CN209387242U - Experimental device for wind-tunnel flow field noise aassessment - Google Patents
Experimental device for wind-tunnel flow field noise aassessment Download PDFInfo
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- CN209387242U CN209387242U CN201920306189.5U CN201920306189U CN209387242U CN 209387242 U CN209387242 U CN 209387242U CN 201920306189 U CN201920306189 U CN 201920306189U CN 209387242 U CN209387242 U CN 209387242U
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Abstract
The application provides an experimental device for noise evaluation of a wind tunnel flow field, and belongs to the field of experimental aerodynamics. The experimental device for wind tunnel flow field noise evaluation comprises an inlet valve, a stabilizing section, a spraying pipe section, an experimental section and a diffusion section which are sequentially communicated. The inlet valve can be dismantled with the stable section and be connected, and the stable section can be dismantled with the spout pipeline section and be connected, and the one end of spouting the pipeline section stretches into inside and can dismantle with the experiment section of experiment section and be connected, and the experiment section is connected with the one end of diffusion section, and the other end of diffusion section is used for connecting the vacuum tank. A control assembly is detachably mounted in the stabilizing section and comprises a first control element used for reducing flow field noise or a second control element used for increasing the flow field noise. The experimental device also comprises a first measuring probe and a second measuring probe, wherein the first measuring probe is arranged in the stable section and is used for measuring the noise at the outlet of the stable section; the second measurement probe is mounted inside the experimental section and is used for measuring the noise at the outlet of the nozzle section.
Description
Technical field
This application involves experimental aerodynamics fields, in particular to a kind of experiment of Flow Field in Wind Tunnel noise evaluation
Device.
Background technique
Wind-tunnel is the capital equipment that aircraft etc. carries out ground simulating, and the dummy vehicle obtained in wind-tunnel pneumatically counts
According to, be in next step carry out full-scale flight test foundation and basis.Therefore, Flow Field in Wind Tunnel quality is more excellent, obtains
Experimental result and live flying test it is closer, can more accurately find and solve the problems, such as Flight Vehicle Design,
The efficiency of Flight Vehicle Design and the success rate of flight test is greatly improved.
In recent years, it is found in the rapid hypersonic aircraft of research and development, ground wind tunnel experiment and live flying try
It tests there are bigger difference, carries out flight test according to ground wind tunnel experimental results, many flight tests is caused to fail.It traces it to its cause
Mainly supersonic speed/hypersonic wind tunnel flow field noise influence that experimental result is generated.
Utility model content
The embodiment of the present application provides a kind of experimental provision of Flow Field in Wind Tunnel noise evaluation, it is intended to analyze Flow Field in Wind Tunnel noise
Source and contribution, reduce influence of the noise to wind tunnel experimental results.
In a first aspect, embodiments herein provides a kind of experimental provision of Flow Field in Wind Tunnel noise evaluation comprising successively
Inlet valve, stable section, nozzle section, experimental section and the diffuser of connection.Inlet valve is detachably connected with stable section, is stablized
Section is detachably connected with nozzle section, and one end of nozzle section extend into inside experimental section and is detachably connected with experimental section, experimental section
It is connect with one end of diffuser, the other end of diffuser is for connecting vacuum tank.Control group has been removably installed in stable section
Part, control assembly include the second control piece for reducing the first control piece of flow field noise or for increasing flow field noise.It is real
Experiment device further includes the first measurement probe and the second measurement probe, and the first measurement probe is installed in stable section and close to stable section
Outlet position, first measurement probe be used for measure stable section exit noise；Second measurement probe is installed on experiment
The position of the outlet of intersegmental part and close nozzle section, the second measurement probe are used to measure the noise in the exit of nozzle section.
In the experimental provision of the Flow Field in Wind Tunnel noise evaluation of the application, inlet valve is detachably connected with stable section, is stablized
Section is detachably connected with nozzle section, and one end of nozzle section extend into inside experimental section and is detachably connected with experimental section, then can be square
Just replacement nozzle section and installation control assembly, the first control piece or the second control piece are mounted in stable section, surveyed by first
The noise for measuring probe measurement stable section exit measures the noise in nozzle section exit by the second measurement probe, to assess
Contribution of the stable section to noise.By replacing different nozzle sections, making an uproar for nozzle section exit is measured by the second measurement probe
Sound, in conjunction with the noise situations for the stable section that the first measurement probe measures, it can be estimated that contribution of the nozzle section to noise.By commenting
The stable section and nozzle section for estimating wind-tunnel analyze source and the contribution of Flow Field in Wind Tunnel noise, to subtract respectively to the contribution of overall noise
Few influence of the flow field noise to experimental result.
In a kind of possible embodiment, the periphery of the first control piece with respect to stable section internal slide and can be held in
The inner wall of stable section, the periphery of the second control piece with respect to stable section internal slide and can be held in the inner wall of stable section, and first
Control piece and the second control piece are each configured to can be by entering the air-flow in stable section from inlet valve.Due to the first control
Product and the second control piece can be with respect to stable section internal slides, then the side that the first control piece and the second control piece pass through sliding
Formula can be installed into stable section and be fixed up, and facilitate operation.
In a kind of possible embodiment, the first control piece has the first through hole of array setting, the hole of first through hole
Diameter is 1 μm~2mm.The aperture of first through hole is smaller, when air-flow passes through the first control piece in stable section, compared in stable section
The case where not installing the first control piece, the first control piece slow down fluid flow rate, make to flow it is more stable, to play noise reduction
Effect.
In a kind of possible embodiment, the second control piece has the second through-hole of array setting, the hole of the second through-hole
Diameter is greater than 10mm, and the size of the interconnecting piece between two adjacent the second through-holes is greater than 5mm.The aperture of second control piece is larger,
Air-flow is unaffected by the flow of the second control piece, and the size of the interconnecting piece between two adjacent second through-holes is greater than
5mm can upset air-flow flowing after the second control piece, to have the function that increase noise.
In a kind of possible embodiment, the inner surface of nozzle section is smooth surface, roughness Ra≤0.01.Jet pipe
The degree of roughness of the inner surface of section has an impact to the noise of nozzle section, and the nozzle section by replacing different inner surfaces can assess it
Influence of the roughness to overall noise, under suitable jet pipe segment length, nozzle section inner surface is if it is smooth surface, nozzle section wall
Face boundary layer can maintain laminar flow, and boundary layer flow field will not generate turbulence noise.
In a kind of possible embodiment, the inner surface of nozzle section is rough surface, roughness Ra > 0.1.If spray
The inner surface of pipeline section is rough surface, and the boundary layer of nozzle section is then turbulent flow, the turbulent flow arteries and veins in nozzle section wall surface turbulent boundary layer
Dynamic is one of the main source of Flow Field in Wind Tunnel noise.
In a kind of possible embodiment, the shrinkage ratio of nozzle section is 5~20.The shrinkage ratio of nozzle section is to nozzle section
Noise has an impact, and the nozzle section by replacing different shrinkage ratios can assess influence of the shrinkage ratio to noise.In addition, nozzle section
Shrinkage ratio is too small to will affect flow field quality, and shrinkage ratio crosses the overall dimensions that conference increase accordingly wind-tunnel, it has not been convenient to nozzle section is replaced,
It is 5~20 that thus the application, which selects the shrinkage ratio of nozzle section, and nozzle section is convenient for changing in the case where not influencing flow field quality.
In a kind of possible embodiment, the length of nozzle section is 300~500mm.The length of nozzle section is to nozzle section
Noise have an impact, the nozzle section by replacing different length can assess influence of the length to noise of nozzle section.
In a kind of possible embodiment, the end of inlet valve is connected with ring flange, the ends of stable section
It is respectively connected with ring flange, one end of nozzle section is connected with ring flange；Wherein one end of the ring flange and stable section of inlet valve
Ring flange is clamped by fixture so that inlet valve is detachably connected with stable section；The ring flange of nozzle section and stable section it is another
The ring flange of one end is clamped by fixture so that nozzle section is detachably connected with stable section.The side of ring flange is clamped by fixture
Formula can be realized quickly connection, disassembly nozzle section and stable section.
In a kind of possible embodiment, the side wall of experimental section offers mounting hole, and one end of nozzle section is from mounting hole
It extend into inside experimental section, is provided with sealing ring between the outer wall of nozzle section and the hole wall of mounting hole.Pass through nozzle section and installation
The cooperation in hole can be realized being detachably connected for nozzle section and experimental section, wherein sealing ring plays the purpose of sealing experiment section.
Detailed description of the invention
It, below will be to use required in embodiment in order to illustrate more clearly of the technical solution of the application embodiment
Attached drawing be briefly described, it should be understood that the following drawings illustrates only some embodiments of the application, therefore is not to be seen as
It is the restriction to range, it for those of ordinary skill in the art, without creative efforts, can be with root
Other relevant attached drawings are obtained according to these attached drawings.
Fig. 1 is the structural schematic diagram of the experimental provision of Flow Field in Wind Tunnel noise evaluation provided by the embodiments of the present application；
Fig. 2 is the structural schematic diagram of supporting element provided by the embodiments of the present application；
Fig. 3 is the structural schematic diagram of the first control piece provided by the embodiments of the present application；
Fig. 4 is the structural schematic diagram of the second control piece provided by the embodiments of the present application；
Fig. 5 is the cross-sectional view of nozzle section provided by the embodiments of the present application.
Icon: 100- experimental provision；110- inlet valve；111- changeover portion；120- stable section；130- nozzle section；131-
Nozzle section entrance；The outlet of 132- nozzle section；133- nozzle section throat；134- jet pipe contraction section；135- nozzle divergence cone；140- is real
Test section；150- control assembly；The first control piece of 151-；151a- first through hole；The second control piece of 152-；The second through-hole of 152a-；
161- first measures probe；162- second measures probe；163- ring flange；The first fixing piece of 164-；The second fixing piece of 165-；
166- supporting element；170- diffuser.
Specific embodiment
To keep the purposes, technical schemes and advantages of the application embodiment clearer, implement below in conjunction with the application
Attached drawing in mode carries out clear, complete description to the technical solution in the application embodiment, it is clear that described reality
The mode of applying is the embodiment of the application a part, rather than whole embodiments.Based on the embodiment in the application, originally
Field those of ordinary skill every other embodiment obtained without making creative work, belongs to this Shen
The range that please be protect.
Therefore, requirement is not intended to limit to the detailed description of the presently filed embodiment provided in the accompanying drawings below to protect
The scope of the present application of shield, but it is merely representative of the selected embodiment of the application.Based on the embodiment in the application, ability
Domain those of ordinary skill every other embodiment obtained without making creative work, belongs to the application
The range of protection.
It should also be noted that similar label and letter indicate similar terms in following attached drawing, therefore, once a certain Xiang Yi
It is defined in a attached drawing, does not then need that it is further defined and explained in subsequent attached drawing.
In the description of the present application, it is to be understood that the orientation of the instructions such as term " length ", " thickness ", "inner", "outside"
Or positional relationship is to be based on the orientation or positional relationship shown in the drawings, and is merely for convenience of description the application and simplifies description, and
It is not that the equipment of indication or suggestion meaning or element must have a particular orientation, be constructed and operated in a specific orientation, therefore
It should not be understood as the limitation to the application.
In addition, term " first ", " second " are used for descriptive purposes only and cannot be understood as indicating or suggesting relative importance
Or implicitly indicate the quantity of indicated technical characteristic.Define " first " as a result, the feature of " second " can be expressed or
Implicitly include one or more of the features.In the description of the present application, the meaning of " plurality " is two or more,
Unless otherwise specifically defined.
In this application unless specifically defined or limited otherwise, the terms such as term " installation ", " setting ", " connection " are answered
It is interpreted broadly, for example, it may be being fixedly connected, may be a detachable connection, or is integral；It can be directly connected,
The connection inside two elements or the interaction relationship of two elements can be can be indirectly connected through an intermediary.It is right
For those skilled in the art, the concrete meaning of above-mentioned term in this application can be understood as the case may be.
In order to facilitate the experimental provision 100 for the Flow Field in Wind Tunnel noise evaluation for understanding the embodiment of the present application, below first to wind-tunnel
Related content be introduced.
Wind-tunnel (wind tunnel) i.e. wind tunnel laboratory generates and controls air-flow, is used to simulated flight device or entity
The mobility status of ambient gas, and it is real to a kind of pipe-like of the function and effect of entity and observation physical phenomenon to measure air-flow
Equipment is tested, it is to carry out that aerodynamic experiment is the most frequently used, one of most effective tool.Wind tunnel experiment is in aircraft development work
An indispensable component part.
Recent study discovery carries out flight experiment according to ground wind tunnel experimental results, results in many flight experiments and loses
It loses.Tracing it to its cause is influence that supersonic speed/hypersonic wind tunnel flow field noise generates experimental result.
Further investigate supersonic speed/influence of the hypersonic wind tunnel flow field noise to experimental measurements, it is necessary first to right
Source, distribution and spectral characteristic of Flow Field in Wind Tunnel noise etc. are assessed.Supersonic speed/hypersonic wind tunnel experiment section measures
Disturbance that noise is transmitted by stable section 120, the induction of 130 wall surface of nozzle section the Mach wave oscillation propagated along characteristic curve direction and
Turbulence pulsation composition in 130 wall boundary layer of nozzle section, wherein the disturbance that stable section 120 transmits includes pressure oscillation (sound
Wave), velocity fluctuation (whirlpool wave), non-uniform temperature (entropy wave).The frequency range of Flow Field in Wind Tunnel noise is very wide, about 0~
1000kHz, it is even higher.For from construction of wind tunnel, wind-tunnel includes the inlet valve 110 being sequentially communicated, stable section 120, spray
Pipeline section 130, experimental section 140 and diffuser 170, air-flow can enter wind turbine apparatus by inlet valve 110.Wind-tunnel
Inlet valve 110,120 structure of stable section, the shrinkage ratio of nozzle section 130, the length of nozzle section 130, nozzle section 130 inner surface
Roughness etc. is all the factor of influence Flow Field in Wind Tunnel noise, and different wind-tunnel components (such as stable section 120, nozzle section 130)
Frequency, power spectrum of the noise of generation etc. be not also identical, and the influence to experiment measurement is also not quite similar.The stable section 120 of wind-tunnel
Disturbance mainly based on middle low frequency, and the disturbance of the nozzle section 130 of wind-tunnel is concentrated mainly on high frequency section.Different frequencies pair
The influence (such as model surface boundary layer transition position) that the aircraft flow field of experimental section 140 generates is also different.Routine assessments wind-tunnel
The method of flow field noise, the pulsation situation of Flow Field in Wind Tunnel parameter mainly in measurement experiment section 140, obtains being each component of wind-tunnel
The conjunction noise of generation, the available identical conjunction noise of the combination of the wind tunnel noise of different frequency, but it ties experiment measurement
Influence it is different, therefore, assess wind tunnel noise, cannot only measure the conjunction noise of the experimental section 140 of wind-tunnel, it is also necessary to noise
Composition carry out decomposition measurement.
Based on this, the embodiment of the present application provides a kind of experimental provision 100 of Flow Field in Wind Tunnel noise evaluation, it is intended to analyze
The source of Flow Field in Wind Tunnel noise and contribution reduce influence of the flow field noise to experimental result.
Below in conjunction with the attached drawing in the embodiment of the present application, the technical solution in the embodiment of the present application is described.
Fig. 1 is please referred to, Fig. 1 shows the structural representation of the experimental provision 100 of the Flow Field in Wind Tunnel noise evaluation of the present embodiment
Figure, the experimental provision 100 are fixed on experiment porch by supporting mechanism.Experimental provision 100 includes the entrance being sequentially communicated
Valve 110, changeover portion 111, stable section 120, nozzle section 130, experimental section 140 and diffuser 170.
Wherein, entrance of the inlet valve 110 as wind-tunnel, air-flow can enter wind turbine apparatus from inlet valve 110.Work as gas
When stream enters wind turbine apparatus, wind tunnel operation work；When inlet valve 110 is closed, wind tunnel operation stops.Illustratively, inlet valve
110 optional butterfly valves of door or quick-acting valve.Connecting interface can be set in the input end of inlet valve 110, the connecting interface
It can be connect with high-pressure gas pipelines, high pressure gas be fed to inlet valve 110 by high-pressure gas pipelines, to keep wind-tunnel
Run working condition.
Changeover portion 111 primarily serves the effect of connection inlet valve 110 and stable section 120.
Stable section 120 is one of the main source of Flow Field in Wind Tunnel noise, to change the pneumatic noise in stable section 120, this
Control assembly 150 is removably installed in the stable section 120 of embodiment, control assembly 150 includes for reducing flow field noise
The first control piece 151 or the second control piece 152 for increasing flow field noise, by by the first control piece 151 or second
Control piece 152 is mounted in stable section 120, i.e., the flow field noise in changeable stable section 120.In order to measure stable section 120
Noise level, the present embodiment are equipped with the first measurement probe 161 close to the position that stable section 120 exports in stable section 120, the
One measurement probe 161 is used to measure the noise level in 120 exit of stable section.
When the flow field noise in stable section 120 to be increased, the second control piece 152 is installed into stable section 120, when wanting
When reducing the flow field noise in stable section 120, the first control piece 151 is installed into stable section 120.In order to facilitate the installation of, originally
The inlet valve 110 of embodiment is detachably connected with stable section 120, and stable section 120 is detachably connected with nozzle section 130.When need
When first control piece 151 or the second control piece 152 are installed, by the opposite end of stable section 120 respectively with inlet valve 110
It is dismantled with nozzle section 130, the first control piece 151 and the second control piece 152 is installed into stable section 120, then by inlet valve
110 connect with one end of stable section 120, and the other end of stable section 120 is connect with nozzle section 130.
Illustratively, the outlet end of inlet valve 110 is connected with ring flange 163, and the ends of stable section 120 is equal
It is connected with ring flange 163, the arrival end of nozzle section 130 is connected with ring flange 163, the ring flange of the outlet end of inlet valve 110
163 are clamped together with the ring flange 163 of wherein one end of stable section 120 by fixture (not shown), thus by entrance
Valve 110 is connected with stable section 120.The ring flange of the other end of the ring flange 163 and stable section 120 of nozzle section 130
163 are clamped by fixture so that nozzle section 130 is connected with stable section 120.When needing to disassemble stable section 120
When, fixture need to only be unclamped, so that the ring flange 163 of wherein one end of the ring flange 163 of inlet valve 110 and stable section 120
Separation, the ring flange 163 of 120 other end of stable section are separated with the ring flange 163 of nozzle section 130.
It should be noted that can also be by the method for the ring flange 163 of inlet valve 110 and wherein one end of stable section 120
Blue disk 163 adopts the mode being tightened by bolts, and is sealed between the ring flange 163 of the two using sealing ring；By stable section 120
The ring flange 163 of the other end locked with the ring flange 163 of nozzle section 130 also by bolt, utilized between the two ring flange 163
Sealing ring is sealed.
In addition, the stable section 120 of the present embodiment is generally cylindric, internal diameter is consistent.First control piece 151 and
Two control pieces 152 are in the form of annular discs, and being each configured to can be by entering the gas in stable section 120 from inlet valve 110
Stream.It should be noted that first control piece 151 and the second control piece 152 are then also when the inside of stable section 120 is rectangular
It is rectangular.As long as the shape of the first control piece 151 and the second control piece 152 can be with the matching internal of stable section 120.Its
In, the outer diameter of the first control piece 151 and the second control piece 152 is slightly less than the internal diameter of stable section 120, so that the first control piece
151 periphery with respect to 120 internal slide of stable section and can be held in the inner wall of stable section 120, the week of the second control piece 152
Edge with respect to 120 internal slide of stable section and can be held in the inner wall of stable section 120.And the inner wall of stable section 120 is equipped with admittedly
Determine block (not shown), control assembly 150 can be supported in fixed stop, to be fixed in stable section 120.Work as stabilization
After section 120 is disassembled from wind-tunnel, the first control piece 151 or the second control piece 152 are slided into from the end of stable section 120
In stable section 120 and it is fixed in stable section 120.
It should be noted that by the type, quantity and the position in stable section 120 that change control assembly 150, it can
Discretely to change the noise level in stable section 120.The type for changing control assembly 150 can be by by the first control piece
151 or second control piece 152 be installed into stable section 120 and realize.The quantity for changing control assembly 150 can be by changing the
The quantity of one control piece 151 or the quantity of the second control piece 152 are realized.It is controlled when installing multiple first in stable section 120
When product 151 or multiple second control pieces 152, circle that can be relatively thin by wall thickness between two adjacent the first control pieces 151
Cylindrical support part 166 (as shown in Figure 2) separates, and the wall thickness of supporting element 166 can be 1~3mm, and cylindric supporting element 166 can be tight
Paste the inner wall of stable section 120.During installation, the first control piece 151 and the interval of supporting element 166 slide into stable section 120, and first
Control piece 151 is fixed block and supports, and two adjacent the first control pieces 151 are supported part 166 and support, by changing supporting element
166 axial dimension is the spacing of adjustable two the first control pieces 151.Similarly, two adjacent the second control pieces 152 it
Between can be separated by the relatively thin cylindric supporting element 166 of wall thickness, no longer repeated herein.
First control piece 151 and the second control piece 152 have different function and effect to noise, the main reason is that first
The through-hole aperture that control piece 151 and the second control piece 152 are arranged is different, and the first small control piece 151 of through-hole aperture has noise reduction
Effect, the second big control piece 152 of through-hole aperture have the function of increasing noise.Illustratively, referring to figure 3., the first control
Part 151 has the first through hole 151a of array setting, and the aperture of first through hole 151a is 1 μm~2mm, for example, the first control piece
151 in other words can individually can use honeycomb using honeycomb and/or damping screen, or individually use damping screen,
Or honeycomb and damping screen are used simultaneously.When using damping screen, the damping screen of multilayered structure can be used, the aperture of every layer of net is in
The trend gradually changed, can be and be gradually reduced, and be also possible to be gradually increased, when installation, by biggish one layer of aperture close to entering
Mouth valve 110 is installed.The aperture of first through hole 151a is smaller, when air-flow passes through the first control piece 151 in stable section 120, phase
The case where compared with the first control piece 151 are not installed in stable section 120, the first control piece 151 slow down fluid flow rate, to rise
To the effect of noise reduction.In addition, the size of the metal part between two adjacent first through hole 151a is less than 2mm, even if air-flow
Flowing whirlpool is formed, can also be destroyed to have the function that noise reduction after the first control piece 151.
Illustratively, referring to figure 4., the second control piece 152 has the second through-hole 152a of array setting, the second through-hole
The aperture of 152a is greater than 10mm.Compared to the aperture of the first control piece 151, the aperture of the second control piece 152 is larger, and air-flow is logical
The flow for crossing the second control piece 152 is substantially unaffected, and the size of the interconnecting piece between two adjacent second through-hole 152a
Greater than 5mm, air-flow will form flowing whirlpool after passing through the second control piece 152 to have the function that increase noise.
Referring to figure 5., the nozzle section 130 of wind-tunnel includes jet pipe contraction section 134 and nozzle divergence cone 135.Jet pipe contraction section
134 refer to that nozzle section entrance 131 arrives the part of nozzle section throat 133, and nozzle divergence cone 135 refers to nozzle section throat 133
To the part (as shown in Figure 5) of nozzle section outlet 132.Wherein, nozzle section throat 133 is that 130 middle section of nozzle section product is the smallest
Position, the ratio between 131 size of nozzle section entrance and 133 size of nozzle section throat are the shrinkage ratio of nozzle section 130.Nozzle section 130
Length, the roughness of 130 inner surface of nozzle section and the shrinkage ratio of nozzle section 130 have an impact to the noise of nozzle section 130.
Therefore, the experimental provision 100 of the present embodiment has more set nozzle sections 130, i.e., with the nozzle section 130 of multiple and different length, tool
The nozzle section 130 for the inner surface for having multiple roughness different, and the nozzle section 130 different with multiple shrinkage ratios.By replacing
Different nozzle sections 130 is changed, to change the length of nozzle section 130, shrinkage ratio and the roughness of inner surface respectively.Wherein, it sprays
When the inner surface of pipeline section 130 is smooth surface, roughness Ra≤0.01 of inner surface.The inner surface of nozzle section 130 is coarse
When surface, roughness Ra > 0.1 of inner surface.The shrinkage ratio of nozzle section 130 is 5~20.The length of nozzle section 130 be 300~
500mm.The boundary layer of nozzle section 130 is generally turbulent flow, and the turbulence pulsation in 130 wall surface turbulent boundary layer of nozzle section is wind-tunnel stream
One of the main source of field noise.Under suitable 130 length of nozzle section, 130 inner surface of nozzle section is if it is smooth surface, spray
130 wall boundary layer of pipeline section can maintain laminar flow, and boundary layer flow field will not generate turbulence noise.
During the experiment, due to needing to replace different nozzle sections 130, the jet pipe of the present embodiment for operating easily,
One end of section 130 extend into 140 inside of experimental section and is detachably connected with experimental section 140.Illustratively, the side of experimental section 140
Wall offers mounting hole, and one end of nozzle section 130 is extend into inside experimental section 140 from mounting hole, the outer wall of nozzle section 130 with
Sealing ring (not shown) is provided between the hole wall of mounting hole.When needing to replace nozzle section 130, stabilization will be hold
The fixture of the ring flange 163 of the ring flange 163 and nozzle section 130 of section 120 unclamps, can be by stable section 120 and nozzle section 130
Separation, then removes the sealing ring between nozzle section 130 and mounting hole, one end of nozzle section 130 is taken out of experimental section 140
Out.It is extend into experimental section 140 alternatively, it is also possible to be arranged to one end of nozzle section 130, the outer wall setting of nozzle section 130
There is flange, is connect the flange of nozzle section 130 with experimental section 140 by bolt or screw.
It should be noted that the quick-replaceable in order to realize stable section 120 and nozzle section 130, the entire reality of the present embodiment
Experiment device 100 takes Miniaturization Design scheme.Wherein, the length of inlet valve 110 is 150~300mm, and entrance outer diameter is 200
~400mm, inlet inside diameter are 150~300mm, and outlet outer diameter is 150~300mm, and exit inside diameter is 100~200mm.Stablize
The length of section 120 is 800~1500mm, and the outer diameter of stable section 120 is 120~220mm, and internal diameter is 100~200mm.Nozzle section
130 length is 300~500mm, and entrance outer diameter is 120~220mm, and inlet inside diameter is 100~200mm, and outlet outer diameter is 50
~100mm, exit inside diameter are 30~120mm.Optionally, the entirety of experimental provision 100 uses stainless steel or aluminum alloy material,
Stainless steel and aluminium alloy matter can get rusty to avoid the inner surface of experimental provision 100, avoid the thick of the inner surface for influencing nozzle section 130
Rugosity, wherein aluminium alloy is lighter, is more advantageous to replacement.
Experimental section 140 has closed chamber, and aircraft experiment is usually to carry out in experimental section 140.Illustratively,
The generally cuboid of experimental section 140, external dimensions (length) are 170~320mm, and inside dimension (length) is
150~300mm.Second measurement probe 162 is installed, wherein the second measurement probe 162 is close to nozzle section 130 in experimental section 140
Outlet position setting.It should be noted that the second measurement probe 162 measured is that the exit of nozzle section 130 is made an uproar
Sound that is to say conjunction noise, the noise situations of obtained stable section 120 be measured in conjunction with the first measurement probe 161, it can be estimated that jet pipe
The noise of section 130.Wherein, experimental section 140 is provided with experiment hatch door, to facilitate the second measurement probe 162 to install.Wherein,
Oscillatory pressure pick-up or hot-wire anemometer can be used in one measurement probe 161 and the second measurement probe 162, is pressed by measurement
Power pulsation or velocity fluctuation measure noise.
It should be noted that the first measurement probe 161 is removably installed in stable section 120, the second measurement probe
162 are removably mounted in experimental section 140.The rapids exported due to stable section 120 in 130 upstream of nozzle section, stable section 120
Mobility will affect the turbulivity of the outlet of nozzle section 130, thus, making an uproar for the outlet of stable section 120 is measured in the first measurement probe 161
When sound, the result that the second measurement probe 162 in experimental section 140 is tested may be inaccurate, can measure probe for second at this time
162 take out out of experimental section 140.It, can be by the first measurement when noise of the second measurement probe 162 in test nozzle section 130
Probe 161 takes out out of stable section 120.Specifically, 120 inner wall of stable section is provided with the first fixing piece 164, and the first measurement is visited
Needle 161 can be inserted in the first fixing piece 164.The second fixing piece 165 is provided in experimental section 140, the second measurement probe 162 can be inserted
Set on the second fixing piece 165.
Diffuser 170 is the pipeline that becomes larger of inner section, and one end is connect with experimental section 140, the other end can with it is true
Slack tank connection.Diffuser 170 is mainly used for the flow slowing down pressurization in wind-tunnel increasing the effective run time of wind-tunnel.
By the description above it is found that type, quantity and the distribution mode of Flow Field in Wind Tunnel noise controllable component 150, jet pipe
The influence of the shrinkage ratio, the roughness of the inner surface of 130 length of nozzle section and nozzle section 130 of section 130.In order to assess each ginseng
The influence of stream field noise is measured, noise is assessed using control variate method in embodiments herein, i.e., is only changed every time
One of parameter, other parameters remain unchanged, by analyzing each variable parameter to the affecting laws of Flow Field in Wind Tunnel noise, to divide
Flow Field in Wind Tunnel noise is analysed, so as to be wind-tunnel noise reduction, influence of the noise to experimental result is analyzed and foundation is provided.It needs to illustrate
It is that the noise situations in 120 exit of stable section can be obtained in the outlet turbulivity by measuring stable section 120, is sprayed by measurement
The outlet turbulivity of pipeline section 130 can be obtained Flow Field in Wind Tunnel and close noise, and obtained noise is measured in conjunction with stable section 120, can be obtained
To the noise situations of nozzle section 130.
When specific assessment, mainly there is the following aspects:
(1) in the roughness for the inner surface for keeping the shrinkage ratio of nozzle section 130,130 length of nozzle section and nozzle section 130
In the case where constant, change type, quantity and the distribution mode of control assembly 150, is then measured by the first measurement probe 161
The outlet turbulivity of stable section 120 measures the outlet turbulivity of nozzle section 130, by the second measurement probe 162 to assess stabilization
The contribution of 120 pairs of entire Flow Field in Wind Tunnel noises of section, can provide reference for 120 noise-reducing design of stable section, obtain a stable section
The smallest 150 mounting means of control assembly of 120 noises is it should be noted that change type, quantity and the distribution of control assembly 150
When mode is specially that the quantity of control assembly 150 is constant, change its type and distribution mode；The type of control assembly 150 is constant
When, change its quantity and distribution mode；When the distribution mode of control assembly 150 is constant, change its value volume and range of product.
(2) it in the case that when keeping noise minimum in stable section 120, the installation of control assembly 150 is constant, keeps simultaneously
In the case that 130 length of nozzle section is constant and the rough inner surface degree of nozzle section 130 is constant, passes through and change nozzle section 130
Shrinkage ratio, the outlet turbulivity of nozzle section 130 is measured using the second measurement probe 162, and then to assess in stable section 120
Under the conditions of the smallest to noise contribution, (shrinkage ratio of nozzle section 130 changes for the contribution of the shrinkage ratio stream field noise of nozzle section 130
Become the changing rule of the change to noise), and then design shrinkage ratio for nozzle section 130 and reference value is provided.
(3) in the case that when keeping noise minimum in stable section 120, the installation of control assembly 150 is constant, and with spray
Premised on shrinkage ratio when the shrinkage ratio of pipeline section 130 is minimum to the contribution of noise and 130 inside surface roughness of nozzle section is constant
In the case of, change the length of nozzle section 130, the outlet turbulivity of nozzle section 130 is measured using the second measurement probe 162, in turn
Come assess nozzle section 130 length stream field noise contribution, obtain the optimization length of nozzle section 130, for nozzle section 130 design
Length provides reference value.
(4) in the case that when keeping noise minimum in stable section 120, the installation of control assembly 150 is constant, and with spray
Premised on the shrinkage ratio of pipeline section 130 is to shrinkage ratio when contributing minimum of noise, the optimization length of nozzle section 130, change jet pipe
The roughness (smooth surface or rough surface) of the inner surface of section 130 measures nozzle section 130 using the second measurement probe 162
Outlet turbulivity, and then assess the contribution of the roughness stream field noise of the inner surface of nozzle section 130, set for nozzle section 130
The inside surface roughness of meter provides reference value.
The foregoing is merely the preferred embodiments of the application, are not intended to limit this application, for this field
For technical staff, various changes and changes are possible in this application.Within the spirit and principles of this application, made any
Modification, equivalent replacement, improvement etc., should be included within the scope of protection of this application.
Claims (10)
1. a kind of experimental provision of Flow Field in Wind Tunnel noise evaluation, which is characterized in that it includes the inlet valve being sequentially communicated, stabilization
Section, nozzle section, experimental section and diffuser；The inlet valve is detachably connected with the stable section, the stable section and institute
It states nozzle section to be detachably connected, one end of the nozzle section extend into inside the experimental section and detachably connects with the experimental section
It connects, the experimental section is connect with one end of the diffuser, and the other end of the diffuser is for connecting vacuum tank；
Control assembly is removably installed in the stable section, the control assembly includes for reducing the first of flow field noise
Control piece or the second control piece for increasing flow field noise；
The experimental provision further includes the first measurement probe and the second measurement probe, and the first measurement probe is installed on described steady
Determine the position of the outlet in section and close to the stable section, the first measurement probe is used to measure the exit of the stable section
Noise；The second measurement probe is installed on the position of the outlet inside the experimental section and close to the nozzle section, described
Second measurement probe is used to measure the noise in the exit of the nozzle section.
2. the experimental provision of Flow Field in Wind Tunnel noise evaluation according to claim 1, which is characterized in that first control piece
Periphery the relatively described stable section internal slide and the inner wall of the stable section can be held in, the periphery of second control piece
The relatively described stable section internal slide and it can be held in the inner wall of the stable section, first control piece and second control
Product is each configured to can be by entering the air-flow in the stable section from the inlet valve.
3. the experimental provision of Flow Field in Wind Tunnel noise evaluation according to claim 2, which is characterized in that first control piece
First through hole with array setting, the aperture of the first through hole are 1 μm~2mm.
4. the experimental provision of Flow Field in Wind Tunnel noise evaluation according to claim 2, which is characterized in that second control piece
The second through-hole with array setting, the aperture of second through-hole are greater than 10mm, between second through-hole of adjacent two
Interconnecting piece size be greater than 5mm.
5. the experimental provision of Flow Field in Wind Tunnel noise evaluation according to claim 1, which is characterized in that the nozzle section it is interior
Surface is smooth surface, roughness Ra≤0.01.
6. the experimental provision of Flow Field in Wind Tunnel noise evaluation according to claim 1, which is characterized in that the nozzle section it is interior
Surface is rough surface, roughness Ra > 0.1.
7. the experimental provision of Flow Field in Wind Tunnel noise evaluation according to claim 1, which is characterized in that the receipts of the nozzle section
Contracting is than being 5~20.
8. the experimental provision of Flow Field in Wind Tunnel noise evaluation according to claim 1, which is characterized in that the length of the nozzle section
Degree is 300~500mm.
9. the experimental provision of Flow Field in Wind Tunnel noise evaluation according to claim 1-8, which is characterized in that it is described enter
The end of mouthful valve is connected with ring flange, and the ends of the stable section is respectively connected with ring flange, and the one of the nozzle section
End is connected with ring flange；The ring flange of wherein one end of the ring flange of the inlet valve and the stable section is clamped by fixture
So that the inlet valve is detachably connected with the stable section；The ring flange of the nozzle section is another with the stable section
The ring flange at end is clamped by fixture so that the nozzle section is detachably connected with the stable section.
10. the experimental provision of Flow Field in Wind Tunnel noise evaluation according to claim 1-8, which is characterized in that described
The side wall of experimental section offers mounting hole, and one end of the nozzle section is extend into inside the experimental section from the mounting hole, institute
It states and is provided with sealing ring between the outer wall of nozzle section and the hole wall of the mounting hole.
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| CN201920306189.5U CN209387242U (en) | 2019-03-11 | 2019-03-11 | Experimental device for wind-tunnel flow field noise aassessment |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109724764A (en) * | 2019-03-11 | 2019-05-07 | 中国人民解放军国防科技大学 | Experimental device and method for evaluating noise of wind tunnel flow field |
| CN111640412A (en) * | 2020-05-29 | 2020-09-08 | 扬州大学 | Air suction type direct-current low-speed wind tunnel noise reduction processing method |
| CN112665815A (en) * | 2020-12-28 | 2021-04-16 | 中国航天空气动力技术研究院 | Low-noise flow field debugging platform |
-
2019
- 2019-03-11 CN CN201920306189.5U patent/CN209387242U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109724764A (en) * | 2019-03-11 | 2019-05-07 | 中国人民解放军国防科技大学 | Experimental device and method for evaluating noise of wind tunnel flow field |
| CN111640412A (en) * | 2020-05-29 | 2020-09-08 | 扬州大学 | Air suction type direct-current low-speed wind tunnel noise reduction processing method |
| CN112665815A (en) * | 2020-12-28 | 2021-04-16 | 中国航天空气动力技术研究院 | Low-noise flow field debugging platform |
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