CN101975652A - Ultrasonic-velocity free vortex wind tunnel - Google Patents
Ultrasonic-velocity free vortex wind tunnel Download PDFInfo
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- CN101975652A CN101975652A CN 201010551448 CN201010551448A CN101975652A CN 101975652 A CN101975652 A CN 101975652A CN 201010551448 CN201010551448 CN 201010551448 CN 201010551448 A CN201010551448 A CN 201010551448A CN 101975652 A CN101975652 A CN 101975652A
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Abstract
本发明提供了一种超声速自由旋涡风洞，包括：过渡段(1)，用于引入气流，并对气流进行第一级整流；稳定段(2)，连接在所述过渡段(1)的下游，用于对气流进行第二级整流；以及喷管实验段(3)，连接在所述稳定段(2)的下游，所述喷管实验段(3)的周壁形成有透明窗口，并包括：喷管部(31)，构造成自由旋涡喷管结构，将气流加速至超声速自由旋涡状态，以及实验部(32)，设置在所述喷管部(31)的下游，使风洞实验部入口气流的速度场满足超声速自由旋涡分布，从而在风洞中可以获得理想的超声速自由旋涡。
The invention provides a supersonic free vortex wind tunnel, comprising: a transition section (1), which is used to introduce airflow and perform first-stage rectification to the airflow; a stabilization section (2), connected to the transition section (1) Downstream, it is used to carry out second-stage rectification to the airflow; And the nozzle test section (3), connected to the downstream of the stable section (2), the peripheral wall of the nozzle test section (3) is formed with a transparent window, and Including: a nozzle part (31), configured as a free vortex nozzle structure, accelerating the airflow to a supersonic free vortex state, and an experiment part (32), arranged downstream of the nozzle part (31), to make wind tunnel experiments The velocity field of the inlet airflow satisfies the supersonic free vortex distribution, so that the ideal supersonic free vortex can be obtained in the wind tunnel.
Description
Technical field
The present invention relates to a kind of wind-tunnel, relate in particular to a kind of supersonic speed free-vortex wind-tunnel.
Background technology
Development along with modern aeromechanics technology, the mechanism of aerodynamics Study on Problems is more and more important, as typically being flowed to compressible the flowing that curvature influences, the research of supersonic speed free-vortex not only has broad application background but also has the most important theories meaning.
Supersonic speed free-vortex velocity field satisfies free-vortex and distributes, and promptly the product of flowing velocity and flow curvature radius is a constant.Because flowing velocity is higher, its flow field has non-permanent and multiple dimensioned feature, the constant flow imaging technique is the important means of these features of research, it needs the free-vortex wind-tunnel to have the good optical measurement environment, and corresponding wind-tunnel optical window need design at the characteristics of research object.
Monograph " supersonic speed free-vortex aerodynamic window's and optical quality thereof " (Yi Shi and etc., publishing house of the National University of Defense technology, 2005) the free-vortex jet pipe method for designing (a kind of typical non-uniform flow jet pipe) found the solution based on the subregion of shortest length jet pipe (MLN) has been proposed, this method design process is as follows:
1) adopt the MLN method for designing to obtain a symmetrical jet pipe profile curve;
2) flow parameter on extraction MLN nozzle exit border is as asymmetric section inlet boundary condition;
3) be divided into several zones such as equal uniform flow district, simple wave district and non-simple wave district with asymmetric section; And
4) utilize free-vortex relational expression, Prandtl-mayer's relation and mass conservation relation to determine the wall curve in asymmetric district.
Adopt this method can access needed free-vortex jet pipe profile curve, numerical value checking result shows that designed jet pipe profile can generate needed free-vortex flow field.
Though the method for designing of existing free-vortex aerodynamic window's does not also have corresponding free-vortex wind-tunnel design proposal at present.
Prior art is mainly emphasized the profile design of free-vortex jet pipe and the design of free-vortex aerodynamic window's, can't directly expand to the design of free-vortex wind-tunnel.
Also there are some deficiencies in existing wind-tunnel designing technique for the research of supersonic speed flow mechanism: the one, and incoming flow turbulivity height, the 2nd, the optic test environment is relatively poor, be difficult to observe jet pipe internal edges interlayer, the 3rd, flox condition is not ideal enough, when especially paying close attention to two-dimensional flow field, sidewall disturbs the three-dismensional effect of bringing obvious.
Summary of the invention
The technical problem to be solved in the present invention provides a kind of wind tunnel device that produces supersonic speed free-vortex flow field, and the free-vortex relational expression is satisfied in this wind tunnel experiment section flow field, and is convenient to the enforcement of optics non-contact testing technology.
For solving the problems of the technologies described above, the invention provides a kind of supersonic speed free-vortex wind-tunnel, it is characterized in that comprise: transition section is used to introduce air-flow; Stable section is connected the downstream of transition section, because steady air flow reduces aerodynamic noise; And jet pipe experimental section, be connected the downstream of stable section, the perisporium of jet pipe experimental section is formed with transparent window, and comprise: spout portion, be configured to the free-vortex nozzle structure, accelerate to supersonic speed free-vortex state with the air-flow in the future self-stabilization section, and experiment portion, be arranged on the downstream of spout portion.
Further, supersonic speed free-vortex wind-tunnel also comprises diffuser, has the inner-cavity structure that shrinks along towards downstream direction.
Further, the xsect of transition section is by the change shape of circular contour to the rectangular profile transition from the upstream extremity downstream end.
Further, the xsect of stable section is rectangular, comprises the periphery wall that parallels and internal perisporium and two sidewalls that are connected described periphery wall and internal perisporium.
Further, the xsect of jet pipe experimental section is rectangular, and perisporium comprises periphery wall with internal perisporium and be connected periphery wall and two sidewalls of internal perisporium, and periphery wall and internal perisporium form free-vortex jet pipe profile curve.
Further, the ratio of width to height of jet pipe experimental section is greater than 4.
Further, four perisporiums of the experiment portion of jet pipe experimental section all are formed with transparent window.
Further, transparent window extends in the perisporium in spout portion zone.
Further, on the wall of jet pipe experimental section the FLOW CONTROL panel can also be set.
Further, also comprise fairing in the stable section, fairing comprises honeycomb and husky net.
The present invention has following technique effect:
1. by a spout portion and experiment portion are set in the jet pipe experimental section of wind-tunnel, and make this spout portion be configured to the free-vortex nozzle structure, on the perisporium of experiment portion, be formed with transparent window, thereby the supersonic speed free-vortex flow field that in wind-tunnel, can obtain, and can pass through transparent window, realize the free-vortex flow field in the wind-tunnel is observed and the optics non-contact testing.
2. the ratio of width to height of jet pipe experimental section is set to greater than 4, is preferably greater than 5, connects the gas viscosity effect of sidewall about can eliminating effectively to the free-vortex influence on flow field, to obtain desirable flow field fluidised form.
3. by transparent window is extended in the perisporium in described spout portion zone, can observe formation front and back evolution process all sidedly with the research freedom swirling flow field.
4. be provided with optical glass by four perisporiums, can adopt optics non-contact testing technology to observe the flow field better at the jet pipe experimental section.
Except purpose described above, feature and advantage, the present invention also has other purpose, feature and advantage.With reference to figure, the present invention is further detailed explanation below.
Description of drawings
Accompanying drawing is used to provide further understanding of the present invention, constitutes the application's a part, and illustrative examples of the present invention and explanation thereof are used to explain the present invention, do not constitute improper qualification of the present invention.In the accompanying drawings:
Fig. 1 shows the one-piece construction synoptic diagram of supersonic speed free-vortex wind-tunnel of the present invention.
Embodiment
Below in conjunction with accompanying drawing embodiments of the invention are elaborated, but the multitude of different ways that the present invention can be defined by the claims and cover is implemented.
Alleged herein periphery wall is meant the perisporium that is positioned in the construction of wind tunnel than the distally for position, free-vortex center, internal perisporium is meant the perisporium that is positioned in the construction of wind tunnel than nearside for position, free-vortex center.
As shown in Figure 1, according to supersonic speed free-vortex wind-tunnel of the present invention, comprise: preceding transition section 1, be used to introduce air-flow, and air-flow carried out first order rectification, the irregular airflow flowing in the external world is made it to form the air-flow with certain flow characteristics by preceding transition section 1, get ready for it enters stable section 2; Stable section 2 is connected the downstream of transition section 1, is used for the air-flow that the past transition section 1 flows into is wherein carried out second level rectification, makes air-flow form the needed flow characteristics of experiment, and air-flow is entered in the jet pipe experimental section 3 so that experimentize; Jet pipe experimental section 3 is connected the downstream of stable section 2, its perisporium is formed with transparent window, and comprise: spout portion 31, spout portion 31 is configured to the free-vortex nozzle structure, the air-flow of self-stabilization section 2 accelerates to the free-vortex state in the future, can make the velocity field of wind tunnel experiment portion inlet air flow satisfy the distribution of supersonic speed free-vortex; Experiment portion 32 is positioned at the downstream of spout portion 31, and is preferably integrally formed with spout portion.By the transparent window of jet pipe experimental section 3, can adopt optics non-contact testing technology that the free-vortex flow field that forms in the jet pipe experimental section is observed.In order to carry out better optics non-contact testing, so that the characteristic in supersonic speed free-vortex flow field is studied, preferably, on four perisporiums of jet pipe experimental section, all be formed with transparent window, wall all is equipped with optical glass, transparent window extends in the perisporium in spout portion 31 zones, so that observe all sidedly and the evolution process of the formation front and back of research freedom swirling flow field.
Be provided with diffuser 4 in the downstream of jet pipe experimental section 3, have the inner-cavity structure that shrinks along towards downstream direction.Diffuser 4 can to carry out diffusion energy-conservation to enter wherein the air-flow of having debugged in jet pipe experimental section 3, and improving the startability of wind-tunnel, and the air-flow after will handling is sent into the next one stage.
In the present embodiment, the xsect of the transition section 1 of supersonic speed free-vortex wind-tunnel is by the change shape of circular contour to the rectangular profile transition from the upstream extremity downstream end.The porch circular contour can be connected with the circular air outlet of outside blowing device easily.If the air outlet of outside blowing device is a rectangle, then the transition section upstream extremity only need dispose corresponding rectangular profile and gets final product.The downstream end that transition section 1 is connected with stable section 2 forms rectangular profile, can well be connected with the rectangular profile of stable section 2.
The xsect of stable section 2 is rectangular, comprises that the periphery wall that parallels with internal perisporium and be connected periphery wall and two sidewalls of internal perisporium, can make stable therein the flowing of gas that enters from transition section 1.The xsect of jet pipe experimental section 3 is rectangular, comprise that periphery wall is with internal perisporium and be connected periphery wall and two sidewalls of internal perisporium, periphery wall and internal perisporium form free-vortex jet pipe profile curve, can make the air-flow that enters from stable section 2 form supersonic speed free-vortex flow field along free-vortex jet pipe profile curve.
In order to overcome the existing relatively poor problem of Flow Field in Wind Tunnel two-dimensional characteristics, the ratio of width to height of jet pipe experimental section 3 of the present invention (promptly, wide and high ratio, mean the ratio of width to height of passage in the jet pipe experimental section, can recently calculating according to distance between the sidewall of the left and right sides and the distance between the internal and external peripheral wall) greater than 4, connect the gas viscosity effect of sidewall about can eliminating effectively to the free-vortex influence on flow field, to obtain desirable flow field fluidised form.Preferably, its ratio of width to height can be set to more than or equal to 5.
As a preferred embodiment of the present invention, comprise fairing in the stable section 2, fairing comprises honeycomb and husky net, and honeycomb can effectively suppress the horizontal pulsation of incoming flow, and it is the small scale vortex that husky net can make the large scale vortex cracked.The whole processing of jet pipe experimental section profile global design to optimize the jet pipe curve, reduces the jet pipe boundary layer thickness, and clutter reduction produces.
When carrying out boundary layer research, on the supersonic speed free-vortex wind tunnel nozzle experimental section wall FLOW CONTROL panel 33 can also be set, can change its surface texture structure (superficial makings that comprises overall region or regional area, the bearing of trend of roughness, the picture on surface whether striped or other shapes are arranged, striped or other patterns etc. for example) realizes fluidised form control, for example can adopt hyperfine machining control roughness.
By foregoing description as can be known, according to supersonic speed free-vortex wind-tunnel of the present invention, realized that the velocity field of wind tunnel experiment portion inlet air flow satisfies the distribution of supersonic speed free-vortex, thereby in wind-tunnel, can obtain desirable supersonic speed free-vortex flow field; Connect the gas viscosity effect of sidewall about can eliminating effectively to the free-vortex influence on flow field, to obtain desirable flow field fluidised form; Can observe formation front and back evolution process all sidedly with the research freedom vortex; Can realize controllable flow field fluidised form, flow field quality is good, and two-dimensional characteristics is good.
The above is the preferred embodiments of the present invention only, is not limited to the present invention, and for a person skilled in the art, the present invention can have various changes and variation.Within the spirit and principles in the present invention all, any modification of being done, be equal to replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (10)
1. a supersonic speed free-vortex wind-tunnel is characterized in that, comprising:
Transition section (1) is used to introduce air-flow, and air-flow is carried out first order rectification;
Stable section (2) is connected the downstream of described transition section (1), is used for air-flow is carried out second level rectification; And
Jet pipe experimental section (3) is connected the downstream of described stable section (2), and the perisporium of described jet pipe experimental section (3) is formed with transparent window, and comprises:
Spout portion (31) is configured to the free-vortex nozzle structure, will accelerating to supersonic speed free-vortex state from the air-flow in the described stable section (2), and
Experiment portion (32) is arranged on the downstream of described spout portion (31).
2. supersonic speed free-vortex wind-tunnel according to claim 1 is characterized in that, also comprises diffuser (4), has the inner-cavity structure that shrinks along towards downstream direction.
3. supersonic speed free-vortex wind-tunnel according to claim 1 is characterized in that the xsect of described transition section (1) is by the change shape of circular contour to the rectangular profile transition from the upstream extremity downstream end.
4. supersonic speed free-vortex wind-tunnel according to claim 1 is characterized in that the xsect of described stable section (2) is rectangular, comprises the periphery wall that parallels and internal perisporium and two sidewalls that are connected described periphery wall and internal perisporium.
5. supersonic speed free-vortex wind-tunnel according to claim 1, it is characterized in that, the xsect of described jet pipe experimental section (3) is rectangular, its described perisporium comprises periphery wall and internal perisporium and two sidewalls that are connected described periphery wall and internal perisporium, and described periphery wall and internal perisporium form free-vortex jet pipe profile curve.
6. supersonic speed free-vortex wind-tunnel according to claim 5 is characterized in that the ratio of width to height of described jet pipe experimental section (3) is greater than 4.
7. supersonic speed free-vortex wind-tunnel according to claim 5 is characterized in that, four perisporiums of the experiment portion of described jet pipe experimental section (3) all are formed with transparent window.
8. supersonic speed free-vortex wind-tunnel according to claim 5 is characterized in that, described transparent window extends in the perisporium in described spout portion (31) zone.
9. supersonic speed free-vortex wind-tunnel according to claim 1 is characterized in that, FLOW CONTROL panel (33) can also be set on the wall of described jet pipe experimental section.
10. according to each described supersonic speed free-vortex wind-tunnel among the claim 1-9, it is characterized in that also comprise fairing (22) in the described stable section (2), described fairing (22) comprises honeycomb and husky net.
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| CN201010551448A CN101975652B (en) | 2010-11-18 | 2010-11-18 | Ultrasonic-velocity free vortex wind tunnel |
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| CN201010551448A CN101975652B (en) | 2010-11-18 | 2010-11-18 | Ultrasonic-velocity free vortex wind tunnel |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102998084A (en) * | 2012-12-28 | 2013-03-27 | 中国人民解放军国防科学技术大学 | Hypersonic velocity spray pipe structure |
| CN102998085A (en) * | 2012-12-31 | 2013-03-27 | 中国人民解放军国防科学技术大学 | Mixing spray pipe runner wall face determination method, mixing spray pipe and supersonic speed mixing wind tunnel |
| CN103115027A (en) * | 2013-02-05 | 2013-05-22 | 中国人民解放军国防科学技术大学 | Supersonic velocity circular flow nozzle with injector |
| CN106218845A (en) * | 2016-08-29 | 2016-12-14 | 清华大学 | A kind of suction passage of hydraulic jet propulsion system |
| CN108240898A (en) * | 2016-12-23 | 2018-07-03 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of impulse type wind-tunnel tandem jet pipe |
| CN108956082A (en) * | 2018-09-20 | 2018-12-07 | 中国空气动力研究与发展中心超高速空气动力研究所 | A kind of rectangular nozzle |
| CN109372637A (en) * | 2018-12-16 | 2019-02-22 | 中国航发沈阳发动机研究所 | A kind of gas turbine exhaust flow path designs method |
| CN109630219A (en) * | 2018-12-16 | 2019-04-16 | 中国航发沈阳发动机研究所 | A kind of gas turbine exhaust |
| CN109655271A (en) * | 2018-12-27 | 2019-04-19 | 南京航空航天大学 | A kind of single pair hypersonic flow is to vortex generating device |
| CN109815549A (en) * | 2018-12-27 | 2019-05-28 | 南京航空航天大学 | A design method for a single pair of supersonic flow vortex generators |
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Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102998084A (en) * | 2012-12-28 | 2013-03-27 | 中国人民解放军国防科学技术大学 | Hypersonic velocity spray pipe structure |
| CN102998084B (en) * | 2012-12-28 | 2015-01-21 | 中国人民解放军国防科学技术大学 | Hypersonic velocity spray pipe structure |
| CN102998085A (en) * | 2012-12-31 | 2013-03-27 | 中国人民解放军国防科学技术大学 | Mixing spray pipe runner wall face determination method, mixing spray pipe and supersonic speed mixing wind tunnel |
| CN102998085B (en) * | 2012-12-31 | 2015-12-09 | 中国人民解放军国防科学技术大学 | Mixing jet tube runner wall defining method, mixing jet tube and mixed supersonic wind-tunnel |
| CN103115027A (en) * | 2013-02-05 | 2013-05-22 | 中国人民解放军国防科学技术大学 | Supersonic velocity circular flow nozzle with injector |
| CN103115027B (en) * | 2013-02-05 | 2015-09-16 | 中国人民解放军国防科学技术大学 | Supersonic velocity circular flow nozzle with injector |
| CN106218845A (en) * | 2016-08-29 | 2016-12-14 | 清华大学 | A kind of suction passage of hydraulic jet propulsion system |
| CN106218845B (en) * | 2016-08-29 | 2018-06-15 | 清华大学 | A kind of suction passage of hydraulic jet propulsion system |
| CN108240898A (en) * | 2016-12-23 | 2018-07-03 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of impulse type wind-tunnel tandem jet pipe |
| CN108956082A (en) * | 2018-09-20 | 2018-12-07 | 中国空气动力研究与发展中心超高速空气动力研究所 | A kind of rectangular nozzle |
| CN109372637A (en) * | 2018-12-16 | 2019-02-22 | 中国航发沈阳发动机研究所 | A kind of gas turbine exhaust flow path designs method |
| CN109630219A (en) * | 2018-12-16 | 2019-04-16 | 中国航发沈阳发动机研究所 | A kind of gas turbine exhaust |
| CN109630219B (en) * | 2018-12-16 | 2022-03-04 | 中国航发沈阳发动机研究所 | Gas turbine exhaust apparatus |
| CN109655271A (en) * | 2018-12-27 | 2019-04-19 | 南京航空航天大学 | A kind of single pair hypersonic flow is to vortex generating device |
| CN109815549A (en) * | 2018-12-27 | 2019-05-28 | 南京航空航天大学 | A design method for a single pair of supersonic flow vortex generators |
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