CN117073963B - Double-nozzle anti-phase pulse jet wind tunnel test device and test method - Google Patents
Double-nozzle anti-phase pulse jet wind tunnel test device and test method Download PDFInfo
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- CN117073963B CN117073963B CN202311324243.6A CN202311324243A CN117073963B CN 117073963 B CN117073963 B CN 117073963B CN 202311324243 A CN202311324243 A CN 202311324243A CN 117073963 B CN117073963 B CN 117073963B
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- 238000012360 testing method Methods 0.000 title claims abstract description 25
- 238000010998 test method Methods 0.000 title claims abstract description 8
- 239000002245 particle Substances 0.000 claims description 8
- 239000000443 aerosol Substances 0.000 claims description 6
- 238000005516 engineering process Methods 0.000 claims description 6
- 238000002474 experimental method Methods 0.000 claims description 4
- 239000011248 coating agent Substances 0.000 claims description 3
- 238000000576 coating method Methods 0.000 claims description 3
- 230000007613 environmental effect Effects 0.000 claims description 3
- 238000010438 heat treatment Methods 0.000 claims description 3
- 230000001678 irradiating effect Effects 0.000 claims description 3
- 238000005259 measurement Methods 0.000 claims description 3
- 230000009977 dual effect Effects 0.000 claims 6
- 238000000926 separation method Methods 0.000 description 18
- 230000000694 effects Effects 0.000 description 5
- 230000005284 excitation Effects 0.000 description 5
- 238000000034 method Methods 0.000 description 5
- 230000005764 inhibitory process Effects 0.000 description 4
- 230000008859 change Effects 0.000 description 3
- 230000008901 benefit Effects 0.000 description 2
- 239000011521 glass Substances 0.000 description 2
- 230000010355 oscillation Effects 0.000 description 2
- 230000010349 pulsation Effects 0.000 description 2
- 230000009467 reduction Effects 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 230000003068 static effect Effects 0.000 description 2
- 239000012780 transparent material Substances 0.000 description 2
- 238000010146 3D printing Methods 0.000 description 1
- 102100027340 Slit homolog 2 protein Human genes 0.000 description 1
- 101710133576 Slit homolog 2 protein Proteins 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000013016 damping Methods 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 230000007480 spreading Effects 0.000 description 1
- 238000010408 sweeping Methods 0.000 description 1
Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
- G01M9/04—Details
-
- G—PHYSICS
- G05—CONTROLLING; REGULATING
- G05B—CONTROL OR REGULATING SYSTEMS IN GENERAL; FUNCTIONAL ELEMENTS OF SUCH SYSTEMS; MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS OR ELEMENTS
- G05B19/00—Programme-control systems
- G05B19/02—Programme-control systems electric
- G05B19/04—Programme control other than numerical control, i.e. in sequence controllers or logic controllers
- G05B19/042—Programme control other than numerical control, i.e. in sequence controllers or logic controllers using digital processors
- G05B19/0423—Input/output
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Abstract
The invention relates to the technical field of wind tunnel test devices, in particular to a double-nozzle anti-phase pulse jet flow wind tunnel test device and a test method. When the jet flow control device is used, the driving motor drives the cylindrical model to rotate, the jet flow control device controls the two jet flow slits to alternately jet flow, and jet flow section airflows which alternate with each other are generated in the jet flow slits.
Description
Technical Field
The invention relates to the technical field of wind tunnel test devices, in particular to a double-nozzle anti-phase pulse jet wind tunnel test device and a test method.
Background
The cylindrical flow-around problem is very classical in hydrodynamics and the unsteady flow through the bluff body often exhibits a large scale Vortex structure such as "karman Vortex street" to induce "Vortex induced oscillations" (Vortex-induced-Induced Vibration: VIV). The engineering field needs to often consider such problems as vibration damping, drag reduction and noise reduction of buildings such as bridges. In view of these problems, researchers have proposed many passive and active flow control methods, and jet flow control techniques in active flow control have received a great deal of attention in recent years because of their strong engineering application prospects. Among them, the unsteady jet has a great advantage in terms of control efficiency as compared with the unsteady jet, such as a pulse jet technique.
The pulse jet flow is an effective method for changing flow separation by periodically injecting momentum into the flow field and improving the capability of the boundary layer to resist the reverse pressure gradient. The above observations are also confirmed from a number of research results using pulsed jets to inhibit flow separation at airfoil surfaces.
For the cylindrical bypass problem, the critical Reynolds number is usually 10 5 In the magnitude range, at subcritical reynolds numbers, flow through the cylinder is laminar, with the separation location typically being on the windward side of the cylinder. There have been many efforts to control laminar separation of cylindrical surfaces using unsteady jets. One is an acoustic excitation jet control mode, which effectively inhibits the air flow separation on the surface of the cylinder and analyzes the induced flow field; one is that the application of synthetic jet control at the front and rear stagnation points of the cylinder effectively reduces the range of the cylinder separation zone; one is to arrange the DBD plasma excitation pulse jet near the cylinder separation point, when the dimensionless excitation frequency is 3 times of the main stream frequency, the vortex shedding can be effectively inhibited, and the control mode of the dimensionless gas source has higher control efficiency, but is generally limited in the aspects of momentum input and excitation duration.
From the published literature, there is little research on active unsteady jet flow separation for cylindrical bypass flow. The control effect and mechanism of the oscillating jet flow on the shedding of the cylindrical vortex are studied through wind tunnel tests, and two rows of oscillating jet flow exciters are placed at the position of the cylinder close to the separation point, so that when the momentum coefficient is 0.2147, compared with the condition without control, the turbulence kinetic energy under the control of the sweeping jet flow is reduced by 73%, and the dimensionless Reynolds shear stress is reduced by 68%. The above work adopts 8 oscillation jet flow exciters in each row, and the influence of the phase difference between different jet flows in the spreading direction on the separation control is not considered although the better separation inhibition efficiency is obtained.
Disclosure of Invention
The invention aims to provide a double-nozzle anti-phase pulse jet wind tunnel test device and a test method, which solve the technical problem that the flow performance of an anti-phase pulse jet technology in the prior art is difficult to control accurately, so that the phase is difficult to adjust stably.
The invention discloses a double-nozzle anti-phase pulse jet wind tunnel test device which comprises a cylindrical model, wherein two jet slits are arranged in the middle of the cylindrical model, two air source inlets are arranged at the lower part of the cylindrical model and are respectively communicated with the two jet slits, a jet control device is arranged on the air source inlets and is used for controlling the two jet slits to alternately jet, and a driving motor is connected to the bottom of the cylindrical model.
When the jet flow control device is used, the driving motor drives the cylindrical model to rotate, the jet flow control device controls the two jet flow slits to alternately jet flow, and jet flow section airflows which alternate with each other are generated in the jet flow slits.
By arranging two jet slits and two air source inlets, the two jet slits can be ensured to jet independently.
Further, the jet flow control device comprises an electromagnetic valve connected with the air source inlet, and the electromagnetic valve is connected with a singlechip.
When the jet flow control device is used, the air source is controlled to enter the jet flow seam from the air source inlet by controlling the opening and closing of the electromagnetic valve through the singlechip, so that the jet flow is controlled.
Further, the driving motor is sleeved with a motor support.
Further, a box balance is arranged on the driving motor.
By arranging the box balance, aerodynamic force and moment received by the model are measured, and the flow separation inhibition effect of the model and the pulsation change after the opposite phase pulse jet flow can be judged according to the measured force and moment signals.
Further, the box-type balance is connected with one end of a supporting rod, and the other end of the supporting rod is connected with the cylindrical model.
Further, the supporting rod is cuboid.
Further, 3D printing screw holes for installing jackscrews are formed in the cylindrical model.
Through set up the screw in the cylinder model inside, the model of solution cylinder shape that can be better links firmly with inside support member.
Further, the screw hole and the cylindrical model are integrally formed.
Further, a lower cover plate is arranged at one end close to the driving motor, and an upper cover plate is arranged at one end far away from the driving motor.
Further, the lower cover plate and the upper cover plate are made of organic glass transparent materials.
The double-nozzle anti-phase pulse jet wind tunnel test method is carried out by using the device.
Further, the method comprises the following specific steps:
s1, placing a test device in a closed space to avoid interference of environmental air flow on an experiment result;
s2, irradiating laser piece light on a section passing through the jet flow seam along the chord direction;
s3, coating the aerosol on the conductive cable and placing the cable outside the sheet light;
s4, electrifying and heating the conductive cable to gasify the aerosol, wherein the jet flow can eject fluorescent particles gasified outside the sheet light into the sheet light, and the jet flow field under the condition of no incoming flow can be measured by a particle velocity measurement technology.
Compared with the prior art, the invention has the following beneficial effects:
the jet control device controls the two jet slits to alternately jet, the anti-phase pulse jet technology has smaller disturbance to the flow field than the traditional pulse jet, and the separation inhibition effect is equivalent; by arranging two jet slits and two air source inlets, the two jet slits can be ensured to jet independently; the single chip microcomputer controls the opening and closing of the electromagnetic valve to control the air source to enter the jet flow seam from the air source inlet, so that independent control of two jet flows is realized, and the mode can also be used as a scheme for independently controlling a plurality of jet flows.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings that are needed in the embodiments will be briefly described below, it being understood that the following drawings only illustrate some embodiments of the present invention and therefore should not be considered limiting the scope, and other related drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
FIG. 1 is a schematic view of a wind tunnel test device according to the present invention.
FIG. 2 is a schematic illustration of a static air jet test experiment in accordance with the present invention.
FIG. 3 is a graph of the results of a static air jet test of the present invention.
In the above figures, the meaning of each symbol is: the fluorescent particle detector comprises a 1-upper cover plate, a 2-jet slit, a 3-jet section, a 4-cylindrical model, a 5-lower cover plate, a 6-electromagnetic valve, a 7-air source inlet, an 8-supporting rod, a 9-singlechip, a 10-motor support, an 11-box balance, a 12-driving motor, a 13-input signal, a 14-wind tunnel inflow, a 15-screw hole, a 16-conductive cable and 17-fluorescent particles.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more clear, the technical solutions in the embodiments of the present invention will be clearly and completely described below, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments.
Example 1
The specific structure of the double-nozzle anti-phase pulse jet wind tunnel test device adopting the device is shown in fig. 1, the device comprises a cylindrical model 4, two jet slits 2 are arranged in the middle of the cylindrical model 4, two air source inlets 7 are arranged at the lower part of the cylindrical model 4, the two air source inlets 7 are respectively communicated with the two jet slits 2, a jet control device is arranged on the air source inlets 7, the two jet control devices control the two jet slits 2 to alternately jet, and a driving motor 12 is connected to the bottom of the cylindrical model 4.
When the flow field measuring device is used, the lower cover plate 5 is arranged at one end close to the driving motor 12, the upper cover plate 1 is arranged at one end far away from the driving motor 12, and the upper cover plate and the lower cover plate are made of organic glass transparent materials, so that the flow field measuring can be better performed through a camera while the three-dimensional effect at two ends of a cylinder is eliminated. The driving motor 12 drives the cylindrical model 4 to rotate, the jet flow control device controls the two jet flow slits 2 to alternately jet flow, the jet flow slits 2 generate air flows of mutually alternate jet flow sections 3, and the anti-phase pulse jet flow technology has smaller disturbance to a flow field than the traditional pulse jet flow. When the wind tunnel incoming flow 14 is started, flow separation can be restrained by jet flow control because flow separation occurs on the cylindrical surface due to the influence of the reverse pressure gradient.
By arranging two jet slits 2 and two air source inlets 7, it is ensured that the two jet slits 2 can jet independently.
Example 2
In this embodiment, as a preferred embodiment of the present invention, as shown in fig. 1, the jet control device is modified from embodiment 1 only in that the jet control device includes a solenoid valve 6 connected to the air source inlet 7, and the solenoid valve 6 is connected to a single chip microcomputer 9.
When in use, the input signal 13 controls the opening and closing of the electromagnetic valve 6 through the singlechip 9 to control the air source to enter the jet slit 2 from the air source inlet 7, so as to realize the control of jet.
Example 3
In this embodiment, as a preferred example of the present invention, the specific structure is shown in fig. 1, and the change is that, based on example 2, the driving motor 12 is sleeved with the motor support 10, the driving motor 12 is provided with the box-type balance 11, the box-type balance 11 is connected with one end of the supporting rod 8, the other end of the supporting rod 8 is connected with the cylindrical model 4, the supporting rod 8 is a cuboid, the cylindrical model 4 is provided with a screw hole 15 for installing a jackscrew, and the screw hole 15 and the cylindrical model 4 are integrally formed.
By arranging the box balance 11, aerodynamic force and moment applied to the model are measured, and the flow separation inhibition effect of the model and the pulsation change after the opposite phase pulse jet can be judged according to the measured force and moment signals.
By arranging the screw holes 15 in the cylindrical model 4, the problem that the cylindrical model is fixedly connected with the inner support rod 8 can be better solved.
Example 4
The test method of the double-nozzle anti-phase pulse jet wind tunnel, which uses the test device in the embodiment 3, has the specific structure shown in figure 2, and comprises the following steps:
s1, placing a test device in a closed space to avoid interference of environmental air flow on an experiment result;
s2, irradiating laser piece light on a section passing through the jet flow seam along the chord direction;
s3, coating the aerosol on the conductive cable and placing the cable outside the sheet light;
and S4, electrifying and heating the conductive cable to gasify the aerosol, wherein the jet flow can eject fluorescent particles gasified outside the sheet light into the sheet light, and the jet flow field under the condition of no incoming flow can be measured by a particle velocity measurement technology.
As a result, as shown in fig. 3, fluctuation in the velocity direction of the observation point 1 was observed within 25ms after the separation control was stabilized. The speed direction under the excitation of the same-phase and opposite-phase pulse jet flows is inθ jet The magnitude of the velocity vector fluctuation after the phase reversal is smaller, and the dimensionless velocity mean square error is different by 6.7%. Description of Cylinder-based double-jet anti-phaseThe pulsed jet can effectively control flow separation and has less influence on the fluctuation of the flow field.
The above is an embodiment exemplified in this example, but this example is not limited to the above-described alternative embodiments, and a person skilled in the art may obtain various other embodiments by any combination of the above-described embodiments, and any person may obtain various other embodiments in the light of this example. The above detailed description should not be construed as limiting the scope of the present embodiments, which is defined in the claims and the description may be used to interpret the claims.
Claims (8)
1. The utility model provides a two spout antiphase pulse jet wind tunnel test device which characterized in that: the jet flow control device comprises a cylindrical model (4), two jet flow slits (2) are formed in the middle of the cylindrical model (4), two air source inlets (7) are formed in the lower portion of the cylindrical model (4), the two air source inlets (7) are respectively communicated with the two jet flow slits (2), a jet flow control device is arranged on the air source inlets (7), the two jet flow slits (2) are controlled by the jet flow control device to alternately jet, and a driving motor (12) is connected to the bottom of the cylindrical model (4);
the test method comprises the following specific steps:
s1, placing a test device in a closed space to avoid interference of environmental air flow on an experiment result;
s2, irradiating laser piece light on a section passing through the jet slit (2) along the chord direction;
s3, coating the aerosol on the conductive cable (16) and placing the cable outside the sheet light;
and S4, electrifying and heating the heat conducting cable (16) to gasify the aerosol, wherein the jet flow can eject fluorescent particles (17) gasified outside the sheet light into the sheet light, and the jet flow field under the condition of no incoming flow can be measured by a particle velocity measurement technology.
2. The dual jet anti-phase pulse jet wind tunnel test device according to claim 1, wherein: the jet flow control device comprises an electromagnetic valve (6) connected with the air source inlet (7), and the electromagnetic valve (6) is connected with a singlechip (9).
3. The dual jet anti-phase pulse jet wind tunnel test device according to claim 1, wherein: the driving motor (12) is sleeved with a motor support (10).
4. A dual jet anti-phase pulse jet wind tunnel test device according to claim 3, wherein: the driving motor (12) is provided with a box balance (11).
5. The dual jet anti-phase pulse jet wind tunnel test device according to claim 4, wherein: the box-type balance (11) is connected with one end of a supporting rod (8), and the other end of the supporting rod (8) is connected with the cylindrical model (4).
6. The dual jet anti-phase pulse jet wind tunnel test device according to claim 5, wherein: the supporting rod (8) is cuboid.
7. The double-nozzle anti-phase pulse jet wind tunnel test device according to claim 1, wherein screw holes (15) for installing jackscrews are formed in the cylindrical model (4).
8. The dual jet anti-phase pulse jet wind tunnel test device according to claim 7, wherein: the screw hole (15) and the cylindrical model (4) are integrally formed.
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| CN202311324243.6A CN117073963B (en) | 2023-10-13 | 2023-10-13 | Double-nozzle anti-phase pulse jet wind tunnel test device and test method |
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| CN202311324243.6A CN117073963B (en) | 2023-10-13 | 2023-10-13 | Double-nozzle anti-phase pulse jet wind tunnel test device and test method |
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| CN117073963A CN117073963A (en) | 2023-11-17 |
| CN117073963B true CN117073963B (en) | 2024-01-26 |
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| CN117073963A (en) | 2023-11-17 |
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