CN108181077A - The two-fluid jet apparatus of changeable incoming flow conditions - Google Patents
The two-fluid jet apparatus of changeable incoming flow conditions Download PDFInfo
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- CN108181077A CN108181077A CN201711345840.1A CN201711345840A CN108181077A CN 108181077 A CN108181077 A CN 108181077A CN 201711345840 A CN201711345840 A CN 201711345840A CN 108181077 A CN108181077 A CN 108181077A
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- G—PHYSICS
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- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
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Abstract
The invention discloses a kind of two-fluid jet apparatus of changeable incoming flow conditions, for being placed in wind-tunnel, are connected to the jet structure above supporter including supporter and support, supporter is provided with gas connection, the gas channel connected with gas connection；The main gas stable cavity connected with gas channel is formed with inside jet structure, jet flow contraction flow region, jet flow throat and jet flow enlarged portion are sequentially connected after main gas stable cavity；The disturbance chamber mutually isolated with main gas stable cavity is also formed with inside jet structure, disturbance chamber is connected with the air inlet pipe for feeding disturbance air source, one of siding of disturbance chamber is provided through connection disturbance chamber and extraneous disturbance channel, and disturbance channel is used to mix with the mainstream incoming that wind tunnel nozzle sprays for gas ejection in disturbance chamber.The present invention can not only realize double venturi shear flow, and the state of also changeable wind tunnel nozzle incoming meets the experiment demand of more kinds of situations, reduces investment outlay, nothing needs to change wind-tunnel facilities.
Description
Technical field
The present invention relates to wind tunnel experiment fields, particularly, are related to a kind of two-fluid jet apparatus of changeable incoming flow conditions.
Background technology
Supersonic speed jet apparatus, for being tested in (height) supersonic wind tunnel, to realize that high speed double venturi flows.Wind
Flowing based on supersonic flows or hypersonic flowing in hole, and supersonic speed jet apparatus is positioned in wind-tunnel, during experiment, two
Shear-mixed can occur for stock flow at high speed, form the flowing of high speed double venturi.
Current supersonic speed jet apparatus only includes：Gas stable cavity, contraction flow region, nozzle throat, enlarged portion, air inlet.
Since current supersonic speed jet apparatus is only mixed in exit jet flow and mainstream flowing, and the incoming flow conditions of mainstream are not
Alterable, incoming experimental state cannot be adjusted, and existing supersonic speed jet apparatus can not meet different object of experiment demands.
Invention content
The present invention provides a kind of two-fluid jet apparatus of changeable incoming flow conditions, to solve existing supersonic speed jet flow
Device can not change the technical issues of incoming flow conditions lead to not meet different object of experiment demands.
The technical solution adopted by the present invention is as follows：
A kind of two-fluid jet apparatus of changeable incoming flow conditions for being placed in wind-tunnel, connects including supporter and support
The jet structure being connected to above supporter, supporter are provided with gas connection, the gas channel connected with gas connection；Jet flow knot
The main gas stable cavity connected with gas channel is formed with inside structure, jet flow contraction flow region, spray are sequentially connected after main gas stable cavity
Flow throat and jet flow enlarged portion；The disturbance chamber mutually isolated with main gas stable cavity is also formed with inside jet structure, disturbs chamber
The one of siding for being connected with, for the air inlet pipe of infeed disturbance air source, to disturb chamber is provided through connection disturbance chamber and the external world
Disturbance channel, disturbance channel be used for for disturbance chamber in gas ejection mixed with the mainstream incoming that wind tunnel nozzle sprays.
Further, the volume for disturbing chamber is less than the volume of main gas stable cavity.Further, disturb the volume of chamber≤
The volume of 0.1 × main gas stable cavity.
Optionally, the quantity for disturbing chamber is multiple, and multiple disturbance chambers are isolated each other.
As a kind of embodiment of said program, disturbance channel is the strip slit for being set to siding.As above-mentioned
The another embodiment of scheme, disturbance channel include the exhausting hole for being set to siding.
Optionally, disturbance channel is vertically arranged with siding；Or optionally, disturbance channel is set with siding in angle, folder
Angle is 15 °~145 °.
Optionally, straight slot is offered on the roof of main gas stable cavity, the side wall of straight slot is provided with caulking groove；Disturb chamber position
In the top of main gas stable cavity, surrounded by the partition board for being located at bottom and surrounding with the embedded siding being assemblied in straight slot,
The periphery of siding is detachably inserted in in caulking groove.Further, it is provided in caulking groove and is assembled between siding and caulking groove for sealing
The sealing ring in gap.
Further, the bottom wall of main gas stable cavity includes tilting tapered inclination positioned at back segment and towards jet flow contraction flow region
Section；Disturbance chamber is the square cavity with oblique angle, and oblique angle is towards jet flow contraction flow region, and oblique angle is identical with the angle of inclination of tilting section.
Further, the angle of inclination of oblique angle and tilting section is 30 °~45 °.
The invention has the advantages that：For the supersonic wind tunnel based on current single spraying pipe, as long as mixing the present invention
Two-fluid jet apparatus, you can realize double venturi shear flow, do not need to be transformed incoming jet pipe and wind-tunnel；The present invention
Changeable incoming flow conditions two-fluid jet apparatus, pass through the disturbance chamber mutually isolated with main gas stable cavity, disturb air source
Enter disturbance chamber, and mixed with the mainstream incoming that wind tunnel nozzle sprays through disturbing channel ejection from air inlet pipe, so as to change wind-tunnel
The state of jet pipe incoming meets the experiment demand of more kinds of situations.Structure using the present invention does not need to change wind tunnel nozzle shape
State, can reduce investment outlay, design work and wind-tunnel facilities replace etc., can realize supersonic speed dual fluid flow, while incoming shape
State quality can change.
Other than objects, features and advantages described above, the present invention also has other objects, features and advantages.
Below with reference to accompanying drawings, the present invention is described in further detail.
Description of the drawings
The attached drawing for forming the part of the application is used to provide further understanding of the present invention, schematic reality of the invention
Example and its explanation are applied for explaining the present invention, is not constituted improper limitations of the present invention.In the accompanying drawings：
Fig. 1 is the stereochemical structure signal of the two-fluid jet apparatus of the changeable incoming flow conditions of first embodiment of the invention
Figure；
Fig. 2 is schematic diagram when two-fluid jet apparatus is not shown side plate in Fig. 1；
Fig. 3 is the front view of two-fluid jet apparatus in Fig. 1；
Fig. 4 is the schematic diagram of jet structure；
Fig. 5 is the schematic diagram for disturbing chamber；
Fig. 6 is showing when side plate is not shown in the two-fluid jet apparatus of the changeable incoming flow conditions of second embodiment of the invention
It is intended to；
Fig. 7 is showing when side plate is not shown in the two-fluid jet apparatus of the changeable incoming flow conditions of third embodiment of the invention
It is intended to；
Fig. 8 is the schematic diagram that the two-fluid jet apparatus of the present invention is placed in wind-tunnel；
The schematic diagram of disturbance compressed air source unit when Fig. 9 is for barotropic disturbance；
The two-fluid jet apparatus that Figure 10 is the present invention carries out the schematic diagram that barotropic disturbance adjusts incoming flow conditions；
Figure 11 is the schematic diagram of disturbance compressed air source unit when being disturbed for negative pressure；
Figure 12 is that the two-fluid jet apparatus of the present invention carries out the schematic diagram of negative pressure disturbance adjusting incoming flow conditions.
Drawing reference numeral explanation：
1st, supporter；10th, gas connection；11st, gas channel；12nd, fixed part；2nd, jet structure；20th, main gas is stablized
Chamber；201st, roof；202nd, bottom wall；203rd, side plate；2020th, tilting section；21st, jet flow contraction flow region；22nd, jet flow throat；23rd, jet flow expands
The portion of opening；24th, chamber is disturbed；240th, siding；241st, channel is disturbed；242nd, oblique angle；243rd, partition board；25th, air inlet pipe；26th, wedge precursor；
3rd, wind tunnel nozzle；40th, gas bomb；41st, pressure-regulating valve；42nd, gas piping；43rd, solenoid valve；44th, hose；50th, vacuum pump；
51st, gas piping；52nd, suction electromagnetic valve；53rd, suction hose.
Specific embodiment
It should be noted that in the absence of conflict, the feature in embodiment and embodiment in the application can phase
Mutually combination.The present invention will be described in detail below with reference to the accompanying drawings and in conjunction with the embodiments.
With reference to Fig. 1 and Fig. 8, the preferred embodiment of the present invention provides a kind of two-fluid jet flow dress of changeable incoming flow conditions
It puts, for being placed in wind-tunnel, the jet structure 2 of 1 top of supporter is connected to including supporter 1 and support.
As shown in Figure 1 to Figure 3, supporter 1 is provided with gas connection 10, the gas channel connected with gas connection 10
11.The main gas stable cavity 20 connected with gas channel 11 is formed with inside jet structure 2, is spray after main gas stable cavity 20
Pipe, jet pipe include the jet flow contraction flow region 21, jet flow throat 22 and the jet flow enlarged portion 23 that sequentially connect.2 inside of jet structure also shape
The mutually isolated disturbance chamber 24 of the main gas stable cavities 20 of Cheng Youyu, disturbance chamber 24 are connected with the air inlet pipe for feeding disturbance air source
25, one of siding 240 of disturbance chamber 24 is provided through connection disturbance chamber 24 and extraneous disturbance channel 241, and disturbance is logical
Road 241 is used to mix for the mainstream incoming that gas ejection is sprayed with wind tunnel nozzle 3 in disturbance chamber 24.
For the supersonic wind tunnel based on current single spraying pipe, as long as mixing the two-fluid jet apparatus of the present invention, you can real
Existing double venturi shear flow, does not need to be transformed incoming jet pipe and wind-tunnel.The present invention two-fluid jet apparatus, by with
The mutually isolated disturbance chamber 24 of main gas stable cavity 20, disturbance air source enter disturbance chamber 24, and through disturbing channel from air inlet pipe 25
241, which spray the mainstream incoming sprayed with wind tunnel nozzle 3, mixes, and so as to change the state of 3 incoming of wind tunnel nozzle, meets more middle feelings
The experiment demand of condition.Structure using the present invention do not need to change 3 state of wind tunnel nozzle, can reduce investment outlay, design work and
Wind-tunnel facilities replacement etc., can realize supersonic speed dual fluid flow, while incoming flow conditions quality can change.
The two-fluid jet apparatus of the present invention is integrated using integral design.Supporter 1 and jet structure 2
By be integrally formed be made or by weld etc. manufacturing process connect it is integral, interfere with each other it is few, the processing of model, repair,
Easy to maintain, shape is succinct.The present invention is due to being integrated monolithic construction, under the premise of jet flow quality is ensured, this hair
Smaller can be made in bright two-fluid jet apparatus size, can be shorter in length, it is blocked up so as to meet (height) supersonic wind tunnel
The requirement of plug degree and tail portion model must be positioned over the requirement of the diamond-shaped area of (height) supersonic wind tunnel experiment.
Supporter 1 is used to support the jet structure 2 above it.The entirety of supporter 1 is in be vertically arranged.Gas channel 11 is set
The front side of supporter 1 is placed in, the rear side of gas channel 11 is provided with fixed part 12, and its front side that the section of fixed part 12 is less than
Partial section.The multiple through-holes offered on fixed part 12, for connecting fixation, fixed part 12 with support device (not shown)
Setting so that installation of the device of the invention in wind-tunnel it is easy, convenient disassembly.What gas connection 10 can be connected through a screw thread
Mode is connected with ambient atmos feeding mechanism, for feeding gas in gas channel 11.
With reference to Fig. 2 and Fig. 3, in this preferred embodiment, inside is emptied to be formed and sequentially be connected by jet structure 2 by metal material
Main gas stable cavity 20, jet flow contraction flow region 21, jet flow throat 22 and jet flow enlarged portion 23 profile, and at roof 201 and bottom
One block of side plate 203 of connection is respectively welded in both sides between wall 202, main gas stable cavity 20 and jet pipe two sides is sealed, shape
Into one cannot reveal gas, can only be from the rectangular chamber that enlarged portion flows out.
Jet structure 2 is further included before main 20 front end of gas stable cavity, the wedge for the outlet of face wind tunnel nozzle 3
Body 26, the sharp end of wedge precursor 26 are located at the front end of whole device.The leading edge of supporter 1 is located at jet flow in the longitudinal direction
The rear of 2 front end wedge precursor 26 of structure.The front end and contact earliest that the sharp end of wedge precursor 26 is located at whole device
To the part of (height) supersonic flow.It is so designed that normal shock wave can occur to avoid incoming, it is ensured that incoming-flow pressure is accurate, to carry
The accuracy of (height) experiment.
In the present embodiment, disturbance chamber 24 is located at the top of main gas stable cavity 20, and bottom and surrounding are by partition board 243 and master
Gas stable cavity 20 is isolated, at the top of siding 240 be for main gas stable cavity 20 roof 201.
Disturbance chamber 24 is connect by air inlet pipe 25 with disturbance air source.The upper end of air inlet pipe 25 is welded in the bottom of disturbance chamber 24
Partition board 243, lower end, which is passed through main gas stable cavity 20 and is connected to outside chamber, disturbs air source.Disturbance air source toward disturbance chamber 24 either spray
Gas can also be sucked by vacuum disturbance chamber 24.
Further, to reduce influence of the disturbance chamber 24 to main gas stable cavity 20, in of the invention, the volume of chamber 24 is disturbed
Less than the volume of main gas stable cavity 20.Preferably, the volume of volume≤0.1 × main gas stable cavity 20 of disturbance chamber 24, such as
This design, the volume of disturbance chamber 24 are far smaller than the volume of main gas stable cavity 20, therefore will not be steady to main gas stable cavity 20
Pressure effect has any impact.
Further, the bottom wall 202 of main gas stable cavity 20 includes positioned at back segment and is tilted towards jet flow contraction flow region 21 tapered
Tilting section 2020.It is a square cavity with oblique angle 242 to disturb chamber 24.Oblique angle 242 is located at the front of jet flow contraction flow region 21.
Oblique angle 242 is towards jet flow contraction flow region 21, and oblique angle 242 is identical with the angle of inclination of tilting section 2020.With reference to Fig. 4, the present embodiment
In, the height of main gas stable cavity 20 is h1, the angle of width w1, the rear part tilting section 2020 is a1.Disturbing chamber 24 is
Height h2, width w2, rear portion oblique angle 242 angle be a2.Main 20 height h1 of gas stable cavity, width w1 are limited by moulded dimension
System determines substantially.In the present invention, to prevent influence of the disturbance chamber 24 to main gas stable cavity 20, for disturbing chamber 24, design is disturbed
Width w2≤the 0.3w1, h2≤0.35w1 of dynamic chamber 24.To ensure main 20 air-flow smooth flow of gas stable cavity to nozzle entry,
In the present invention, design oblique angle 242 is identical with the angle of inclination of tilting section 2020：30 °≤a1=a2≤45 °.
In the present invention, disturbance channel 241 can be both vertically arranged with siding 240, may be designed in siding 240 in folder
Angle is set.
With reference to Fig. 1 and Fig. 5, in the present embodiment, disturbance channel 241 is the strip slit for being set to siding 240.It disturbs narrow
The width of seam is w3, and disturbance slit and horizontal angle are a3.The gas of barotropic disturbance is sprayed from disturbance slit, and negative pressure is disturbed
It is dynamic to be aspirated from disturbance slit.It does not destroy the basic flowing state of mainstream incoming for guarantee, while ensures reliably to fabricate, this
Invent value range 0.3mm≤w3≤3mm of preferred W3.Preferably, 15 °≤a3≤145 ° of a3 value ranges.
With reference to Fig. 6, as the second embodiment of the present invention, identical with first embodiment basic principle, difference exists
In in the present embodiment, the siding 240 for surrounding disturbance chamber 24 is dismountable structure.
In the present embodiment, straight slot is offered on the roof 201 of main gas stable cavity 20, is provided in the side wall of straight slot embedding
Slot.Disturbance chamber 24 is located at the top of main gas stable cavity 20, is assemblied in by the partition board 243 for being located at bottom and surrounding with embedded
Siding 240 in straight slot surrounds, and the periphery of siding 240 is detachably inserted in in caulking groove.To ensure the sealing performance of disturbance chamber 24,
The sealing ring for sealing fit-up gap between siding 240 and caulking groove is provided in caulking groove.It for example, can be in the side wall of straight slot
U-shaped caulking groove is opened up, and U-shaped sealing ring is assembled in caulking groove, and sealing ring has elasticity, by by the periphery card of siding 240
Enter in U-shaped sealing ring, siding 240 and the fixation and sealing of roof 201, which are matched, to be realized to the extruding of sealing ring by 240 periphery of siding
It closes.Alternatively, siding 240 can also be assemblied in caulking groove by way of oblique cutting importing.In the present embodiment, disturbance slit is opened in
It, so can be by replacing different sidings 240, to change shape of slit, slit sizes, slit above Embedded siding 240
Angle so as to change the flowing gas state above of siding 240, that is, changes the state of 3 incoming of wind tunnel nozzle.Such design only needs
The siding 240 with different disturbance channels 241 is replaced according to requirement of experiment, does not need to change the state of wind tunnel nozzle 3, section
Great amount of investment, design work and wind-tunnel facilities replacement etc. are saved, it is only necessary to a mini Mod, it is possible to realize supersonic speed two-fluid
Flowing, while incoming flow conditions quality can change.
With reference to Fig. 7, as the third embodiment of the present invention, identical with first embodiment basic principle, difference exists
In disturbance channel 241 includes the exhausting hole for being set to siding 240.
In the present embodiment, the circular through-hole of a row is arranged on 24 upper surfaces of disturbance chamber, that is, siding 240.The gas of barotropic disturbance
Body is sprayed from array of circular apertures, and negative pressure disturbance is aspirated from array of circular apertures, so as to change the operating status of mainstream.To ensure not destroy
The basic flowing state of mainstream incoming, while ensure reliably to fabricate, in the present embodiment, the value model of the diameter d of through-hole
Enclose preferably 0.5mm≤d≤2mm.The value range of centre distance L between two neighboring circular through hole is preferably 1.5W3≤L
≤3W3.It is best that the value range of the angle a3 of through-hole and horizontal plane is similarly 30 °≤a3≤145 °.
With reference to Fig. 1 and Fig. 8, when two-fluid jet apparatus of the invention is placed in experiment in wind-tunnel, gas flow is as follows:
Ambient atmos enter gas channel 11 by gas connection 10, subsequently into main gas stable cavity 20, due to main gas
The volume of body stable cavity Room 20 is far longer than jet flow throat 22 and jet outlets, therefore 20 indoor gas pressure of main gas stable cavity
Power will be very steady, be not in gas pulsation, pulsation.Gas after stabilization enters jet flow contraction flow region 21, in jet flow contraction flow region
21 effects are lower to be accelerated, until jet flow throat 22 reaches the velocity of sound, jet flow throat 22 is jet apparatus least part, passes through jet flow throat 22
Gas afterwards further speeds up into supersonic flow V2 under the action of jet flow enlarged portion 23, and is sprayed from outlet.Outlet sprays
Supersonic flow V2 mix shearing with front incoming mainstream V1, form double venturi flowing, reach basic effect shown in Fig. 8.
The significance of the device is for the supersonic wind tunnel based on current single spraying pipe, as long as mixing this device, you can is realized double
Jet pipe shear flow does not need to be transformed incoming jet pipe and wind-tunnel.
Two-fluid jet apparatus using the present invention to the adjustings of incoming flow conditions in two kinds of situation, first, barotropic disturbance, two
It is negative pressure disturbance.
In addition disturbance compressed air source unit as shown in Figure 9 need to be configured in barotropic disturbance：Gas bomb 40, pressure-regulating valve 41, gas
Body pipeline 42, solenoid valve 43, hose 44.Basic principle be from gas bomb 40 come out gas by pressure-regulating valve 41 adjust to
Convenient pressure, after solenoid valve 43 is opened, gas enters air inlet pipe 25 by hose 44, enters back into disturbance chamber 24, logical by disturbing
Road 241 ejects, so as to influence to change (height) Supersonic crossflow operating status, as shown in Figure 10.
In addition disturbance compressed air source unit as shown in Figure 11 need to be configured in negative pressure disturbance：Vacuum pump 50, gas piping 51, suction
Solenoid valve 52, suction hose 53.Basic principle is that vacuum pump 50 starts, and the opening of suction electromagnetic valve 52 is connected by suction hose 53
Air inlet pipe 25 aspirates disturbance chamber 24, and disturbance chamber 24 is allowed to reach negative pressure state, disturbs the pressure inside channel 241 less than outer
The gas pressure of portion's Supersonic crossflow, (height) Supersonic crossflow can receive negative-pressure ward effect, so as to change (height) supersonic speed master
Operating status is flowed, as shown in Figure 12.
In other embodiments, the quantity of disturbance chamber 24 may be multiple, such as two even three, and multiple disturbances
Chamber 24 is isolated each other.Each chamber is mutually isolated, is used to implement different function.
The two-fluid jet flow model of the present invention can not only realize that supersonic flow mixes shearing shape with front incoming mainstream
Nozzle Flow in pairs, while can also change incoming flow conditions, meets more experiment demands, practical application effect more preferably, performance
Stablize, using reliable.
The foregoing is only a preferred embodiment of the present invention, is not intended to restrict the invention, for the skill of this field
For art personnel, the invention may be variously modified and varied.All within the spirits and principles of the present invention, that is made any repaiies
Change, equivalent replacement, improvement etc., should all be included in the protection scope of the present invention.
Claims (10)
1. a kind of two-fluid jet apparatus of changeable incoming flow conditions, for being placed in wind-tunnel, which is characterized in that including supporter
(1) and support is connected to jet structure (2) above the supporter (1),
The supporter (1) is provided with gas connection (10), the gas channel (11) connected with the gas connection (10)；
The main gas stable cavity (20) connected with the gas channel (11), the master are formed with inside the jet structure (2)
Jet flow contraction flow region (21), jet flow throat (22) and jet flow enlarged portion (23) are sequentially connected after gas stable cavity (20)；
The disturbance chamber (24) mutually isolated with the main gas stable cavity (20), institute are also formed with inside the jet structure (2)
Disturbance chamber (24) is stated to be connected with to feed the air inlet pipe (25) for disturbing air source, one of siding of the disturbance chamber (24)
(240) it is provided through connecting the disturbance chamber (24) and extraneous disturbance channel (241), the disturbance channel (241) is used for
The mainstream incoming sprayed for gas ejection in the disturbance chamber (24) with wind tunnel nozzle (3) mixes.
2. the two-fluid jet apparatus of changeable incoming flow conditions according to claim 1, which is characterized in that
The volume of the disturbance chamber (24) is less than the volume of the main gas stable cavity (20).
3. the two-fluid jet apparatus of changeable incoming flow conditions according to claim 2, which is characterized in that
The volume of volume≤0.1 × main gas stable cavity (20) of the disturbance chamber (24).
4. the two-fluid jet apparatus of changeable incoming flow conditions according to claim 1, which is characterized in that
The quantity of the disturbance chamber (24) is multiple, and multiple disturbance chambers (24) are isolated each other.
5. the two-fluid jet apparatus of changeable incoming flow conditions according to claim 1, which is characterized in that
The disturbance channel (241) is the strip slit for being set to the siding (240)；
Or the described disturbance exhausting hole of channel (241) including being set to the siding (240).
6. the two-fluid jet apparatus of changeable incoming flow conditions according to claim 1, which is characterized in that
The disturbance channel (241) is vertically arranged with the siding (240)；
Or the disturbance channel (241) is set with the siding (240) in angle, the angle is 15 °~145 °.
7. the two-fluid jet apparatus of changeable incoming flow conditions according to claim 1, which is characterized in that
Straight slot is offered on the roof (201) of the main gas stable cavity (20), the side wall of the straight slot is provided with caulking groove；
The disturbance chamber (24) positioned at the top of the main gas stable cavity (20), by be located at the partition board of bottom and surrounding with it is embedding
Enter the siding (240) that formula is assemblied in the straight slot to surround, the periphery of the siding (240) is detachably inserted in described embedding
In slot.
8. the two-fluid jet apparatus of changeable incoming flow conditions according to claim 7, which is characterized in that
The sealing ring for sealing fit-up gap between the siding (240) and the caulking groove is provided in the caulking groove.
9. the two-fluid jet apparatus of changeable incoming flow conditions according to claim 1, which is characterized in that
The bottom wall (202) of the main gas stable cavity (20) is including being located at back segment and being tilted towards the jet flow contraction flow region (21) tapered
Tilting section (2020)；
The disturbance chamber (24) is the square cavity with oblique angle (242), and the oblique angle (242) is towards the jet flow contraction flow region
(21), and the oblique angle (242) are identical with the angle of inclination of the tilting section (2020).
10. the two-fluid jet apparatus of changeable incoming flow conditions according to claim 9, which is characterized in that
The angle of inclination of the oblique angle (242) and the tilting section (2020) is 30 °~45 °.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711345840.1A CN108181077B (en) | 2017-12-15 | 2017-12-15 | Double-fluid jet device capable of changing inflow state |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711345840.1A CN108181077B (en) | 2017-12-15 | 2017-12-15 | Double-fluid jet device capable of changing inflow state |
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| CN108181077A true CN108181077A (en) | 2018-06-19 |
| CN108181077B CN108181077B (en) | 2020-01-21 |
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| JPH05248985A (en) * | 1992-03-05 | 1993-09-28 | Mitsubishi Heavy Ind Ltd | Wind tunnel |
| 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 |
| CN104280205A (en) * | 2014-10-24 | 2015-01-14 | 中国人民解放军国防科学技术大学 | Supersonic velocity laminar flow spraying pipe and supersonic velocity quiet wind tunnel thereof |
| CN104729825A (en) * | 2015-04-03 | 2015-06-24 | 中国航天空气动力技术研究院 | Auxiliary jet-flow system for controlling high speed wind tunnel transonic flow field |
| CN105973565A (en) * | 2016-06-29 | 2016-09-28 | 中国航天空气动力技术研究院 | Lateral jet flow system for wind tunnel interference test |
| CN106840589A (en) * | 2017-03-30 | 2017-06-13 | 中国人民解放军63820部队吸气式高超声速技术研究中心 | Simulate the experimental provision and experimental technique of hot Jet enterference |
-
2017
- 2017-12-15 CN CN201711345840.1A patent/CN108181077B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH05248985A (en) * | 1992-03-05 | 1993-09-28 | Mitsubishi Heavy Ind Ltd | Wind tunnel |
| 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 |
| CN104280205A (en) * | 2014-10-24 | 2015-01-14 | 中国人民解放军国防科学技术大学 | Supersonic velocity laminar flow spraying pipe and supersonic velocity quiet wind tunnel thereof |
| CN104729825A (en) * | 2015-04-03 | 2015-06-24 | 中国航天空气动力技术研究院 | Auxiliary jet-flow system for controlling high speed wind tunnel transonic flow field |
| CN105973565A (en) * | 2016-06-29 | 2016-09-28 | 中国航天空气动力技术研究院 | Lateral jet flow system for wind tunnel interference test |
| CN106840589A (en) * | 2017-03-30 | 2017-06-13 | 中国人民解放军63820部队吸气式高超声速技术研究中心 | Simulate the experimental provision and experimental technique of hot Jet enterference |
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| Publication number | Publication date |
|---|---|
| CN108181077B (en) | 2020-01-21 |
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