A composite material cylinder and method of manufacturing the same

Abstract

The application provides a composite material cylinder and a manufacturing method thereof, the manufacturing method comprising the following steps: forming a cylinder structure by means of a composite material preform; wherein the composite material preform is a tubular part and has opposite starting end and tail end; installing a core mold in the inner hole of the cylinder structure and wrapping an outer mold on the outer side of the cylinder structure, so as to form a molding cavity between the core mold and the outer mold; wherein the cylinder structure is located in the molding cavity; filling the molding cavity with liquid, and manufacturing the composite material cylinder by means of a liquid forming process. In the manufacturing method, the cylinder structure is formed by means of the composite material preform, and only has a free end formed by the tail end of the composite material preform, so that the probability of debonding is effectively reduced, and the tail end is annularly wrapped outside the inner layer and can be more constrained, so that even if part of the tail end is debonded, large-area debonding is difficult to occur.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of composite material cylinder manufacturing, in particular to a composite material cylinder and a manufacturing method thereof. BACKGROUND

[0002] The case is one of the important components in the aero-engine and gas turbine, for example, the fan containment case, which surrounds the outside of the blade. There are a large number of high-speed rotating blades in the aero-engine and gas turbine. In the case of external impact, process defects and other situations, the rotating blades may fall off, so the fan containment case is required to have good containment to ensure that high-speed high-energy fragments do not penetrate the case, thereby avoiding damage to equipment and personnel. Moreover, the engine rotor after the blade flies off has a huge unbalanced load, which will cause the engine to vibrate continuously before stopping, during which the case is required to maintain a certain structural integrity and not to disintegrate.

[0003] At the same time, the size of the simultaneous containment case is large, and its weight will have a significant impact on the total weight of the engine, thereby affecting the efficiency of the engine. The low-temperature end case in the new generation of commercial engines generally uses carbon fiber composite materials. Patent EP1674244 proposes to use a three-axis woven preform to form a fan containment case with a uniform thickness by using a resin liquid molding process. Patent EP1674671 proposes a fan containment case with variable thickness, and the reinforcing phase of the composite material core of the case is a multi-layered woven fabric aligned in the circumferential direction. In addition, the composite layer is obtained by spirally winding the woven fabric. Patent US8322971B2 proposes a composite material containment case, which first uses a three-dimensional weaving method to process a variable-thickness fiber preform, then winds the preform on a mandrel to obtain a case preform, and then obtains the case by resin liquid molding.

[0004] However, the above-mentioned containment case prepared by laying the preform on the mandrel, such as the composite material containment case provided in patent US8322971B2, has free ends at the beginning and end of the winding preform inside and outside the containment case, and the preform end at the circumferential two ends of the containment case is also free. In use, the free end is prone to disconnection, which in turn causes large-area interlayer debonding. Moreover, after the blade falls off, the engine will vibrate violently for a period of time, causing the interface debonding area to increase, eventually leading to a significant decrease in the stiffness of the containment case, and even the disintegration of the containment case, which poses a great threat to the safety of people and machines. SUMMARY

[0005] The present application aims to provide a composite material cylinder manufacturing method, which can improve the technical problem of the existing composite material cylinder manufactured by winding, which is prone to large-area debonding.

[0006] The present application also aims to provide a composite material cylinder which can improve the technical problem of large-area debonding of the existing composite material cylinder manufactured by winding.

[0007] The embodiments of the present application can be implemented by the following ways:

[0008] A composite material cylinder manufacturing method comprises:

[0009] The composite material preform is sleeved to form a cylindrical structure; wherein the composite material preform is a tubular member and has opposite starting end and tail end;

[0010] The core mold is installed in the inner hole of the cylindrical structure, and the outer mold is wrapped outside 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;

[0011] The liquid is filled into the cavity, and the composite material cylinder is manufactured by liquid molding process.

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

[0013] The tail end of the composite material preform is sleeved into the annular body from the circumferential opening of the annular body, and the tail end is pulled 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 sleeved on the annular body to form the cylindrical structure.

[0015] Optionally, the annular body is made of a heat-meltable material.

[0016] Optionally, after the step of forming a cavity between the core mold and the outer mold, the composite material cylinder manufacturing method 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 sprue of the mold.

[0019] Optionally, in the composite material preform, the thickness of the starting end decreases in the direction away from the tail end.

[0020] Optionally, the length of the starting end is greater than or equal to the arc length corresponding to 10° of the outer periphery of the composite cylindrical member.

[0021] Optionally, the thickness of the tail end decreases in a direction away from the starting end in the composite preform.

[0022] Optionally, the length of the tail end is greater than or equal to the arc length corresponding to 10° of the outer periphery of the composite cylindrical member.

[0023] Optionally, the starting end of the composite preform is closed, and the tail end of the composite preform is open.

[0024] Optionally, the composite 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 wrap layer structure of the cylindrical structure; the starting end is an end portion of one of the preform sections at one end of the composite preform, and the tail end is an end portion of one of the preform sections at the other end of the composite preform; the inner diameters of the plurality of preform sections gradually increase from the starting end to the tail end to adapt to the radial length changes of different wrap layers of the cylindrical structure.

[0025] Optionally, the composite preform is a fabric made by weaving, and the warp direction of the fabric is the length direction of the composite preform, and the weft direction of the fabric is the circumferential direction of the composite preform.

[0026] Optionally, the material of the composite preform is at least one of carbon fiber, glass fiber, Kevlar fiber, polyimide fiber, or SiC fiber.

[0027] A composite cylindrical member is manufactured by the method.

[0028] A composite cylindrical member has a cylindrical structure formed by a composite preform wrap, the composite preform is a tubular member having opposite starting end and tail end, and the tail end is wrapped outside the wrap layer where the starting end is located.

[0029] The composite cylindrical member and the manufacturing method thereof provided by the embodiments of the present application have the following beneficial effects:

[0030] The embodiment of the present application provides a composite material cylinder manufacturing method, which comprises the following steps: forming a cylinder structure by means of a composite material preform; wherein the composite material preform is a tubular member, and has opposite starting end and tail end; installing a core mold in the inner hole of the cylinder structure, and wrapping an outer mold on the outer side of the cylinder structure, so as to form a cavity between the core mold and the outer mold; wherein the cylinder structure is located in the cavity; and filling liquid into the cavity, and manufacturing the composite material cylinder by means of a liquid forming process. In the composite material cylinder manufacturing method, the cylinder structure is formed by means of the composite material preform, and only has one free end formed by the tail end of the composite material preform, so that the debonding probability is effectively reduced. In addition, the composite material preform is tubular, and correspondingly, the tail end is annularly wrapped outside the inner layer, so that the tail end can be more constrained. Even if the tail end is partially debonded, it is difficult to be widely debonded, so that the reliability of the composite material cylinder is ensured, and the problems of stiffness reduction and even disintegration caused by wide debonding in the use process are avoided.

[0031] The embodiment of the present application also provides a composite material cylinder, which is manufactured by means of the composite material cylinder manufacturing method, so that the composite material cylinder also has the beneficial effects of low debonding probability, difficulty in wide debonding even if the tail end is partially debonded, and the reliability of the composite material cylinder is ensured, and the problems of stiffness reduction and even disintegration caused by wide debonding in the use process are avoided.

[0032] The embodiment of the present application also provides a composite material cylinder, which has a cylinder structure formed by means of a composite material preform, the composite material preform is a tubular member, and has opposite starting end and tail end; the tail end is wrapped outside the starting end, so that only one free end is formed, the debonding probability is effectively reduced, and the composite material preform is tubular, and correspondingly, the tail end is annularly wrapped outside the inner layer, so that the tail end can be more constrained. Even if the tail end is partially debonded, it is difficult to be widely debonded, so that the reliability of the composite material cylinder is ensured, and the problems of stiffness reduction and even disintegration caused by wide debonding in the use process are avoided. BRIEF DESCRIPTION OF DRAWINGS

[0033] The above features and advantages of the present application can be better understood by reading the following detailed description of the embodiments of the present application in conjunction with the accompanying drawings. In the drawings, various components are not necessarily drawn to scale, and components having similar or related properties or features can have the same or similar reference numbers.

[0034] Figure 1 A step diagram of a composite material cylinder manufacturing method according to an aspect of the present application is shown;

[0035] Figure 2 A structural schematic view of a containment cartridge is shown according to an aspect of the present application;

[0036] Figure 3 A front structural schematic view of a composite preform is shown according to an aspect of the present application;

[0037] Figure 4 A left structural schematic view of a composite preform is shown according to an aspect of the present application;

[0038] Figure 5 A structural schematic view of a toroidal body is shown according to an aspect of the present application;

[0039] Figure 6 A structural schematic view is shown according to an aspect of the present application when performing step S11 of the composite cylindrical piece manufacturing method;

[0040] Figure 7 A structural schematic view is shown according to an aspect of the present application when performing step S12 of the composite cylindrical piece manufacturing method;

[0041] Figure 8 A structural schematic view of a manufactured cylindrical structure is shown according to an aspect of the present application;

[0042] Figure 9 A structural schematic view is shown according to an aspect of the present application when performing step S13 of the composite cylindrical piece manufacturing method; Figure 8 An enlarged structural schematic view of portion I;

[0043] Figure 10 A front structural schematic view of a composite preform is shown according to another aspect of the present application.

[0044] Reference signs:

[0045] 100 - cylindrical structure; 110 - composite preform; 111 - starting end; 112 - tail end; 113 - preform segment; 114 - first preform segment; 115 - second preform segment; 121 - inner layer structure; 122 - outer layer structure; 130 - toroidal body; 131 - circumferential opening; 132 - first free end; 133 - second free end; 140 - inner bore; 200 - containment cartridge. DETAILED DESCRIPTION

[0046] The present application is described in detail below with reference to the attached drawing figures and specific embodiments. It is to be noted that the aspects described below with reference to the drawing figures and specific embodiments are merely exemplary and should not be understood to limit the scope of the present application in any way.

[0047] In the description of the present application, it should be noted that the terms "upper", "lower", "inner", "outer", "vertical" and the like indicating the orientation or positional relationship are based on the orientation or positional relationship shown in the drawings, or the orientation or positional relationship in which the product of the present application is usually placed, and do not indicate or imply that the device or element must have a particular orientation or be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation of the present application.

[0048] At the same time, it should be noted that the terms "first", "second" and the like are used only for differentiation and description, and cannot be understood as indicating or implying relative importance.

[0049] In the description of the present application, it should be noted that unless otherwise explicitly specified or limited, the terms "mounting", "connecting", "connection" should be understood broadly, for example, it can be fixedly connected, integrally connected, or detachably connected; it can be mechanically connected, or electrically connected; it can be directly connected, or indirectly connected through an intermediate medium, or the internal connection of two elements, etc. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0050] In the description of the present embodiment, the cylindrical member is a hollow and circumferentially closed or has an opening shell-shaped structural member.

[0051] Figure 1 The step diagram of the composite material cylindrical member manufacturing method provided by the present embodiment is shown. Please refer to Figure 1 The present embodiment provides a composite material cylindrical member manufacturing method, and accordingly, a composite material cylindrical member is also provided, such as Figure 2 The structural schematic diagram of one specific example of the composite material cylindrical member provided by the present embodiment is shown, that is, in the present embodiment, the composite material cylindrical member is a containing cartridge 200. It can be understood that in some other embodiments, other types of composite material cylindrical members can also be manufactured by using the composite material cylindrical member manufacturing method provided by the present embodiment.

[0052] In the present embodiment, the composite material cylindrical member manufacturing method comprises the following steps:

[0053] S01: Forming a cylindrical structure 100 by looping a composite material preform 110.

[0054] Figure 3 The front view structural schematic diagram of the composite material preform 110 provided by the present embodiment is shown, Figure 4 The left view structural schematic diagram of the composite material preform 110 provided by the present embodiment is shown. As Figure 3 And Figure 4As shown, the composite preform 110 is a hollow tubular member, and the composite has opposite starting end 111 and tail end 112. The composite tubular member manufacturing method can further include a step of manufacturing the composite preform 110 before performing step S01. In this embodiment, the composite preform 110 is a fabric formed by weaving of composite yarns, which can be a three-dimensional fabric or a two-dimensional fabric formed into a hollow tube by stitching. Specifically, the composite preform 110 can be woven by a three-dimensional loom process using at least one of carbon fiber, glass fiber, Kevlar fiber, polyimide fiber, or SiC fiber (silicon carbide fiber).

[0055] Further, the warp direction of the fabric is the length direction of the composite preform 110 (as shown by direction A in Figure 3 Further, the weft direction of the fabric is the circumferential direction of the composite preform 110 (as shown by direction R in Figure 4 It should be noted that since the composite preform 110 is a composite fabric, it has a certain deformability and flexibility, and the circular tube structure shown in Figure 4 is a shape maintained under external force.

[0056] Further, during weaving, the thickness of the composite preform 110 at different locations can be manufactured according to the design of the composite tubular member to be manufactured, so as to achieve a square preform that mimics the profile and thickness distribution of the composite tubular member to be manufactured. Specifically, the thickness of the composite preform 110 at different locations can be changed by adjusting the number of layers of yarns during weaving.

[0057] Specifically, the step of looping the composite preform 110 to form the tubular structure 100 includes:

[0058] S11: The tail end 112 of the composite preform 110 is looped into the annular body 130 from the circumferential opening 131 of the annular body 130, and the tail end 112 is pulled until the starting end 111 of the composite preform 110 is fitted on the annular body 130.

[0059] Figure 5 shows a structural schematic diagram of the annular body 130 provided in this embodiment, Figure 6 shows a structural schematic diagram of the step S11 in the composite tubular member manufacturing method provided in this embodiment. Please refer to Figure 5 and Figure 6In this embodiment, the pre-deformation of the composite material preform 110 during the snare process is achieved by using an annular body 130 with a circumferential opening 131, which improves the accuracy of the snare and deformation of the composite material preform 110 and simplifies the molding tooling and process. Since the annular body 130 has a circumferential opening 131, it has two free ends forming the circumferential opening 131: a first free end 132 and a second free end 133. Furthermore, to ensure the positioning of the composite material preform 110 on the annular body 130 during the snare operation, the starting end 111 of the composite material preform 110 is closed, while the tail end 112 of the composite material preform 110 is open, allowing the snare to be made from the tail end 112 of the composite material preform 110.

[0060] During the trapping operation, firstly, through the open end 112 of the composite material preform 110, the end 112 is fitted onto the first free end 132. Then, the end 112 is pulled towards the second free end 133 until the closed 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 fitted onto the first free end 132 of the annular body 130, while the tail end 112 is detached from the annular body 130 from the second free end 133. In such a case... Figure 6 The portion of the composite material preform 110 that is fitted onto the annular body 130 forms the innermost ring-shaped layer structure of the cylindrical structure 100.

[0061] S12: The tail end 112 of the composite material preform 110 is fitted onto the starting end 111 through 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.

[0062] Figure 7 This diagram illustrates the structure during step S12 of the composite material cylindrical part manufacturing method provided in this embodiment. Figure 8 A schematic diagram of the manufactured cylindrical structure 100 is shown. Figure 9 for Figure 8 A magnified structural diagram of section I. Please refer to the reference. Figures 5-9 By opening the tail end 112 of the composite material preform 110, the tail end 112 is fitted into the first free end 132. At this time, the starting end 111 of the composite material preform 110 is fitted onto the first free end 132, forming part of the innermost ring-shaped layer structure of the cylindrical structure 100. Therefore, when the tail end 112 is fitted into the first free end 132, the tail end 112 wraps around the outer periphery of the starting end 111 of the composite material preform 110 (e.g., Figure 7The circumferential opening 131 of the annular body 130 is covered by the composite preform 110, forming a circumferential closure of the annular structure. Then the pulling of the tail end 112 of the composite preform 110 along the circumferential direction of the annular body 130 is continued until the composite preform 110 is completely looped on the annular body 130, forming a cylindrical structure 100 as shown in Figure 8 In this embodiment, the cylindrical structure 100 is made of the composite preform 110 and the annular body 130, which is completely wrapped inside the composite preform 110.

[0063] Further, in order to facilitate the removal of the annular body 130 so that the final composite cylindrical structure does not have the annular body 130 as the inner core, the annular body 130 can be made of a material that can be melted by heating, such as a resin that can be melted at a low temperature, etc. Alternatively, in some other embodiments, the annular body 130 can also be in the form of inflation, etc.

[0064] Alternatively, in the composite preform 110 provided in this embodiment, the thickness of the starting end 111 decreases along the direction away from the tail end 112, i.e. the closer to the end of the composite preform 110, the smaller the thickness of the starting end 111, thereby helping to reduce the step height of the end, thereby reducing the possibility of stress concentration leading to interface failure. 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 cylindrical structure, i.e. the length of the starting end 111 is greater than or equal to 1 / 36 of the outer circumference of the composite cylindrical structure.

[0065] Similarly, in the composite preform 110 provided in this embodiment, the thickness of the tail end 112 decreases along the direction away from the starting end 111, i.e. the closer to the end of the composite preform 110, the smaller the thickness of the tail end 112, thereby helping to reduce the step height of the end, thereby reducing the possibility of stress concentration leading to interface failure. 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 structure, i.e. the length of the tail end 112 is greater than or equal to 1 / 36 of the outer circumference of the composite cylindrical structure.

[0066] It can be understood that the thickness of the starting end 111 and the tail end 112 can also be set to be equal, for example, in the structure as shown in Figure 9 In the structure as shown in

[0067] Furthermore, the composite preform 110 has multiple preform segments 113 distributed from the starting end 111 to the tail end 112. Each preform segment 113 is used to form a ring-shaped layer structure of the cylindrical structure 100. The starting end 111 is the end portion of a preform segment 113 located at one end of the composite preform 110, and the tail end 112 is the end portion of a preform segment 113 located at the other end of the composite preform 110. Thus, the preform segment 113 at the tail end 112 is wrapped in the outer layer, and the preform segment 113 at the starting end 111 is closer to the annular body 130 than the preform segment 113 at the tail end 112. To avoid quality problems caused by excessive deformation of the composite preform 110, the composite preform 110 is configured such that the inner diameter of the multiple preform segments 113 increases sequentially from the starting end 111 to the tail end 112 to accommodate the radial length variation of different ring-shaped layers of the cylindrical structure 100.

[0068] like Figure 9 As shown, in the cylindrical structure 100 formed in this embodiment, the cylindrical structure 100 has two nested layer structures, namely an inner layer structure 121 and an outer layer structure 122. Correspondingly, as... Figure 5 The composite material preform 110 shown has two preform sections 113, which are a first preform section 114 and a second preform section 115, respectively. 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 the 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 the outer layer structure 122.

[0069] In other words, in the manufactured cylindrical structure 100, the second preform section 115 wraps around the first preform section 114, and the first preform section 114 is fitted to the outer surface of the annular body 130. Thus, the inner diameter of the first preform section 114 is equal to the axial length of the annular body 130 (including the flange length if present), 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 component to be manufactured is a variable thickness structure, the thickness of each preform section 113 is set differently according to requirements. In this case, the inner diameter of the second preform section 115 wrapping around 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.

[0070] It should be noted that the number of snare layer structures contained in the cylindrical structure 100 is not limited here, and it can be understood that in other embodiments, the number of snare layer structures contained in the cylindrical structure 100 can also be set to other values greater than or equal to 1 according to requirements, such as 1.5 or 4, etc. Accordingly, when the number of snare layer structures contained 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 snare layer structures contained in the cylindrical structure 100 is 4, the composite material preform 110 has four preform sections 113 (as shown in Figure 10

[0071] S02: Install the core mold in the inner hole 140 of the cylindrical structure 100, and wrap the outer mold on the outside of the cylindrical structure 100, so as to form a cavity between the core mold and the outer mold.

[0072] Insert the core mold (not shown in the figure) into the inner hole 140 of the cylindrical structure 100, and define the radial inner side wall surface of the manufactured composite material cylindrical part through the core mold. Then wrap the outer mold (not shown in the figure) on the outside of the cylindrical structure 100, and define the radial outer side wall surface of the manufactured composite material cylindrical part through 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 flexible material.

[0073] It should be noted that the specific structure of the core mold and the outer mold can be set according to the structure of the composite material cylindrical part to be manufactured.

[0074] S03: Inject liquid into the cavity to manufacture the composite material cylindrical part by using a liquid forming process.

[0075] Specifically, the liquid includes but is not limited to liquid resin. After the liquid resin is injected into the cavity, the corresponding liquid forming process suitable for the specific type of composite material cylindrical part can be used according to the specific type of composite material cylindrical part. Here, the liquid forming process is not specifically limited. Then the resin is cured by using heating, pressurizing, vacuumizing or other process methods according to the liquid forming process. After the structure of the cured resin is demolded from the mold (i.e. the core mold and the outer mold), the composite material cylindrical part can be obtained. It can be understood that the cured structure can also be subjected to subsequent processing such as machining after demolding.

[0076] ​Since the cylindrical structure 100 manufactured in the embodiment further has the annular body 130, after the step S02 is performed, the composite material cylindrical part manufacturing method can further include a step S04 of removing the annular body 130. Obviously, in some other embodiments, if the cylindrical structure 100 manufactured does not have the annular body 130, or according to the composite material cylindrical part to be manufactured, the annular body 130 does not need to be removed, the composite material cylindrical part manufacturing method can also not include the step S04, and it can be understood that, if according to the composite material cylindrical part to be manufactured, the annular body 130 does not need to be removed, the specific material of the annular body 130 and the like can be selected and arranged according to the requirements. Specifically, in the embodiment, the step S04 of removing the annular body 130 includes:

[0077] S41: heating the cylindrical structure 100 and the mold until the temperature reaches the melting temperature of the annular body 130.

[0078] S42: discharging the molten liquid formed by melting the annular body 130 from the sprue of the mold.

[0079] That is, in the embodiment, the mold is further formed with a sprue communicating with the cavity, and the specific position of the sprue can be arranged on the outer mold or the core mold according to the requirements, which is not limited here.

[0080] 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 material cylindrical part is filled into the cavity, and the melting temperature of the annular body 130 can be set to be not higher than the temperature of the liquid for curing the composite material cylindrical part. In this way, the step S04 can be performed during the execution of the step S03. Specifically, before the step S03 is performed, the core mold and the outer mold are closed to compact the cylindrical structure 100 to the designed size, and then the liquid is injected into the cavity. After the liquid is injected, the step S04 is performed, and finally the curing operation of the liquid is performed. Alternatively, in some other embodiments, the melting temperature of the annular body 130 can be set to be lower than the temperature when the liquid for manufacturing the composite material cylindrical part is filled into the cavity. In this way, the step S04 can be performed after the step S02 is performed and before the step S03 is performed.

[0081] The composite material cylindrical part and the manufacturing method thereof provided by the embodiments of the present application adopt the method of preform + liquid forming, compared with the current process of winding the flat plate preform on the core mold, the device for fixing and pre-deforming the preform on the core mold is not needed, the preform can be pre-deformed when the composite material preform 110 is laid up, the precision of laying up and deforming the composite material preform 110 is improved, and the forming process and process are simplified. The composite material cylindrical part manufactured has only one free end of the tail end 112, and the free end is annular and will bear more constraints, reducing the possibility of interface debonding.

[0082] Meanwhile, the embodiment of the present application also provides a composite material cylinder, which comprises a cylinder structure 100 formed by winding a composite material preform 110, and the composite material preform 110 is a tubular member having opposite starting end 111 and tail end 112, and the tail end 112 is wrapped outside the winding layer where the starting end 111 is located.

[0083] The above merely provides the specific implementation of the present application, but the protection scope of the present application is not limited to this, any person skilled in the art can easily think of the changes or replacements within the technical range disclosed by the present application, which should be covered in the protection scope of the present application.

Claims

1. A method for manufacturing a composite cylindrical component, characterized in that: The method for manufacturing the composite material cylindrical component includes: The composite material preform is encased to form a cylindrical structure; wherein the composite material preform is a tubular component and has a starting end and a tail end, the tail end being wrapped around the outside of the encasing layer where the starting end is located; A core mold is installed in the inner hole of the cylindrical structure, and an outer mold is wrapped around the outside 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; Liquid is filled into the cavity, and a composite cylindrical part is manufactured using a liquid molding process.

2. The method for manufacturing composite cylindrical parts according to claim 1, characterized in that: The step of forming a cylindrical structure by enclosing the composite material preform includes: Insert the tail end of the composite material preform into the annular body through the circumferential opening of the annular body, and pull the tail end until the starting end of the composite material preform is fitted onto the annular body; The composite material preform is fitted onto the starting end through 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 composite cylindrical parts according to claim 2, characterized in that: The annular body is made of a heat-fusible material.

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

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

6. The method for manufacturing composite cylindrical parts 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 part.

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

8. The method for manufacturing composite cylindrical parts 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 part.

9. The method for manufacturing composite cylindrical parts 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 composite cylindrical parts according to claim 1, characterized in that: The composite material preform has multiple preform sections distributed from the starting end to the tail end, and each preform section is used to form a ring-shaped layer structure of the cylindrical structure; The starting end is the end portion of a preform section located at one end of the composite material preform, and the tail end is the 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 diameter of the plurality of prefabricated sections increases sequentially to accommodate the radial length variation of different ring layers of the cylindrical structure.

11. The method for manufacturing composite cylindrical parts according to claim 1, characterized in that: The composite material preform is a woven fabric, 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 composite cylindrical parts according to claim 1, characterized in that: The material of the composite material preform is at least one of carbon fiber, glass fiber, Kevlar fiber, polyimide fiber or SiC fiber.

13. A composite material cylindrical component, characterized in that: The composite cylindrical component is manufactured using the composite cylindrical component manufacturing method as described in any one of claims 1-12.

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