cylindrical structure 100 is 4, the composite material preform 110 has four preform sections 113 (such as Fig.10 shown).

[0072] S02: Install the core mold in the inner hole 140 of the cylindrical structure 100, and wrap the outer mold around the outer side of the cylindrical structure 100, so as to form a cavity between the core mold and the outer mold.

[0073] A core mold (not shown) is inserted into the inner hole 140 of the cylindrical structure 100, and the radial inner wall surface of the composite cylindrical member to be manufactured is defined by the core mold. Then an outer mold (not shown) is wrapped around the outer side of the cylindrical structure 100, and the radial outer wall surface of the composite cylindrical member to be manufactured is defined by the outer mold, so that the cylindrical structure 100 is wrapped in the cavity formed between the core mold and the outer mold. Optionally, the outer mold can be a rigid outer mold or an outer mold made of a flexible material.

[0074] It should be noted that the specific structures of the core mold and the outer mold can be set according to the structure of the composite material cylindrical part to be manufactured.

[0075] S03: injecting liquid into the cavity and forming a composite cylindrical part by liquid molding process.

[0076] Specifically, the liquid includes but is not limited to liquid resin. After the liquid resin is injected into the cavity, a liquid molding process suitable for the corresponding structure can be used according to the specific type of the composite cylindrical part. The liquid molding process is not specifically limited here. Then, the resin is cured by heating, pressurizing, vacuuming or other process methods according to the liquid molding process. The structure after the resin is cured is demoulded from the mold (i.e., the core mold and the outer mold) to obtain the composite cylindrical part. It is understandable that the cured structure can also be subjected to subsequent processing such as machining after demoulding.

[0077] Since the cylindrical structure 100 manufactured in this embodiment also has an annular body 130, after executing step S02, the composite cylindrical member manufacturing method may also include step S04 of removing the annular body 130. Obviously, in some other embodiments, if the manufactured cylindrical structure 100 does not have an annular body 130, or the annular body 130 does not need to be removed according to the composite cylindrical member to be manufactured, the composite cylindrical member manufacturing method may not include step S04. At the same time, it can be understood that if the annular body 130 does not need to be removed according to the composite cylindrical member to be manufactured, the specific material of the annular body 130 can be selected and set according to the needs. Specifically, in this embodiment, the step S04 of removing the annular body 130 includes:

[0078] S41 : heating the cylindrical structure 100 and the mold until the temperature reaches the melting temperature of the annular body 130 .

[0079] S42: The molten liquid formed by melting the annular body 130 is discharged from the mold through the outlet of the mold.

[0080] That is, in this embodiment, the mold is also formed with a gate connected to the cavity, and the specific position of the gate can be set on the outer mold or the core mold according to needs, and it is not specifically limited here.

[0081] It should be noted that the melting temperature of the annular body 130 can be set to be higher than the temperature when the liquid for manufacturing the composite cylindrical member is filled into the mold cavity, and the melting temperature of the annular body 130 can be set to be no higher than the temperature of the liquid for solidifying the composite cylindrical member, so that step S04 can be performed during the execution of step S03. Specifically, before executing step S03, the core mold and the outer mold are molded together until the cylindrical structure 100 is compacted to the designed size, and then the liquid is injected into the mold cavity. After the liquid is injected, step S04 is executed, and finally the liquid is solidified. Alternatively, in some other embodiments, the melting temperature of the annular body 130 can also be set to be lower than the temperature when the liquid for manufacturing the composite cylindrical member is filled into the mold cavity, so that step S04 can be performed after executing step S02 and before step S03.

[0082] The composite cylindrical part and the manufacturing method thereof provided by the embodiment of the present invention are obtained by the method of preform + liquid molding. Compared with the current process of winding a flat preform on a core mold, it is not necessary to add a device for fixing and pre-deforming the preform on the core mold. The composite preform 110 can be pre-deformed when draping, thereby improving the draping and deformation accuracy of the composite preform 110 and simplifying the molding process tooling and process. The manufactured composite cylindrical part has only one free end, the tail end 112, and this free end is annular, which will be subjected to more constraints and reduce the possibility of interface debonding.

[0083] At the same time, an embodiment of the present invention also provides a composite material cylindrical part, which includes a cylindrical structure 100 formed by a composite material preform 110, and the composite material preform 110 is a tubular part having a relative starting end 111 and a tail end 112, and the tail end 112 is wrapped around the outside of the trap layer where the starting end 111 is located.

[0084] The above description is only a specific implementation mode of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by any technician familiar with the technology in the field within the technical scope disclosed by the present invention should be covered within the protection scope of the present invention.

Claims

1. A method for manufacturing a composite cylindrical member, characterized in that: The composite material cylindrical member manufacturing method comprises: The composite material preform is encircled to form a cylindrical structure; wherein the composite material preform is a tubular member having a starting end and a tail end opposite to each other; Installing the core mold in the inner hole of the cylindrical structure and wrapping the outer mold on the outer side of the cylindrical structure, thereby forming a cavity between the core mold and the outer mold; wherein the cylindrical structure is located in the cavity; The cavity is filled with liquid, and a composite material cylindrical part is manufactured by adopting a liquid molding process.

2. The method for manufacturing a composite cylindrical member according to claim 1, characterized in that: The step of encircling the composite material preform to form a cylindrical structure comprises: Inserting the tail end of the composite material preform into the annular body from the circumferential opening of the annular body, and pulling the tail end until the starting end of the composite material preform is sleeved on the annular body; The composite material preform is sleeved on the starting end from the circumferential opening, and the tail end is pulled to move circumferentially along the annular body until the composite material preform is completely encircled on the annular body to form the cylindrical structure.

3. The method for manufacturing a composite cylindrical member according to claim 2, characterized in that: The annular body is made of a heat-meltable material.

4. The method for manufacturing a composite material cylindrical member according to claim 3, characterized in that: After the step of forming a cavity between the core mold and the outer mold, the method for manufacturing a composite material cylindrical member further includes: The cylindrical structure and the mold are heated until the temperature reaches the melting temperature of the annular body; wherein the mold comprises a core mold and an outer mold; The molten liquid formed by melting the annular body is discharged from the mold through the outlet gate of the mold.

5. The method for manufacturing a composite cylindrical member according to claim 1, characterized in that: In the composite material preform, the thickness of the starting end decreases gradually in a direction away from the tail end.

6. The method for manufacturing a composite material cylindrical member according to claim 5, characterized in that: The length of the starting end is greater than or equal to the arc length corresponding to 10° of the outer circumference of the composite cylindrical member.

7. The method for manufacturing a composite material cylindrical member according to claim 1, characterized in that: In the composite material preform, the thickness of the tail end decreases gradually in a direction away from the starting end.

8. The method for manufacturing a composite material cylindrical member according to claim 7, characterized in that: The length of the tail end is greater than or equal to the arc length corresponding to 10° of the outer circumference of the composite cylindrical member.

9. The method for manufacturing a composite material cylindrical member according to claim 1, characterized in that: The starting end of the composite material preform is closed, and the tail end of the composite material preform is open.

10. The method for manufacturing a composite material cylindrical member according to claim 1, characterized in that: The composite material preform has a plurality of preform sections distributed from the starting end to the tail end, and each of the preform sections is used to form a ring layer structure of the cylindrical structure; The starting end is an end portion of a preform section located at one end of the composite material preform, and the tail end is an end portion of a preform section located at the other end of the composite material preform; From the starting end to the tail end, the inner diameters of the plurality of preform sections are increased in sequence to adapt to the radial length changes of different snare layers of the cylindrical structure.

11. The method for manufacturing a composite material cylindrical member according to claim 1, characterized in that: The composite material preform is a fabric made by weaving, wherein the warp direction of the fabric is the length direction of the composite material preform, and the weft direction of the fabric is the circumferential direction of the composite material preform.

12. The method for manufacturing a composite material cylindrical member according to claim 1, characterized in that: The composite material preform is made of at least one of carbon fiber, glass fiber, Kevlar fiber, polyimide fiber or SiC fiber.

13. A composite cylindrical part, characterized in that: The composite material cylindrical component is manufactured by the composite material cylindrical component manufacturing method according to any one of claims 1 to 12.

14. A composite cylindrical part, characterized in that: The composite cylindrical part has a cylindrical structure formed by a composite preform loop. The composite preform is a tubular part having a relative starting end and a tail end. The tail end is wrapped around the outside of the loop layer where the starting end is located.

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