CN107219056A - Continuous high-speed wind-tunnel cooling system liquid nitrogen sprays into experimental section - Google Patents
Continuous high-speed wind-tunnel cooling system liquid nitrogen sprays into experimental section Download PDFInfo
- Publication number
- CN107219056A CN107219056A CN201710354277.8A CN201710354277A CN107219056A CN 107219056 A CN107219056 A CN 107219056A CN 201710354277 A CN201710354277 A CN 201710354277A CN 107219056 A CN107219056 A CN 107219056A
- Authority
- CN
- China
- Prior art keywords
- liquid nitrogen
- experimental section
- tunnel
- upstream
- sprays
- 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.)
- Granted
Links
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
- G01M9/04—Details
Landscapes
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The present invention proposes that a kind of continuous high-speed wind-tunnel cooling system liquid nitrogen sprays into experimental section, is made up of stack shell, 4 gas exhaust piping interfaces, 16 upstream liquid nitrogen nozzle interfaces, 16 downstream liquid nitrogen nozzle interfaces, upstream flange, downstream flange, 12 walings, 3 ring stiffeners, 1 upstream base and 2 downstream bases；Liquid nitrogen sprays into the axial flow compressor section outlet of the upstream face connection continuous high-speed wind-tunnel of experimental section, and the downstream end face of liquid nitrogen penetrating experimental section connects the diffuser entrance of continuous high-speed wind-tunnel；Liquid nitrogen sprays into experimental section and is provided with liquid nitrogen spray orifice and gas exhaust piping interface, for installing liquid nitrogen nozzle and discharge duct；Liquid nitrogen sprays into experimental section bottom and is provided with base, for supporting and adjusting level height.The structure safety of wind-tunnel, realizes uniform, the controllable spray of liquid nitrogen in wind-tunnel, support is provided to build up China's first set continuous high-speed wind-tunnel cooling system when cooling operation has been effectively ensured in the present invention.
Description
Technical field
It is specifically that one kind is used for continuous high-speed wind-tunnel the present invention relates to the design field of wind-tunnel experimental section under low temperature environment
The liquid nitrogen of cooling system sprays into experimental section.
Background technology
Wind tunnel experiment Reynolds number is improved to reducing experimental error, the aerodynamic data tool for being more nearly live flying state is obtained
It is significant.Reynolds number determines by fluid density, temperature, speed and moulded dimension, in experimental section size and fluid media (medium) not
In the case of malleable, cooling can increase fluid density, reduce viscosity.Liquid nitrogen is a kind of lower boiling inert substance,
With the features such as evaporation is fast, chemical property is stable, using the vaporization endothermic effect of liquid nitrogen, liquid nitrogen is sprayed into wind-tunnel, band leaks out
Heat in hole, is that a kind of improve tests Reynolds number effective way.Hydrojet nitrogen cooling system is clearance-type work system, it is not necessary to
Powerful controller switching equipment and refrigeration system, can largely save fixing equipment investment；Refrigerating capacity is big and temperature range is wide, liquid nitrogen
Pressure is sprayed into easily in regulated in wider range；Space-consuming is smaller：Liquid nitrogen sprays into system closely, the equipment such as liquid nitrogen tank car
It can rent temporarily；Maintenance cost is low, it is not necessary to substantial amounts of line service.China is at present in low temperature continuous high-speed wind-tunnel
Aspect still belongs to blank, therefore, and the hydrojet nitrogen cooling system developed suitable for continuous high-speed wind-tunnel is innovated to China's Wind Tunnel Technique
It is significant with weapons SoS.
Wind tunnel experiment Reynolds number is improved to reducing experimental error, the aerodynamic data tool for being more nearly live flying state is obtained
It is significant.Reynolds number determines by fluid density, temperature, speed and moulded dimension, in experimental section size and fluid media (medium) not
In the case of malleable, cooling can increase fluid density, reduce viscosity.Liquid nitrogen is a kind of lower boiling inert substance,
With the features such as evaporation is fast, chemical property is stable, using the vaporization endothermic effect of liquid nitrogen, liquid nitrogen is sprayed into wind-tunnel, band leaks out
Heat in hole, is that a kind of improve tests Reynolds number effective way.Hydrojet nitrogen cooling system is clearance-type work system, it is not necessary to
Powerful controller switching equipment and refrigeration system, can largely save fixing equipment investment；Refrigerating capacity is big and temperature range is wide, liquid nitrogen
Pressure is sprayed into easily in regulated in wider range；Space-consuming is smaller：Liquid nitrogen sprays into system closely, the equipment such as liquid nitrogen tank car
It can rent temporarily；Maintenance cost is low, it is not necessary to substantial amounts of line service.China is at present in low temperature continuous high-speed wind-tunnel
Aspect still belongs to blank, therefore, and the hydrojet nitrogen cooling system developed suitable for continuous high-speed wind-tunnel is innovated to China's Wind Tunnel Technique
It is significant with weapons SoS.
As the above analysis, the structure of continuous high-speed wind-tunnel is special, operating condition is complicated, it is necessary to develop a set of special
Experimental section is sprayed into the liquid nitrogen of continuous high-speed wind-tunnel cooling system, with before wind tunnel body and axial flow compressor safety is ensured
Put the penetrating for realizing liquid nitrogen.
The content of the invention
The technical barrier of hydrojet nitrogen cooling system can not be applicable in order to solve conventional steel structure wind tunnel experiment section, the present invention
Propose that a kind of liquid nitrogen suitable for continuous high-speed wind-tunnel cooling system sprays into experimental section, from low temperature resistant high duty metal material
Material, designs the hydrojet nitrogen experimental section and liquid nitrogen spray orifice arrangement matched with continuous high-speed wind-tunnel, realizes liquid nitrogen in wind-tunnel
Uniformly, controllable spray.
The technical scheme is that：
A kind of continuous high-speed wind-tunnel cooling system liquid nitrogen sprays into experimental section, it is characterised in that：Liquid nitrogen sprays into experiment
The axial flow compressor section outlet of the upstream face connection continuous high-speed wind-tunnel of section, liquid nitrogen sprays into the downstream end face connection of experimental section
The diffuser entrance of continuous high-speed wind-tunnel；Liquid nitrogen sprays into experimental section and is provided with liquid nitrogen spray orifice and gas exhaust piping interface, for pacifying
Fill liquid nitrogen nozzle and discharge duct；Liquid nitrogen sprays into experimental section bottom and is provided with base, for supporting and adjusting level height.
A kind of further preferred scheme, continuous high-speed wind-tunnel cooling system liquid nitrogen sprays into experimental section, its feature
It is：The liquid nitrogen sprays into experimental section by stack shell, 4 gas exhaust piping interfaces, 16 upstream liquid nitrogen nozzle interfaces, 16 downstream liquid
Under nitrogen nozzle interface, upstream flange, downstream flange, 12 walings, 3 ring stiffeners, 1 upstream base and 2
Base is swum to constitute.
A kind of further preferred scheme, continuous high-speed wind-tunnel cooling system liquid nitrogen sprays into experimental section, its feature
It is：The stack shell is conical hollow cylinder, is made up of stainless steel material 0Cr18Ni9, and stack shell upstream face internal diameter is d, under
It is 1.22d to swim end face internal diameter, and stack shell length is 2d, and wall thickness is 0.03d；The upstream flange external diameter is 1.11d, and internal diameter is d, thick
Spend for 0.07d, be circumferentially uniformly provided with the through hole that 60 internal diameters are 0.015d, for connecting the outlet of wind-tunnel axial flow compressor；Under
Trip flange outer diameter is 1.33d, and internal diameter is 1.22d, and thickness is 0.07d, and it is the logical of 0.015d to be circumferentially uniformly provided with 60 internal diameters
Hole, for connecting wind-tunnel diffuser entrance.
A kind of further preferred scheme, continuous high-speed wind-tunnel cooling system liquid nitrogen sprays into experimental section, its feature
It is：4 gas exhaust piping interface structures are identical, are made by stainless steel material 0Cr18Ni9, pass through welding manner and stack shell side
The steam vent connection of wall；Gas exhaust piping interface is installed section and is located at away from liquid nitrogen penetrating experimental section upstream face 0.33d positions, 4
Gas exhaust piping interface is respectively arranged in 45 °, 135,225 °, the 315 ° of positions observed along inverse airflow direction and install section.
A kind of further preferred scheme, continuous high-speed wind-tunnel cooling system liquid nitrogen sprays into experimental section, its feature
It is：Gas exhaust piping interface includes interface pipeline, flange and cover plate；The long 0.08d of interface pipeline, external diameter is 0.067d, wall
Thickness is 0.005d；Flange external diameter is 0.1d, and internal diameter is 0.09d, and thickness is 0.011d, and 6 are arranged circumferentially directly along it
Footpath is 0.01d through hole, for connecting gas exhaust piping；Cover plate external diameter, thickness are identical with flange, for being not connected to exhaust
Sealing exhaust pipe road interface during pipeline.
A kind of further preferred scheme, continuous high-speed wind-tunnel cooling system liquid nitrogen sprays into experimental section, its feature
It is：16 upstream liquid nitrogen nozzle interfaces and 16 downstream liquid nitrogen nozzle interface structures are identical, by stainless steel material
0Cr18Ni9 is made, and the liquid nitrogen spray orifice with stack shell side wall by way of welding is connected；Upstream liquid nitrogen nozzle interface installs section
Experimental section upstream face 0.61d positions are sprayed into positioned at away from liquid nitrogen, 16 upstream liquid nitrogen nozzle interfaces are respectively arranged in along inverse air-flow
Direction observation install 10 ° of section, 40 °, 50 °, 80 °, 100 °, 130 °, 140 °, 170 °, 190 °, 220 °, 230 °, 260 °,
280 °, 310 °, 320 °, 350 ° of positions；Downstream liquid nitrogen nozzle interface is installed section and is located at away from liquid nitrogen penetrating experimental section upstream face
1.44d positions, 16 downstream liquid nitrogen nozzle interfaces be respectively arranged in observed along inverse airflow direction install 10 ° of section, 40 °,
50 °, 80 °, 100 °, 130 °, 140 °, 170 °, 190 °, 220 °, 230 °, 260 °, 280 °, 310 °, 320 °, 350 ° of positions.
A kind of further preferred scheme, continuous high-speed wind-tunnel cooling system liquid nitrogen sprays into experimental section, its feature
It is：Upstream liquid nitrogen nozzle interface external diameter is 0.075d, and internal diameter is 0.043d, and major part thickness is 0.016d, and microcephaly's thickness is
0.01d, is arranged circumferentially the internal thread hole that 4 a diameter of 0.01d, hole depth are 0.005d, for connecting upstream liquid nitrogen along it
Nozzle.
A kind of further preferred scheme, continuous high-speed wind-tunnel cooling system liquid nitrogen sprays into experimental section, its feature
It is：12 waling structure is identical, is made by stainless steel material 0Cr18Ni9, and length is 2d, and width is 0.15d,
Thickness is 0.006d, the transversary intensity for strengthening stack shell；12 waling is circumferentially uniformly distributed along stack shell, each
30 ° are spaced between reinforcement, stack shell is connected in the axial direction by way of welding.
A kind of further preferred scheme, continuous high-speed wind-tunnel cooling system liquid nitrogen sprays into experimental section, its feature
It is：3 ring stiffener is made by stainless steel material 0Cr18Ni9, is closed circle structure, for strengthening the vertical of stack shell
To structural strength；3 ring stiffeners are located at away from stack shell upstream face 0.83d, 1.67d, 1.83d positions respectively, pass through welding
Mode annular be connected to edge on waling；It is respectively from upstream face to the 3 of downstream end face ring stiffener diameters
1.24d, 1.41d, 1.41d width are 0.07d, and thickness is 0.006d.
A kind of further preferred scheme, continuous high-speed wind-tunnel cooling system liquid nitrogen sprays into experimental section, its feature
It is：1 upstream base and 2 downstream bases are made by stainless steel material 0Cr18Ni9, and three bases are distributed in bikini
Liquid nitrogen is supported to spray into experimental section, upstream base is installed on the 0.33d positions away from stack shell upstream face, 2 downstream bases point between two parties
Be not installed on away from stack shell upstream face 1.75d, circumferentially 135 ° with 225 ° of position.
Beneficial effect
Instant invention overcomes the technical barrier that conventional steel structure wind tunnel experiment section can not be applied to hydrojet nitrogen cooling system,
By selecting low temperature resistant high-strength metal material, liquid nitrogen sprays into experimental section pneumatic structure and designed with nozzle interface, solves liquid nitrogen
The problems such as selection of spray position, tunnel pressure regulation and nozzle layout are with installing.Using the technical program, cooling has been effectively ensured
The structure safety of wind-tunnel, realizes uniform, the controllable spray of liquid nitrogen in wind-tunnel during operation, high to build up China's first set continous way
Fast wind-tunnel cooling system provides support.
The additional aspect and advantage of the present invention will be set forth in part in the description, and will partly become from the following description
Obtain substantially, or recognized by the practice of the present invention.
Brief description of the drawings
The above-mentioned and/or additional aspect and advantage of the present invention will become from description of the accompanying drawings below to embodiment is combined
Substantially and be readily appreciated that, wherein：
Accompanying drawing 1 is the assembly relation that liquid nitrogen sprays into experimental section and wind-tunnel；
1- axial flow compressors, 2- liquid nitrogen sprays into experimental section, the diffusers of 3- the 4th, 4- wind tunnel bodies.
Accompanying drawing 2 is that liquid nitrogen sprays into experimental section structure chart；
5- upstream flanges, 6- walings, 7- gas exhaust piping interfaces, 8- upstream nozzle flanges, 9- stack shells, 10-
Downstream nozzle flange, 11- downstream flanges, 12- upstreams base, 13- ring stiffeners, 14- downstreams base.
Accompanying drawing 3 is that liquid nitrogen sprays into experimental section side view；
7- gas exhaust piping interfaces, 8- upstream nozzle flanges, 13- ring stiffeners, 6- walings, 12- upstreams
Base, 9- stack shells, 14- downstreams base.
Accompanying drawing 4 is gas exhaust piping interface structure figure；
15- through holes, 16- cover plates, 17- flanges, 18- interface pipelines.
Accompanying drawing 5 is nozzle interface flange arrangement figure；
19- screwed holes, 20- flanges.
Accompanying drawing 6 is that NF-6 continuous high-speed wind-tunnel liquid nitrogen sprays into experimental section；
Accompanying drawing 7 is NF-6 continuous high-speed wind-tunnel gas exhaust piping interfaces；
Accompanying drawing 8 is NF-6 continuous high-speed wind-tunnel nozzle interface flanges；
Accompanying drawing 9 is NF-6 continuous high-speed wind-tunnel hydrojet nitrogen cooling system schematic diagrams；
21- wind tunnel noumenons, 22- liquid nitrogen storage devices, 23- supplies air distribution system, 24- control systems, 25- fluid-N2 sprayings dress
Put.
Tunnel airstream and the situation of change of hole wall temperature when accompanying drawing 10 is pull-down test；
Accompanying drawing 11 is the stagnation temperature change during pull-down test；
Accompanying drawing 12 is the Ma numbers change during pull-down test.
Embodiment
Embodiments of the invention are described below in detail, the example of the embodiment is shown in the drawings, wherein from beginning to end
Same or similar label represents same or similar element or the element with same or like function.Below with reference to attached
The embodiment of figure description is exemplary, it is intended to for explaining the present invention, and be not considered as limiting the invention.
In the description of the invention, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", " length ", " width ",
" thickness ", " on ", " under ", "front", "rear", "left", "right", " vertical ", " level ", " top ", " bottom ", " interior ", " outer ", " up time
The orientation or position relationship of the instruction such as pin ", " counterclockwise " are, based on orientation shown in the drawings or position relationship, to be for only for ease of
The description present invention and simplified description, rather than indicate or imply that the device or element of meaning must have specific orientation, Yi Te
Fixed azimuth configuration and operation, therefore be not considered as limiting the invention.
The present embodiment is the liquid nitrogen penetrating experimental section for NF-6 continuous high-speed wind-tunnel cooling systems.NF-6 wind-tunnel are for we
State's First continuous high-speed wind-tunnel, is also the domestic currently the only one continuous high-speed wind-tunnel put into operation.The wind-tunnel
Overall performance reaches domestically leading, international most advanced level.In order to verify the feasibility and beneficial effect of this invention, with NF-6
Continuous high-speed wind-tunnel is implementing platform, for the overall plan and main technical requirements of wind-tunnel cooling system, development and design
The liquid nitrogen of NF-6 continuous high-speed wind-tunnel cooling systems sprays into experimental section, and has carried out testing results.
Liquid nitrogen, which sprays into experimental section, is a part of continuous high-speed wind-tunnel closed-loop path, while being also wind-tunnel cooling
The bogey of system liquid nitrogen injection system.Liquid nitrogen sprays into the assembly relation of experimental section and wind-tunnel as shown in figure 1, wherein, liquid nitrogen
The upstream face for spraying into experimental section connects the outlet of wind-tunnel axial flow compressor, and downstream end face connects entering for the diffuser of wind-tunnel the 4th
Mouthful；Liquid nitrogen sprays into experimental section and is provided with liquid nitrogen spray orifice and gas exhaust piping interface, for installing liquid nitrogen nozzle and discharge duct；Liquid nitrogen
Spray into experimental section bottom and be provided with base, for supporting it to conduct oneself with dignity and adjusting level height.
Liquid nitrogen sprays into experimental section, including stack shell, 4 gas exhaust piping interfaces, 16 upstream liquid nitrogen nozzle interfaces, 16 downstreams
Liquid nitrogen nozzle interface, upstream flange, downstream flange, 12 walings, 3 ring stiffeners, 1 upstream base and 2
Downstream base.As shown in Figure 2 and Figure 3.Wherein：
Stack shell is conical hollow cylinder, is made up of stainless steel material (0Cr18Ni9), and upstream face internal diameter is 1800mm,
Downstream end face internal diameter is 2200mm, and stack shell length is 3600mm, and wall thickness is 54mm.Its upstream flange outer diameter is 2000mm, internal diameter
For 1800mm, thickness is 126mm, is circumferentially uniformly provided with the through hole that 60 internal diameters are 28mm, for connecting the compression of wind-tunnel axle stream
Machine is exported；Downstream flange external diameter is 2400mm, and internal diameter is 2200mm, and thickness is 126mm, is circumferentially uniformly provided with 60 internal diameters and is
28mm through hole, for connecting the diffuser entrance of wind-tunnel the 4th, is shown in Fig. 6.
4 gas exhaust piping interface structures are identical, are made by stainless steel material (0Cr18Ni9), by way of welding with
Stack shell steam vent is connected；Gas exhaust piping interface is installed section and is located at away from liquid nitrogen penetrating experimental section upstream face 600mm positions, 4
Gas exhaust piping interface be respectively arranged in along from inverse airflow direction (from downstream end face to upstream face) install 45 ° of section,
135th, 225 °, 315 ° of positions.The long 144mm of interface pipeline, external diameter is 122mm, and wall thickness is 9mm, and flange external diameter is 180mm,
Internal diameter is 160mm, and thickness is 20mm, 6 a diameter of 18mm through hole is arranged circumferentially along it, for connecting gas exhaust piping；4
Individual gas exhaust piping interface is provided with external diameter, thickness and flange identical cover plate, for being sealed when being not connected to gas exhaust piping
Pipe interface, is shown in Fig. 7.
16 upstream liquid nitrogen nozzle interface structures are identical, are made by stainless steel material (0Cr18Ni9), pass through welding
Mode is connected with stack shell liquid nitrogen spray orifice；Upstream liquid nitrogen nozzle interface is installed section and is located at away from liquid nitrogen penetrating experimental section upstream face
1100mm positions, 16 upstream liquid nitrogen nozzle interfaces are respectively arranged in along inverse airflow direction and (seen from downstream end face to upstream face
Examine, be vertically upward 0 °) observation install 10 ° of section, 40 °, 50 °, 80 °, 100 °, 130 °, 140 °, 170 °, 190 °,
220 °, 230 °, 260 °, 280 °, 310 °, 320 °, 350 ° of positions.Upstream liquid nitrogen nozzle interface external diameter is 135mm, and internal diameter is
78mm, major part thickness is 27.71mm, and microcephaly's thickness is 20.61mm, and being arranged circumferentially 4 a diameter of 18mm, hole depths along it is
9mm internal thread hole, for upstream liquid nitrogen nozzle, is shown in Fig. 8.
16 downstream liquid nitrogen nozzle interface structures and material are identical with upstream liquid nitrogen nozzle interface, see Fig. 8.Downstream liquid
Nitrogen nozzle interface is installed section and is located at away from liquid nitrogen penetrating experimental section upstream face 2600mm positions, 16 downstream liquid nitrogen nozzle interfaces
Equally it is installed on along inverse airflow direction (being vertically upward 0 ° from downstream end face to upstream face) observation and section is installed
10 °, 40 °, 50 °, 80 °, 100 °, 130 °, 140 °, 170 °, 190 °, 220 °, 230 °, 260 °, 280 °, 310 °, 320 °, 350 °
Position.
12 waling structure is identical, is made by stainless steel material (0Cr18Ni9), and length is 3600mm, width
For 270mm, thickness is 10mm, the transversary intensity for strengthening stack shell.Circumferential uniform point along stack shell of 12 walings
30 ° are spaced between cloth, each reinforcement, stack shell is connected in the axial direction by way of welding.
3 ring stiffeners are made by stainless steel material (0Cr18Ni9), closed circle structure, for strengthening stack shell
Vertical structure intensity.3 ring stiffeners are located at away from stack shell upstream face 1500mm, 3000mm, 3300mm positions respectively, pass through
The mode annular of welding is connected to edge on waling.From upstream face to the 3 of downstream end face ring stiffener diameters point
Not Wei 2232mm, 2538mm, 2538mm width be 126mm, thickness is 10mm.
1 upstream base and 2 downstream bases are made by stainless steel material (0Cr18Ni9), general framework structure；Bottom
Seat sprays into experimental section in bikini distribution support liquid nitrogen, and upstream base is installed on the 600mm positions away from stack shell upstream face between two parties,
2 downstream bases are respectively arranged in away from stack shell upstream face 3150mm, circumferentially (from downstream end face to upstream face, hung down
Straight upward direction is 0 °) 135 ° of positions with 225 °.
In the present embodiment, liquid nitrogen penetrating experimental section is connected to NF-6 continous ways height by upstream flange and downstream flange
The outlet of fast wind-tunnel axial flow compressor and the entrance of the 4th diffuser, closed-loop path is constituted with wind-tunnel other parts；By 32 liquid
Nitrogen nozzle is connected to liquid nitrogen by 32 liquid nitrogen nozzle interfaces and sprays into experimental section, forms the fluid-N2 spraying device of cooling system.Liquid nitrogen
The assembly relation for spraying into experimental section and wind-tunnel and cooling system is as shown in Figure 9.Complete liquid nitrogen to spray into after the installation of experimental section, start
Wind-tunnel, runs hydrojet nitrogen cooling system, chooses Ma=0.8 transonic speed model experiment operating mode, tests liquid nitrogen and sprays into experiment
Section and wind-tunnel and the matching performance of cooling system.
Figure 10 provides the situation of change of tunnel airstream and hole wall temperature, and Figure 11 gives the stagnation temperature situation of change of wind-tunnel, figure
12 give the situation of change of test section Ma numbers.It can find out from figure：When stable section gas flow temperature is less than -20 DEG C, spray
Wind tunnel wall temperature is still near 20 DEG C of normal temperature at ring, shows that liquid nitrogen sprays into experiment fragment position and chosen and nozzle interface design
Rationally, the ultralow temperature protection question of wind tunnel wall material is efficiently solved, it is ensured that the structure safety of wind-tunnel；Test section Ma numbers
Average value reaches 0.8, and Mach number deviation is | Δ Ma |≤0.003, and meet σMa≤ 0.003,9 stagnation temperature measuring points of wind-tunnel stable section
Average value reaches -20 DEG C, and meetsShow that liquid nitrogen sprays into experimental section structure and meets wind-tunnel design specification, liquid nitrogen spray
Enter experimental section to match well with wind-tunnel cooling system, realize the cooling operation of continuous high-speed wind-tunnel, temperature index, which reaches, to be set
Meter is required.
Although embodiments of the invention have been shown and described above, it is to be understood that above-described embodiment is example
Property, it is impossible to limitation of the present invention is interpreted as, one of ordinary skill in the art is not departing from the principle and objective of the present invention
In the case of above-described embodiment can be changed within the scope of the invention, change, replace and modification.
Claims (10)
1. a kind of continuous high-speed wind-tunnel cooling system liquid nitrogen sprays into experimental section, it is characterised in that：Liquid nitrogen sprays into the upper of experimental section
The axial flow compressor section outlet of end face connection continuous high-speed wind-tunnel is swum, liquid nitrogen sprays into the downstream end face connection continous way of experimental section
The diffuser entrance of high-speed wind tunnel；Liquid nitrogen sprays into experimental section and is provided with liquid nitrogen spray orifice and gas exhaust piping interface, for installing liquid nitrogen
Nozzle and discharge duct；Liquid nitrogen sprays into experimental section bottom and is provided with base, for supporting and adjusting level height.
2. a kind of continuous high-speed wind-tunnel cooling system liquid nitrogen sprays into experimental section according to claim 1, it is characterised in that：Institute
State liquid nitrogen and spray into experimental section by stack shell, 4 gas exhaust piping interfaces, 16 upstream liquid nitrogen nozzle interfaces, 16 downstream liquid nitrogen nozzles
Interface, upstream flange, downstream flange, 12 walings, 3 ring stiffeners, 1 upstream base and 2 downstream bases
Constitute.
3. a kind of continuous high-speed wind-tunnel cooling system liquid nitrogen sprays into experimental section according to claim 2, it is characterised in that：Institute
Stack shell is stated for conical hollow cylinder, is made up of stainless steel material 0Cr18Ni9, stack shell upstream face internal diameter is d, downstream end face
Internal diameter is 1.22d, and stack shell length is 2d, and wall thickness is 0.03d；The upstream flange external diameter is 1.11d, and internal diameter is d, and thickness is
0.07d, is circumferentially uniformly provided with the through hole that 60 internal diameters are 0.015d, for connecting the outlet of wind-tunnel axial flow compressor；Downstream method
Blue external diameter is 1.33d, and internal diameter is 1.22d, and thickness is 0.07d, is circumferentially uniformly provided with the through hole that 60 internal diameters are 0.015d, uses
In connection wind-tunnel diffuser entrance.
4. a kind of continuous high-speed wind-tunnel cooling system liquid nitrogen sprays into experimental section according to claim 2, it is characterised in that：4
Individual gas exhaust piping interface structure is identical, is made by stainless steel material 0Cr18Ni9, passes through the row of welding manner and stack shell side wall
Stomata is connected；Gas exhaust piping interface is installed section and is located at away from liquid nitrogen penetrating experimental section upstream face 0.33d positions, 4 blast pipes
Road interface is respectively arranged in 45 °, 135,225 °, the 315 ° of positions observed along inverse airflow direction and install section.
5. a kind of continuous high-speed wind-tunnel cooling system liquid nitrogen sprays into experimental section according to claim 2, it is characterised in that：Row
Air pipe interface includes interface pipeline, flange and cover plate；The long 0.08d of interface pipeline, external diameter is 0.067d, and wall thickness is
0.005d；Flange external diameter be 0.1d, internal diameter is 0.09d, and thickness is 0.011d, along its be arranged circumferentially 6 it is a diameter of
0.01d through hole, for connecting gas exhaust piping；Cover plate external diameter, thickness are identical with flange, for being not connected to gas exhaust piping
When sealing exhaust pipe road interface.
6. a kind of continuous high-speed wind-tunnel cooling system liquid nitrogen sprays into experimental section according to claim 2, it is characterised in that：16
Individual upstream liquid nitrogen nozzle interface and 16 downstream liquid nitrogen nozzle interface structures are identical, are made by stainless steel material 0Cr18Ni9,
Liquid nitrogen spray orifice with stack shell side wall by way of welding is connected；Upstream liquid nitrogen nozzle interface is installed section and is located at away from liquid nitrogen penetrating
Experimental section upstream face 0.61d positions, 16 upstream liquid nitrogen nozzle interfaces are respectively arranged in install along the observation of inverse airflow direction and cut
10 ° of face, 40 °, 50 °, 80 °, 100 °, 130 °, 140 °, 170 °, 190 °, 220 °, 230 °, 260 °, 280 °, 310 °, 320 °,
350 ° of positions；Downstream liquid nitrogen nozzle interface is installed section and sprayed into positioned at away from liquid nitrogen under experimental section upstream face 1.44d positions, 16
Trip liquid nitrogen nozzle interface be respectively arranged in observed along inverse airflow direction install 10 ° of section, 40 °, 50 °, 80 °, 100 °, 130 °,
140 °, 170 °, 190 °, 220 °, 230 °, 260 °, 280 °, 310 °, 320 °, 350 ° of positions.
7. a kind of continuous high-speed wind-tunnel cooling system liquid nitrogen sprays into experimental section according to claim 2, it is characterised in that：On
It is 0.075d to swim liquid nitrogen nozzle interface external diameter, and internal diameter is 0.043d, and major part thickness is 0.016d, and microcephaly's thickness is 0.01d, along it
The internal thread hole that 4 a diameter of 0.01d, hole depth are 0.005d is arranged circumferentially, for connecting upstream liquid nitrogen nozzle.
8. a kind of continuous high-speed wind-tunnel cooling system liquid nitrogen sprays into experimental section according to claim 2, it is characterised in that：12
Bar waling structure is identical, is made by stainless steel material 0Cr18Ni9, and length is 2d, and width is 0.15d, and thickness is
0.006d, the transversary intensity for strengthening stack shell；12 waling is circumferentially uniformly distributed along stack shell, each reinforcement
Between be spaced 30 °, be connected to stack shell in the axial direction by way of welding.
9. a kind of continuous high-speed wind-tunnel cooling system liquid nitrogen sprays into experimental section according to claim 2, it is characterised in that：3
Bar ring stiffener is made by stainless steel material 0Cr18Ni9, is closed circle structure, the vertical structure for strengthening stack shell
Intensity；3 ring stiffeners are located at away from stack shell upstream face 0.83d, 1.67d, 1.83d positions respectively, by way of welding
Annular is connected to edge on waling；From upstream face to the 3 of downstream end face ring stiffener diameters be respectively 1.24d,
1.41d, 1.41d width are 0.07d, and thickness is 0.006d.
10. a kind of continuous high-speed wind-tunnel cooling system liquid nitrogen sprays into experimental section according to claim 2, it is characterised in that：1
Individual upstream base and 2 downstream bases are made by stainless steel material 0Cr18Ni9, and three bases are in bikini distribution support liquid
Nitrogen sprays into experimental section, and upstream base is installed on the 0.33d positions away from stack shell upstream face between two parties, and 2 downstream bases are respectively mounted
In away from stack shell upstream face 1.75d, circumferentially 135 ° with 225 ° of position.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710354277.8A CN107219056B (en) | 2017-05-18 | 2017-05-18 | Liquid nitrogen spraying experiment section of continuous high-speed wind tunnel cooling system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710354277.8A CN107219056B (en) | 2017-05-18 | 2017-05-18 | Liquid nitrogen spraying experiment section of continuous high-speed wind tunnel cooling system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107219056A true CN107219056A (en) | 2017-09-29 |
| CN107219056B CN107219056B (en) | 2023-05-26 |
Family
ID=59944266
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710354277.8A Active CN107219056B (en) | 2017-05-18 | 2017-05-18 | Liquid nitrogen spraying experiment section of continuous high-speed wind tunnel cooling system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107219056B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111735603A (en) * | 2020-08-24 | 2020-10-02 | 中国航空工业集团公司沈阳空气动力研究所 | Connecting and sealing structure between wind tunnel compressor and tunnel body |
| CN115371943A (en) * | 2022-10-26 | 2022-11-22 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Jet bent frame device for realizing wind tunnel cooling by using liquid nitrogen medium |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1083587A (en) * | 1993-09-20 | 1994-03-09 | 中国科学院力学研究所 | The mat heat separator reduces the cryonetic wind tunnel of stagnation temperature |
| JP2007033314A (en) * | 2005-07-28 | 2007-02-08 | Mitsubishi Heavy Ind Ltd | Wind tunnel test apparatus |
| CN102192828A (en) * | 2010-03-02 | 2011-09-21 | 中国科学院理化技术研究所 | Low-temperature wind tunnel |
| CN104314690A (en) * | 2014-10-21 | 2015-01-28 | 西北工业大学 | Plasma phase-changing control air inlet passage and control method |
| CN104458190A (en) * | 2014-12-09 | 2015-03-25 | 苟仲武 | Liquid air source energy-saving efficient wind tunnel device and method thereof |
| CN104634536A (en) * | 2015-01-28 | 2015-05-20 | 天津大学 | Economic and efficient opening direct current type ice wind tunnel |
| CN104961109A (en) * | 2015-05-21 | 2015-10-07 | 李远明 | Low-temperature wind tunnel nitrogen recovery device, and recovery method |
| GB201608953D0 (en) * | 2016-05-20 | 2016-07-06 | Gkn Aerospace Services Ltd | Ice test devices |
| CN206740356U (en) * | 2017-05-18 | 2017-12-12 | 西北工业大学 | Continuous high-speed wind-tunnel cooling system liquid nitrogen sprays into experimental section |
-
2017
- 2017-05-18 CN CN201710354277.8A patent/CN107219056B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1083587A (en) * | 1993-09-20 | 1994-03-09 | 中国科学院力学研究所 | The mat heat separator reduces the cryonetic wind tunnel of stagnation temperature |
| JP2007033314A (en) * | 2005-07-28 | 2007-02-08 | Mitsubishi Heavy Ind Ltd | Wind tunnel test apparatus |
| CN102192828A (en) * | 2010-03-02 | 2011-09-21 | 中国科学院理化技术研究所 | Low-temperature wind tunnel |
| CN104314690A (en) * | 2014-10-21 | 2015-01-28 | 西北工业大学 | Plasma phase-changing control air inlet passage and control method |
| CN104458190A (en) * | 2014-12-09 | 2015-03-25 | 苟仲武 | Liquid air source energy-saving efficient wind tunnel device and method thereof |
| CN104634536A (en) * | 2015-01-28 | 2015-05-20 | 天津大学 | Economic and efficient opening direct current type ice wind tunnel |
| CN104961109A (en) * | 2015-05-21 | 2015-10-07 | 李远明 | Low-temperature wind tunnel nitrogen recovery device, and recovery method |
| GB201608953D0 (en) * | 2016-05-20 | 2016-07-06 | Gkn Aerospace Services Ltd | Ice test devices |
| CN206740356U (en) * | 2017-05-18 | 2017-12-12 | 西北工业大学 | Continuous high-speed wind-tunnel cooling system liquid nitrogen sprays into experimental section |
Non-Patent Citations (5)
| Title |
|---|
| CHAO GAO 等: "The Overall Scheme Design and Debugging of the Liquid Nitrogen Injection Cooling System in NF-6 Wind Tunnel" * |
| YU WEIQING 等: "The Study of Measurement Techniques of Microscale Roll Moment Balance for Dynamic Test" * |
| 廖达雄 等: "大型低温高雷诺数风洞及其关键技术综述" * |
| 计光华: "液氮在低温风洞中的应用" * |
| 赖欢 等: "大型高速低温风洞冷量回收的方法研究" * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111735603A (en) * | 2020-08-24 | 2020-10-02 | 中国航空工业集团公司沈阳空气动力研究所 | Connecting and sealing structure between wind tunnel compressor and tunnel body |
| CN115371943A (en) * | 2022-10-26 | 2022-11-22 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Jet bent frame device for realizing wind tunnel cooling by using liquid nitrogen medium |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107219056B (en) | 2023-05-26 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102914416B (en) | Direct-cooling freezing wind tunnel realization method and direct-cooling freezing wind tunnel realization system | |
| BR102015002974B1 (en) | Apparatus and method for preventing the formation of ice in an engine | |
| CN105181290B (en) | A kind of high temperature jet pipe for combustion gas stream wind-tunnel | |
| CN108168832A (en) | A kind of throat structure for improving tube wind tunnel experiment Reynolds number | |
| CN105628331A (en) | Energy-saving environment-friendly layout of large-scale routine hypersonic wind tunnel | |
| CN107219056A (en) | Continuous high-speed wind-tunnel cooling system liquid nitrogen sprays into experimental section | |
| AU2013338645B2 (en) | Nozzle for distribution of a fluid | |
| CN106081155A (en) | A kind of aircraft anti-deicing system test analog | |
| CN102190084A (en) | De-icing system comprising detection means for detecting an air leak in the hot air supply | |
| CN204788954U (en) | Be used for high temperature high pressure exhaust refrigerated water spray pipeline | |
| CN105275619B (en) | A kind of frost prevention method suitable for Aero-Space engine forecooler | |
| CN206740356U (en) | Continuous high-speed wind-tunnel cooling system liquid nitrogen sprays into experimental section | |
| CN110712764A (en) | Subsonic velocity envelope ablation test device used under high enthalpy condition | |
| CN108534981B (en) | High temperature wind tunnel is with collecting mouthful water spray heat sink | |
| CN106950031A (en) | Continuous high-speed wind-tunnel cooling system fluid-N2 spraying device | |
| CN107355409A (en) | Gas-liquid two-phase flow accuracy controlling device and regulation and control method | |
| CN105758214A (en) | Large-temperature-difference water spray cooling device capable of bearing ultra-high temperature | |
| CN103831005B (en) | A kind of water-cooling wall erosion protection system for SNCR denitration | |
| CN106289787B (en) | Tail room for engine testsand exhaust system | |
| CN211854994U (en) | Cooler for ultra-high temperature gas | |
| CN106382467A (en) | Long-distance liquid oxygen supply system and precooling method thereof | |
| CN104538067B (en) | Removable cut simulating piece and installation method thereof and cut simulation system | |
| CN209640306U (en) | A kind of big hot-fluid supersonic jet jet pipe of band active cooling | |
| CN115680781B (en) | Impeller exhaust device with cooling function | |
| CN207018233U (en) | A kind of gas-liquid two-phase flow regulation device |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |