Carbon fiber full-winding pressure vessel

Abstract

The invention relates to the technical field of high-pressure pressure vessels, and discloses a carbon fiber fully-wound pressure vessel, which comprises a gas cylinder body, a gas inlet, a gas outlet and a gas outlet, the turbulent flow assembly is fixedly installed in an inner cavity of the gas cylinder body, the turbulent flow assembly comprises a first turbulent flow blade set and a second turbulent flow blade set, the first turbulent flow blade set and the second turbulent flow blade set are alternately arranged, in the circumferential direction of the gas cylinder body, the first turbulent flow blade set comprises a plurality of first blade bodies, and the second turbulent flow blade set comprises a plurality of second blade bodies; the first blade body and the second blade body are obliquely arranged in opposite directions relative to the axis of the gas cylinder body. By arranging the turbulent flow blade sets which are opposite in inclination direction and alternate in the axial direction, multi-direction diversion and disturbance are conducted on airflow inflated at a high speed, the kinetic energy concentration degree of the airflow in the local area of the tail end of the gas cylinder body is reduced, and therefore the sudden temperature rise, caused by kinetic energy concentration conversion, of the local area of the tail end of the gas cylinder body is relieved; the cycle life of the pressure vessel is prolonged.

Description

Technical Field

[0001] This invention relates to the field of high-pressure vessel technology, and specifically to a carbon fiber fully wound pressure vessel. Background Technology

[0002] High-pressure hydrogen storage technology is a core component of the development of the hydrogen energy industry. Among them, the 70MPa type IV carbon fiber fully wound gas cylinder has become a key piece of equipment for vehicle-mounted and stationary hydrogen storage systems due to its high hydrogen storage density of more than 4.5wt% and excellent lightweight performance.

[0003] During the hydrogen filling process, under 70MPa high-pressure hydrogen filling conditions, the hydrogen enters through the filling inlet and forms a concentrated jet along the axial direction. Approximately 60% to 70% of the kinetic energy is released in the tail region of the cylinder through violent collisions and compression, converting into heat energy and causing a sudden increase in local temperature at the bottom of the cylinder. The inner liner of the carbon fiber wound cylinder is typically made of polyamide 6 (PA6) nylon. However, PA6 nylon has an upper limit to its long-term operating temperature; high temperatures reduce the crystallinity of PA6, leading to a decrease in the impact resistance of the bottom area. Simultaneously, the epoxy resin matrix in the carbon fiber wound cylinder undergoes a glass transition at high temperatures, resulting in a decrease in the interlaminar shear strength of the composite material at the bottom area, shortening the cylinder's cycle life. This limits the cycle life of conventional high-pressure hydrogen cylinders to no more than 1200 cycles. Summary of the Invention

[0004] In view of this, the present invention provides a carbon fiber fully wound pressure vessel to solve the problem of short cycle life of the existing 70MPa type IV carbon fiber fully wound gas cylinder.

[0005] In a first aspect, the present invention provides a carbon fiber fully wound pressure vessel, comprising: The gas cylinder body has an inflation inlet at one end along the axial direction and a closed end, wherein the inflation inlet is connected to the inner cavity of the gas cylinder body. A flow-deflecting assembly is fixedly installed in the inner cavity of the gas cylinder body. The flow-deflecting assembly includes a first flow-deflecting blade group and a second flow-deflecting blade group. Along the axial direction of the gas cylinder body, the first flow-deflecting blade group and the second flow-deflecting blade group are arranged alternately. Along the circumferential direction of the gas cylinder body, the first flow-deflecting blade group includes a plurality of first blade bodies, and the second flow-deflecting blade group includes a plurality of second blade bodies. Both the first blade bodies and the second blade bodies are arranged at an inclination relative to the axis of the gas cylinder body, and the inclination directions of the first blade bodies and the second blade bodies are opposite.

[0006] When high-pressure hydrogen is filled into a carbon fiber fully wound pressure vessel, under a high-pressure hydrogen filling condition of 70 MPa, the high-pressure gas enters the inner cavity of the cylinder body through the filling inlet and flows axially. As the airflow flows sequentially through the alternating first and second sets of turbulence blades, it is guided by the first and second blade bodies respectively. Since the two sets of blade bodies are tilted in opposite directions, the first turbulence blade group guides part of the axial airflow to a circumferential direction for diffusion, while the following second turbulence blade group guides the airflow to the opposite circumferential direction for diffusion. This alternating action forces the axial jet to be decomposed and its direction changed multiple times, achieving multi-directional dispersion and stepped dissipation of airflow kinetic energy in the circumferential space, thereby breaking the pattern of airflow flowing straight in the axial direction and releasing kinetic energy at the end. By setting up turbulence blade groups with opposite tilt directions and alternating axial directions, a bidirectional alternating flow channel is constructed in the inner cavity of the cylinder, which can effectively divert and turbulent the high-speed filling airflow in multiple directions. Improving the uniformity of airflow distribution within the cylinder cavity and reducing the concentration of kinetic energy in localized areas at the cylinder's end reduces the sudden temperature rise in localized areas at the cylinder's end caused by concentrated kinetic energy conversion. This allows for a smoother and more uniform temperature rise curve during high-pressure rapid inflation, enabling the pressure vessel to maintain high structural strength after multiple inflation / deflation cycles, thereby extending the pressure vessel's cycle life.

[0007] In one optional implementation, the turbulence component further includes: The mounting component is fixedly installed in the inner cavity of the gas cylinder body along the axial direction of the gas cylinder body; A first connector is fixedly installed on the mounting component and extends circumferentially along the gas cylinder body. The first blade body is fixedly installed on the end of the first connector away from the mounting component. The second connector is fixedly installed on the mounting component and extends circumferentially along the gas cylinder body. The second blade body is fixedly installed on the end of the second connector away from the mounting component.

[0008] The mounting component is fixedly installed axially within the cylinder body, providing axial support for the entire aerodynamic assembly. The first and second connectors are respectively fixedly installed on the mounting component and extend circumferentially along the cylinder body, together forming the radial support frame of the aerodynamic assembly. The first blade body is fixedly installed on the end of the first connector furthest from the mounting component, and the second blade body is fixedly installed on the end of the second connector furthest from the mounting component. This allows the first and second blade bodies to be indirectly and securely installed on the mounting component via the connectors, reliably transferring the aerodynamic force of the blades to the mounting component and the cylinder body structure. By setting up the mounting component, the first connector, and the second connector, a graded support and fixing structure is constructed, enhancing the overall mechanical strength and rigidity of the aerodynamic assembly. This effectively resists the impact of high-pressure, high-speed airflow and potential vibrations, ensuring the positional stability and structural reliability of the aerodynamic blades during operation and avoiding the risk of blade failure due to deformation or detachment under stress.

[0009] In one alternative embodiment, along the circumference of the gas cylinder body, the length of the first connector is less than the length of the second connector, or the length of the second connector is less than the length of the first connector.

[0010] When the high-pressure airflow enters axially, the airflow on the same circumferential cross-section of the gas cylinder body will simultaneously impact the first and second blade bodies located at different circumferential positions. This forces the airflow to move radially in the circumferential direction while moving axially, more effectively dispersing any possible axial flow and reducing the impact of the airflow on the gas cylinder body in the axial direction.

[0011] In one optional embodiment, the mounting component is a connecting shaft, which is coaxially arranged with the inner cavity of the gas cylinder body, and both the first connecting component and the second connecting component extend outward from the center of the gas cylinder body.

[0012] Using a coaxially arranged connecting shaft as an installation component, it cooperates with the first and second connecting components to form a support structure for the turbulence component. This maximizes the alignment and coaxiality of the turbulence component within the gas cylinder cavity, reduces additional vibrations or local stress concentrations that may be caused by component eccentricity, and improves the structural stability for long-term use.

[0013] In one alternative embodiment, a third blade body is provided on the connecting shaft, and the third blade body is inclined toward the side away from the air inlet.

[0014] A third blade, inclined away from the inflation inlet, is installed on the connecting shaft, which is equivalent to setting a turbulence and guiding element at the central axis of the airflow channel. The third blade can initially block and deflect the axial high-speed jet in the core area of ​​the gas cylinder's internal cavity, consume some of the airflow energy and change its direction, forming a synergistic turbulence effect in conjunction with the first and second blades.

[0015] In one optional embodiment, the first blade body is inclined toward the inflation inlet, and the second blade body is inclined away from the inflation inlet. The angle between the axis of the first blade body and the axis of the gas cylinder body and the angle between the axis of the second blade body and the axis of the gas cylinder body are equal in value and opposite in direction.

[0016] The tilt directions of the first and second blade bodies are set to be opposite, with equal absolute angles. When the airflow passes through the first blade body, it is guided towards the edge of the second blade body. As the airflow is guided to the second blade body, it is dispersed by the turbulence of the second blade body, and then guided towards the edge of the next set of first blade bodies, where it is further dispersed by the turbulence of the next set of first blade bodies. After passing through multiple sets of first and second turbulence blade groups in this manner, when the airflow reaches the end of the gas cylinder body, its kinetic energy is greatly reduced, which can significantly weaken the impact force of the airflow on the end of the gas cylinder.

[0017] In one alternative embodiment, the angle between the axis of the first blade body and the axis of the gas cylinder body is 60°.

[0018] In one alternative implementation, the first blade body and / or the second blade body are flat plates or curved plates.

[0019] In one optional embodiment, the length of the first blade body and / or the second blade body is 1 / 3 to 1 / 2 of the inner diameter of the gas cylinder body.

[0020] In one optional embodiment, a flow passage is provided between the first blade body and the second blade body along the circumferential direction of the gas cylinder body. This avoids the blades forming a completely closed obstruction in the circumferential direction, ensures the continuity of the airflow channel, prevents excessively high local pressure from being generated on the first and second turbulence blade groups near the filling inlet, and ensures the overall stability of the structure. Attached Figure Description

[0021] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0022] Figure 1 This is a schematic diagram of the structure of a carbon fiber fully wound pressure vessel provided in an embodiment of the present invention.

[0023] Figure 2 This is a perspective view of a carbon fiber fully wound pressure vessel provided in an embodiment of the present invention.

[0024] Figure 3 This is an axial cross-sectional schematic diagram of a carbon fiber fully wound pressure vessel provided in an embodiment of the present invention.

[0025] Figure 4 This is a cross-sectional schematic diagram of a carbon fiber fully wound pressure vessel provided in an embodiment of the present invention.

[0026] Figure 5 Simulation cloud map of the temperature rise during filling of carbon fiber fully wound gas cylinders in existing technology.

[0027] Figure 6 The simulation cloud map shows the temperature rise during filling of the carbon fiber fully wound pressure vessel provided in the embodiment of the present invention.

[0028] Figure 7 This is a comparison curve of the filling temperature rise of a carbon fiber fully wound gas cylinder in the prior art and the carbon fiber fully wound pressure vessel provided in the embodiments of the present invention.

[0029] Explanation of reference numerals in the attached drawings: 1. Gas cylinder body; 101. Gas filling inlet; 102. Valve seat; 103. Inner liner; 104. Reinforcing layer; 2. Baffle assembly; 201. Mounting component; 2011. Connecting shaft; 2012. Third blade body; 202. First connecting component; 203. Second connecting component; 204. First blade body; 205. Second blade body. Detailed Implementation

[0030] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0031] The following is combined Figures 1 to 7The following describes embodiments of the present invention.

[0032] According to an embodiment of the present invention, in one aspect, a carbon fiber fully wound pressure vessel is provided, including a gas cylinder body 1 and a flow-turbulence assembly 2 disposed inside the gas cylinder body 1, such as... Figures 1 to 4 As shown.

[0033] The gas cylinder body 1 is typically elongated cylindrical, with an inflation inlet 101 at one axial end for connecting to an external gas supply system, and a closed structure at the other end, forming a sealed inner cavity for storing high-pressure media. The inflation inlet 101 is connected to the inner cavity of the gas cylinder body 1 via a valve seat 102 structure to ensure smooth inflation and deflation. The main structure of the gas cylinder body 1 includes an inner liner 103 made of plastic materials such as PA6 nylon, and a carbon fiber resin composite material reinforcement layer 104 formed on the outside of the inner liner 103 through a winding process, thereby achieving a high-strength, lightweight container structure.

[0034] The turbulence-disrupting assembly 2 is fixedly installed inside the cylinder body 1. The turbulence-disrupting assembly 2 includes a first turbulence-disrupting blade group and a second turbulence-disrupting blade group. Viewed from the axial perspective of the cylinder body 1, the first and second turbulence-disrupting blade groups are arranged alternately along the length of the cylinder body 1. Further, viewed from the circumferential perspective of the cylinder body 1, the first turbulence-disrupting blade group includes multiple first blade bodies 204 distributed around an axis, and the second turbulence-disrupting blade group includes multiple second blade bodies 205 distributed around an axis. Each first blade body 204 and each second blade body 205 is set to be inclined at an angle relative to the central axis of the cylinder body 1, and the overall inclination direction of the first blade body 204 is opposite to the overall inclination direction of the second blade body 205.

[0035] During the inflation process of the carbon fiber fully wound pressure vessel, for example, when 70MPa high-pressure hydrogen is injected into the pressure vessel, the high-pressure gas flows at high speed into the inner cavity of the gas cylinder body 1 through the inflation inlet 101 and mainly moves axially towards the end of the vessel. When this axial jet encounters the first and second sets of axially alternating turbulence blades, the flow path of the jet is continuously disturbed. The airflow is first affected by the first blade body 204 in the first turbulence blade group. Because the first blade body 204 has a specific tilt direction, it guides a portion of the axial airflow to deflect and diffuse around the gas cylinder. Then, the airflow continues to advance and impacts the next set of second blade bodies 205. Because the tilt direction of the second blade body 205 is opposite to that of the first blade body 204, the second blade body 205 guides the airflow to another direction around the gas cylinder body 1 for deflection and diffusion. Along the cylinder axis, the forward and reverse flow alternate multiple times, forcing the originally concentrated axial jet to be dispersed and change direction by the turbulence. This causes the kinetic energy of the high-pressure jet to no longer be concentrated at the end of the cylinder body 1 and released all at once, but to be dispersed in multiple directions in the circumferential space and gradually dissipated in a stepwise manner through friction and mixing with the blades and inner wall.

[0036] By constructing a bidirectional alternating flow channel composed of blades with opposite tilting directions and alternating axial directions within the inner cavity of the gas cylinder body 1, active multidirectional diversion and three-dimensional disturbance of the high-speed inflated airflow can be implemented. This improves the uniformity of airflow distribution throughout the entire inner cavity of the gas cylinder body 1, effectively reducing the degree of kinetic energy accumulation in the local area at the end of the gas cylinder body 1. The reduction in kinetic energy concentration can greatly alleviate the phenomenon of sudden temperature rise in the local area at the end of the gas cylinder body 1 caused by adiabatic compression and violent collision. Therefore, under typical high-pressure rapid inflation conditions, the pressure vessel provided in this embodiment can obtain a smoother temperature rise curve with a more uniform axial and circumferential distribution. This not only improves the safety of a single inflation process, avoiding thermal damage to the plastic inner liner 103 and resin matrix caused by local overheating, but also, in the long run, because the temperature rise of each inflation is controlled, the thermal fatigue stress borne by the material is greatly reduced, allowing the pressure vessel to maintain high material performance and structural integrity even after multiple cycles of inflation and deflation, thereby extending the overall cycle life of the pressure vessel.

[0037] In this embodiment, the turbulence-disrupting component 2 includes a mounting member 201, a first connecting member 202, and a second connecting member 203. The mounting member 201 is fixedly installed in the inner cavity of the gas cylinder body 1 along the axial direction. The mounting member 201 is typically made of a high-strength metal rod or metal tube. Its two ends can be rigidly connected to the extension sections of the valve seats 102 at both ends of the gas cylinder body 1 by welding, threaded connection, or snap-fit. The diameter of the mounting member 201 can be set to 1 / 20 to 1 / 10 of the inner diameter of the gas cylinder body 1 to ensure that it has sufficient bending stiffness to support the weight of the entire turbulence-disrupting component 2 and resist the dynamic load generated by the airflow impact. The first connecting member 202 is fixedly installed on the mounting member 201 by means of bolt fastening, welding, or integral molding. The first connecting member 202 extends circumferentially along the cylinder body 1, and its extension length can be adjusted according to the inner diameter of the cylinder body 1 and the installation requirements of the blade body. The first blade body 204 is fixedly installed on the end of the first connecting member 202 away from the mounting member 201 by means of riveting, welding, or nesting and then welding. The connection area between the first blade body 204 and the first connecting member 202 can be provided with reinforcing ribs to improve the connection strength. The second connecting member 203 is also fixedly installed on the mounting member 201 by means of bolt fastening, welding, or integral molding. The second connecting member 203 extends circumferentially along the cylinder body 1. The second blade body 205 is fixedly installed on the end of the second connecting member 203 away from the mounting member 201 by means of riveting, welding, or nesting and then welding.

[0038] Mounting member 201 is fixedly installed axially in the inner cavity of the gas cylinder body 1, providing a reliable axial support foundation for the entire turbulence assembly 2 and ensuring that the turbulence assembly 2 will not undergo axial displacement or bending deformation under airflow impact. First connecting member 202 and second connecting member 203 are respectively fixedly installed on mounting member 201 and extend circumferentially along the gas cylinder body 1, together forming a radial support frame for the turbulence assembly 2. This frame can effectively transfer the circumferential force on the blade body to mounting member 201. First blade body 204 is fixedly installed on the end of first connecting member 202 away from mounting member 201, and second blade body 205 is fixedly installed on the end of second connecting member 203 away from mounting member 201. This allows the first blade body 204 and second blade body 205 to be indirectly and securely installed on mounting member 201 through connecting members, thereby reliably transferring the turbulence force of the blades to mounting member 201 and the gas cylinder body 1 structure, preventing the blade root from directly bearing the entire load and causing fatigue fracture.

[0039] By setting the mounting component 201, the first connector 202 and the second connector 203, a graded support and fixing structure is constructed, which enhances the overall mechanical strength and rigidity of the turbulence assembly 2, thereby effectively resisting the impact of high-pressure and high-speed airflow and the vibration that may be caused, ensuring the positional stability and structural reliability of the turbulence blades in the working state, avoiding the risk of blade failure due to deformation or detachment under force, and extending the service life of the turbulence assembly 2.

[0040] In this embodiment, along the circumferential direction of the gas cylinder body 1, the length of the first connector 202 is designed to be smaller than the length of the second connector 203, or the length of the second connector 203 is designed to be smaller than the length of the first connector 202. The two configurations are selected according to the actual flow field optimization requirements.

[0041] When the high-pressure airflow enters along the axial direction of the cylinder body 1, the airflow on the same circumferential cross section of the cylinder body 1 will simultaneously impact the first blade body 204 and the second blade body 205, which are located at different circumferential positions. Due to the different lengths of the connecting parts supporting the first blade body 204 and the second blade body 205, there is a difference in the radial position of the first blade body 204 and the second blade body 205 within the inner cavity of the cylinder body 1. This difference in radial position forces the airflow to move radially along the circumference while moving axially, more effectively dispersing any possible axial flow and reducing the impact of the airflow on the cylinder body 1 in the axial direction.

[0042] As another optional implementation, the length difference between the first connector 202 and the second connector 203 can be a stepped length change, that is, along the direction from the air inlet 101 to the tail of the bottle, the length of the connector gradually increases or decreases, or increases first and then decreases, or decreases first and then increases, to adapt to the law of airflow energy attenuation.

[0043] Furthermore, the mounting component 201 takes the form of a connecting shaft 2011, which is coaxially arranged with the inner cavity of the gas cylinder body 1. The first connecting component 202 and the second connecting component 203 both extend outward from the center of the connecting shaft 2011 along the radial direction of the gas cylinder body 1 to form a radial support structure. The first connecting component 202 and the second connecting component 203 both adopt a connecting column structure.

[0044] The coaxially arranged connecting shaft 2011 is used as the mounting component 201, which cooperates with the first connecting component 202 and the second connecting component 203 to form the support structure of the turbulence component 2. This maximizes the alignment and coaxiality of the turbulence component 2 in the inner cavity of the gas cylinder body 1, reduces additional vibration or local stress concentration that may be caused by component eccentricity, and improves the structural stability for long-term use.

[0045] In another embodiment, the mounting member 201 may also be a frame structure, comprising a plurality of connecting rings distributed along the axial direction of the gas cylinder body 1 and connecting rods for sequentially connecting adjacent connecting rings into a whole. The first connecting member 202 and the second connecting member 203 are both fixedly connected to the connecting rings and extend toward the central axis of the gas cylinder body 1.

[0046] In one embodiment, a third blade body 2012 is disposed on the connecting shaft 2011. The third blade body 2012 is configured with its inclined direction facing away from the inflation inlet 101, and its position is located on the geometric centerline of the airflow channel. When the high-pressure jet rushes in from the inflation inlet 101, the third blade body 2012, located on the centerline, performs the first active interception and deflection of the airflow with the highest core velocity, dissipating some of its kinetic energy in advance and guiding it to diffuse outwards. When the airflow subsequently contacts the outer first blade body 204 and second blade body 205, its velocity and flow structure have been preliminarily optimized, thereby achieving the synergy between the central pre-turbulence and the outer main turbulence, making the entire kinetic energy dissipation process smoother and more efficient. The third blade body 2012 has multiple blades spaced apart in the circumferential direction of the connecting shaft 2011 and is evenly distributed along the circumferential direction of the connecting shaft 2011 to form an independent central turbulence group; the tilt angle of the third blade body 2012 can be designed to be the same as that of the first blade body 204 but in the opposite direction, or designed to be the same as that of the second blade body 205 but in the opposite direction.

[0047] In one embodiment, the first blade body 204 is inclined toward the inflation inlet 101, and the second blade body 205 is inclined away from the inflation inlet 101. The angle between the first blade body 204 and the axis of the gas cylinder body 1 and the angle between the second blade body 205 and the axis of the gas cylinder body 1 are equal in magnitude and opposite in direction.

[0048] The tilt directions of the first blade body 204 and the second blade body 205 are set to be opposite, with equal absolute angles, forming a strictly symmetrical bidirectional flow channel. When the airflow passes through the first blade body 204, it is guided towards the edge of the second blade body 205. As the airflow is guided towards the second blade body 205, it is dispersed by the turbulence of the second blade body 205, and then guided towards the edge of the next set of first blade bodies 204, where it is further dispersed by the turbulence of the next set of first blade bodies 204. After passing through multiple sets of first and second turbulence blade groups in this manner, when the airflow reaches the end of the gas cylinder body 1, its kinetic energy is greatly reduced, significantly weakening the impact force of the airflow on the end of the gas cylinder.

[0049] As another optional implementation, the angle between the first blade body 204 and the second blade body 205 can be finely adjusted based on the length of the gas cylinder body 1 and the filling rate. The longer the length and the higher the filling rate, the smaller the angle can be to increase the number of flow guiding times.

[0050] In one embodiment, the angle between the first blade body 204 and the axis of the gas cylinder body 1 is specifically 60°, and the angle between the second blade body 205 and the axis of the gas cylinder body 1 is correspondingly -60°. As another optional embodiment, this angle can be adjusted within the range of 45° to 75° according to actual operating conditions. For example, a smaller 45° angle can be used in high-speed filling conditions to increase the number of flow diversions, while a larger 75° angle can be used in low-speed filling conditions to enhance the single flow diversion effect. The angle can also gradually change along the axial direction of the gas cylinder body 1, for example, using a larger angle near the filling inlet 101 and a smaller angle near the tail of the cylinder to match the airflow energy attenuation characteristics.

[0051] In one embodiment, the first blade body 204 and the second blade body 205 can be either a flat plate structure or an arc-shaped plate structure. The flat plate structure can be designed as a rectangular flat plate, a trapezoidal flat plate, or an irregularly shaped flat plate with a flow guide notch, and the arc-shaped plate can be designed as a single-curvature arc-shaped plate or a double-curvature arc-shaped plate. In this embodiment, both the first blade body 204 and the second blade body 205 adopt an arc-shaped plate structure.

[0052] The surfaces of the first blade body 204 and the second blade body 205 can be electropolished to reduce surface roughness, or coated with an anti-friction coating to reduce frictional heat generation. The edges of the first blade body 204 and the second blade body 205 can be rounded to reduce stress concentration and airflow impact noise. The first blade body 204 and the second blade body 205 can adopt a multi-layer composite structure, such as an aluminum alloy substrate covered with a carbon fiber reinforcement layer 104, to improve strength and stiffness.

[0053] In one embodiment, the length of the first blade body 204 and the second blade body 205 is between 1 / 3 and 1 / 2 of the inner diameter of the gas cylinder body 1. For the gas cylinder body 1 with a smaller inner diameter, the length of the blade body can be 1 / 2 of the inner diameter to enhance the flow guiding effect; for the gas cylinder body 1 with a larger inner diameter, the length of the blade body can be 1 / 3 of the inner diameter to avoid excessive blockage; the length of the blade body can be differentiated in the same set of blades, for example, some blade bodies can be long and some can be short to form an asymmetric flow field; the length of the blade body can increase axially, that is, a shorter length is used near the gas filling inlet 101 and a longer length is used near the tail of the cylinder to increase the turbulence intensity in the end region.

[0054] In one embodiment, a flow passage A is reserved between the first blade body 204 and the second blade body 205 along the circumferential direction of the gas cylinder body 1, meaning that the first blade body 204 and the second blade body 205 are discontinuous in the circumferential direction. This avoids the blades forming a completely closed obstruction in the circumferential direction, ensures the smoothness of the airflow channel, prevents the generation of excessively high local pressure on the first and second turbulence blade groups near the inflation inlet 101, and ensures the overall stability of the structure.

[0055] This application aims to resolve the contradiction between "temperature surge" and structural reliability in existing 70MPa high-pressure hydrogen cylinders during hydrogen filling. It seeks to achieve uniform circumferential diffusion of airflow, ensuring that the circumferential flow velocity deviation of the fluid in the inner cavity of the cylinder body 1 does not exceed 5%, the turbulence intensity is reduced by 30%–40%, and the kinetic energy of the airflow is dissipated in a stepwise manner, thereby reducing the overall temperature rise of the cylinder body 1 by at least 25%, and ensuring that the highest temperature at the end of the cylinder body 1 does not exceed 75°C.

[0056] The turbulence-dispersing component 2 adopts an alternating angle layout, with the first blade body 204 and the second blade body 205 of each group arranged in an alternating array of 60° and -60°. When the 70MPa high-pressure airflow enters the inner cavity through the air inlet 101 and impacts the turbulence-dispersing grid structure formed by the first blade body 204 and the second blade body 205, part of the airflow diffuses upward circumferentially along the first blade body 204, and the other part diffuses downward circumferentially along the second blade body 205, forming a "bidirectional diversion" effect, which makes the circumferential distribution deviation of the airflow ≤5%, and reduces the local kinetic energy concentration by 20%~30% compared with a single-angle structure.

[0057] Three to six sets of first and second turbulence vane groups are arranged along the axial direction of the gas cylinder. When the length of the gas cylinder body 1 is 800mm to 1000mm, three to four sets are used; when it is 1000mm to 1500mm, four to six sets are used. The distance between adjacent sets of first and second turbulence vane groups is 100mm to 180mm, increasing by 5mm to 10mm from the filling inlet 101 side to the cylinder tail, adapting to the airflow energy attenuation law. Each set of first and second turbulence vane groups contains four to six blades, evenly distributed along the circumference to ensure uniform distribution of the circumferential airflow channel.

[0058] The first blade body 204 and the second blade body 205 are made of 6061-T6 aluminum alloy with a thickness of 2~4mm, tensile strength ≥290MPa, yield strength ≥240MPa, and length of 1 / 3~1 / 2 of the inner diameter of the gas cylinder body 1. When the inner diameter of the gas cylinder body 1 is 150mm~200mm, the length of the first blade body 204 and the second blade body 205 is preferably 50mm~80mm. The surfaces of the first blade body 204 and the second blade body 205 are electrolytically polished with a roughness of no more than 0.8μm to reduce the frictional heat generated by the airflow and the blade.

[0059] This application uses a segmented injection molding process to manufacture the PA6 inner liner 103. The mold is made of mold steel and is precision polished. It is equipped with a high-precision temperature control system to ensure the surface quality of the inner liner 103. During the injection molding process, the melt temperature, injection pressure and holding pressure parameters are strictly controlled. A stop positioning structure is designed on the mating surface to provide a reference for subsequent welding.

[0060] The turbulence component 2 is connected to the valve seat 102 through a pre-assembly process. The valve seat 102 is pre-processed with a high-precision slot. The turbulence component 2 is embedded with an interference fit and then welded in sections by argon arc welding. Tooling is used to ensure verticality. After welding, a coordinate measuring machine is used to check the symmetry and position deviation to ensure assembly accuracy.

[0061] The bidirectional guiding design of the first blade body 204 and the second blade body 205 on the turbulence component 2 ensures that the circumferential diffusion deviation of the airflow is no more than 5%, the turbulence intensity is reduced from 18% of the traditional structure to below 11%, and the vortex region volume is reduced by 65%. Under the conditions of 70MPa inflation pressure and 5kg / min inflation flow rate, computational fluid dynamics (CFD) fluid simulation shows that the traditional gas cylinder exhibits axial concentrated jet flow, and a local high-temperature region appears on the gas cylinder body 1 at the tail end, such as... Figure 5 As shown in the simulation cloud map, during the filling of a conventional gas cylinder without turbulence, the temperature distribution of the inlet side and the axial concentrated jet area is significantly increased due to the lack of turbulent airflow guidance. A distinct localized high-temperature region appears at the end of the cylinder body 1. It should be noted that this localized high-temperature region B is a localized high temperature appearing on the inner liner 103 of the cylinder body 1, not the high-temperature region displayed by the high-pressure gas inside the cylinder body 1.

[0062] The carbon fiber fully wound pressure vessel of this application, through a bidirectional circumferential diffusion flow field, reduces the average temperature rise of the entire cylinder from 65℃ to 45℃, a reduction of 30.8%, and the highest temperature at the end of cylinder body 1 from 95℃ to 72℃, a reduction of 24.2%. Figure 6 The simulated temperature rise cloud map of the carbon fiber fully wound pressure vessel shows the "two-way guiding-circumferential diffusion" effect of the turbulence component 2 on the airflow, making the temperature distribution more uniform in the circumferential and axial directions within the cylinder, significantly reducing the high-temperature concentration areas, and intuitively demonstrating the temperature rise control effect. Moreover, the temperature is uniform on the cylinder body 1, with no localized high-temperature areas.

[0063] In addition, such as Figure 7 As shown in the figure, the temperature rise curves during the filling process reveal that the black curve represents the temperature rise of a conventional gas cylinder, while the red curve represents the temperature rise of the carbon fiber fully wound pressure vessel of this application. The temperature rise at the inlet and end of the carbon fiber fully wound pressure vessel of this application tends to stabilize at the end of filling, and the temperature remains lower than that of a conventional gas cylinder throughout the entire process.

[0064] Although embodiments of the invention have been described in conjunction with the accompanying drawings, those skilled in the art can make various modifications and variations without departing from the spirit and scope of the invention, and all such modifications and variations fall within the scope defined by the appended claims.

Claims

1. A carbon fiber fully wound pressure vessel, characterized in that, include: The gas cylinder body (1) has an air inlet (101) at one end along the axial direction and a closed end at the other end. The air inlet (101) is connected to the inner cavity of the gas cylinder body (1). A flow-deflecting assembly (2) is fixedly installed in the inner cavity of the gas cylinder body (1). The flow-deflecting assembly (2) includes a first flow-deflecting blade group and a second flow-deflecting blade group. Along the axial direction of the gas cylinder body (1), the first flow-deflecting blade group and the second flow-deflecting blade group are arranged alternately. Along the circumference of the gas cylinder body (1), the first flow-deflecting blade group includes a plurality of first blade bodies (204), and the second flow-deflecting blade group includes a plurality of second blade bodies (205). The first blade bodies (204) and the second blade bodies (205) are both arranged at an inclination relative to the axis of the gas cylinder body (1), and the inclination directions of the first blade bodies (204) and the second blade bodies (205) are opposite.

2. The carbon fiber fully wound pressure vessel according to claim 1, characterized in that, The turbulence component (2) further includes: Mounting component (201) is fixedly installed in the inner cavity of the gas cylinder body (1) along the axial direction of the gas cylinder body (1); The first connector (202) is fixedly installed on the mounting member (201) and extends circumferentially along the gas cylinder body (1). The first blade body (204) is fixedly installed at the end of the first connector (202) away from the mounting member (201). The second connector (203) is fixedly installed on the mounting member (201) and extends circumferentially along the gas cylinder body (1). The second blade body (205) is fixedly installed at the end of the second connector (203) away from the mounting member (201).

3. The carbon fiber fully wound pressure vessel according to claim 2, characterized in that, Along the circumference of the gas cylinder body (1), the length of the first connector (202) is less than the length of the second connector (203) or the length of the second connector (203) is less than the length of the first connector (202).

4. The carbon fiber fully wound pressure vessel according to claim 2 or 3, characterized in that, The mounting component (201) is a connecting shaft (2011), which is coaxially arranged with the inner cavity of the gas cylinder body (1). The first connecting component (202) and the second connecting component (203) both extend outward from the center of the gas cylinder body (1).

5. The carbon fiber fully wound pressure vessel according to claim 4, characterized in that, A third blade body (2012) is provided on the connecting shaft (2011), and the third blade body (2012) is inclined toward the side away from the air inlet (101).

6. The carbon fiber fully wound pressure vessel according to any one of claims 1 to 3, characterized in that, The first blade body (204) is inclined toward the air inlet (101), and the second blade body (205) is inclined away from the air inlet (101). The angle between the first blade body (204) and the axis of the gas cylinder body (1) and the angle between the second blade body (205) and the axis of the gas cylinder body (1) are equal in value and opposite in direction.

7. The carbon fiber fully wound pressure vessel according to claim 6, characterized in that, The angle between the axis of the first blade body (204) and the axis of the gas cylinder body (1) is 60°.

8. The carbon fiber fully wound pressure vessel according to any one of claims 1 to 3, characterized in that, The first blade body (204) and / or the second blade body (205) are flat plates or curved plates.

9. The carbon fiber fully wound pressure vessel according to any one of claims 1 to 3, characterized in that, The length of the first blade body (204) and / or the second blade body (205) is 1 / 3 to 1 / 2 of the inner diameter of the gas cylinder body (1).

10. The carbon fiber fully wound pressure vessel according to any one of claims 1 to 3, characterized in that, Along the circumference of the gas cylinder body (1), a flow passage is reserved between the first blade body (204) and the second blade body (205).

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