A flame-retardant wind turbine nacelle cover that is easy to seal and assemble

Abstract

The present invention discloses a flame-retardant wind turbine nacelle cover that is easy to seal and assemble, belonging to the technical field of wind turbines, and includes a nacelle cover body containing flame-retardant materials and a stabilizing plate arranged at the vertical opening of the nacelle cover body, wherein the stabilizing plate of the annular structure is installed at the vertical opening of the nacelle cover body through elastic sliding to buffer the installation of the main shaft of the unit, and the opening structure is covered with an elastically deformable sealing layer, and the gap between the main shaft bearing seat and the nacelle cover body is sealed and protected by the expansion of the sealing layer, and the expansion mechanism arranged in the sealing ring guides the deformation of the sealing layer through the movement of the stabilizing plate. The flame-retardant wind turbine nacelle cover that is easy to seal and assemble redesigns the structure inside and outside the cabin and at the connection point, which can not only perform auxiliary assembly and sealing operations on the connection, but also utilize the characteristics of the high-altitude use environment of the nacelle cover to promote the circulation of airflow in the cabin and sufficient heat exchange through high-altitude airflow.

Description

Technical Field

[0001] The present invention relates to the technical field of wind turbines, and in particular to a nacelle structure of a wind turbine, and in particular to a flame-retardant nacelle cover of a wind turbine that is easy to seal and assemble. Background Art

[0002] The main structure of the wind power generation equipment is composed of the control equipment at the bottom of the tower, the wind turbine blades, the main shaft and gear set and the generator equipment at the top of the tower. The tower body of the wind turbine generator is used to install the control equipment, etc., and the top of the tower body is used to install the wind turbine blade main shaft and gears, etc., and the nacelle cover is used to seal and protect the main shaft, gear set and generator from the outside. For example, the prior art has a nacelle cover for a wind turbine set with the announcement number CN106351805B, which includes a nacelle cover body, and one or more front wind-catching holes are provided on the side wall of one end of the nacelle cover body close to the wind rotor blade group. The front wind-catching holes are all arranged toward the wind rotor blade group to capture the airflow generated when the wind rotor blade group is in operation. A matching front wind-guiding filter interlayer is provided on the inner wall of the nacelle cover body at the front wind-catching hole. The airflow captured by the front wind-catching hole enters the front wind-guiding filter interlayer for filtration and is then guided to the wind turbine set equipment in the nacelle for heat dissipation. The invention has the advantages of reasonable design, good heat dissipation effect, dust and rainproof, high strength and more environmentally friendly.

[0003] Another example is a modular wind turbine nacelle cover with publication number CN116464611A, which belongs to the technical field of wind turbines. It includes a front end, a middle end and a rear end. The two ends of the middle end are respectively connected to the front end and the rear end. The middle end includes a top cover, a bottom plate, a connecting mechanism and a plurality of side plates. The plurality of side plates are divided into two groups and are respectively located on both sides of the bottom plate. The side plates are arranged along the length direction of the top cover. The side plates are located between the bottom plate and the top cover. The two ends of the side plates are respectively connected to the bottom plate and the top cover through a connecting mechanism. The two adjacent side plates are connected through a connecting mechanism. This application has the effect of facilitating the transportation of the nacelle cover, improving the utilization rate of the mold used to make the nacelle cover, and improving the work efficiency of producing the nacelle cover.

[0004] This type of prior art generally uses built-in refrigeration or air flow equipment to enable the nacelle cover to have the function of dissipating heat and cooling the gear group and generator of the wind turbine set. However, due to the unreasonable design of the sealing technology, the assembly between the nacelle cover and the main shaft bearing seat is prone to incomplete sealing to varying degrees. Although it will not have a significant impact on the safety of the equipment, it is easy for external rain, snow or dust to enter the interior of the nacelle cover through the unsealed area, causing the corrosion and aging of the components in the nacelle cover to accelerate. Summary of the invention

[0005] The object of the present invention is to provide a flame-retardant wind turbine nacelle cover which is easy to seal and assemble, so as to solve the problem raised in the above background technology that due to the unreasonable design of the sealing technology, the assembly point between the nacelle cover and the main shaft bearing seat is prone to incomplete sealing to varying degrees. Although it will not have a significant impact on the safety of the equipment, it is easy for external rain, snow or dust to enter the interior of the nacelle cover through the unsealed area, resulting in accelerated corrosion and aging of the components in the nacelle cover.

[0006] To achieve the above-mentioned purpose, the present invention provides the following technical solutions: a flame-retardant wind turbine nacelle cover that is easy to seal and assemble, comprising a nacelle cover body containing flame-retardant material and a stabilizing plate arranged at the opening of the vertical surface of the nacelle cover body, wherein the stabilizing plate of an annular structure is installed at the opening of the vertical surface of the nacelle cover body by elastic sliding to buffer the installation of the main shaft of the unit, a sealing ring is fixed to the inner wall of the opening position of the nacelle cover body, wherein the annular inner wall of the sealing ring is an open structure, and the opening structure is covered with an elastically deformable sealing layer, and the sealing layer is connected to an expansion mechanism, and the gap between the main shaft bearing seat and the nacelle cover body is sealed and protected by the expansion of the sealing layer, and the expansion mechanism arranged in the sealing ring guides the deformation of the sealing layer through the movement of the stabilizing plate.

[0007] Preferably, the expansion mechanism comprises a plate body with the same annular structure and the left side of which is sealed and fixed on the left inner wall of the sealing ring, and a ring body horizontally slidably installed in the sealing ring is arranged above the plate body;

[0008] Preferably, the right side space of the ring body is connected to the space where the sealing layer is located through the right side gap of the plate body, and the left side space of the ring body is a non-sealed space.

[0009] Preferably, a slide bar is installed on the left side surface of the ring body, and the left end of the slide bar slides through the sealing ring and the cabin cover and is fixed to the inner wall of the stabilizing plate.

[0010] Preferably, a fan blade is installed at the inner wall of the cabin cover, wherein the fan blade is connected to a driving mechanism provided in the cabin cover;

[0011] Preferably, the driving mechanism rotates the fan blades through the high air flow outside the nacelle cover to increase the air circulation in the nacelle cover.

[0012] Preferably, the driving mechanism includes a blade and a rotating shaft for connecting the blade and the fan blade, the blade is located in a mesh box fixed on the outside of the cabin cover, and the middle section of the horizontally distributed rotating shaft is rotatably mounted on the side wall of the cabin cover.

[0013] Preferably, a pipeline group is provided in the cabin cover, wherein the pipeline group is connected with a circulation mechanism so that the cooling medium in the pipeline circulates;

[0014] Preferably, the pipe group includes an inner pipe and an outer pipe, wherein the inner pipe is located at the bottom end of the interior of the cabin and is distributed in a winding state, and the outer pipe is also distributed in a winding state between the blades and the cabin cover.

[0015] Preferably, the input end of the inner tube is connected to the output end of the outer tube, wherein the input end of the inner tube is connected in the box body, and the input end of the outer tube is also connected in the box body.

[0016] Preferably, the circulation mechanism comprises a box body and a turbine arranged in the box body;

[0017] Preferably, the turbine is fixed on the rotating shaft, wherein the turbine forms a fluid conveying space in the box body, and the output end and the input end of the space are respectively connected to the inner tube and the outer tube.

[0018] Preferably, the circulation mechanism comprises a pressing plate located on the side of the outer tube, and the pressing plate is fixed on the bracket;

[0019] Preferably, the left and right sides of the bracket are slidably connected to the rod structure protruding from the outer surface of the cabin cover, and the axis position of the bracket is penetrated and threadedly connected by the middle section with bidirectional threads on the surface of the shaft.

[0020] Preferably, one-way valves are provided in both the inner tube and the outer tube.

[0021] Compared with the prior art, the beneficial effects of the present invention are as follows: the flame-retardant wind turbine nacelle cover which is easy to seal and assemble redesigns the structures inside and outside the nacelle and at the connection points, which can not only perform auxiliary assembly and sealing operations on the connection points, but also utilize the characteristics of the high-altitude use environment of the nacelle cover to promote the circulation of airflow in the nacelle and sufficient heat exchange through high-altitude airflow, as shown in the following content:

[0022] 1. The structural design of the stabilizing plate and the sealing layer can be assembled during the spindle bearing seat or the spindle installation process, and the movement of the stabilizing plate can make the ring body slide synchronously in the sealing ring through the movement of the stabilizing plate, thereby generating internal pressure changes to guide the deformation of the sealing layer to seal the assembly gap, and also facilitate secondary adjustments during subsequent maintenance;

[0023] 2. The use of propeller blades in conjunction with fan blades can utilize the air flow characteristics of the high altitude position of the cabin cover and the external airflow power to drive the internal fan blades to rotate, thereby ensuring that the air circulation inside the cabin is increased without using other electronic control equipment and without direct connection between the inside and outside of the cabin;

[0024] Furthermore, the pipe group composed of the inner pipe and the outer pipe can cooperate with the use of the circulation mechanism to effectively assist in adjusting the operating temperature of the unit in the cabin. At the same time, the circulation mechanism is used to realize automatic air cooling of the cooling medium in the pipe group, which is more energy-saving and environmentally friendly. The energy-saving effect is better when the circulation mechanism is linked with the rotation of the blades, that is, the rotation of the shaft.

[0025] Furthermore, the use of the circulation mechanism composed of the bracket and the pressure plate can not only utilize the rotation of the rotating shaft to drive the pressure plate to circulate and compress the outer tube to cause deformation and realize the circulation flow of the cooling medium, but also can improve the heat exchange effect through the deformation of the pipe by combining the turbine structure and utilizing the pressure plate to squeeze the pipe, thereby further improving the cooling effect in the cabin cover. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 This is a schematic diagram of the overall structure of Embodiment 1 of the present invention;

[0027] Figure 2 This is a schematic diagram of the sealing ring structure of the present invention;

[0028] Figure 3 This is a schematic diagram of the structure of the stabilizing plate of the present invention;

[0029] Figure 4 This is a schematic diagram of the internal structure of the sealing ring of the present invention;

[0030] Figure 5 This is a schematic diagram of the external structure of the second embodiment of the present invention;

[0031] Figure 6 For the present invention Figure 5 Schematic diagram of the internal structure of the cabin cover;

[0032] Figure 7 It is a schematic diagram of the box body connection structure of the present invention;

[0033] Figure 8 This is a schematic diagram of the distribution structure of the pipeline group of the present invention;

[0034] Fig. 9 This is a schematic diagram of the external structure of the third embodiment of the present invention;

[0035] Fig.10 For the present invention Fig. 9 Schematic diagram of the pipeline group connection structure in .

[0036] In the figure: 1. cabin cover; 2. stabilizing plate; 3. sealing ring; 4. sealing layer; 5. sliding rod; 6. ring body; 7. plate body; 8. blades; 9. mesh box; 10. rotating shaft; 11. fan blades; 12. inner tube; 13. outer tube; 14. box body; 15. turbine; 16. pressure plate; 17. bracket. DETAILED DESCRIPTION

[0037] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0038] See also Figure 1-Figure 10 , the present invention provides the following technical solutions:

[0039] Embodiment 1: The existence of this solution is mainly to solve the problem that there is a gap between the main shaft bearing seat and the nacelle cover due to construction in the prior art. The solution is not the rubber strips existing in the prior art, but Figure 1-Figure 4The scheme shown in the figure comprises a cabin cover 1 containing a flame retardant material and a stabilizing plate 2 arranged at the vertical opening of the cabin cover 1, wherein the annular stabilizing plate 2 is elastically slidably installed at the vertical opening of the cabin cover 1 to buffer the installation of the unit main shaft, and a sealing ring 3 is fixed to the inner wall of the opening position of the cabin cover 1, wherein the annular inner wall of the sealing ring 3 is an open structure, and the opening structure is covered with an elastically deformable sealing layer 4, and the sealing layer 4 is connected to the expansion mechanism, and the expansion of the sealing layer 4 is used to expand the gap between the main shaft bearing seat and the cabin cover 1. The sealing protection is performed at the gap, and the expansion mechanism arranged in the sealing ring 3 guides the deformation of the sealing layer 4 by moving the stabilizing plate 2. The expansion mechanism includes a plate body 7 with the same annular structure and the left side is sealed and fixed on the left inner wall of the sealing ring 3. A ring body 6 horizontally slidably installed in the sealing ring 3 is arranged above the plate body 7. The right side space of the ring body 6 is connected with the space where the sealing layer 4 is located through the right side gap of the plate body 7, and the left side space of the ring body 6 is a non-sealed space. A sliding rod 5 is installed on the left side of the ring body 6. The left end of the sliding rod 5 slides through the sealing The ring 3 and the cabin cover 1 are fixed to the inner wall of the stabilizing plate 2. In the present embodiment, the stabilizing plate 2 and the cabin cover 1 are connected in a single sliding connection. In this connection mode, the stabilizing plate 2 will be squeezed and contacted with the main shaft component during the main shaft assembly process. Therefore, the stabilizing plate 2 will correspondingly drive the slide rod 5 to move in the direction close to the cabin cover 1, so the ring body 6 will also move synchronously. At this time, the right side space of the ring body 6 is compressed. When the pressure increases, the sealing layer 4 will also deform synchronously, and in this way, the areas where the bearing seat or other components are prone to gaps are squeezed and fitted. The difference from the prior art is mainly because this scheme can not only perform sealing assembly in the above manner, but also use another connection method to further seal the gaps in daily maintenance. For example, a screw is set at the edge of the inner wall of the stabilizing plate 2, and the screw is passed through the side wall of the cabin cover 1 and fastened with a nut. When the sealing layer 4 ages during daily maintenance, it can be further sealed by further tightening the nut. The position of the stabilizing plate 2 can also be adjusted by the nut screw to adapt to thermal expansion and contraction.

[0040] Embodiment 2: In order to avoid fire in the cabin caused by aging of circuits or short circuit of electronic control components, flame retardant materials are added to the plate materials of the cabin cover in the prior art. Although the flame retardant performance is better, the thermal conductivity and cooling performance of the cabin itself will be reduced accordingly. Although the cabin itself is located at a high altitude, the internal air circulation is poor due to the isolation of the cabin board. Directly using electrical equipment such as fans will not only increase the power consumption of the equipment, but also increase the temperature in the cabin due to the increase of electronic control equipment. Therefore, in order to solve this problem, the following contents are disclosed in this solution, specifically as follows: Figure 5-Figure 6As shown, a fan blade 11 is installed on the inner wall of the cabin cover 1, wherein the fan blade 11 is connected to a driving mechanism arranged in the cabin cover 1, and the driving mechanism rotates the fan blade 11 through the high-altitude airflow outside the cabin cover to increase the air circulation in the cabin cover 1, and the driving mechanism includes a blade 8 and a rotating shaft 10 for connecting the blade 8 and the fan blade 11, the blade 8 is located in a net box 9 fixed on the outside of the cabin cover 1, and the middle section of the horizontally distributed rotating shaft 10 is rotatably installed on the side wall of the cabin cover 1. At high altitudes, the wind force is generally large and the direction is changeable, so the blade 8 is designed on the outside of the cabin cover, and the airflow drives the rotating shaft 10 to rotate through the blade 8, and the fan blade 11 inside the cabin cover is in a rotating state through the rotating shaft 10, thereby achieving the purpose of increasing the airflow circulation effect inside the cabin cover by using the external airflow when the inside and outside of the cabin cover are not connected, which is more energy-saving and environmentally friendly, and will not destroy the flame retardant properties and structural strength of the cabin made of flame retardant materials.

[0041] In this embodiment, in order to further enhance the cooling effect in the nacelle cover and ensure that there is no need to use a refrigerator to perform secondary cooling on the cooling medium such as water-borne insulating oil, the following scheme is also disclosed, which also uses high-altitude airflow for cooling. For details, please refer to Figure 5-Figure 8 A pipeline group is arranged in the cabin cover 1, wherein the pipeline group is connected with the circulation mechanism to circulate the cooling medium in the pipeline, wherein the pipeline group includes an inner pipe 12 and an outer pipe 13, wherein the inner pipe 12 is located at the bottom end of the interior of the cabin and is distributed in a winding manner, and the outer pipe 13 is also distributed in a winding state between the blade 8 and the cabin cover 1, the input end of the inner pipe 12 is connected to the output end of the outer pipe 13, wherein the input end of the inner pipe 12 is connected to the box body 14, and the input end of the outer pipe 13 is also connected to the box body 14, the circulation mechanism includes the box body 14 and a turbine 15 arranged in the box body 14, wherein the turbine 15 is fixed on the rotating shaft 10, wherein the turbine 15 makes the box body 14 A fluid conveying space is formed, and the output end and the input end of the space are respectively connected to the inner tube 12 and the outer tube 13. During the rotation of the rotating shaft 10, it will not only drive the fan blades 11 to rotate to enhance the air flow, but also drive the turbine 15 to rotate synchronously. Therefore, the fluid conveying effect generated during the rotation of the turbine 15 will be that the cooling medium flows along the box body 14, the inner tube 12, the outer tube 13 and then returns to the box body 14. When the medium flows in the inner tube 12, it will fully absorb the temperature in the cabin, and after entering the outer tube 13, it will efficiently exchange heat due to the high air flow, so it can cool the cooling medium that has absorbed heat, which is more energy-saving and environmentally friendly.

[0042] Embodiment 3: This scheme discloses another circulation mechanism, which includes a pressure plate 16 located on the side of the outer tube 13, and the pressure plate 16 is fixed on a bracket 17. The left and right sides of the bracket 17 are slidably connected to the rod structure protruding from the outer surface of the cabin cover 1, and the axial position of the bracket 17 is penetrated and threadedly connected by the middle section of the rotating shaft 10 with a two-way thread on the surface. Both the inner tube 12 and the outer tube 13 are provided with a one-way valve. The original design of the circulation mechanism has two usage modes. The first mode is not coexisting with the above-mentioned circulation mechanism, and the box body 14 structure is only used as a cooling medium. The transfer and accommodation facility is a transfer and accommodation facility. When the rotating shaft 10 is in a rotating state, the bidirectional threaded section on its surface will drive the bracket 17 to move back and forth along the axial direction of the rotating shaft 10. Therefore, during the movement, the pressing plate 16 will repeatedly squeeze and relax the outer tube 13. During this process, the outer tube 13 made of elastic material will deform back and forth. Since the inner and outer pipes are both provided with one-way flow limiting valves, when the outer tube 13 is squeezed, the liquid will flow in the direction of entering the box body 14. When the outer tube 13 recovers its deformation, the cooling medium will be drawn out of the box body 14, thereby realizing the circulation of the cooling medium.

[0043] Another way is to use it in conjunction with the turbine 15. The one-way valve structure can be retained or removed. In this way, the turbine 15 is still used to achieve the circulation and transportation effect. Therefore, when the pressure plate 16 squeezes the outer tube 13, the inner tube 12 will expand due to the increased pressure. Therefore, unlike the unilateral deformation of the outer tube 13 in the above-mentioned solution, the expansion of the inner tube 12 will increase the contact area between the fluid and the internal space of the cabin, and the outer tube 13 will also increase the heat exchange area due to flattening, thereby significantly improving the circulation and cooling effects.

[0044] Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions and variations may be made to the embodiments without departing from the principles and spirit of the present invention, and that the scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A flame-retardant wind turbine nacelle that is easy to seal and assemble, comprising a nacelle cover body (1) containing flame-retardant material and a stabilizing plate (2) arranged at an opening of a vertical surface of the nacelle cover body (1), wherein the stabilizing plate (2) of an annular structure is installed at the opening of the vertical surface of the nacelle cover body (1) by elastic sliding to provide a buffer for the installation of the main shaft of the unit, and the characteristics are: A sealing ring (3) is fixed to the inner wall of the opening position of the nacelle cover (1), wherein the annular inner wall of the sealing ring (3) is an open structure, and the opening structure is covered with an elastically deformable sealing layer (4), and the sealing layer (4) is connected to an expansion mechanism, and the gap between the main shaft bearing seat and the nacelle cover (1) is sealed and protected by the expansion of the sealing layer (4), and the expansion mechanism arranged in the sealing ring (3) guides the deformation of the sealing layer (4) by moving the stabilizing plate (2); The expansion mechanism comprises a plate body (7) having an annular structure and the left side of which is sealed and fixed on the left inner wall of the sealing ring (3); a ring body (6) is arranged above the plate body (7) and is horizontally slidably mounted in the sealing ring (3); the right side space of the ring body (6) is connected to the space where the sealing layer (4) is located through the right side gap of the plate body (7); and the left side space of the ring body (6) is a non-sealed space; A slide bar (5) is installed on the left side surface of the ring body (6), and the left end of the slide bar (5) slides through the sealing ring (3) and the cabin cover (1) and is fixed to the inner wall of the stabilizing plate (2); The inner wall of the cabin cover (1) is provided with a fan blade (11), wherein the fan blade (11) is connected to a driving mechanism provided in the cabin cover (1), and the driving mechanism rotates the fan blade (11) through high air flow outside the cabin cover, thereby increasing air circulation in the cabin cover (1); The driving mechanism comprises a paddle (8) and a rotating shaft (10) for connecting the paddle (8) and a fan blade (11); the paddle (8) is located in a net box (9) fixed outside the cabin cover (1), and the middle section of the horizontally distributed rotating shaft (10) is rotatably mounted on the side wall of the cabin cover (1).

2. The flame-retardant wind turbine nacelle cover that is easy to seal and assemble according to claim 1, characterized in that: The cabin cover (1) is provided with a pipeline group, wherein the pipeline group is connected to a circulation mechanism so that a cooling medium in the pipeline circulates, wherein the pipeline group comprises an inner pipe (12) and an outer pipe (13), wherein the inner pipe (12) is located at the bottom end of the cabin and is distributed in a winding manner, and the outer pipe (13) is also distributed in a winding state at a position between the blade (8) and the cabin cover (1).

3. The flame-retardant wind turbine nacelle cover that is easy to seal and assemble according to claim 2, characterized in that: The input end of the inner tube (12) and the output end of the outer tube (13) are connected, wherein the input end of the inner tube (12) is connected in the box body (14), and the input end of the outer tube (13) is also connected in the box body (14).

4. The flame-retardant wind turbine nacelle cover that is easy to seal and assemble according to claim 3 is characterized in that: The circulation mechanism comprises a box body (14) and a turbine (15) arranged in the box body (14), wherein the turbine (15) is fixed on the rotating shaft (10), wherein the turbine (15) forms a fluid conveying space in the box body (14), and the output end and the input end of the space are respectively connected to the inner tube (12) and the outer tube (13).

5. The flame-retardant wind turbine nacelle cover that is easy to seal and assemble according to claim 4, characterized in that: The circulation mechanism comprises a pressure plate (16) located on the side of the outer tube (13), and the pressure plate (16) is fixed on a bracket (17). The left and right sides of the bracket (17) are slidably connected to a rod structure protruding from the outer surface of the cabin cover (1), and the axis position of the bracket (17) is penetrated by a middle section with a bidirectional thread on the surface of the rotating shaft (10) and is threadedly connected.

6. The flame-retardant wind turbine nacelle cover that is easy to seal and assemble according to claim 5, characterized in that: Both the inner tube (12) and the outer tube (13) are provided with a one-way valve.

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