CN112504617B - Method for simulating downburst flow by coupling wall surface jet flow and boundary layer wind tunnel of multi-blade wing grid - Google Patents
Method for simulating downburst flow by coupling wall surface jet flow and boundary layer wind tunnel of multi-blade wing grid Download PDFInfo
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Abstract
The invention discloses a method for simulating downburst by a boundary layer wind tunnel coupling wall surface jet flow and a multi-blade wing grid, wherein an axial flow fan of a wall surface jet flow device is started to obtain a jet flow wind field, and the height of an air outlet of the wall surface jet flow device and the angle of an air outlet adjusting plate are adjusted, so that the spatial characteristic distribution of the jet flow wind field is changed, and the maximum radial wind speed of the jet flow wind field is at a set height; simultaneously, starting a wind tunnel fan to form a background wind field with set flow rate in a wind tunnel flow passage; coupling the jet flow wind field and the background wind field to obtain a downburst flow outflow wind field with set spatial characteristic distribution; the angle of a guide plate of the guide device is adjusted to change along with time according to a set rule, so that the spatial characteristic distribution of a background wind field changes along with time, the flow field characteristic of a downburst outflow wind field changes along with time, and the sudden change characteristic of the downburst outflow wind field changing along with time is simulated. The method can simulate the spatial characteristics of the downburst effluent wind development area, and can also simulate the time-varying unsteady state characteristics and the vortex area development characteristics of the downburst effluent wind.
Description
Technical Field
The invention belongs to the technical field of wind tunnel simulation tests, and particularly relates to a method for simulating downburst in a boundary layer wind tunnel by coupling wall jet and multi-blade winged gratings.
Background
On the background of annual global climate deterioration, downburst storm disasters frequently occur, and serious damage is caused to structures such as buildings, public facilities, power transmission tower systems and the like within the action radius of the downburst storm disasters. The actual measurement result shows that the wind field characteristics of downburst and typhoon, tornado and other wind disasters are obviously different, so that the wind field simulation of the downburst in the wind tunnel test has a unique mode.
The physical simulation of the downburst in the wind engineering community is divided into two categories, one category is used for simulating the whole process of the development and change of the downburst, and the other category is used for simulating the outflow process of the downburst. In a conventional boundary layer wind tunnel, two main modes are provided for simulating a downburst outflow process, one mode is that a 'nose type' wind profile which changes along with the height is formed by generating extra wall wind speed at the bottom of the wind tunnel and assisting a guide plate at a joint by using a wall surface jet flow principle; the other method is that the principle that a guide plate changes the wind direction is utilized, horizontal airflow descends through a multi-wing-grid device arranged at a test section between an air inlet and a turntable, and the wind speed at the turntable can be changed by adjusting the rotation angle of the wing grids, so that the time course of the downburst outflow wind speed is simulated. The first device, while capable of generating downburst effluent wind profiles, is not capable of effectively simulating the time-varying characteristics of wind speed after downburst has fully developed and is not capable of effectively simulating the vortex structure rolling up at the downburst effluent front edge; the second device can simulate the time-varying characteristics of downburst wind speed and the vortex structure after the airflow hits the ground, but cannot effectively simulate the spatial distribution characteristics of downburst at any rotation angle of the deflector. However, engineers are more concerned with considering both downburst gust characteristics and the wind effect on the building structure created by the vortex structure action of the outflow front. Therefore, the method has more engineering significance for correctly simulating the time-varying characteristic and the space distribution characteristic of the downburst wind speed by an effective means so as to analyze the wind effect of the building structure.
Disclosure of Invention
In view of the above, an object of the present invention is to provide a method for simulating downburst in a boundary layer wind tunnel coupling a wall jet with a multi-blade cascade, which can simulate both the spatial characteristics and the time-varying unsteady characteristics of the downburst.
In order to achieve the purpose, the invention provides the following technical scheme:
a method for simulating downburst by coupling wall surface jet flow and a boundary layer wind tunnel of a multi-blade wing grid is characterized in that an axial flow fan of a wall surface jet flow device is started to obtain a stable jet flow wind field, and the angle of an air outlet adjusting plate of the wall surface jet flow device is adjusted, so that the spatial characteristic distribution of the jet flow wind field is changed, and the maximum radial wind speed of the jet flow wind field is enabled to appear at a set height; simultaneously, starting a wind tunnel fan to form a background wind field with set flow rate in a wind tunnel flow passage; coupling the jet flow wind field and the background wind field to obtain a downburst flow outflow wind field with set spatial characteristic distribution;
the angle of a guide plate of the guide device is adjusted to change along with time according to a set rule, so that a background wind field changes along with time, and the unsteady time-varying characteristic of downburst outflow wind is simulated.
Further, turbulent flow is formed in the area, close to the bottom surface of the wind tunnel flow channel, of the background wind field by using a turbulent flow generating device, and the turbulent flow characteristic of the downburst outflow wind field in the area close to the ground is simulated.
Furthermore, the angle of a guide plate of the guide device is controlled, so that the background wind field and the bottom surface of the wind tunnel channel are collided and then dispersed all around, and a vortex region of downburst outflow wind with unsteady time-varying characteristics is formed.
Further, the turbulence generating device, the flow guiding device and the wall surface jet device are sequentially arranged in the wind tunnel flow channel along the flow direction of the background wind field.
Further, the turbulence generating means comprises a grating and a coarse element, the grating being arranged on an upstream side of the coarse element.
Furthermore, the grid comprises a plurality of vertical grid plates arranged at intervals and a plurality of horizontal grid plates arranged at intervals, and holes for air flow to pass through are formed between the vertical grid plates and the horizontal grid plates in an array mode.
Furthermore, the rough elements are arranged in at least two rows, each row comprises at least two rough elements, and the two adjacent rows of rough elements are arranged in a staggered manner.
Further, the flow guide device comprises two upright posts which are respectively positioned at two sides, a plurality of flow guide plates are arranged between the two upright posts at intervals, rotating shafts are arranged on the flow guide plates, the flow guide plates are arranged between the two upright posts in a rotating fit mode through the rotating shafts, and a rotation driving device for driving the flow guide plates to rotate around the rotating shafts is further arranged in the wind tunnel flow channel; the width of each guide plate is larger than or equal to the distance between the adjacent guide plates and the rotating shaft.
Further, the rotation driving device comprises a motor and a transmission shaft in transmission connection with an output shaft of the motor, and a worm gear mechanism or a helical gear transmission mechanism is arranged between each transmission shaft and each rotating shaft.
Further, the wall surface jet device comprises an axial flow fan and a jet flow channel connected with an air outlet of the axial flow fan, the jet flow channel comprises a stable section, a rotary section and a jet flow outlet section, the rotary section is positioned between the stable section and the jet flow outlet section, and the air outlet of the wall surface jet device is arranged at one end of the jet flow outlet section, which is opposite to the rotary section; a transition section is arranged between the air outlet of the axial flow fan and the stabilizing section and is connected with the air outlet of the axial flow fan, and the bottom surface of the jet flow outlet section is flush with the bottom surface of the wind tunnel flow channel; the included angle between the air inlet direction and the air outlet direction of the rotary section is 180 degrees, the widths of the air inlet and the air outlet of the rotary section are equal to the width of the air tunnel flow channel, the flow area of the air inlet of the rotary section is larger than that of the air outlet of the rotary section, and the flow area of the rotary section is gradually reduced along the air flow direction from the air inlet to the air outlet of the rotary section.
Furthermore, first flow guide groups are arranged in the stabilizing section at intervals, and each first flow guide group comprises a plurality of first flow guide sheets arranged at intervals in the width direction of the stabilizing section; a second flow guide group is arranged in the rotary section and comprises a plurality of second flow guide sheets which are arranged at intervals along the height direction of the rotary section; and a third guide vane group is arranged in the jet flow outlet section at intervals, and comprises a plurality of third guide vanes arranged at intervals along the width direction of the jet flow outlet section.
Further, the third guide vane groups are arranged into two groups at intervals along the airflow direction of the jet flow outlet section, and a flow adjusting mechanism for adjusting the outlet airflow flow of the jet flow outlet section is arranged between the two groups of third guide vane groups; the flow regulating mechanism comprises a regulating plate hinged to the bottom surface of the jet flow outlet section and a regulating cylinder used for driving the regulating plate to rotate so as to regulate the flow area between the regulating plate and the top surface of the jet flow outlet section.
Furthermore, both ends of all the second guide vanes are located on the same plane, and an included angle between the plane and the airflow emergent direction of the jet flow outlet section is 60 degrees.
The invention has the beneficial effects that:
the invention relates to a method for simulating downburst by coupling a wall surface jet flow with a boundary layer wind tunnel of a multi-blade wing grid, which is characterized in that a wall surface jet flow device is utilized to generate a jet flow wind field with specific spatial distribution characteristics and is coupled with a background wind field with set flow rate in a wind tunnel runner, so that a downburst outflow wind field with set spatial characteristic distribution can be obtained, and then a flow guide device is utilized to change the background wind field along with time, so that the flow characteristics of the downburst outflow wind field can be changed along with time, and the sudden change characteristics of the downburst outflow wind field along with time can be simulated; in conclusion, the method for simulating downburst by coupling the boundary layer wind tunnel of the wall surface jet flow and the multi-blade wing grating can simulate the spatial characteristic of downburst effluent wind and the time-varying unsteady characteristic of the downburst effluent wind.
Drawings
In order to make the object, technical scheme and beneficial effect of the invention more clear, the invention provides the following drawings for explanation:
FIG. 1 is a schematic structural diagram of a downburst simulation apparatus suitable for use in the method of the present invention for simulating a downburst in a boundary layer wind tunnel coupling a wall jet with a multi-bladed cascade;
FIG. 2 is a schematic view of a grid structure;
FIG. 3 is a schematic view of the structure of the diversion device;
FIG. 4a is a schematic structural diagram of a wind field profile generating device;
FIG. 4b is a top view of FIG. 4 a;
FIG. 5 is a graph of a vertical wind profile of a downburst wind produced in a simulation of the present embodiment;
FIG. 6 is a graph of deflector angle versus time;
FIG. 7 is a graph of background wind flow rate over time;
FIG. 8 is a graph of the vertical wind profile of a downburst outflow at various times during the time course obtained by simulation.
1-a wind tunnel flow channel; 2-a grid; 3-coarse element; 4-a flow guide device; 5-wind field profile generating means; 6-a turntable device; 7-vertical grating plates; 8-horizontal grid plates; 9-holes; 10-upright post; 11-a flow guide plate; 12-a rotating shaft; 13-a motor; 14-a drive shaft; 15-bevel gear drive; 16-an axial flow fan; 17-a stabilization section; 18-a turn section; 19-jet outlet section; 20-a transition section; 21-a first guide vane; 22-a second guide vane; 23-a third guide vane; 24-an adjusting plate; 25-adjusting the cylinder.
Detailed Description
The present invention is further described with reference to the following drawings and specific examples so that those skilled in the art can better understand the present invention and can practice the present invention, but the examples are not intended to limit the present invention.
The method for simulating downburst flow by the boundary layer wind tunnel coupling the wall surface jet flow and the multi-blade cascade comprises the following steps: starting an axial flow fan 16 of the wall surface jet device 5 to obtain a stable jet wind field, and adjusting the angle of an air outlet adjusting plate 24 of the wall surface jet device 5, so that the spatial characteristic distribution of the jet wind field is changed, and the maximum radial wind speed of the jet wind field is at a set height; simultaneously, starting a wind tunnel fan to form a background wind field with set flow rate in the wind tunnel flow passage 1; coupling the jet flow wind field and the background wind field to obtain a downburst outflow wind field with set spatial characteristic distribution; the angle of the guide plate 11 of the guide device 4 is adjusted to change with time according to a set rule, as shown in fig. 6-8, so that the background wind field changes with time, the flow field characteristic of the downburst outflow wind field changes with time, and the sudden change characteristic of the downburst outflow wind field changing with time is simulated. Preferably, in the present embodiment, the turbulence generating device is further used to form turbulence in the region of the background wind field near the bottom surface of the wind tunnel flow channel 1, so as to achieve the technical purpose of simulating the turbulence characteristics of the downburst outflow wind field in the near-ground region, i.e. to simulate the vortex structure of the downburst outflow wind front edge. And controlling the angle of a guide plate 11 of the guide device 4 to enable the background wind field and the bottom surface of the wind tunnel channel 1 to collide and then radiate to the periphery, so that a vortex region of downburst outflow wind with unsteady time-varying characteristics is formed.
Specifically, the turbulence generating device, the flow guiding device 4 and the wall surface jet device 5 of the present embodiment are sequentially arranged in the wind tunnel flow passage 1 along the flow direction of the background wind field. Wherein, the turbulence generating device comprises a grating 2 and a rough element 3; the flow guide device 4 is used for simulating the non-stationary transient characteristic of downburst; and the wall surface jet device 5 is used for simulating the vertical spatial distribution characteristic of the downdraft storm field. The coarse cell 3 of the present embodiment is located between the grating 2 and the flow guiding device 4, i.e. the grating 2 is arranged on the upstream side of the coarse cell 3. The wind tunnel flow channel 1 of the embodiment is further provided with a turntable device 6 for mounting a component to be tested, wherein the turntable device 6 is located on one side of the wall surface jet device 5, which faces away from the flow guide device 4, i.e. the turntable device 6 is located on the downstream side of the wall surface jet device 5. The turntable device 6 is used for mounting a test model structure, so as to simulate the effect of a downburst outflow wind field with time-varying and abrupt characteristics on the test model structure.
Further, grid 2 includes a plurality of vertical grid plates 7 that the interval set up and a plurality of horizontal grid plates 8 that the interval set up, and the array forms the hole 9 that is used for the air current to pass through between vertical grid plate 7 and the horizontal grid plate 8. The grating 2 of the present embodiment comprises 4 equally spaced vertical grating plates 7 and 5 equally spaced horizontal grating plates 8. The wind tunnel flow channel 1 of the embodiment has the dimensions of 15m in length, 2.4m in width and 1.8m in height, the vertical grid plate 7 has the dimensions of 30cm in width and 1.8m in height, and the horizontal grid plate 8 has the dimensions of 15cm in width and 2m in length. Specifically, the rough elements 3 are arranged in at least two rows, each row includes at least two rough elements 3, and two adjacent rows of rough elements 3 are arranged in a staggered manner. The rough elements 3 of this embodiment are arranged in 6 rows, and of the two adjacent rough elements 3, one row is provided with 6 rough elements, and the other row is provided with 5 rough elements. Of course, the size and arrangement of the grating 2 and the coarse elements 3 should be properly adjusted according to the requirements on the turbulence of the boundary layer wind field in the experimental process.
Further, the flow guiding device 4 comprises two upright posts 10 respectively positioned at two sides, a plurality of flow guiding plates 11 are arranged between the two upright posts 10 at intervals, a rotating shaft 12 is arranged on each flow guiding plate 11, the flow guiding plates 11 are arranged between the two upright posts 10 in a rotating fit manner through the rotating shaft 12, and a rotating driving device for driving the flow guiding plates 11 to rotate around the rotating shaft 12 is further arranged in the wind tunnel flow channel 1; the width of the guide plate 11 is larger than or equal to the distance between the two adjacent guide plates 11 and the rotating shaft 12. The width of the baffle 11 of the embodiment is equal to the distance between the rotating shafts 12 of two adjacent baffles 11. Specifically, the size of the guide plate is 30cm wide, 2m long and 1cm thick, that is, the distance between the rotating shafts 12 of two adjacent guide plates 11 is 30 cm. The rotation driving device of this embodiment includes a motor 13 and a transmission shaft 14 in transmission connection with an output shaft of the motor 13, a worm gear mechanism or a helical gear mechanism 15 is respectively disposed between the transmission shaft 14 and each of the rotating shafts 12, and a worm gear mechanism or a helical gear mechanism 15 is respectively disposed between the transmission shaft 14 and each of the rotating shafts 12. Preferably, the rotation driving devices are respectively provided with 2 corresponding to the two columns 10, and are used for synchronously driving the two ends of the guide plate 11 to rotate so as to prevent the rotation angles of the two ends of the guide plate 11 from deviating. Specifically, the guide plate 11 is parallel to the bottom surface of the wind tunnel flow channel 1 as an initial angle, and the rotation angle of the guide plate 11 in the embodiment is-40 to 60 degrees. The motor 13 of this embodiment adopts a step motor, and the step motor can provide a large torque to maintain the rotation angle position of the deflector 11, and further, the step motor can make the deflector 11 be located at the set angle position at a specific time point through the curve relationship between the preset time and the angle position of the deflector 11, thereby achieving the technical purpose of simulating the non-stationary transient characteristic of downburst.
Further, the wind field profile generating device 5 comprises an axial flow fan 16 and a jet flow channel connected with an air outlet of the axial flow fan 16, the jet flow channel comprises a stabilizing section 17, a turning section 18 and a jet flow outlet section 19, the turning section 18 is located between the stabilizing section 17 and the jet flow outlet section 19, and an air outlet of the wall surface jet device 5 is arranged at one end, back to the turning section 18, of the jet flow outlet section 19. A transition section 20 is arranged between an air outlet of the axial flow fan 16 and the stabilizing section 17 for connection, and the bottom surface of the jet flow outlet section 19 is flush with the bottom surface of the wind tunnel flow channel 1; the included angle between the air inlet direction and the air outlet direction of the rotary section 18 is 180 degrees, the widths of the air inlet and the air outlet of the rotary section 18 are equal to the width of the wind tunnel flow channel 1, the flow area of the air inlet of the rotary section 18 is larger than that of the air outlet of the rotary section, and the flow area of the rotary section 18 is gradually reduced along the airflow direction from the air inlet to the air outlet of the rotary section. Specifically, the axial flow fans 16 of the present embodiment are provided with 3 fans in parallel, and a transition section 20 is provided between the air outlet of each axial flow fan 16 and the stabilizing section 17. The stabilizing section 17 of this embodiment is provided with a first guide vane group at intervals, and the first guide vane group includes a plurality of first guide vanes 21 arranged at intervals along the width direction of the stabilizing section 17. A second diversion group is arranged in the rotary section 18, the second diversion group comprises a plurality of second diversion pieces 22 which are arranged at intervals along the height direction of the rotary section 18, two ends of all the second diversion pieces 22 are positioned on the same plane, and an included angle between the plane and the airflow emergent direction of the jet flow outlet section 19 is 60 degrees. A third guide vane group is arranged in the jet flow outlet section 19 at intervals, and the third guide vane group comprises a plurality of third guide vanes 23 arranged at intervals along the width direction of the jet flow outlet section 19. Specifically, the third guide vane groups are arranged into two groups at intervals along the airflow direction of the jet flow outlet section 19, and a flow adjusting mechanism for adjusting the outlet airflow flow of the jet flow outlet section 19 is arranged between the two groups of third guide vane groups; the flow regulating mechanism comprises a regulating plate 24 which is hinged with the bottom surface of the jet flow outlet section 19 and a regulating cylinder 25 which is used for driving the regulating plate 24 to rotate so as to regulate the flow area between the regulating plate 24 and the top surface of the jet flow outlet section 19.
The rotating speed of the axial flow fan 16 in the wind field profile generation device of the embodiment is adjustable so as to change the wall surface jet flow speed; the flow regulating mechanism at the joint changes the height of the inlet through the driving of the regulating cylinder to form semi-limited jet flow, so that the aim of simulating the vertical space distribution characteristic of a downdraft storm wind field is fulfilled.
The method for simulating downburst by coupling the wall surface jet flow with the boundary layer wind tunnel of the multi-blade wing grid comprises the steps of generating a jet flow wind field with specific spatial distribution characteristics by using a wall surface jet flow device, coupling the jet flow wind field with a background wind field with a set flow rate in a wind tunnel channel, so that a downburst outflow wind field with set spatial characteristic distribution can be obtained, and changing the background wind field with time by using a flow guide device, so that the flow characteristics of the downburst outflow wind field can be changed with time, and the sudden change characteristics of the downburst outflow wind field with time can be simulated; in conclusion, the method for simulating the downburst in the boundary layer wind tunnel by coupling the wall jet with the multi-blade winglets in the embodiment can simulate the spatial characteristics of the developed area of the downburst outflow wind and can also simulate the time-varying unsteady characteristics and the developed characteristics of the vortex area of the downburst outflow wind.
The above-mentioned embodiments are merely preferred embodiments for fully illustrating the present invention, and the scope of the present invention is not limited thereto. The equivalent substitution or change made by the technical personnel in the technical field on the basis of the invention is all within the protection scope of the invention. The protection scope of the invention is subject to the claims.
Claims (10)
1. A method for simulating downburst flow by a boundary layer wind tunnel coupling wall surface jet flow and a multi-blade wing grid is characterized by comprising the following steps: starting an axial flow fan (16) of the wall surface jet device (5) to obtain a stable jet wind field, and adjusting the angle of an adjusting plate (24) at the air outlet of the wall surface jet device (5), so that the spatial characteristic distribution of the jet wind field is changed, and the maximum radial wind speed of the jet wind field is at a set height; simultaneously, starting a wind tunnel fan to form a background wind field with set flow rate in the wind tunnel flow passage (1); coupling the jet flow wind field and the background wind field to obtain a downburst storm wind field with the set wind speed spatial distribution characteristic in the development area;
the angle of a guide plate (11) of the guide device (4) is adjusted to change along with time according to a set rule, so that a background wind field changes suddenly along with time, and the unsteady time-varying characteristic of a downburst outflow wind development area is simulated; the angle of a guide plate (11) of the guide device (4) changes along with time and sequentially becomes a first wind speed sudden increase stage, a second wind speed sudden increase stage and a third wind speed sudden decrease stage; the rotating direction of the guide plate (11) in the first sudden wind speed increasing stage is the same as that of the guide plate (11) in the second sudden wind speed increasing stage, and the rotating direction of the guide plate (11) in the third sudden wind speed decreasing stage is opposite to that of the guide plate (11) in the first sudden wind speed increasing stage.
2. The method for simulating downburst in a boundary layer wind tunnel coupled with wall jet and multi-blade cascade of claim 1, wherein the method comprises the following steps: turbulent flow is formed in the area, close to the bottom surface of the wind tunnel flow channel (1), of the background wind field by using a turbulent flow generating device, and the turbulent flow characteristic of the downburst outflow wind field in the area close to the ground is simulated.
3. The method for simulating downburst in a boundary layer wind tunnel coupled with wall jet and multi-blade cascade of claim 1, wherein the method comprises the following steps: and controlling the angle of a guide plate (11) of the guide device (4) to enable a background wind field to collide with the bottom surface of the wind tunnel flow channel (1) and then radiate the bottom surface to the periphery, so that a vortex region of downburst outflowing wind with unsteady time-varying characteristics is formed.
4. The method for simulating downburst in a boundary layer wind tunnel coupled with wall jet and multi-blade cascade of claim 2, wherein the method comprises the following steps: the turbulence generating device, the flow guide device (4) and the wall surface jet device (5) are sequentially arranged in the wind tunnel flow channel (1) along the flow direction of a background wind field.
5. The method for simulating downburst in a boundary layer wind tunnel coupled with wall jet and multi-blade cascade of claim 2, wherein the method comprises the following steps: the turbulence generating device comprises a grid (2) and a coarse element (3), the grid (2) being arranged on the upstream side of the coarse element (3); the grille (2) comprises a plurality of vertical grille plates (7) arranged at intervals and a plurality of horizontal grille plates (8) arranged at intervals, and holes (9) for air flow to pass through are formed between the vertical grille plates (7) and the horizontal grille plates (8) in an array manner; the rough elements (3) are arranged in at least two rows, each row comprises at least two rough elements (3), and the two adjacent rows of rough elements (3) are arranged in a staggered manner.
6. The method for simulating downburst in a boundary layer wind tunnel coupled with wall jet and multi-blade cascade of claim 1, wherein the method comprises the following steps: the flow guide device (4) comprises two upright posts (10) which are respectively positioned at two sides, a plurality of flow guide plates (11) are arranged between the two upright posts (10) at intervals, rotating shafts (12) are arranged on the flow guide plates (11), the flow guide plates (11) are arranged between the two upright posts (10) through the rotating shafts (12) in a rotating fit mode, and a rotation driving device for driving the flow guide plates (11) to rotate around the rotating shafts (12) is further arranged in the wind tunnel flow channel (1); the width of each guide plate (11) is larger than or equal to the distance between the adjacent guide plates (11) and the rotating shafts (12).
7. The method for simulating downburst flow in a boundary layer wind tunnel coupling wall jet with a multi-blade cascade as claimed in claim 1, wherein: the wall surface jet device (5) comprises an axial flow fan (16) and a jet flow channel connected with an air outlet of the axial flow fan (16), the jet flow channel comprises a stabilizing section (17), a rotating section (18) and a jet flow outlet section (19), the rotating section (18) is positioned between the stabilizing section (17) and the jet flow outlet section (19), and the air outlet of the wall surface jet device (5) is arranged at one end, back to the rotating section (18), of the jet flow outlet section (19); a transition section (20) is arranged between an air outlet of the axial flow fan (16) and the stabilizing section (17) for connection, and the bottom surface of the jet flow outlet section (19) is flush with the bottom surface of the wind tunnel flow channel (1); the included angle between the air inlet direction and the air outlet direction of the rotary section (18) is 180 degrees, the widths of the air inlet and the air outlet of the rotary section (18) are equal to the width of the wind tunnel flow channel (1), the flow area of the air inlet of the rotary section (18) is larger than that of the air outlet of the rotary section, and the flow area of the rotary section (18) is gradually reduced along the airflow direction from the air inlet to the air outlet of the rotary section.
8. The method for simulating downburst in a boundary layer wind tunnel coupling wall jet with a multi-vane cascade of claim 7, wherein the method comprises the following steps: first flow guide groups are arranged in the stabilizing section (17) at intervals, and each first flow guide group comprises a plurality of first flow guide sheets (21) arranged at intervals in the width direction of the stabilizing section (17); a second flow guide group is arranged in the rotary section (18), and the second flow guide group comprises a plurality of second flow guide sheets (22) which are arranged at intervals along the height direction of the rotary section (18); the jet flow outlet section (19) is internally provided with a third guide vane group at intervals, and the third guide vane group comprises a plurality of third guide vanes (23) which are arranged at intervals along the width direction of the jet flow outlet section (19).
9. The method of simulating downburst in a boundary layer wind tunnel coupling a wall jet with a multi-vane cascade of claim 8, wherein: the third guide vane groups are arranged into two groups at intervals along the airflow direction of the jet flow outlet section (19), and a flow regulating mechanism for regulating the outlet airflow flow of the jet flow outlet section (19) is arranged between the two groups of third guide vane groups; the flow regulating mechanism comprises a regulating plate (24) connected with the bottom surface of the jet flow outlet section (19) in a hinged mode and a regulating cylinder (25) used for driving the regulating plate (24) to rotate so as to regulate the flow area between the regulating plate (24) and the top surface of the jet flow outlet section (19).
10. The method of simulating downburst in a boundary layer wind tunnel coupling a wall jet with a multi-vane cascade of claim 8, wherein: both ends of all the second flow deflectors (22) are positioned on the same plane, and the included angle between the plane and the airflow emergent direction of the jet flow outlet section (19) is 60 degrees.
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| CN206695972U (en) * | 2017-03-30 | 2017-12-01 | 华南理工大学 | A kind of flow tunnel testing device for being used to simulate thunderstorm downburst |
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