CN107941450B - Jet angle vortex generator for inhibiting low-frequency pressure pulsation of open jet wind tunnel - Google Patents
Jet angle vortex generator for inhibiting low-frequency pressure pulsation of open jet wind tunnel Download PDFInfo
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- CN107941450B CN107941450B CN201710855108.2A CN201710855108A CN107941450B CN 107941450 B CN107941450 B CN 107941450B CN 201710855108 A CN201710855108 A CN 201710855108A CN 107941450 B CN107941450 B CN 107941450B
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- 238000012360 testing method Methods 0.000 description 20
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- 230000002829 reductive effect Effects 0.000 description 11
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
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Abstract
The invention discloses a jet angle vortex generator for inhibiting low-frequency pressure pulsation of an open jet wind tunnel, which comprises a jet (2), wherein two turbulence bodies (1) are fixedly arranged on each wall of the jet; the fluid is in an arc-shaped structure consisting of a rectangular spoiler bottom surface (11), two spoiler side surfaces (14) and a flow direction surface (12). The angle vortex generator conducts long-distance corner diversion on the jet airflow, changes the direction of vortex, damages a large-scale vortex structure generated by instability of a shearing layer, inhibits low-frequency pressure pulsation to a great extent, and can greatly reduce wind tunnel low-frequency pressure pulsation.
Description
Technical Field
The invention relates to a jet angle vortex generator, in particular to a jet angle vortex generator for inhibiting low-frequency pressure pulsation of an open jet wind tunnel, and belongs to the technical field of wind tunnel experiments.
Background
Because of the instability of the shear layer (Kelvin-Helmholtz) at the jet boundary, the free jet will create a large scale vortex structure at a distance downstream of the jet orifice due to the shear layer destabilization. These vortex structures interact with the collector downstream of the open jet wind tunnel test section and its reflected pressure pulsations, resulting in low frequency pressure pulsations in the test section flow field. The low-frequency pressure pulsation damages the flow field quality, and seriously affects the accuracy of aerodynamic and aeroacoustic measurement of the test model. In order to develop high-quality aerodynamic and aerodynamic noise test research in an open jet wind tunnel, it is particularly important to control low-frequency oscillation of the jet wind tunnel and obtain relatively stable flow field and sound field test environments. In addition, the energy loss is caused by the flow field and cavity structure oscillation caused by the low-frequency pressure pulsation and the interaction between vortex and sound, so that the low-frequency pressure pulsation is weakened or inhibited, and the method has positive significance in saving energy and improving the energy utilization efficiency of the open jet wind tunnel.
In the prior art, the control measures for the low-frequency pressure pulsation mainly comprise two modes.
One is: optimizing the structure shape of the collector; the control principle is that the pressure fluctuation generated by the interaction of the collector and the large-scale vortex structure is reduced by changing the geometrical size, the shape and the like of the collector. The difficulty and disadvantage of this approach is that it is difficult to design and is very engineering, especially for wind tunnels that have been built, changing the collector structure and shape is often limited by the tunnel structure.
The other is: the vortex generators (the traditional vortex generators are mainly rectangular or triangular two-dimensional spoilers and three-dimensional vortex generators such as cubes, triangular cones and the like) are arranged on the jet nozzle; the control principle is that small-scale vortex is generated to promote the transition of the shear layer into turbulent flow, and the turbulent flow can inhibit the formation of a large-scale structure of the shear layer, so as to inhibit low-frequency pressure pulsation. Fig. 1 shows that in the prior art, a vortex body (the lower wall of the nozzle is not distributed) is arranged at the nozzle of the rectangular opening jet wind tunnel, and fig. 2 shows that in the prior art, a triangle-shaped disturbance fluid (the lower wall of the nozzle is not distributed) is arranged at the nozzle of the rectangular opening jet wind tunnel. The disadvantages of such vortex generators are: 1) Whether the flow disturbance plate or the flow disturbance plate is used for disturbing the fluid, the edges of the corners on the appearance are more, so that high-frequency noise is brought to the flow disturbance plate, and acoustic measurement is seriously influenced; 2) The circumferential distribution mode and the installation number are more (about 20-30 nozzles are installed around), so that the laminar flow core area of the test measurement section is reduced, the quality of a flow field is destroyed, for example, the direction field, the turbulence degree and the like are increased, the aerodynamic measurement is seriously influenced, and the superimposed high-frequency noise is more serious; 3) The material is mostly metal, the installation is complex, and certain damage exists on the existing wind tunnel nozzle; 4) The other type is flexible material, is easy to damage after being loaded by wind, is easy to force and vibrate, and has strong high-frequency noise. Overall, this type of approach has the following drawbacks: firstly, the control effect is limited, and the amplitude of the low-frequency pressure pulsation cannot be greatly reduced; secondly, the traditional vortex generator enables the jet boundary layer after transition to have higher flow mixing efficiency and higher jet boundary expansion speed, so that the area of a laminar flow core part which can be used for a test is reduced; thirdly, the vortex generator generates high-frequency noise after flow transition, and adverse effect is brought to acoustic measurement. In addition, with the enhancement of testing means and the improvement of the requirements of tested designs on testing indexes, the existing vortex generator control means cannot meet the requirements of advanced aircrafts/high-speed trains/automobiles and the like on high-precision and high-quality testing results.
Disclosure of Invention
Aiming at the problems in the prior art, the invention provides the jet angle vortex generator for inhibiting the low-frequency pressure pulsation of the open jet wind tunnel, and the appearance design and the distribution mode of the vortex generator are changed, so that the low-frequency pressure pulsation of the wind tunnel can be greatly reduced, the laminar flow core area of a test is not reduced, and high-frequency background noise is not increased.
The invention realizes the above purpose through the following technical scheme: the jet angle vortex generator for inhibiting low-frequency pressure pulsation of an open jet wind tunnel comprises a jet, wherein two disturbing fluids are fixedly arranged on each wall of the jet; the fluid is in an arc structure consisting of a rectangular spoiler bottom surface, two spoiler side surfaces and a flowing surface.
Further, the spout is composed of four walls, and two ends of each wall are respectively provided with a disturbing fluid.
Further, the flow direction surface is of a curved surface structure.
Further, the flow direction surface is of an airfoil curved surface structure.
Further, a chamfer is arranged at the contact position of the side face of the turbulence body and the flow direction surface.
Further, the side surface of the turbulence body is connected with the flow direction surface at a right angle.
Further, the dimensional relationships among the fluid disruption, flow direction surface, spout and chamfer are:
L1＝L5×(0.5～1)；
L2＝L4×(0.02～0.1)；
L3＝L1×(0.05～0.2)；
R1＝L1×(1.5～3)；
R2＝L3×(0.001～0.5)；
wherein, the bottom surface of the turbulence body is L1 in length and L2 in width; the height from the bottom surface of the disturbing fluid to the highest position of the flow direction surface is L3; the radius of the curved surface of the flow direction surface is R1; the chamfer radius is R2; l4 is the spout width, L5 is the spout depth, and L6 is the spout height.
Further, the distance between the front end of the disturbing fluid and the outlet of the nozzle is L7, the distance between the side face of the disturbing fluid and the side wall of the adjacent nozzle is L8, and the distance between the side face of the disturbing fluid arranged on the side wall of the nozzle and the wall of the adjacent nozzle is L9;
the dimensional relationship between them is:
L7＝L5×(0～0.1)；
L8＝L4×(0.02～0.1)；
L9＝L6×(0.02～0.1)；
wherein L4 is the nozzle width, L5 is the nozzle depth, and L6 is the nozzle height.
The beneficial effects of the invention are as follows: the angle vortex generator conducts long-distance corner diversion on the jet airflow, changes the direction of vortex, damages a large-scale vortex structure generated by instability of a shearing layer, inhibits low-frequency pressure pulsation to a great extent, and can greatly reduce the low-frequency pressure pulsation of a wind tunnel; the angular vortex generator adopts a design that the flow direction surface is a long curved surface and is in a chamfer angle, so that high-frequency noise caused by multiple edges and angles on the appearance is avoided, and high-frequency background noise is not increased; the corner vortex generator is arranged at the end parts of the four walls of the nozzle, namely the contact positions of the four walls, so that the main body parts of the 4 walls above, below, left and right of the nozzle keep original appearance, and the damage of a large number of turbulence bodies in the circumferential direction of the nozzle to the flow field quality of the test measurement section is avoided; the laminar flow core area of the test can be ensured not to be reduced; the angular vortex generator is simple to install and not easy to damage, and can obtain high-precision and high-quality test results.
Drawings
FIG. 1 is a prior art wind tunnel nozzle rectangular vortex generator;
FIG. 2 is a prior art wind tunnel nozzle triangular vortex generator;
FIG. 3 is a schematic view of the overall structure of the angular vortex generator of the present invention;
FIG. 4 is a schematic view showing the structure of the angular vortex generator installed on the nozzle in a front view;
FIG. 5 is a schematic view of a spoiler according to the present invention;
FIG. 6 is a schematic diagram of a fluid-disturbing front view of the present invention;
FIG. 7 is a schematic top view of a spoiler according to the present invention;
FIG. 8 is a schematic cross-sectional view of a body housing of the present invention;
FIG. 9 is a comparison of pressure pulsation coefficients Cp before and after installation of the corner vortex generator in the embodiment;
FIG. 10 is a diagram showing the far field background noise SPL contrast before and after the installation of the corner vortex generator in the example;
FIG. 11 is a graph showing turbulence level comparisons before and after installation of the corner vortex generators in the examples;
FIG. 12 is an elevation view of the vortex generators mounted in a circumferential distribution of the nozzle;
FIG. 13 is a comparison of the circumferential distribution of the nozzle and the pressure pulsation coefficient Cp of the corner vortex generators in the example;
FIG. 14 is a comparison of the center static pressure pulsation coefficient Cp of a test section provided with a flexible spoiler and an angular vortex generator in the embodiment;
FIG. 15 is a far field background noise SPL contrast for an embodiment in which a deflector element and an angular vortex generator are installed;
in the figure: 1. the device comprises a disturbing fluid, 2, a nozzle, 11, a bottom surface of the disturbing body, 12, a flow direction surface, 13, a chamfer, 14 and a side surface of the disturbing body.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
As shown in fig. 3: a jet angle vortex generator for suppressing low-frequency pressure pulsation of jet wind tunnel is based on redesign of the shape design and distribution mode of vortex bodies and includes such steps as installing all the vortex bodies in jet
One device formed is called an angular vortex generator.
The angular vortex generator comprises a nozzle 2, wherein the nozzle 2 is surrounded by four walls, and the end parts of the four walls are connected end to end, so that a cuboid-shaped structure with two open ends is formed.
As shown in fig. 4: two turbulence bodies 1 are fixedly arranged on four walls of the nozzle 2, and specifically, two end positions of each wall are respectively provided with one turbulence body 1. The spoiler 1 includes a rectangular spoiler bottom 11, two spoiler sides 14, and a flow direction surface 12, in other words, as shown in fig. 5, the spoiler 1 includes a circular arc structure formed by the spoiler bottom 11, the spoiler sides 14, and the flow direction surface 12.
The flow direction surface 12 may be a curved surface structure or an airfoil-shaped curved surface structure.
The turbulence body 1 may have no chamfer (the side surface of the turbulence body is connected with the flow direction surface at right angles), and may also have a chamfer, where the chamfer is located at the contact position between the side surface 14 of the turbulence body and the flow direction surface 12.
The design of the profile of the disturbing fluid 11: as shown in fig. 3, 4 and 6 to 8, the dimensional relationships among the disturbing fluid 11, the flow direction surface 2, the spout 1 and the chamfer 13 are as follows:
L1＝L5×(0.5～1)；
L2＝L4×(0.02～0.1)；
L3＝L1×(0.05～0.2)；
R1＝L1×(1.5～3)；
R2＝L3×(0.001～0.5)；
wherein, the bottom surface of the turbulence body is L1 in length and L2 in width; the height from the bottom surface of the disturbing fluid to the highest position of the flow direction surface is L3; the radius of the curved surface of the flow direction surface is R1; the chamfer radius is R2; l4 is the spout width, L5 is the spout depth, and L6 is the spout height.
The installation and distribution mode of the angular vortex generator at the nozzle is designed: as shown in fig. 3 and fig. 4, the distance between the front end of the spoiler 1 and the outlet of the nozzle 2 is L7, the distance between the spoiler side 14 and the side wall adjacent to the nozzle 2 is L8, and the distance between the spoiler side 14 mounted on the side wall of the nozzle 2 and the wall adjacent to the nozzle 2 is L9;
the dimensional relationship between them is:
L7＝L5×(0～0.1)；
L8＝L4×(0.02～0.1)；
L9＝L6×(0.02～0.1)；
wherein L4 is the nozzle width, L5 is the nozzle depth, and L6 is the nozzle height.
As can be seen from fig. 9: the jet orifice without the vortex generator is compared with the pressure pulsation coefficient Cp before and after the jet orifice with the angular vortex generator, the angular vortex generator conducts long-distance diversion on jet orifice airflow, the original vortex direction is changed, a large-scale vortex structure generated by instability of a shearing layer is damaged, and low-frequency pressure pulsation is restrained to a great extent.
As can be seen from fig. 10: the far field background noise SPL around the installation angle vortex generator is compared, the suppression effect of the angle vortex generator is obvious, especially the wind speed used in wind tunnels is also the range of 60 m/s-70 m/s of the wind speed with strong pressure pulsation, the far field low frequency pressure pulsation amplitude reduction reaches 70% -80%, because the fluid surface of the angle vortex generator is designed into a long curved surface and a chamfer angle, the high frequency noise caused by polygonal edges and polygons on the appearance is avoided, and the background noise behind the installation angle vortex generator is not obviously increased.
As can be seen from fig. 11: because the angular vortex generators are distributed only at the corners of the jet opening, 8 angular vortex generators are installed, so that the main body parts of 4 walls above, below, left and right of the jet opening keep original appearance, and the damage of a large number of vortex bodies in the circumferential direction of the jet opening to the quality of the flow field of the test measuring section is avoided. As can be seen, the turbulence level after installation of the angular vortex generator is reduced overall in the range of 50m/s to 70m/s of the usual wind speed, especially at the test measurement center position (axial 5 m).
As shown in fig. 12: the vortex generators are distributed in the circumferential direction of the nozzle; as shown in fig. 13, the test section far-field pressure pulsation coefficient Cp of the circumferential distribution pattern and the corner portion pattern. Compared with circumferential distribution, the angular vortex generator has the advantages that the angular distribution mode of the angular vortex generator obviously weakens low-frequency pressure pulsation in the range of 60-70 m/s of wind speed with strong pressure pulsation. In addition, the number of the vortex generators is greatly reduced, so that the influence on the flow field quality and the sound field quality of the test section is obviously reduced.
As shown in fig. 14: and the nozzles are respectively provided with a flexible spoiler and a test section center static pressure pulsation coefficient Cp of the angular vortex generator for comparison. Compared with the flexible spoiler, the static pressure pulsation in the center of the test section is obviously reduced after the angle vortex generator is installed. In addition, the defect that the flexible material is easy to vibrate to excite pulsation of other frequency bands is avoided.
As shown in fig. 15: the jet nozzle is provided with a jet flow guiding unit and far-field background noise SPL of the angular vortex generator. Compared with the installation of the flow guiding unit, the installation of the angular vortex generator greatly reduces far-field background noise by 5-10 dB.
The above embodiments are provided for convenience of description of the present invention, and are not intended to limit the present invention in any way, and any person skilled in the art will make partial changes or modifications to the present invention without departing from the technical scope of the present invention.
Claims (6)
1. The utility model provides a jet angle vortex generator that suppresses opening jet wind tunnel low frequency pressure pulsation, includes spout (2), its characterized in that: two turbulence bodies (1) are fixedly arranged on each wall of the nozzle (2); the vortex body (1) is of an arc-shaped structure consisting of a rectangular vortex body bottom surface (11), two vortex body side surfaces (14) and a flow direction surface (12);
the nozzle (2) consists of four walls, and two ends of each wall are respectively provided with a turbulence body (1);
the distance between the front end of the turbulence body (1) and the outlet of the nozzle (2) is L7, the distance between the side surface (14) of the turbulence body and the side wall adjacent to the nozzle (2) is L8, and the distance between the side surface (14) of the turbulence body arranged on the side wall of the nozzle (2) and the wall adjacent to the nozzle (2) is L9;
the dimensional relationship between them is:
L7＝L5×(0～0 .1)；
L8＝L4×(0 .02～0 .1)；
L9＝L6×(0 .02～0 .1)；
wherein L4 is the nozzle width, L5 is the nozzle depth, and L6 is the nozzle height.
2. The jet angle vortex generator for suppressing low-frequency pressure pulsation of an open jet wind tunnel according to claim 1, wherein: the flow direction surface (12) is of a curved surface structure.
3. The jet angle vortex generator for suppressing low-frequency pressure pulsation of an open jet wind tunnel according to claim 1, wherein: the flow direction surface (12) is of an airfoil curved surface structure.
4. The jet angle vortex generator for suppressing low-frequency pressure pulsation of an open jet wind tunnel according to claim 1, wherein: a chamfer (13) is arranged at the contact position of the side surface (14) of the turbulence body and the flow direction surface (12).
5. The jet angle vortex generator for suppressing low-frequency pressure pulsation of an open jet wind tunnel according to claim 1, wherein: the side surface (14) of the turbulence body is connected with the flow direction surface (12) at a right angle.
6. The jet angle vortex generator for suppressing low-frequency pressure pulsation of an open jet wind tunnel according to claim 4, wherein: the dimensional relationship among the turbulence body (1), the flow direction surface (12), the nozzle (2) and the chamfer (13) is as follows:
L1＝L5×(0 .5～1)；
L2＝L4×(0 .02～0 .1)；
L3＝L1×(0 .05～0 .2)；
R1＝L1×(1 .5～3)；
R2＝L3×(0 .001～0 .5)；
wherein, the bottom surface of the turbulence body is L1 in length and L2 in width; the height from the bottom surface of the disturbing fluid to the highest position of the flow direction surface is L3; the radius of the curved surface of the flow direction surface is R1; the chamfer radius is R2; l4 is the spout width, L5 is the spout depth, and L6 is the spout height.
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| CN116242576B (en) * | 2023-05-11 | 2023-07-25 | 中国空气动力研究与发展中心低速空气动力研究所 | Floor suitable for open wind tunnel with floor test and open wind tunnel with floor |
| CN117740308B (en) * | 2024-02-19 | 2024-04-19 | 中国空气动力研究与发展中心高速空气动力研究所 | Jet micro-embedded turbulence method and device for controlling large-scale high-speed jet noise |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU1606743A1 (en) * | 1988-04-05 | 1990-11-15 | Завод-Втуз При Производственном Объединении Турбостроения "Ленинградский Металлический Завод" | Method of and diffuser for converting fluid stream energy |
| JP2003106715A (en) * | 2001-09-26 | 2003-04-09 | Kansai Electric Power Co Inc:The | Ice making method and ice making device by cancelling underwater supercooling |
| CN101067584A (en) * | 2007-06-14 | 2007-11-07 | 同济大学 | Opening back-flowing suppressing low-speed wind tunnel low-frequency buffeting ejector structure |
| CN101301931A (en) * | 2008-04-28 | 2008-11-12 | 全力 | Method and apparatus for manufacturing compound vortex and compound vortex aerocraft |
| CN103691351A (en) * | 2013-12-06 | 2014-04-02 | 中国矿业大学 | Jet flow self-absorption foaming agent parallel foaming system |
| CN105865742A (en) * | 2016-04-07 | 2016-08-17 | 中国空气动力研究与发展中心低速空气动力研究所 | Wind tunnel test aero-engine thrust vector jet pipe steering system |
| CN106404340A (en) * | 2016-12-19 | 2017-02-15 | 大友（苏州）风洞技术有限公司 | Wind tunnel collecting port |
-
2017
- 2017-09-20 CN CN201710855108.2A patent/CN107941450B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| SU1606743A1 (en) * | 1988-04-05 | 1990-11-15 | Завод-Втуз При Производственном Объединении Турбостроения "Ленинградский Металлический Завод" | Method of and diffuser for converting fluid stream energy |
| JP2003106715A (en) * | 2001-09-26 | 2003-04-09 | Kansai Electric Power Co Inc:The | Ice making method and ice making device by cancelling underwater supercooling |
| CN101067584A (en) * | 2007-06-14 | 2007-11-07 | 同济大学 | Opening back-flowing suppressing low-speed wind tunnel low-frequency buffeting ejector structure |
| CN101301931A (en) * | 2008-04-28 | 2008-11-12 | 全力 | Method and apparatus for manufacturing compound vortex and compound vortex aerocraft |
| CN103691351A (en) * | 2013-12-06 | 2014-04-02 | 中国矿业大学 | Jet flow self-absorption foaming agent parallel foaming system |
| CN105865742A (en) * | 2016-04-07 | 2016-08-17 | 中国空气动力研究与发展中心低速空气动力研究所 | Wind tunnel test aero-engine thrust vector jet pipe steering system |
| CN106404340A (en) * | 2016-12-19 | 2017-02-15 | 大友（苏州）风洞技术有限公司 | Wind tunnel collecting port |
Non-Patent Citations (2)
| Title |
|---|
| 俄罗斯的发动机进口流场畸变评定指南;刘大响, 叶培梁;燃气涡轮试验与研究(第03期);全文 * |
| 合成射流微扰动对后台阶湍流分离流动控制的实验研究;李斌斌;姚勇;姜裕标;黄勇;顾蕴松;程克明;;航空学报(第02期);全文 * |
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