CN101975653A - Supersonic-speed axisymmetric mixing layer wind tunnel - Google Patents
Supersonic-speed axisymmetric mixing layer wind tunnel Download PDFInfo
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Abstract
The invention provides a supersonic-speed axisymmetric mixing layer wind tunnel which is characterized by comprising a transition section (1), a stabilization section (2) and a spray pipe experimental section (3), wherein the transition section is used for introducing an airflow; the stabilization section is provided with a first partition board (21) which divides the introduced airflow into two airflows; the spray pipe experimental section is connected at the downstream part of the stabilization section (2) and forms a fan-shaped axisymmetric structure relative to an axis (O) of revolution; the cross section of the peripheral wall of the spray pipe experimental section (3) is in a sector ring shape; a transparent window is formed on the peripheral wall; a spray pipe part (31) and a mixing experimental section (32) are formed on the spray pipe experimental section (3); and a second partition board (33) is arranged in the spray pipe part and the mixing experimental section is used for forming an axisymmetric mixing layer. By using the supersonic-speed axisymmetric mixing layer wind tunnel, the supersonic-speed axisymmetric mixing layer flow field of a totally-circular flow channel can be simulated and implementing the optical non-contact testing technology becomes convenient.
Description
Technical field
The present invention relates to a kind of wind-tunnel, relate in particular to a kind of supersonic speed axisymmetric mixing layer wind-tunnel.
Background technology
The supersonic speed axisymmetric mixing layer is meant that the moving different coaxial high velocity air of parameter of two plumes mixes the flow field structure that forms in freedom or restricted clearance, extensively be present in the flow fields such as Pneumatic air adjusting of scramjet engine, supersonic speed injector, high-speed missile air curtain cooling optical window and high-energy laser, related flow stability, change twist, vortex structure interacts and problem such as turbulent flow far beyond incompressible mixolimnion complexity, correlative study demands urgently carrying out in a deep going way.
Wind-tunnel is the important device that produces the supersonic speed axisymmetric mixing layer.Owing to there is instability, any small sample perturbations on wind-tunnel border all may change the flow field structure of mixolimnion, cause changeing twisting in advance and take place, even in the relatively poor wind-tunnel of incoming flow flow field quality, come laminar boundary layer and experimental section wall itself just to have the disturbance of various frequencies, this is very disadvantageous for research mixolimnion flow field structure.The supersonic speed axisymmetric mixing layer has three-dimensional, non-permanent and multiple dimensioned feature, the constant flow imaging technique is the important means of these features of research, it needs the mixolimnion wind-tunnel to have the good optical measurement environment, and corresponding wind-tunnel optical window need design at the characteristics of research object.
The PhD dissertation of Stanford University " An experimental investigation of highcompressibility mixing layers.T.Rossmann; 2001 " is extensively being used for reference on the basis of existing mixolimnion wind-tunnel design experiences, has proposed the compressible mixolimnion wind-tunnel based on shock tube and high pressure tank driving.The flow at high speed of this wind-tunnel is driven by shock tube, and low speed flows by the supply of aluminum gas-holder, is typical blow down wind tunnel.In order to produce mixolimnion, the upper and lower wall of wind tunnel nozzle section is respectively the high, low speed jet pipe wall, produces the different air-flow of Mach number thereby utilize demarcation strip to separate at nozzle exit between the two.Jet pipe does not have sticking wall curve and adopts the method for characteristic design, and the experimental formula correction is adopted in the influence in boundary layer.The nozzle section downstream directly connects test chamber, and it is of a size of, and 10cm is wide, 40cm is high, 1.2m is long.Because former shock tube is the drive system of a gun wind tunnel, corresponding mixolimnion wind tunnel nozzle and experimental section are actual to be to be placed in the experimental section of this gun wind tunnel.
AIAA report " A.D.Cutler; Supersonic Coaxial Jet Experiment forCFD Code Validation; AIAA-99-3588; 1999 " has proposed a kind of coaxial jet experimental provision, this device is made of inside and outside two-layer coaxial jet pipe, interior outer nozzle Mach number is 1.8, but because the inner nozzle stagnation temperature is higher, corresponding flowing velocity is bigger.Inner nozzle diameter 10.0mm, outer nozzle diameter 60.47mm, jet pipe gas directly is discharged in the atmosphere.
Therefore, lack the wind-tunnel of specializing in axisymmetric mixing layer in the prior art; Coaxial jet device in the known technology, the turbulivity height, outlet is influenced by free atmosphere; In the wind tunnel test of reality, the optic test environment is relatively poor, has had a strong impact on to use the observation of optics non-contact testing technology to whole flow field.
Summary of the invention
The technical problem to be solved in the present invention provides a kind of wind-tunnel that produces the supersonic speed axisymmetric mixing layer, is used to the exhibition of studying to the influence of curvature to mixed supersonic laminar flow field structure, 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 axisymmetric mixing layer wind-tunnel, comprising: transition section is used to introduce air-flow; Stable section is connected the downstream of transition section, has first demarcation strip, and the inner chamber of stable section is divided into epicoele and cavity of resorption, and the air-flow that is used for introducing is divided into two strands of air-flows; And jet pipe experimental section, be connected the downstream of stable section, and be fan-shaped axially symmetric structure with respect to a rotation, the xsect of the perisporium of combined experiments portion is fan-shaped ring, be formed with transparent window on the perisporium, perisporium comprises periphery wall, internal perisporium and two sidewalls that connect periphery wall and internal perisporium, the jet pipe experimental section is formed with: spout portion, wherein be provided with second demarcation strip, accelerating to the supersonic speed state respectively from two strands of air-flows in epicoele and the cavity of resorption, and combined experiments portion, be arranged on the downstream of spout portion, be used to mix two strands of air-flows of supersonic speed state to form axisymmetric mixing layer.
Further, supersonic speed axisymmetric mixing layer wind-tunnel also comprises diffuser, has the inner-cavity structure that shrinks along towards downstream direction.
Further, above-mentioned supersonic speed axisymmetric mixing layer wind-tunnel also comprises middle transition section, be connected between stable section and the jet pipe experimental section, the cross sectional shape of its passage carries out the transition to the cross sectional shape corresponding with the jet pipe experimental section of downstream end from the cross sectional shape corresponding with the stable section of upstream extremity, is formed with the 3rd demarcation strip that is connected first demarcation strip and second demarcation strip in the middle transition section.
Further, second demarcation strip of above-mentioned supersonic speed axisymmetric mixing layer wind-tunnel, first demarcation strip and be connected the 3rd demarcation strip between this two and continue landform mutually and be integral the median septum structure.
Further, second demarcation strip is removably disposed in the described jet pipe experimental section.
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.
Further, form the first jet pipe expansion limit one of in periphery wall and the internal perisporium, the rotation bus of the wall relative rotation axi line on the first jet pipe expansion limit is the first jet pipe profile curve, in periphery wall and the internal perisporium another forms the unexpansive limit of jet pipe, and the wall on this unexpansive limit of jet pipe is a straight line along the rotation bus of rotation direction.
Further, second demarcation strip in the spout portion forms the second jet pipe expansion limit, and the wall on this second jet pipe expansion limit is the second jet pipe profile curve with respect to the rotation bus of rotation.
Further, the wall on the unexpansive limit of jet pipe is the cylinder or the conical surface.
Further, each perisporium of jet pipe experimental section is integrally formed, thereby the wall on the wall on jet pipe expansion limit and the unexpansive limit of jet pipe all forms the continuous wall of one.
Further, the Zhou Jing of the channel cross-section of jet pipe experimental section is than t 〉=3, wherein t determines according to following formula: t=c '/r ', and wherein c ' is the circumferential lengths of the unexpansive limit of outside nozzle wall, r ' is the space length between outside nozzle unexpansive limit wall and the expansion limit wall.
Further, be formed with transparent window on the periphery wall of jet pipe experimental section and in the internal perisporium one or two, be formed with transparent window on one or two in two sidewalls.
Further, transparent window extends to the subsonic speed section region of spout portion forward.
Further, the downstream end of second demarcation strip of jet pipe experimental section is formed with tiltedly and splits.
Further, tiltedly split the most advanced and sophisticated edge that has the transitional surface that is cambered surface or plane inclination and form by transitional surface.
Further, be provided with total voltage regulator in the epicoele of stable section, total voltage regulator is double-deck orifice plate, carries out the change of runner and the adjusting of incoming flow stagnation pressure by the degree of misalignment of adjusting two orifice plates.
Further, also comprise the leap epicoele that is positioned at total voltage regulator downstream and the fairing of cavity of resorption in the stable section, fairing comprises honeycomb and husky net.
The present invention has following technique effect:
1. the flow field structure of annular channel is difficult to observe by optics non-contact testing technology, the present invention is configured to be fan-shaped axially symmetric structure with respect to a rotation (O) by the jet pipe experimental section with wind-tunnel, make the xsect of the perisporium of described combined experiments portion be fan-shaped ring, and on perisporium, be formed with transparent window, so both can simulate the superfield speed axisymmetric flow field of loopful runner, be convenient to implement optics non-contact testing technology again.
2. owing in the spout portion of jet pipe experimental section, be provided with demarcation strip, thereby can generate two supersonic flows in spout portion, thereby in the flow field of combined experiments portion formation supersonic speed axisymmetric mixing layer, to realize research to the flow field characteristic of supersonic speed axisymmetric mixing layer.
3. the middle transition section 5 of section transitions is set between described stable section 2 and described jet pipe experimental section 3, can makes the air-flow of stable section enter the jet pipe experimental section reposefully, thereby help generating desirable axisymmetric mixing layer flow field fluidised form.
4. the Zhou Jing of jet pipe experimental section ratio is set to greater than 3, is preferably greater than 4, and the boundary layer that connects sidewall about can eliminating effectively is beneficial to obtain desirable flow field fluidised form to the mixolimnion influence on flow field.
5. each perisporium of jet pipe experimental section is integrally formed, thereby the wall on the wall on described jet pipe expansion limit and the unexpansive limit of jet pipe all forms the continuous wall of one, thereby the whole jet pipe wall curvature of face is continuous, helps the whole flow field wave absorption.
6. the present invention adopts the jet pipe experimental section of sector crosssection, thereby simulates loopful shape runner by the part annular channel, has saved the processing funds, has reduced wind tunnel flow rate, has saved testing expenses.
7. second demarcation strip is removably to be provided with, thereby by changing second demarcation strip, can realize mixolimnion is controlled.
8. the transparent window of described jet pipe experimental section upstream extends to the subsonic speed zone of described spout portion from described combined experiments portion, more preferably, can upstream extend to the inlet of spout portion always, be convenient to adopt of the observation of optics non-contact testing technology like this whole flow field.
9. the downstream end by second demarcation strip in the jet pipe experimental section is provided with to change and twists portion, can realize controllable flow field fluidised form, and the mixolimnion flow field quality is good, and two-dimensional characteristics is good.
10. tiltedly split the most advanced and sophisticated edge that has transitional surface and be positioned at downstream end, help eliminating the mixolimnion shock wave.
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 axisymmetric mixing layer wind-tunnel of the present invention;
Fig. 2 is the perspective view of analysing and observe of the supersonic speed axisymmetric mixing layer wind-tunnel among Fig. 1;
Fig. 3 is the perspective view of the jet pipe experimental section of the supersonic speed axisymmetric mixing layer wind-tunnel among Fig. 1;
Fig. 4 is the 6 kind configuration synoptic diagram of the spout portion of jet pipe experimental section along the longitudinal profile of rotation, wherein not shown second demarcation strip.
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 the rotation of jet pipe experimental section, internal perisporium is meant the perisporium that is positioned in the construction of wind tunnel than nearside for this rotation.
Referring to Fig. 1, Fig. 2, show according to a kind of supersonic speed axisymmetric mixing layer 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, and 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, to enter stable section 2 ready for it; Stable section 2, be connected the downstream of transition section 1, have first demarcation strip 21, the inner chamber of stable section 2 is divided into epicoele 201 and cavity of resorption 202, the air-flow that is used for introducing is divided into two strands of air-flows, and two strands of air-flows after will separating are sent in the jet pipe experimental section 3 so that experimentize; And jet pipe experimental section 3, be connected the downstream of stable section 2, and be fan-shaped axially symmetric structure with respect to a rotation O, make the supersonic speed axisymmetric mixing layer wind-tunnel of present embodiment can simulate the supersonic speed axisymmetric flow field of loopful runner.
The xsect of the perisporium of jet pipe experimental section 3 is fan-shaped ring, be formed with transparent window on the perisporium, perisporium comprises periphery wall 3a, internal perisporium 3b and two sidewall 3c that connect periphery wall 3a and internal perisporium 3b, 3d, comprise: spout portion 31, wherein be provided with second demarcation strip 33, accelerating to the supersonic speed state respectively from two strands of air-flows in epicoele 201 and the cavity of resorption 202, can make the velocity field of two strands of air-flows of wind-tunnel combined experiments portion inlet all satisfy the Supersonic Gas distributions, thereby in the flow field of combined experiments portion formation supersonic speed axisymmetric mixing layer, to realize research to the flow field characteristic of supersonic speed axisymmetric mixing layer; And combined experiments portion 32, two strands of air-flows that are used to mix the supersonic speed state to be forming axisymmetric mixing layer, thereby can obtain desirable supersonic speed axisymmetric mixing layer in wind-tunnel, so that the flow field characteristic of supersonic speed axisymmetric mixing layer is studied.
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.
Because the architectural characteristic of jet pipe experimental section 3, transition section 5 between stable section 2 and jet pipe test section 3, also being provided with, the cross sectional shape of its passage carries out the transition to the cross sectional shape corresponding with the jet pipe experimental section 3 of downstream end from the cross sectional shape corresponding with the stable section 2 of upstream extremity, can make the air-flow of stable section 2 enter jet pipe experimental section 3 reposefully, thereby help generating desirable axisymmetric mixing layer flow field fluidised form.Also be formed with the 3rd demarcation strip 51 that is connected first demarcation strip 21 and second demarcation strip 33 in the middle transition section 5.This structure of middle transition section 5 makes stable section 2 and jet pipe experimental section 3 need not to be provided with transition section, need not influence original structure, can guarantee stable the carrying out of testing.Middle transition section 5 can be processed separately again, has complicated process structure when having avoided in stable section 2 or jet pipe experimental section 3, this transition section being set, improved difficulty of processing, increased the appearance of problems such as cost, can make the air-flow of stable section 2 enter jet pipe experimental section 3 reposefully, thereby help generating desirable axisymmetric mixing layer flow field fluidised form.In a unshowned embodiment, also be provided with the back transition section between jet pipe experimental section 3 and the diffuser 4, the cross sectional shape of this transition section passage carries out the transition to the cross sectional shape corresponding with the diffuser 4 of downstream end from the cross sectional shape corresponding with the jet pipe experimental section 3 of upstream extremity, make jet pipe experimental section 3 more natural with being connected of diffuser 4, also reduce difficulty of processing, improved experimental precision.
Supersonic speed axisymmetric mixing layer wind-tunnel in the present embodiment, its second demarcation strip 33, first demarcation strip 21 and be connected the 3rd demarcation strip 51 between this two and continue landform mutually and be integral the median septum structure, when the dependency structure on the median septum being adjusted in order to satisfy the different experiments needs, can easily mounted median septum be removed, and change the outfit and be adjusted into the median septum of desired structure, can improve conventional efficient effectively, save time.Further, second demarcation strip 33 is removably disposed in the jet pipe experimental section 3, since the importance of second demarcation strip 33 and in order to satisfy the experiment needs to having specific (special) requirements on its structure, therefore, separately second demarcation strip 33 removably is provided with, can realize mixolimnion is controlled, adding man-hour, also can process, simplify processing technology, save machining period different parts, simultaneously, even second demarcation strip 33 goes wrong, also only need change itself, other parts still can be continued to use.
In the present embodiment, the xsect of the transition section 1 of supersonic speed axisymmetric mixing layer 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.
In a unshowned embodiment, can also be provided with the 4th demarcation strip in the inner chamber of transition section 1, the inner chamber of described transition section 1 is divided into epicoele and cavity of resorption.Can be respectively applied for the gas that feeds different medium in the epicoele of transition section and the cavity of resorption, to satisfy different requirement of experiment.
In the jet pipe experimental section 3, form the first jet pipe expansion limit one of among periphery wall 3a and the internal perisporium 3b, the rotation bus of the wall relative rotation axi line on the first jet pipe expansion limit is the first jet pipe profile curve L1, among periphery wall 3a and the internal perisporium 3b another forms the unexpansive limit of jet pipe, and the wall on this unexpansive limit of jet pipe is straight line L2 along the rotation bus of rotation direction.Second demarcation strip 33 in the spout portion 31 forms the second jet pipe expansion limit, and the wall on this second jet pipe expansion limit is the second jet pipe profile curve with respect to the rotation bus of rotation.The wall on the unexpansive limit of jet pipe is the cylinder or the conical surface.Each perisporium of jet pipe experimental section 3 is integrally formed, thereby the wall on the wall on jet pipe expansion limit and the unexpansive limit of jet pipe all forms the continuous wall of one, thereby the whole jet pipe wall curvature of face is continuous, helps the whole flow field wave absorption.
Again referring to Fig. 4, it is depicted as the 6 kind configurations of jet pipe experimental section along the longitudinal profile of rotation, be marked with (a) and (b), (c), (d), (e), (f) respectively, from this 6 kinds of configurations, can see, the periphery wall 3a and second demarcation strip 33 are formed after the rotation of rotation O direction by bus separately respectively, internal perisporium 3b is cylindrical or conical, periphery wall 3a (or second demarcation strip 33) forms the jet pipe profile curve of jet pipe, or internal perisporium 3b (or second demarcation strip 33) formation jet pipe profile curve, periphery wall 3a is cylindrical or conical.6 kinds of configurations (for for purpose of brevity, not shown second demarcation strip 33) specify as follows.
Plant in the configuration at (a), with respect to rotation O, the bus of periphery wall 3a is jet pipe profile curve L1, and the bus of internal perisporium 3b is straight line L1, and straight line L1 relative rotation axi line O is parallel;
Plant in the configuration at (b), with respect to rotation O, the bus of periphery wall 3a is jet pipe profile curve L1, and the bus of internal perisporium 3b is straight line L2, and straight line L2 relative rotation axi line O is from upstream to the downstream gradually away from rotation O with predetermined angle inclination;
Plant in the configuration at (c), with respect to rotation O, the bus of periphery wall 3a is jet pipe profile curve L1, and the bus of internal perisporium 3b is straight line L2, and straight line L2 relative rotation axi line O is from upstream to the downstream gradually near rotation O with predetermined angle inclination;
Plant in the configuration at (d), with respect to rotation O, the bus of periphery wall 3a is straight line L2, and the bus of internal perisporium 3b is jet pipe profile curve L1, and straight line L2 relative rotation axi line O is parallel;
Plant in the configuration at (e), with respect to rotation O, the bus of periphery wall 3a is straight line L2, and the bus of internal perisporium 3b is jet pipe profile curve L1, and straight line L2 relative rotation axi line O is from upstream to the downstream gradually near rotation O with predetermined angle inclination;
Plant in the configuration at (f), with respect to rotation O, the bus of periphery wall 3a is straight line L2, and the bus of internal perisporium 3b is jet pipe profile curve L1, and straight line L2 relative rotation axi line O is from upstream to the downstream gradually away from rotation O with predetermined angle inclination.
In addition, in order to overcome the problem of loopful shape wind tunnel test difficulty, the Zhou Jing of the channel cross-section of jet pipe experimental section 3 is than t 〉=3 in the circular experimental section of the present invention, wherein t determines according to following formula: (wherein c ' is the circumferential lengths of unexpansive limit wall to t=c '/r ', wherein c ' is the circumferential lengths of the unexpansive limit of outside nozzle wall, and r ' is the space length between outside nozzle unexpansive limit wall and the expansion limit wall.Preferably, Zhou Jing is than t 〉=4, and the boundary layer that connects sidewall about can eliminating effectively is beneficial to obtain desirable flow field fluidised form to target mixolimnion influence on flow field.
Be formed with transparent window on the periphery wall 3a of jet pipe experimental section 3 and among the internal perisporium 3b one or two, two sidewall 3c, be formed with transparent window among the 3d one or two, particularly can all form transparent window at its four perisporiums, thereby be convenient to the technology implementation of optics non-contact testing, be convenient to observe the mixolimnion flow field structure, can study the influence of incoming flow boundary layer flow field structure.Though transparent window shown in Fig. 1 and 2 is arranged on combined experiments portion 32, can know, the transparent window of jet pipe experimental section 3 can also upstream extend to the subsonic speed zone of spout portion 31 from combined experiments portion 32, preferably, can upstream extend to the inlet of spout portion 31 always, be convenient to adopt optics non-contact testing technology that whole flow field is observed like this.
The downstream end of second demarcation strip 33 of jet pipe experimental section 3 is formed with tiltedly splits 331, tiltedly split 331 and have transitional surface that is cambered surface or plane inboard inclination downstream and the most advanced and sophisticated edge that is positioned at downstream end, help eliminating the mixolimnion shock wave, can the pilot-gas fluidised form, make it satisfy the requirement of Flow Field in Wind Tunnel quality.In order to control the fluidised form of mixolimnion incoming flow, the demarcation strip surface adopts hyperfine skilled worker's technology to control its texture, is used to bring out upstream edge interlayer unstable wave, realizes the FLOW CONTROL of mixed downstream layer.
Regulate for the ease of pressure inflow gas, make the gas that enters have different fluidised forms, in low mach one side total voltage regulator 23 is housed, in order to adjusting low mach air-flow stagnation pressure, thereby the static pressure of the outlet of the epicoele of spout portion 31 of jet pipe experimental section 3 and cavity of resorption is equated.In the present embodiment, be that total voltage regulator 23 is set in the epicoele 201 of stable section 2, scalable flows through the air-flow stagnation pressure in it.Total voltage regulator 23 is double-deck orifice plate, can carry out the change of runner and the adjusting of incoming flow stagnation pressure by the degree of misalignment of adjusting two orifice plates.Also comprise the fairing 22 that is separately positioned on epicoele 201 and cavity of resorption 202 that is positioned at total voltage regulator 23 downstreams in the stable section 2, this fairing 22 comprises honeycomb and husky net.Total voltage regulator 23 utilizes the gas viscosity dissipation effect to regulate the incoming flow stagnation pressure, realize the pressure coupling of mixolimnion, 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 number of plies of the two and arrangement mode can make up according to the uniformity coefficient in flow field.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.The whole processing of its perisporium, the middle part does not need flange to connect, and connects the problem that produces shock wave thereby overcome flange.
By foregoing description as can be known, according to supersonic speed axisymmetric mixing layer wind-tunnel of the present invention, both can simulate the supersonic speed axisymmetric flow field of loopful runner, be convenient to implement optics non-contact testing technology again, form the flow field of supersonic speed axisymmetric mixing layer in combined experiments portion, can realize research to the flow field characteristic of supersonic speed axisymmetric mixing layer, connect the boundary layer of sidewall about can eliminating effectively to target mixolimnion influence on flow field, be beneficial to obtain desirable flow field fluidised form, can realize controllable flow field fluidised form, the mixolimnion flow field quality is good, and two-dimensional characteristics is good, and helps the whole flow field wave absorption.
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 (18)
1. a supersonic speed axisymmetric mixing layer wind-tunnel is characterized in that, comprising:
Transition section (1) is used to introduce air-flow;
Stable section (2) is connected the downstream of described transition section (1), has first demarcation strip (21), and the inner chamber of stable section is divided into epicoele (201) and cavity of resorption (202), and the air-flow that is used for introducing is divided into two strands of air-flows; And
Jet pipe experimental section (3), be connected the downstream of described stable section (2), and be fan-shaped axially symmetric structure with respect to a rotation (O), the xsect of the perisporium of described jet pipe experimental section (3) is fan-shaped ring, be formed with transparent window on the described perisporium, described perisporium comprise periphery wall (3a), internal perisporium (3b) and connect described periphery wall (3a) and two sidewalls of internal perisporium (3b) (3c, 3d), described jet pipe experimental section (3) is formed with:
Spout portion (31) wherein is provided with second demarcation strip (33), will accelerating to the supersonic speed state respectively from two strands of air-flows in described epicoele (201) and the cavity of resorption (202), and
Combined experiments portion (32) is arranged on the downstream of described spout portion (31), is used to mix described two strands of air-flows of supersonic speed state to form axisymmetric mixing layer.
2. supersonic speed axisymmetric mixing layer 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 axisymmetric mixing layer wind-tunnel according to claim 1, it is characterized in that, also comprise middle transition section (5), be connected between described stable section (2) and the described jet pipe experimental section (3), the cross sectional shape of its passage carries out the transition to the corresponding cross sectional shape of described jet pipe experimental section (3) with downstream end from the cross sectional shape corresponding with the described stable section (2) of upstream extremity, is formed with the 3rd demarcation strip (51) that is connected described first demarcation strip (21) and second demarcation strip (33) in the transition section (5) in described.
4. supersonic speed axisymmetric mixing layer wind-tunnel according to claim 3, it is characterized in that described second demarcation strip (33), described first demarcation strip (21) and be connected the 3rd demarcation strip (51) between this two and continue landform mutually and be integral the median septum structure.
5. supersonic speed axisymmetric mixing layer wind-tunnel according to claim 1 is characterized in that described second demarcation strip (33) is removably disposed in the described jet pipe experimental section (3).
6. supersonic speed axisymmetric mixing layer 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.
7. supersonic speed axisymmetric mixing layer wind-tunnel according to claim 1 is characterized in that the xsect of described stable section (2) is rectangular.
8. supersonic speed axisymmetric mixing layer wind-tunnel according to claim 1, it is characterized in that, form the first jet pipe expansion limit one of in described periphery wall (3a) and the internal perisporium (3b), the rotation bus of the described relatively rotation of wall on the described first jet pipe expansion limit is the first jet pipe profile curve, in described periphery wall (3a) and the internal perisporium (3b) another forms the unexpansive limit of jet pipe, and the wall on this unexpansive limit of jet pipe is a straight line along the rotation bus of described rotation direction.
9. supersonic speed axisymmetric mixing layer wind-tunnel according to claim 8, it is characterized in that, described second demarcation strip (33) in the described spout portion (31) forms the second jet pipe expansion limit, and the wall on this second jet pipe expansion limit is the second jet pipe profile curve with respect to the rotation bus of described rotation.
10. supersonic speed axisymmetric mixing layer wind-tunnel according to claim 8 is characterized in that the wall on the unexpansive limit of described jet pipe is the cylinder or the conical surface.
11. supersonic speed axisymmetric mixing layer wind-tunnel according to claim 1 is characterized in that each perisporium of described jet pipe experimental section (3) is integrally formed, thereby the wall on the wall on described jet pipe expansion limit and the unexpansive limit of jet pipe all forms the continuous wall of one.
12. supersonic speed axisymmetric mixing layer wind-tunnel according to claim 8 is characterized in that, the Zhou Jing of the channel cross-section of described jet pipe experimental section (3) is than t 〉=3, and wherein t determines according to following formula:
t＝c’/r’，
Wherein c ' is the circumferential lengths of the unexpansive limit of outside nozzle wall, and r ' is the space length between outside nozzle unexpansive limit wall and the expansion limit wall.
13. supersonic speed axisymmetric mixing layer wind-tunnel according to claim 1, it is characterized in that, be formed with transparent window on the periphery wall (3a) of described jet pipe experimental section (3) and in the internal perisporium (3b) one or two, (3c 3d) is formed with transparent window in one or two to two sidewalls.
14. supersonic speed axisymmetric mixing layer wind-tunnel according to claim 13 is characterized in that, described transparent window extends to the subsonic speed section region of described spout portion (31) forward.
15. supersonic speed axisymmetric mixing layer wind-tunnel according to claim 8 is characterized in that, the downstream end of described second demarcation strip (33) of described jet pipe experimental section (3) is formed with tiltedly splits (331).
16. supersonic speed axisymmetric mixing layer wind-tunnel according to claim 15 is characterized in that, described tiltedly split (331) have transitional surface that is cambered surface or plane inclination and the most advanced and sophisticated edge that is formed by described transitional surface.
17. supersonic speed axisymmetric mixing layer wind-tunnel according to claim 1, it is characterized in that, be provided with total voltage regulator (23) in the epicoele of described stable section (2), described total voltage regulator is double-deck orifice plate, carries out the change of runner and the adjusting of incoming flow stagnation pressure by the degree of misalignment of adjusting two orifice plates.
18. supersonic speed axisymmetric mixing layer wind-tunnel according to claim 13, it is characterized in that, comprise the fairing (22) that is positioned at described total voltage regulator (23) downstream in the epicoele (201) of described stable section (2) and the cavity of resorption (202) respectively, described fairing (22) comprises honeycomb and husky net.
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