Wind tunnel test device based on Magnus effect

Abstract

The invention discloses a wind tunnel experiment device, and particularly relates to the field of a rotor sail device utilizing the Magnus effect and a ship using the device, and the device comprises a driving measurement part, a supporting base, a rotor base, a supporting rod and a rotor. The supporting base and the rotor base are concentrically installed on the test ground, the lower end of the supporting rod penetrates through the rotor base to be connected with the supporting base, and the driving measuring component is installed at the upper end of the supporting rod and connected with the interior of the rotor. When the driving measurement component drives, the driving measurement component drives the rotor to rotate, and when the rotating rotor is subjected to the effect of wind in the incoming flow direction, lateral lift force perpendicular to the incoming flow direction can be generated. When the device is used for testing, rotors at multiple positions can be arranged, Magnus effect experiments of a plurality of independent rotor systems can be carried out at the same time, and aerodynamic characteristics under interference among the rotors can be researched. The supporting structures are all built-in, so that the interference of supporting pieces on a pneumatic flow field is greatly reduced, and the measurement precision is high.

Description

Technical Field

[0001] The present invention relates to the technical fields of new transport ships and fluid mechanics wind tunnel tests, and in particular to a wind tunnel test device based on the Magnus effect. Background Art

[0002] With increasing global attention to energy efficiency and environmental protection, the shipping industry is constantly seeking ways to reduce fuel consumption and lower emissions. The Magnus effect offers the possibility of harnessing wind power to propel ships, helping to reduce dependence on traditional fossil fuels and lower greenhouse gas emissions.

[0003] The application of the Magnus effect can reduce fuel consumption and operating costs for ships. By installing a cylinder on a ship and driving it to rotate in the wind, a force perpendicular to the wind speed is generated, providing propulsion for the ship, thereby reducing engine load and fuel consumption. Furthermore, the Magnus effect can be used not only for propulsion but also for ship roll reduction. Magnus effect-based roll reduction systems exhibit a better range of swing speeds, and their performance improves with increasing swing angle, providing new research directions for ship seakeeping strategies.

[0004] Currently, when conducting wind tunnel tests based on the Magnus effect, measurement results are often affected by auxiliary support devices, and the size of the test model itself is also limited. Therefore, the present invention adopts relevant structural measures to minimize the influence of these factors. Summary of the Invention

[0005] The purpose of this patented invention is to design a wind tunnel test device based on the Magnus effect.

[0006] The technical solution of a wind tunnel test device based on the Magnus effect of the present invention is as follows:

[0007] A wind tunnel test device based on the Magnus effect comprises a drive and measurement component, a support base, a rotor base, a support rod, a rotor and a multi-rod support component; the support base and the rotor base are concentrically installed on a test ground, the lower end of the support rod passes through the rotor base and is connected to the support base, the upper end of the support rod is installed with a drive and measurement component, and the drive and measurement component is connected to the inside of the rotor through the multi-rod support component, which is used to reduce radial runout interference and interference of uneven aerodynamic force of external wind load and the influence of installation error on motion stability; a gap is left between the support base and the rotor to prevent the rotor from contacting the support base due to vibration; when the drive and measurement component is driven, the drive and measurement component drives the multi-rod support component to rotate, and then the multi-rod support component drives the rotor to rotate, and when the rotating rotor is affected by wind in the incoming flow direction, the Magnus effect causes the rotor to be subjected to a force perpendicular to the incoming flow direction.

[0008] Furthermore, the driving and measuring components are arranged inside the rotor, so that the device does not require external auxiliary support, thereby avoiding the auxiliary support generating turbulence in the aerodynamic flow field, thereby preventing interference with the test results of the aerodynamic flow field of the test model.

[0009] Furthermore, the drive measurement component includes a force balance, a drive motor and a rotating shaft bracket; the force balance is installed at the upper end of the support rod, the drive motor is installed at the upper end of the force balance, and the rotating shaft bracket is installed at the upper end of the drive motor and fixed to the outer casing of the drive motor, so that the aerodynamic force applied to the test model directly acts on the outer casing of the drive motor, thereby reducing the radial runout of the output shaft of the drive motor.

[0010] Furthermore, the multi-rod support component includes an outer hole-connecting end, a support rod and a support main shaft; the lower part of the hole-connecting end is connected to the upper surface of the rotating shaft bracket, and the hole-connecting end is circumferentially connected to the inner wall of the rotor, and the lower end of the support main shaft is inserted from the hole-connecting end into the interior of the rotating shaft bracket and connected to the output shaft of the driving motor, so that the output shaft of the driving motor can drive the support main shaft to rotate, and the support main shaft is rotatably connected to the rotating shaft bracket through a bearing; when the driving motor is driven, the support main shaft rotates, and the bearing supports the support main shaft without affecting the rotation of the support main shaft; a plurality of outer support rods are provided around the support main shaft on the upper surface of the hole-connecting end, and the plurality of outer support rods are all connected to the inside of the rotor, forming a frame structure of a multi-rod support.

[0011] Furthermore, the driving shaft of the driving motor is connected to the supporting main shaft via a coupling, and an elastic element is provided in the coupling for compensating for radial runout of the driving shaft of the driving motor.

[0012] Furthermore, the force balance is detachably installed and can be replaced according to measurement requirements.

[0013] Furthermore, a limiting component for limiting the axial displacement of the supporting spindle is provided below the bearing.

[0014] Furthermore, the top end of the rotor is connected to an end plate, and the inner wall of the end plate is connected to the upper end of the supporting main shaft.

[0015] Furthermore, the device supports multiple groups arranged in parallel, each group equipped with an independent force balance and data acquisition system for studying the aerodynamic interference effect of multiple rotors.

[0016] The beneficial effects of the present invention are:

[0017] Compared with the traditional Magnus effect wind tunnel test device, the present invention does not require external auxiliary supports, avoiding the interference of turbulence generated by the external support structure on the aerodynamic flow field in the traditional wind tunnel test, ensuring that the test data is closer to the actual working conditions; at the same time, it adopts a multi-support rod frame structure, which can effectively resist wind load unevenness and installation errors; through the connection between the rotating shaft bracket and the motor housing, etc., the radial runout is effectively reduced, thereby ensuring that the device can still maintain stable operation during high-speed rotation; because the device occupies a small area, it is convenient to carry out multiple sets of rotating drum interference tests when actually conducting tests, with high flexibility and overall broad application prospects. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is a structural perspective view of the device of the present invention.

[0019] Figure 2 This is a front view of the device of the present invention without the rotor base and the rotor.

[0020] Figure 3 This is a structural disassembly diagram of a single group of the device of the present invention.

[0021] Figure 4 It is a cross-sectional view of the drive shaft and the rotating shaft bracket in the device of the present invention.

[0022] Figure 5 This is a schematic diagram of the arrangement of two groups of devices of the present invention.

[0023] Figure 6 This is a schematic diagram of the device of the present invention being subjected to wind from the incoming direction during the test. DETAILED DESCRIPTION

[0024] The following is combined with Figures 1 to 6 The present invention is further described.

[0025] The purpose of the present invention is to design a wind tunnel test device based on the Magnus effect that has good stability, accuracy, ease of operation and good layout performance under high speed conditions.

[0026] refer to Figure 1 and 3, a wind tunnel test device based on the Magnus effect, comprising a driving and measuring component, a supporting base 1, a rotor base 2, a support rod 3, a rotor 5 and a multi-rod supporting component; the supporting base 1 and the rotor base 2 are concentrically installed on the test ground, the lower end of the support rod 3 passes through the rotor base 2 and is connected to the supporting base 1, the upper end of the support rod 3 is installed with a driving and measuring component, and the driving and measuring component is connected to the inside of the rotor 5 through a multi-rod supporting component, which is used to reduce radial runout interference and interference of uneven aerodynamic force of external wind load and the influence of installation error on motion stability; a gap is left between the supporting base 1 and the rotor 5 to prevent the rotor 5 from contacting the supporting base 1 due to vibration; when the driving and measuring component is driven, the driving and measuring component drives the multi-rod supporting component to rotate, and then the multi-rod supporting component drives the rotor 5 to rotate. When the rotating rotor 5 is affected by wind in the incoming flow direction, the Magnus effect causes the rotor 5 to be subjected to a force perpendicular to the incoming flow direction.

[0027] refer to Figure 1 The driving and measuring components are arranged inside the rotor 5, so that the device does not require external auxiliary support, thereby avoiding the auxiliary support generating turbulence in the aerodynamic flow field, thereby avoiding interference with the test results of the aerodynamic flow field of the test model.

[0028] refer to Figure 1 、 2 , 3 and 4, the driving and measuring components include a force balance 4, a driving motor 6 and a rotating shaft bracket 7; the force balance 4 is installed at the upper end of the support rod 3, the driving motor 6 is installed at the upper end of the force balance 4, and the rotating shaft bracket 7 is installed at the upper end of the driving motor 6 and fixed to the outer casing of the driving motor 6, so that the aerodynamic force applied to the test model directly acts on the outer casing of the driving motor 6, thereby reducing the radial runout of the output shaft of the driving motor 6.

[0029] refer to Figure 1 、 2 , 3 and 4, the multi-rod support component includes an outer holed connection end, a support rod 8 and a support main shaft 9; the lower part of the holed connection end is connected to the upper surface of the rotating shaft bracket 7, and the holed connection end is circumferentially connected to the inner wall of the rotor 5, and the lower end of the support main shaft 9 is inserted from the holed connection end into the interior of the rotating shaft bracket 7 and connected to the output shaft of the drive motor 6, so that the output shaft of the drive motor 6 can drive the support main shaft 9 to rotate, and the support main shaft 9 is rotatably connected to the rotating shaft bracket 7 through a bearing; when the drive motor 6 is driven, the support main shaft 9 rotates, and the bearing supports the support main shaft 9 without affecting the rotation of the support main shaft 9; a plurality of outer support rods 8 are provided around the support main shaft 9 on the upper surface of the holed connection end, and the plurality of outer support rods 8 are all connected to the inside of the rotor 5, forming a frame structure of multi-rod support.

[0030] refer to Figure 4The driving shaft of the driving motor 6 is connected to the supporting main shaft 9 through a coupling. An elastic element is provided in the coupling to compensate for the radial runout of the driving shaft of the driving motor 6.

[0031] refer to Figure 1 and 2 The force measuring balance 4 is detachably mounted and can be replaced according to measurement requirements.

[0032] refer to Figure 4 A limiting component for limiting the axial displacement of the supporting main shaft 9 is provided below the bearing.

[0033] refer to Figure 1 、 2 3. The top end of the rotor 5 is also connected to an end plate 10, and the inner wall of the end plate 10 is connected to the upper end of the supporting main shaft 9.

[0034] refer to Figure 4 ,The device supports multiple groups of parallel arrangements, each group is equipped with an independent force balance 4 and a data acquisition system for studying the ,aerodynamic interference effect of multiple rotors.

[0035] As attached Figure 1 A wind tunnel experimental device based on the Magnus effect includes a support base 1, a rotor base 2, a support rod 3, a force balance 4, a rotor 5, a drive motor 6, a rotating shaft bracket 7, an outer support rod 8, a support main shaft 9, and an end plate 10; wherein the support base 1 and the rotor base 2 are fixedly connected to the experimental ground; a certain gap is reserved between the rotor base 2 and the overall rotor system above, and the overall device system above is wrapped by the rotor 5, the support rod 3 passes through the bottom of the rotor base 2, and the top of the support rod 3 is respectively installed with a fixed force balance 4 and a drive motor 6 from bottom to top; the drive motor 6 is connected to the external rotor 5 through the rotating shaft bracket 7 with a flange, and the upper and lower connecting flanges adopt a multi-support rod frame structure, specifically, multiple outer support rods 8 and a support main shaft 9 are connected to the rotating drum through flanges to enhance the overall structural strength above the motor and ensure the stability of the device at high speed.

[0036] During the test, when current was supplied to the device, the drive motor 6 drove the shaft in the shaft bracket 7 to rotate and transmitted the torque to the upper frame structure, including the outer support rods 8 and the supporting main shaft 9, and drove the end plate 10 to rotate. After the target speed was reached, the wind tunnel was started to blow air. When the Magnus rotor system was acted upon by the force of the incoming wind 11, it would be subjected to a lateral lift perpendicular to the incoming direction. When the wind speed stabilized, this lift was measured by the force balance 4 and combined with the sensor and the measurement and control computer for analysis, thereby obtaining the aerodynamic characteristic curve of the Magnus rotor system under the action of the incoming wind.

[0037] As attached Figure 1The figure shows a perspective view of the structure of the present invention; a wind tunnel experimental device based on the Magnus effect, including: a support base 1, a rotor base 2, a support rod 3, a force measuring balance 4, a rotor 5, a drive motor 6, a rotating shaft bracket 7, an outer support rod 8, a support main shaft 9, and an end plate 10; wherein the frame structure for upper and lower connection includes multiple outer support rods 8 and a support main shaft 9.

[0038] As attached Figure 2 and attached Figure 3 As shown, the device of the present invention has a simple structure and has no additional external upper and lower auxiliary supports. The rotor system includes components such as a support base 1 and a rotor base 2. A certain gap is left between the rotor base 2 and the rotor 5 to prevent the rotor 5 from vibrating and contacting the rotor base 2 during the test, thereby affecting the test data; in addition, almost all the supporting and fixing devices of the device of the present invention are contained inside the rotor system model, which can avoid the interference of the aerodynamic flow field of the test model due to the use of external supports, and has high measurement accuracy; in addition, since the measuring and motion equipment are all centrally installed inside the model, the experimental device occupies a small space and has high flexibility. Balances of different sizes can be used and multiple sets of rotating drum interference experiments can be carried out. Overall, it has broad application prospects.

[0039] As attached Figure 4 As shown, the experimental invention adds a rotating shaft bracket to the driving shaft of the model, and the bracket is fixedly connected to the motor housing. Two single-row angular contact ball bearings 12 are installed between the supporting main shaft 9 and the rotating shaft bracket 7, which support the supporting main shaft 9 without affecting the rotation of the shaft; in addition, a spring retaining ring 14 is additionally installed under the single-row angular contact ball bearing 12 to prevent the supporting main shaft 9 from loosening and falling off; the fixed connection between the bracket and the motor housing allows the aerodynamic force exerted on the rotor model to directly act on the motor housing connected to the balance, thereby avoiding radial force on the motor output shaft 13, which also provides a guarantee for the stability of the device of the present invention at high speeds.

[0040] As attached Figure 5 As shown in the figure, when conducting multiple Magnus effect rotor wind tunnel model tests (two groups are used as an example in this figure), the rotor positions in the wind tunnel test section are arranged according to the wind tunnel measurement environment and conditions, as well as the measurement requirements. Each rotor set has its own independent sensor and data acquisition system, allowing it to independently collect data on the aerodynamic forces under the Magnus effect during the test. Due to the small footprint of this device, it is convenient to conduct multiple rotor interference tests in actual testing, providing high flexibility and broad application prospects.

[0041] The foregoing description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Those skilled in the art will readily appreciate that various modifications and variations of the present invention are possible. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of the present invention are intended to be within the scope of protection of the present invention.

Claims

1. A wind tunnel test device based on the Magnus effect, characterized by: It comprises a driving and measuring component, a supporting base (1), a rotor base (2), a support rod (3), a rotor (5) and a multi-rod supporting component; The support base (1) and the rotor base (2) are concentrically mounted on the test ground, the lower end of the support rod (3) passes through the rotor base (2) and is connected to the support base (1), the upper end of the support rod (3) is mounted with a drive measurement component, and the drive measurement component is connected to the inside of the rotor (5) via a multi-rod support component, so as to reduce the influence of radial runout interference and the interference of uneven aerodynamic force of external wind load and the influence of installation error on motion stability; A gap is left between the support base (1) and the rotor (5) to prevent the rotor (5) from contacting the support base (1) due to vibration; When the driving and measuring component is driven, the driving and measuring component drives the multi-rod support component to rotate, and then the multi-rod support component drives the rotor (5) to rotate. When the rotating rotor (5) is acted upon by wind in the incoming flow direction, the Magnus effect causes the rotor (5) to be subjected to a force perpendicular to the incoming flow direction.

2. The wind tunnel test device based on the Magnus effect according to claim 1, characterized in that: The driving and measuring component is arranged inside the rotor (5), so that the device does not need external auxiliary support, thereby avoiding the auxiliary support generating turbulence in the aerodynamic flow field, thereby preventing interference with the test results of the aerodynamic flow field of the test model.

3. The wind tunnel test device based on the Magnus effect according to claim 2, characterized in that: The driving and measuring component comprises a force measuring balance (4), a driving motor (6) and a rotating shaft bracket (7); The force balance (4) is mounted on the upper end of the support rod (3), the drive motor (6) is mounted on the upper end of the force balance (4), and the rotating shaft bracket (7) is mounted on the upper end of the drive motor (6) and fixed to the housing of the drive motor (6), so that the aerodynamic force applied to the test model directly acts on the housing of the drive motor (6), thereby reducing the radial runout of the output shaft of the drive motor (6).

4. The wind tunnel test device based on the Magnus effect according to claim 3, characterized in that: The multi-rod support component comprises an outer hole connection end, a support rod (8) and a support main shaft (9); the lower portion of the hole connection end is connected to the upper surface of the shaft bracket (7), and the hole connection end is circumferentially connected to the inner wall of the rotor (5); the lower end of the support main shaft (9) is inserted from the hole connection end into the interior of the shaft bracket (7) and connected to the output shaft of the drive motor (6), so that the output shaft of the drive motor (6) can drive the support main shaft (9) to rotate, and the support main shaft (9) is rotationally connected to the shaft bracket (7) through a bearing; when the drive motor (6) is driven, the support main shaft (9) rotates, and the bearing supports the support main shaft (9) without affecting the rotation of the support main shaft (9); A plurality of outer support rods (8) are provided on the upper surface of the hole-carrying connection end around the supporting main shaft (9), and the plurality of outer support rods (8) are all connected to the inside of the rotor (5), forming a multi-rod support frame structure.

5. The wind tunnel test device based on the Magnus effect according to claim 4, characterized in that: The driving shaft of the driving motor (6) is connected to the supporting main shaft (9) via a coupling, and an elastic element is provided in the coupling for compensating for radial runout on the driving shaft of the driving motor (6).

6. The wind tunnel test device based on the Magnus effect according to claim 2, characterized in that: The force measuring balance (4) is detachably mounted and can be replaced according to measurement requirements.

7. The wind tunnel test device based on the Magnus effect according to claim 4, characterized in that: A limiting component for limiting the axial displacement of the supporting main shaft (9) is provided below the bearing.

8. The wind tunnel test device based on the Magnus effect according to claim 4, characterized in that: The top end of the rotor (5) is also connected to an end plate (10), and the inner wall of the end plate (10) is connected to the upper end of the supporting main shaft (9).

9. The wind tunnel test device based on the Magnus effect according to claim 1, characterized in that: The device supports multiple groups of parallel arrangements, each group is equipped with an independent force balance (4) and a data acquisition system, and is used to study the aerodynamic interference effect of multiple rotors.

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