CN105043711B - A kind of the wind-tunnel diffuser and wind-tunnel diffusion method of compatible multi nozzle - Google Patents
A kind of the wind-tunnel diffuser and wind-tunnel diffusion method of compatible multi nozzle Download PDFInfo
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- CN105043711B CN105043711B CN201510472465.1A CN201510472465A CN105043711B CN 105043711 B CN105043711 B CN 105043711B CN 201510472465 A CN201510472465 A CN 201510472465A CN 105043711 B CN105043711 B CN 105043711B
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Abstract
The invention discloses a kind of wind-tunnel diffuser of compatible multi nozzle and wind-tunnel diffusion methods；The wind-tunnel diffuser is made of collector (1), contraction section (2), second throat (3) and the expansion segment (4) being sequentially connected；The collector includes collection port (11), direct tube section (12), first support (13), guide rail (14) and driving device (15)；When replacing different sized nozzles, second throat, contraction section, second throat and expansion segment all remain unchanged, to form supersonic speed flowing full in collector by the collection port for replacing different bores and the position for adjusting direct tube section (12) relative constriction section (2), to realize the compatibility of multiple and different sized nozzles；To solve the state compatibling problem of the multiple and different scale jet pipes of high temperature ultrasonic speed wind-tunnel.Not only reduce the construction cost of wind-tunnel, and make wind-tunnel be more convenient for using.
Description
Technical field
The present invention relates to a kind of wind-tunnel diffuser and wind-tunnel diffusion methods.
Background technique
Wind-tunnel be can it is artificially generated and control air-flow, with the flowing of simulated flight device or object ambient gas, and can measure
Air-flow is to the effect of object and a kind of pipe-like testing equipment of observation physical phenomenon.The effect of diffuser is by certain
The hypersonic flow that jet pipe sprays is changed into sub-critical flow or the lower air-flow of Mach number by multishock, as far as possible raising diffusion effect
Rate improves exhaust capacity, to mitigate the burden of exhaust system below, while being also beneficial to the starting of supersonic nozzle, and energy
It is enough energy saving.Diffuser is generally made of collector, contraction section, second throat and four part of expansion segment.Second throat refers to
Equal straight sections, the usually the smallest position in diffuser middle section in diffuser among contraction section and expansion segment；Second throat is wind
The general term in hole field is for the first throat of wind-tunnel, and first throat refers to that wind tunnel heater is used to generate
Ultrasonic venturi.
High-temperature fuel gas supersonic wind tunnel carries out hot examination to model using the high temperature supersonic airstream of nozzle exit, different
Nozzle exit diameter corresponds to different emulation modes, which needs the supersonic nozzle of the different bores of compatible more sets.Conventional
The method of the compatible jet pipe of diffuser is that the diffuser second throat of corresponding diameter is replaced according to jet pipe bore, in replacement second throat
When, the size of the collector, contraction section and the diffuser that are connected therewith also changes correspondingly, and this mode can obtain preferable diffusion
Device efficiency, but corresponding manufacturing cost is higher, and is used interchangeably inconvenience.
Summary of the invention
The technical problem to be solved by the present invention is to：One kind wind-tunnel diffuser at low cost, easy to use and diffusion are provided
Method, the state that can be realized the multiple and different scale jet pipes of high-temperature fuel gas supersonic wind tunnel is compatible, ensure that in experimental cabin and is formed
Uniform high-quality gas flow field.
The present invention includes following technical solution：
A kind of wind-tunnel diffuser of compatible multi nozzle, the wind-tunnel diffuser is by the collector, the contraction section, that are sequentially connected
Two venturis and expansion segment composition, the collector are used to collect the gas of jet pipe ejection, which is characterized in that the collector includes
Collection port, direct tube section, first support, guide rail and driving device；Collection port be it is tubaeform, collection port point diameter is than rear end diameter
Greatly, collection port point diameter determines that collection port rear end is connected with direct tube section front end according to jet size；First support upper end and straight
Cylinder section front end is fixedly connected, and first support lower end is mounted on guide rail, and first support can be opposite under the drive of the drive
Guide rail sliding；Contraction section is inserted into direct tube section rear end, and direct tube section being capable of the sliding of relative constriction section.
Collection port point diameter is 1.2 times of corresponding jet size.
Direct tube section internal diameter is 1.15 times of maximum jet size.
The diameter of the second throat is maximum jet size.
Contraction section includes straight tube shape coat part and truncated cone constriction；Straight tube shape outer race section is inserted into direct tube section rear end
The front end divided, direct tube section being capable of the slidings of relative constriction section straight tube shape coat part；The rear end of straight tube shape coat part and the frustum of a cone
Shape constriction is fixedly connected.
12 groups of spring leafs are arranged circumferentially between the rear end and straight tube shape coat part of direct tube section.
The compatible method of multi nozzle is carried out using above-mentioned wind-tunnel diffuser, when replacing different sized nozzles, second throat,
Contraction section, second throat and expansion segment all remain unchanged, by the collection port and the opposite receipts of adjustment direct tube section of replacing different bores
The position of contracting section to form supersonic speed flowing full in collector, to realize the compatibility of multiple and different sized nozzles.
The present invention has the following advantages that compared with prior art：
This method, using two venturis are fixed, covers difference by adjusting collector for the first time to realize that same set of wind-tunnel is compatible more
The jet pipe of bore, and be applied to high-temperature fuel gas stream supersonic wind tunnel, that is, a diffuser ontology is used, different working conditions is logical
It crosses and replaces the mode of corresponding collector collection port and collector sliding and improve diffuser efficiency, realize different combustion gas streams
Experimental cabin pressure and nozzle exit static pressure matched well under environment, ensure that and form uniform high-quality gas stream in experimental cabin
, solve the state compatibling problem of the multiple and different scale jet pipes of high temperature ultrasonic speed wind-tunnel；It is compared with traditional wind-tunnel, reduces manufacture
Cost, while wind-tunnel is more convenient to use.
Detailed description of the invention
Fig. 1 is diffuser schematic diagram of the present invention；
Fig. 2 is collector structure schematic diagram of the present invention；
Fig. 3 is collector of the present invention and contraction section assembling schematic diagram；
Fig. 4 is the interface diagram of collector of the present invention and contraction section；
Fig. 5 is second throat schematic diagram；
Fig. 6 is the simulated flow pattern for adjusting collector, and the nozzle exit diameter of Fig. 6 a is 340mm, and the nozzle exit of Fig. 6 b is straight
Diameter is 500mm, and the nozzle exit diameter of Fig. 6 c is 740mm.
Specific embodiment
Just the present invention is described further in conjunction with attached drawing below.
The basic schematic diagram of wind-tunnel diffuser is as shown in Figure 1, mainly by collector 1, contraction section 2, second throat 3, expansion
Section 4 forms, and effect is to improve extension pressur efficiency, improve exhaust capacity.Collector 1 sprays as shown in Fig. 2, mainly collecting jet pipe
Supersonic speed combustion gas, can smoothly enter into it in diffuser；Contraction section 2 mainly realizes supersonic airstream by reducing area
Slow down and is pressurized；Second throat 3 is an isodiametric direct tube section, as shown in figure 5, supersonic airstream passes through one in second throat
Serial shock train realizes pressurization of slowing down, and is changed into subsonic flow in second throat near exit；Expansion segment 4 is to pass through increase
Area come realize subsonic flow deceleration pressurization.Two factors that experimental cabin pressure is directly affected in diffuser are second throats
Size and collector size and location.
The area ratio of second throat and nozzle exit has direct influence to diffuser performance.It is sprayed thus according to this testing stand
The flow parameter of pipe outlet, carries out detailed Pneumatic Calculation, the size of available second throat.The maximum stream flow in a certain section
It is directly proportional to sectional area and stagnation pressure, it is inversely proportional with the square root of stagnation temperature.To guarantee that wind-tunnel does not block, any
The maximum stream flow of moment second throat should all be not less than the flow of the moment jet pipe.Diffuser second throat size is true according to the following formula
It is fixed.
A in formula (2)1、A2It is the area of nozzle area and second throat respectively, m is gas flow, and q is flow function, and K is
Constant relevant with exchangeability, η are less than 1 constant, P1Indicate the pressure of spout outlet, P2Indicate the pressure of second throat,
T*Indicate total temperature；In view of losing after normal shock wave to the viscous pressure of diffuser, stagnation pressure is multiplied by a pressure less than 1 after formula medium wave
Power recovery coefficient.The size that can be obtained by the second throat corresponding to jet pipe in this way, since the size of second throat is fixed, because
This chooses size of the second throat size for corresponding to maximum jet pipe as fixed second throat.Can also according to engineering experience,
The diameter of second throat (D) is directly designed as maximum jet size (Dmax)。
When supersonic airstream forms flowing full not in collector, influence of the diffuser second throat diameter to experimental cabin compared with
Greatly, and when collector forms supersonic speed flowing full, the bore and distance of collector collection port then can generate direct shadow to lock pressure
It rings.According to engineering experience, the diameter D of collector collection port1With nozzle exit diameter D2Relationship be：D1=1.2D2.Therefore, exist
In the case where stationary diffuser second throat, the control to lock pressure can be realized by the adjusting to collector bore and position
System, to obtain the gas flow field of varying environment.
For the jet pipe of different scales, the size of second throat is secured in diffuser, reduces diffuser in this way
Efficiency, while also will affect the pressure in experimental cabin；Therefore it is collected in the invention discovery using replacement is corresponding
Device collection port and the mode of collector sliding carry out the pressure of Adjustment Tests field, and guarantee obtains the gas flow field of high-quality.
As shown in Fig. 2, collector includes collection port 11, direct tube section 12, first support 13, guide rail 14 and driving device 15.
Collection port is tubaeform.11 point diameter of collection port is bigger than rear end diameter, and 11 point diameter of collection port is determined according to jet size,
11 rear end of collection port is connected with 12 front end of direct tube section.Preferably, horn inlet diameter is 1.2 times of jet size.Direct tube section
12 internal diameters are 1.15 times of maximum jet size.When replacing various sizes of jet pipe, collection port inlet diameter is according to jet pipe bore
It is adjusted, rear portion is connected size constancy with direct tube section, i.e. loudspeaker metastomium is constant, entrance and opening angle adjustment；To real
The matching of static pressure after existing experimental cabin pressure and jet pipe go out.13 upper end of first support is fixedly connected with 12 front end of direct tube section, and first
13 lower end of frame is mounted on guide rail 14, and first support 13 opposite rail 14 can be slided under the driving of driving device 15.
As shown in figure 3, contraction section 2 includes straight tube shape coat part 21 and truncated cone constriction 22；After direct tube section 12
End insertion straight tube shape coat part 21, direct tube section 12 can 2 straight tube shape coat part 21 of relative constriction section sliding, to can realize
The opposite sliding of collector.The rear end of straight tube shape coat part 21 is fixedly connected with 22 front end of truncated cone constriction, and second
Bracket is used to support truncated cone constriction 22；The point diameter of truncated cone constriction 22 is bigger than rear end diameter.
As shown in figure 4,12 groups of spring leafs 16 are arranged circumferentially between the rear end and straight tube shape coat part 21 of direct tube section 12,
Purpose is when keeping collector mobile, can to play guiding role and prevent from causing it due to factors such as mismachining tolerance, thermal deformations
Between there is locking phenomenon.
According to collection port apart from the pneumatic requirement of spout and the requirement of test area, the movement of available collector
Range.Such as：Minimum and maximum distance of the collection port apart from nozzle exit is respectively 1.0m and 2.9m in the present invention, therefore mobile
Distance is 1.9m.Preferably, the first support 13 is two, is mounted in two parallel linear guides, the driving dress
Setting 15 can be achieved collector back-and-forth motion using motor driven ball screws pair, meet the need of jet pipe exchange and various different models
It asks.
Diffuser second throat diameter 700mm adjusts separately collector when replacing the jet pipe of 740/ Φ of Φ, 500/ Φ 340
Inlet diameter is 880/ Φ of Φ, 560/ Φ 400, and Mach cloud atlas is as shown in Figure 6.It can be seen that by analog result, flow field can smoothly be built
Vertical, lock pressure and nozzle exit pressure match are good.This Replacing Scheme can utmostly share diffuser, reduce pork barrel.
Unspecified part of the present invention belongs to common sense well known to those skilled in the art.
Claims (5)
1. a kind of wind-tunnel diffuser of compatible multi nozzle, the wind-tunnel diffuser is by the collector (1), the contraction section that are sequentially connected
(2), second throat (3) and expansion segment (4) composition, the collector (1) are used to collect the gas of jet pipe ejection, and feature exists
In the collector includes collection port (11), direct tube section (12), first support (13), guide rail (14) and driving device (15)；It receives
Ji Kou (11) be it is tubaeform, collection port (11) point diameter is bigger than rear end diameter, and collection port (11) point diameter is straight according to jet pipe
Diameter determines that collection port (11) point diameter is 1.2 times of corresponding jet size, collection port (11) rear end and direct tube section (12)
Front end is connected, and direct tube section (12) internal diameter is 1.15 times of maximum jet size, and the diameter of the second throat (3) is maximum jet pipe
Diameter；First support (13) upper end is fixedly connected with direct tube section (12) front end, and first support (13) lower end is mounted on guide rail (14)
On, first support (13) opposite rail (14) can be slided under the driving of driving device (15)；The insertion of direct tube section (12) rear end
Contraction section (2), direct tube section (12) being capable of relative constriction section (2) slidings；
Minimum and maximum distance of the collection port (11) apart from nozzle exit is respectively 1.0m and 2.9m.
2. the wind-tunnel diffuser of compatible multi nozzle as described in claim 1, it is characterised in that：Contraction section (2) includes straight tube shape
Coat part (21) and truncated cone constriction (22)；Before straight tube shape coat part (21) are inserted into direct tube section (12) rear end
End, direct tube section (12) being capable of relative constriction section (2) straight tube shape coat part (21) slidings；The rear end of straight tube shape coat part (21)
It is fixedly connected with truncated cone constriction (22).
3. the wind-tunnel diffuser of compatible multi nozzle as claimed in claim 2, it is characterised in that：Direct tube section (12) rear end with
12 groups of spring leafs (16) are arranged circumferentially between straight tube shape coat part (21).
4. the wind-tunnel diffuser of compatible multi nozzle as described in claim 1, it is characterised in that：The wind-tunnel diffuser is for height
Warm combustion gas supersonic wind tunnel.
5. carrying out the compatible method of multi nozzle using wind-tunnel diffuser described in claim 1, which is characterized in that different in replacement
When sized nozzles, contraction section (2), second throat (3) and expansion segment (4) are all remained unchanged, by the collection for replacing different bores
The position of mouth and adjustment direct tube section (12) relative constriction section (2) to form supersonic speed flowing full in collector, to realize more
The compatibility of a difference sized nozzles.
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| CN201510472465.1A CN105043711B (en) | 2015-08-04 | 2015-08-04 | A kind of the wind-tunnel diffuser and wind-tunnel diffusion method of compatible multi nozzle |
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Families Citing this family (11)
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| CN105092203A (en) * | 2015-08-27 | 2015-11-25 | 北京航天长征飞行器研究所 | Wind tunnel diffuser compatible with multiple nozzles and wind tunnel diffusion method |
| CN105738068B (en) * | 2016-01-28 | 2018-04-17 | 南京航空航天大学 | A kind of decresment type face rotates continuously adjustable wind tunnel nozzle and adjusts the device being used as power |
| CN106198031B (en) * | 2016-08-30 | 2018-08-03 | 北京航天三发高科技有限公司 | Tail room for engine testsand exhaust system |
| CN107966262B (en) * | 2017-11-20 | 2019-07-12 | 北京航天长征飞行器研究所 | A kind of high-temperature vacuum wind tunnel test cabin and diffuser overall structure and sliding compensation method for thermal with sliding thermal compensation function |
| CN107806977B (en) * | 2017-11-29 | 2024-04-09 | 中国航空工业集团公司沈阳空气动力研究所 | Combined wide Mach number high enthalpy pulse wind tunnel tube structure |
| CN108362466B (en) * | 2017-12-29 | 2021-01-26 | 中国空气动力研究与发展中心设备设计及测试技术研究所 | Horizontal throat block driving device for continuous transonic wind tunnel semi-flexible wall nozzle guide rail |
| CN111006838B (en) * | 2019-11-29 | 2021-10-01 | 中国航天空气动力技术研究院 | Nested movable wind tunnel collector device |
| CN112945509B (en) * | 2021-04-22 | 2022-04-15 | 中国空气动力研究与发展中心超高速空气动力研究所 | Opening plugging device for contraction section of hypersonic speed wind tunnel diffuser |
| CN113418689A (en) * | 2021-06-30 | 2021-09-21 | 中国航发贵州黎阳航空动力有限公司 | Measuring tool for detecting injection direction of fuel spray rod |
| CN113701984B (en) * | 2021-10-28 | 2022-01-18 | 中国空气动力研究与发展中心超高速空气动力研究所 | Hypersonic wind tunnel diffuser and design method thereof |
| CN114563159B (en) * | 2022-04-28 | 2022-07-08 | 中国空气动力研究与发展中心超高速空气动力研究所 | Hypersonic low-density wind tunnel nozzle inner axis Mach number measuring device and method |
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| JP3225842B2 (en) * | 1996-07-09 | 2001-11-05 | トヨタ自動車株式会社 | Blower |
| JP5262297B2 (en) * | 2008-05-28 | 2013-08-14 | 株式会社日立プラントテクノロジー | Rectifier |
| CN201983918U (en) * | 2011-03-22 | 2011-09-21 | 中国人民解放军国防科学技术大学 | Retractable diffuser for supersonic wind tunnel |
| CN203688195U (en) * | 2013-12-19 | 2014-07-02 | 中国航天空气动力技术研究院 | Supersonic velocity diffusion device with active injection |
| CN104458189B (en) * | 2014-10-17 | 2017-05-17 | 北京航天益森风洞工程技术有限公司 | Process layout method for conventional hypersonic speed wind tunnel |
| CN104359644B (en) * | 2014-10-17 | 2017-03-01 | 北京航天益森风洞工程技术有限公司 | Hypersonic low density wind tunnel variable Mach number nozzle |
| CN104675760B (en) * | 2015-02-13 | 2017-03-01 | 浙江大学 | A kind of nozzle-adjustable steam ejector |
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