CN208383417U - A kind of subsonic jets formula air feeders calibration wind tunnel - Google Patents
A kind of subsonic jets formula air feeders calibration wind tunnel Download PDFInfo
- Publication number
- CN208383417U CN208383417U CN201821225417.8U CN201821225417U CN208383417U CN 208383417 U CN208383417 U CN 208383417U CN 201821225417 U CN201821225417 U CN 201821225417U CN 208383417 U CN208383417 U CN 208383417U
- Authority
- CN
- China
- Prior art keywords
- section
- segment
- wind tunnel
- steady flow
- contraction section
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Landscapes
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
A kind of pneumatic probe correction wind-tunnel of velocity of sound jetting type in Asia that the utility model belongs to air feeders calibration wind tunnel field, speed of incoming flow in particular to can be improved；It includes sequentially connected entrance expansion segment, steady flow segment, contraction section and experimental section；Entrance expansion segment is gradually expanded from end to steady flow segment, and the contraction section is from steady flow segment to experimental section Stepwize Shrink；Inlet porting spreader on the entrance expansion segment, the steady flow segment include along distinguished and admirable to the exterior ring cap set gradually, honeycomb and several inner ring sleeves and broken whirlpool net that are spaced apart from each other setting；Total pressure probe mounting base is set close to steady flow segment on the contraction section, static pressure hole is arranged in separate steady flow segment on contraction section.Wind tunnel body volume reduces, and occupied area reduces, and is easily installed and is laid out.After rationally designing wind-tunnel and shrinking when each unit size, it is able to use under small electric machine power and realizes biggish free stream Mach number.
Description
Technical field
The utility model belongs to air feeders calibration wind tunnel field, in particular to a kind of subsonic speed that speed of incoming flow can be improved
The pneumatic probe correction wind-tunnel of jetting type.
Background technique
Wind-tunnel (Wind tunnel): i.e. wind tunnel laboratory is to generate and control in a manual manner air-flow, makes its satisfaction
Specific flow field needs and then is used to a kind of pipe-like experimental facilities of simulated flight device or entity ambient gas mobility status.Calibration
Wind-tunnel belongs to one kind of wind-tunnel, can generate air-flow uniform and stable and with certain pressure and speed, pneumatic to meet
The needs of probe correction.
Wind tunnel experiment is indispensable important component in aerodynamics and its associated mechanical research field.Fluid
The wind tunnel experiment of terms of mechanics is broadly divided into dynamometry experiment, surveys compacting is tested and thermometric is tested etc..Air feeders are as easy
Load cell is widely used in wind tunnel experiment.But air feeders need to be calibrated using calibration wind tunnel before use,
The flow field quality of wind-tunnel, outlet size, mounting arrangements requirement and energy consumption etc. are to influence calibration result or experimental cost at this time
An important factor for.Currently, the most volume of air feeders calibration wind tunnel that can provide higher free stream Mach number is more huge, institute's duty
Between it is larger, and operating cost is higher.Separately there is the low-speed wind tunnel of some smaller sizes, the free stream Mach number that can be provided is lower,
Higher inlet flow conditions needed for having been unable to meet probe calibration.Therefore, it is necessary to a kind of Sizes, simple to install, flow field product
The good calibration wind tunnel of matter come meet probe calibration to higher free stream Mach number the needs of.
The shortcomings that existing calibration wind tunnel is primarily present following aspect:
(1) bulky dimensions take up a large area, difficult to install, and then cause construction cost higher.
(2) wind-tunnel achievable free stream Mach number range in part is relatively narrow；When wind tunnel body size is larger, wanted to obtain
The stabilization incoming flow asked, higher to the pressure requirements of gas source, this leads to wind tunnel operation high expensive.
Summary of the invention
In view of the defect of the prior art, the utility model provides a kind of subsonic jets formula air feeders calibration wind tunnel, should
Calibration wind tunnel can generate stable high Mach incoming flow (up to 0.9Ma) under lesser hole body size, solve most of Asias
The problem that velocity of sound calibration wind tunnel volume is larger, occupied area is wide, operating cost is high has higher flexibility and ease for use.
In order to achieve the above objectives, the utility model proposes technical solution be a kind of calibration of subsonic jets formula air feeders
Wind-tunnel comprising sequentially connected entrance expansion segment, steady flow segment, contraction section and experimental section；Entrance expansion segment is from end to steady
Stream section is gradually expanded, and the contraction section is from steady flow segment to experimental section Stepwize Shrink；Inlet porting shunts on the entrance expansion segment
Cone, the steady flow segment includes along distinguished and admirable to the exterior ring cap set gradually, honeycomb and several inner ring sleeves for being spaced apart from each other setting
And broken whirlpool net；Total pressure probe mounting base is set close to steady flow segment on the contraction section, static pressure is arranged in separate steady flow segment on contraction section
Hole.
Preferably, the entrance expansion segment, steady flow segment, contraction section pass through be arranged in entrance expansion segment rear end front plate and
The rear plate that contraction section front end is arranged in is fixed.
Preferably, several inner ring sleeves for being spaced apart from each other setting and broken whirlpool net include the level-one inner ring sleeve set gradually,
The broken whirlpool net of level-one, second level inner ring sleeve, the broken whirlpool net of second level, three-level inner ring sleeve, the broken whirlpool net of three-level and level Four inner ring sleeve.
Preferably, the broken whirlpool net of the level-one, the broken whirlpool net of second level and the broken whirlpool net of three-level be followed successively by 100 mesh/cun, 200 mesh/cun,
400 mesh/cun.
Preferably, the section of the experimental section is circle；Experimental section radius is 17.5mm.
Further, the shrinkage ratio of the contraction section is taken as 8, and contraction section outlet size is that R2 is 35mm, import circle size
R1 is 284mm, shrinks 0.5-1.0 times that segment length uses inlet diameter
Preferably, shrinking segment length is 200mm.
Preferably, the steady flow segment is cylinder.
Preferably, the honeycomb is made of side by side multiple cross-section small pipelines, and small pipeline is regular hexagonal section, takes bee
Nest bore is 3mm, length 50mm.
Preferably, the entrance expansion segment molded line is linear type, inlet size diameter 200mm, outlet size diameter
284mm。
Preferably, the contraction section is the contraction molded line based on Vito Xin Siji formula, and formula is as follows:
In formula, R2- contraction section outlet size, R1- import circle size, x- axial distance, a- contraction segment length；It uses first
Fortran edits out the point program for calculating coordinate of curve, calculates corresponding specific disengaging port radius and shrinks the point of segment length
Coordinate；Counted coordinate is imported into inside UG later, generates and shrinks segment model, pass through Ansys CFX numerical value software for calculation
Flow Field Calculation is carried out, optimal contraction section flow field quality is analyzed, to obtain contraction segment model；
In formula, C indicates shrinkage ratio, C=(h0/h1)2, wherein L is selected, it can be changed in broad range, and
h0It is given contraction section entrance height size, h1It is given contraction section outlet height size.X is in given L length range
Interior shrinkage curve abscissa, y are the shrinkage curve ordinates in given L length range.
The utility model has the beneficial effects that wind tunnel body volume reduces, occupied area reduces, and is easily installed and is laid out.?
After rational design wind-tunnel shrinks when each unit size, it is able to use under small electric machine power and realizes biggish free stream Mach number,
After rationally adjusting frequency converter frequency, Mach number may make continuously to adjust in the range of 0.1-0.9.It is low in cost, wind-tunnel
Hole body uses aluminum alloy materials, can reduce wind-tunnel weight under the premise of meeting intensity requirement, reduces cost.Used air blast
Machine power is smaller, and operating cost also can decrease.
The form that the utility model chooses wind-tunnel is jetting type, and calibration wind tunnel hole body includes: that air inlet section, steady flow segment (include
Fairing), contraction section and experimental section.The air inlet section is damaged for expanding air-flow with reducing air-flow in the flowing of steady flow segment
It loses；The steady flow segment, to eliminate the large vortex stucture in flowing, is reduced for the fisrt feature air-flow to be carried out broken whirlpool, rectification
The turbulence level of air-flow generates second of feature air-flow；So-called contraction section, under the premise of flow separation does not occur to air-flow
It is steady to accelerate, to obtain the third the uniform and stable feature air-flow for meeting Mach number requirement.
Detailed description of the invention
Fig. 1 is the vertical section of wind tunnel body；
Fig. 2 is entrance expansion segment structural schematic diagram；
Fig. 3 is sectional view along A-A in Fig. 2；
Fig. 4 is B-B direction cross-sectional view in Fig. 3；
Fig. 5 is contraction section structural schematic diagram；
Fig. 6 be in Fig. 5 C-C to cross-sectional view；
Fig. 7 is contraction section model curve schematic diagram；
Fig. 8 is the outline drawing of wind-tunnel；
In figure: 1, entrance expansion segment, 2, steady flow segment, 3, contraction section, 4, experimental section, 5, inlet distribution cone, 6, exterior ring cap, 7,
Honeycomb, 8, total pressure probe mounting base, 9, static pressure hole, 10, front plate；11, rear plate, 12, level-one inner ring sleeve, 13, level-one it is broken
Whirlpool net, 14, second level inner ring sleeve, 15, the broken whirlpool net of second level, 16, three-level inner ring sleeve, 17, the broken whirlpool net of three-level, 18, level Four inner ring sleeve,
19, molded line, 20, total pressure probe are shunk.
Specific embodiment
With reference to the accompanying drawing, the utility model is further described.
Embodiment 1
A kind of subsonic jets formula air feeders calibration wind tunnel, it is characterised in that: including sequentially connected entrance expansion segment
1, steady flow segment 2, contraction section 3 and experimental section 4；Entrance expansion segment 1 is gradually expanded from end to steady flow segment, the contraction section 3 by
Steady flow segment 2 is to 4 Stepwize Shrink of experimental section；Inlet porting spreader 5 on the entrance expansion segment 1, the steady flow segment 2 include along
It is distinguished and admirable to the exterior ring cap 6 set gradually, honeycomb 7 and several inner ring sleeves and broken whirlpool net that are spaced apart from each other setting；The contraction section 3
Upper that total pressure probe mounting base 8 is arranged close to steady flow segment 2, static pressure hole 9 is arranged in separate steady flow segment 2 on contraction section 3.
Further, the entrance expansion segment 1, steady flow segment 2, contraction section 3 pass through before entrance expansion segment rear end is arranged in
Clamping plate 10 and the rear plate 11 that contraction section front end is arranged in are fixed.
Further, several inner ring sleeves for being spaced apart from each other setting and broken whirlpool net include the level-one inner ring sleeve set gradually
12, the broken whirlpool net 13 of level-one, second level inner ring sleeve 14, the broken whirlpool net 15 of second level, three-level inner ring sleeve 16, the broken whirlpool net 17 of three-level and level Four inner ring
Set 18.
Generally, the form that the utility model chooses wind-tunnel is jetting type, and calibration wind tunnel hole body includes: that air inlet section (enters
Mouthful expansion segment 1), steady flow segment 2 (including fairing), contraction section 3 and experimental section.The air inlet section, for expanding air-flow, with
Air-flow is reduced in the flow losses of steady flow segment；The steady flow segment, for the fisrt feature air-flow to be carried out broken whirlpool, rectification, with
The large vortex stucture in flowing is eliminated, the turbulence level of air-flow is reduced, generates second of feature air-flow；So-called contraction section, for not
Occur steadily to accelerate air-flow under the premise of flow separation, to obtain the third the uniform and stable feature for meeting Mach number requirement
Air-flow.The vertical section of wind tunnel body is as shown in Figure 1.It should be noted that such as being shunk in the design and selection course of associated components
Length, the Performance Match of curve form and each component of section, using multiple CFD calculating and the continuous amendment of result, finally
The optimal structure of size is obtained.
The section of experimental section 4 is circle；It can guarantee that exit flow is uniform and stable, reduce the dry of hole wall boundary-layer to the greatest extent
It disturbs.Because needing end of probe in plane x in probe calibration procedure, y both direction has deflection, and circular section more can guarantee out
Implication stream it is uniform.
4 radius of experimental section is 17.5mm, and end of probe need to deflect 30 ° of needs in x, y both direction, while consider spy
The influence of the size of needle section, it is 17.5mm that the utility model, which chooses 4 radius of experimental section,.
Contraction section 3 is it acts as air-flow is accelerated, and speed needed for reaching experiment, when design should meet claimed below:
When along contraction flow, Dong Bishang is not separated air-flow；The air flow demand that contraction section 3 exports is uniform, straight and stable；
Contraction section is unsuitable too long.
The shrinkage ratio of contraction section 3 is taken as 8, can obtain preferable flow field quality.3 outlet size of contraction section is according to experimental section
Size take R2 be 35mm, according to shrinkage ratio calculate import circle size R1 be about 284mm, shrink segment length generally use import straight
0.5-1.0 times of diameter, taking L is 200mm.
Common 3 molded line of contraction section specifically includes that Vickers curve, moves axis Vickers curve, bicubic curve, five power curves
Deng.Contraction section 3 uses the contraction molded line 19 based on Vito Xin Siji formula, and formula is as follows:
R2- contraction section outlet size, R1- import circle size, x- axial distance, a- shrink segment length；
The point program for calculating coordinate for editing out curve using Fortran first, calculate corresponding specific disengaging port radius with
And shrink the point coordinate of segment length.Counted coordinate is imported into inside UG later, generates and shrinks segment model, pass through Ansys
CFX numerical value software for calculation carries out Flow Field Calculation, optimal contraction section flow field quality is analyzed, to obtain contraction segment model.This reality
With novel contraction section vertical profile drawing, as shown in Figure 5.
In formula, C indicates shrinkage ratio, C=(h0/h1)2, wherein L is selected, it can be changed in broad range, and
h0It is given contraction section entrance height size, h1It is given contraction section outlet height size.X is in given L length range
Interior shrinkage curve abscissa, y are the shrinkage curve ordinates in given L length range.
Stable section uses cylinder design in the utility model, and bed-plate dimension is determined according to contraction section import.Inside it
Be equipped with honeycomb and broken whirlpool net etc. fairings, its purpose is that make air-flow uniformly, reduce turbulivity.
The honeycomb is made of side by side many cross-section small pipelines, and shape is such as honeycomb, its role is to lead straight air-flow,
So that it is parallel to wind-tunnel axis, while the large eddies in air-flow are divided into micro cyclone, is conducive to the decaying for accelerating vortex.
Meanwhile honeycomb pipeline also helps the VELOCITY DISTRIBUTION for improving air-flow to the friction of air-flow.In the utility model, to reduce loss system
Number uses regular hexagonal section.Meanwhile to reach preferable rectification effect, taking honeycomb bore is 3mm, length 50mm.
The effect of broken whirlpool net is to reduce stream turbulence.In the utility model, it joined three layers of broken whirlpool in wind-tunnel steady flow segment
Net, the thickness of net be followed successively by 100 mesh/cun, 200 mesh/cun, 400 mesh/cun.
The effect of expansion segment is that the kinetic energy of air-flow is transformed into pressure energy, to reduce air-flow in the energy loss of steady flow segment.
In the utility model, expansion segment molded line is linear type, and inlet size is determined according to fan outlet size, diameter 200mm, outlet
Size is determining according to steady flow segment size, diameter 284mm.Meanwhile to improve the uniformity of air-flow, it is added and shunts in expansion segment
Cone.
After the size for determining each component of wind tunnel body, wind tunnel body entirety lateral dimension is 726mm, compared with other
Subsonic speed air feeders calibration wind tunnel, size greatly reduce.
The present embodiment selects two-stage centrifugal type air blower, rated power 17.5KW, it is possible to provide air-flow incoming flow stagnation pressure is
60000Pa.Air blower is located at wind-tunnel inducer upstream, is connect by gas-guide pipeline and ring flange with wind tunnel body.
The present embodiment the utility model has the advantages that compared with existing calibration wind tunnel technology, the present embodiment has the advantage that
Wind tunnel body volume reduces, and occupied area reduces, and is easily installed and is laid out；Rationally designing, wind-tunnel contraction is when each
After unit size, it is able to use under small electric machine power and realizes biggish free stream Mach number, by rationally adjusting frequency converter frequency
Afterwards, Mach number may make continuously to adjust in the range of 0.1-0.9；Low in cost, wind tunnel body uses aluminum alloy materials, full
It can reduce wind-tunnel weight under the premise of sufficient intensity requirement, reduce cost.Used blower power is smaller, and operating cost also can
It decreases.
The embodiments of the present invention are described in detail above, but the content is only the preferable of the utility model
Embodiment should not be considered as limiting the scope of the present invention.It is all to become according to equalization made by the scope of the utility model
Change and improve etc., it shall still fall within the scope of this patent.
Claims (10)
1. a kind of subsonic jets formula air feeders calibration wind tunnel, it is characterised in that: including sequentially connected entrance expansion segment, surely
Flow section, contraction section and experimental section；Entrance expansion segment is gradually expanded from end to steady flow segment, and the contraction section is from steady flow segment to reality
Test a section Stepwize Shrink；Inlet porting spreader on the entrance expansion segment, the steady flow segment include along distinguished and admirable to setting gradually
Exterior ring cap, honeycomb and several inner ring sleeves and broken whirlpool net that are spaced apart from each other setting；It is arranged on the contraction section close to steady flow segment
Static pressure hole is arranged far from steady flow segment on contraction section in total pressure probe mounting base.
2. a kind of subsonic jets formula air feeders calibration wind tunnel according to claim 1, it is characterised in that: the entrance
Expansion segment, steady flow segment, contraction section pass through the front plate that entrance expansion segment rear end is arranged in and the rear folder that contraction section front end is arranged in
Plate is fixed.
3. a kind of subsonic jets formula air feeders calibration wind tunnel according to claim 1, it is characterised in that: described mutual
Spaced several inner ring sleeves and broken whirlpool net include the level-one inner ring sleeve set gradually, the broken whirlpool net of level-one, second level inner ring sleeve, two
The broken whirlpool net of grade, three-level inner ring sleeve, the broken whirlpool net of three-level and level Four inner ring sleeve.
4. a kind of subsonic jets formula air feeders calibration wind tunnel according to claim 3, it is characterised in that: the level-one
The broken whirlpool net of broken whirlpool net, second level and the broken whirlpool net of three-level be followed successively by 100 mesh/cun, 200 mesh/cun, 400 mesh/cun.
5. a kind of subsonic jets formula air feeders calibration wind tunnel according to claim 1, it is characterised in that: the experiment
The section of section is circle；Experimental section radius is 17.5mm.
6. a kind of subsonic jets formula air feeders calibration wind tunnel according to claim 1, it is characterised in that: the contraction
The shrinkage ratio of section is taken as 8, and contraction section outlet size is that R2 is 35mm, and import circle size R1 is 284mm, shrink segment length use into
0.5-1.0 times of mouth circle size R1.
7. a kind of subsonic jets formula air feeders calibration wind tunnel according to claim 1, it is characterised in that: the current stabilization
Section is cylinder.
8. a kind of subsonic jets formula air feeders calibration wind tunnel according to claim 1, it is characterised in that: the honeycomb
Device is made of side by side multiple cross-section small pipelines, and small pipeline is regular hexagonal section, and taking honeycomb bore is 3mm, length 50mm.
9. a kind of subsonic jets formula air feeders calibration wind tunnel according to claim 1, it is characterised in that: the entrance
Expansion segment molded line is linear type, inlet size diameter 200mm, outlet size diameter 284mm.
10. a kind of subsonic jets formula air feeders calibration wind tunnel according to claim 1, it is characterised in that: the receipts
The contraction segment model of contracting section, curve equation are as follows:
In formula, C indicates shrinkage ratio, C=(h0/h1)2, wherein L is selected, and h0It is given contraction section entrance height size,
h1It is given contraction section outlet height size；X is the shrinkage curve abscissa in given L length range, and y is given
L length range in shrinkage curve ordinate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821225417.8U CN208383417U (en) | 2018-07-31 | 2018-07-31 | A kind of subsonic jets formula air feeders calibration wind tunnel |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821225417.8U CN208383417U (en) | 2018-07-31 | 2018-07-31 | A kind of subsonic jets formula air feeders calibration wind tunnel |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208383417U true CN208383417U (en) | 2019-01-15 |
Family
ID=64962034
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821225417.8U Active CN208383417U (en) | 2018-07-31 | 2018-07-31 | A kind of subsonic jets formula air feeders calibration wind tunnel |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208383417U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108709712A (en) * | 2018-07-31 | 2018-10-26 | 大连凌海华威科技服务有限责任公司 | Subsonic jets formula air feeders calibration wind tunnel |
-
2018
- 2018-07-31 CN CN201821225417.8U patent/CN208383417U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108709712A (en) * | 2018-07-31 | 2018-10-26 | 大连凌海华威科技服务有限责任公司 | Subsonic jets formula air feeders calibration wind tunnel |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108709712A (en) | Subsonic jets formula air feeders calibration wind tunnel | |
| CN207215423U (en) | A kind of subsonic wind tunnel | |
| CN105043711B (en) | A kind of the wind-tunnel diffuser and wind-tunnel diffusion method of compatible multi nozzle | |
| CN103411769B (en) | For the air inlet stable-pressure device of gas-turbine unit swirler performance test | |
| CN108345714B (en) | Numerical simulation method for parameter design of inner annular jet flow pressure stabilizing cavity | |
| CN101750204A (en) | Engine simulator for dynamic simulation test in high-speed wind tunnel | |
| CN110160734A (en) | Wind tunnel nozzle, active noise reducing device and method based on porous media | |
| CN104316286B (en) | A kind of rotor aerodynamic testing platform low turbulence design method | |
| CN112229639B (en) | Design method of aero-engine intake total pressure distortion generation device | |
| CN208383417U (en) | A kind of subsonic jets formula air feeders calibration wind tunnel | |
| CN107843435A (en) | Engine variable sector inlet pressure distortion analog board | |
| CN106596038B (en) | The calculation method of the mute wind tunnel nozzle suction flow of supersonic and hypersonic | |
| CN107504066A (en) | A kind of integral shaft symmetrical jet pressure stabilizing cavity supplied to high pressure disk gas bearing | |
| CN109353527A (en) | Using the BLI air intake duct of mixed flow control method | |
| CN111307394B (en) | Multistage power controllable backflow type wind tunnel | |
| CN103500265A (en) | Method for confirming wind tunnel shrink section curve | |
| CN112747930B (en) | Air inlet distortion generating device of aircraft engine | |
| CN106678179A (en) | Cylindrically symmetric internal circumferential jet flow pressure stabilizing chamber supplying gas to high-pressure disc gas bearing | |
| CN208026450U (en) | Gas driven generator blowing experiment device | |
| CN109827737B (en) | Variable outlet synthetic jet actuator | |
| CN207750264U (en) | Injection type centrifugal blower | |
| CN212513627U (en) | Air inlet system for annular blade cascade performance tester | |
| CN107976236B (en) | Steady flow structure and steady flow method of sonic nozzle gas flow standard device | |
| CN212082713U (en) | Supersonic steady-state pressure probe with plasma jet device | |
| CN211370561U (en) | Air inlet channel |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |