CN208043384U - A kind of high enthalpy impulse wind tunnel pipe structure of the wide Mach number of combined type - Google Patents
A kind of high enthalpy impulse wind tunnel pipe structure of the wide Mach number of combined type Download PDFInfo
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- CN208043384U CN208043384U CN201721632690.8U CN201721632690U CN208043384U CN 208043384 U CN208043384 U CN 208043384U CN 201721632690 U CN201721632690 U CN 201721632690U CN 208043384 U CN208043384 U CN 208043384U
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Abstract
The utility model belongs to High Mach number experimental technique field, is related to a kind of high enthalpy impulse wind tunnel pipe structure of the wide Mach number of combined type, including：High drive section (1), double film sections (2), the first low pressure are by drive section (3), the second low pressure by drive section (4), it is connected using form of flanges between each section, second low pressure is replaced between drive section (4) and high temperature section (5), wherein high temperature section (5) includes upstream high temperature isolating device (6), heating tube (7) and the additional hot systems (8) of pipe and the fast open system of downstream high temperature (9), it manages additional hot systems and is layed in heating tube periphery, connected using form of flanges between each section.The utility model is similar to traditional pulse wind-tunnel in structure, not complicated start control mechanism, the heating temperature and length of high temperature section tube body can be designed by test requirements document and be met by pneumatic operation logic, it is simple in structure, reliable, there is operability in practical implementation.
Description
Technical field
The invention belongs to High Mach number experimental technique fields, in particular to a kind of high enthalpy arteries and veins of the wide Mach number of combined type
Rush wind-tunnel pipe structure.
Background technology
High enthalpy impulse wind tunnel is one kind of High Mach number ground-testing plant, it is therefore an objective to reappear flying for aircraft as far as possible
Row environment, and binding test technology obtain the aerodynamic parameter of dummy vehicle in the present context.Impulse wind tunnel is based on sharp earliest
Wave duct principle grows up, and according to the difference of the method for operation, there is through-type shock tunnel, reflection-type shock tunnel, gun wind tunnel
And tube wind tunnel etc..
It (by drive section caliber and is sprayed based on the shock tunnel that shock tube principle grows up due to there is " big venturi effect "
Pipe venturi size mismatches), it is difficult to ensure the rupture of membranes repeatability in the case of nozzle area contraction ratio is smaller so that equipment is very difficult to apply in
Below Mach number 5.Tube wind tunnel is as a kind of special pulsing unit, since simple in structure, parameter regulation is convenient, flow field quality is high
The advantages that, it is sub-/across/supersonic speed field be developed and apply.
As hypersonic aircraft develops the increase of demand, impulse type wind-tunnel is badly in need of extending to compared with low mach section, special
It is not to need that there is across Mach number service ability.Such as Mach after the further upgrading of U.S. CUBRC LENS II shock tunnels
Number ranging from 2.7~8.0, but to sacrifice effective operation of apparatus time and flow field quality as cost.Therefore how to ensure
Expand Mach number range of operation under the premise of impulse type performance of wind tunnel, become research emphasis, technological means needs further development.
Invention content
The present invention is directed to propose a kind of wide Mach number high enthalpy wind tunnel pipe structure of combined type, is existed with solving existing impulse wind tunnel
The problem that operation is difficult in wide range of Mach numbers, flow field quality is low.
The technical scheme is that：A kind of wide Mach number high enthalpy wind tunnel pipe structure of combined type, including：High drive section
1, double film sections 2, the first low pressure are connected between each section using form of flanges by drive section 3, the second low pressure by drive section 4, special
Sign is, when realizing bimodal combination driving operation, is opened up by the replacement between drive section 4 and high temperature section 5 by the second low pressure
Wind-tunnel Mach number range of operation is opened up, wherein high temperature section 5 comprising upstream high temperature isolating device 6, heating tube 7 and manages additional hot systems 8
With the fast open system 9 of downstream high temperature, manages additional hot systems and be layed in heating tube periphery, connected using form of flanges between each section.
For the additional hot systems 8 of pipe containing internal layer high-temperature heating body 10 and outer layer insulating layer 11, it is direct that internal layer is heated at high temperature body
It is contacted with heating tube surfaces, bread wraps up in insulating layer outside it.
The high-temperature heating body generally uses electrical heating form, is preheated to heat storage by high temperature resistance element.
The high drive section 1, double film sections 2, the first low pressure are by drive section 3, by the second low pressure by drive section 4 and high temperature
The bimodal combination driving method of operation is realized in replacement between section 5.
The bimodal combination driving method of operation, uses tube wind tunnel operational mode, in Mach number in middle low mach section
> 5.0, with shock tunnel mode operation.
The diameter of the tube body is determined that the ratio needs of tube body overall length and each section consider by tube wind tunnel operational modal
Two kinds of operational modals.
The diameter of the tube body is determined that the selection of value is limited by two aspects by tube wind tunnel operational modal：On the one hand,
In order to weaken reflection of the dilatational wave on cold heat section interface, from flow Conservation Relationship, can theoretically derive cold
There are following relationships with high temperature section caliber for section caliber：
Wherein, dhotFor high temperature section internal diameter of tube body, dcoldFor cold section of internal diameter of tube body, ThotFor high temperature section tubular body gas temperature
It spends (being determined by experimental condition), TcoldFor cold section of tubular body gas temperature (being usually room temperature)；
On the other hand, it is contemplated that tube wall boundary-layer influences, and tubular body flows Mach number M1Generally between 0.02~0.2 it
Between, which depends on nozzle exit size and high temperature section caliber ratio, and specific relationship is as follows：
Wherein, d*For nozzle throat size, r is specific heats of gases ratio.Meanwhile in test gas total temperature, stagnation pressure and high temperature section
Gas total temperature, stagnation pressure have following relationship：
Wherein, subscript t, 1 indicates that test gas parameter, subscript 0 indicate gas parameter in high temperature section.
The ratio of the length of the tube body, tube body overall length and each section needs to consider two kinds of operational modals, tube wind tunnel
Under operational mode, there are following relationship between run time and tube body overall length and high temperature section tube length：
Wherein, t1For run time, L is tube body overall length, and Δ L is high temperature section tube length, and a is the velocity of sound in pipe, and u is in pipe
Flow velocity.
Beneficial effects of the present invention：To solve the above-mentioned problems, the present invention proposes a kind of bimodal combination driving operation
Mode：At middle low mach section (Mach number 3.0~5.0), can be answered using tube wind tunnel operational mode by being heated at high temperature outside pipe
Existing flying condition total enthalpy；At High Mach number section (Mach number > 5.0), with shock tunnel mode operation, enthalpy can further improve.
Description of the drawings
Fig. 1 is the wide Mach number high enthalpy wind tunnel tube body layout of combined type of the present invention and replaces schematic diagram.
Fig. 2 is the high temperature section heating system structural schematic diagram of the present invention.
Specific implementation mode
As shown in Figure 1, the wide Mach number high enthalpy wind tunnel of combined type, it includes：Body portion, nozzle section, test section, vacuum chamber
Deng；It is connected using form of flanges between each section.Body portion includes：High drive section 1, double film sections 2, the first low pressure are driven
The 3, second low pressure of section includes that upstream high temperature isolating device 6 (can be used ball valve or cut by drive section 4, high temperature section 5, wherein high temperature section 5
Only valve, within opening time 5s), heating tube 7 and the additional hot systems 8 of pipe and the fast open system of downstream high temperature 9 (can be used axial flow valve or
Film breaking unit, within opening time 15ms).
Additional hot systems 8 are managed containing internal layer high-temperature heating body 10 and outer layer insulating layer 11, internal layer high-temperature heating body directly with add
Hot tube surfaces contact, bread wraps up in insulating layer outside it.
It is heated at high temperature body and generally uses electrical heating form, heat storage is preheated by high temperature resistance element.
High drive section 1, double film sections 2, the first low pressure are by drive section 3, by the second low pressure by drive section 4 and high temperature section 5
Between replacement, realize bimodal combination driving the method for operation.
The bimodal combination driving method of operation, uses tube wind tunnel operational mode, in Mach number > in middle low mach section
5.0, with shock tunnel mode operation.
The diameter of tube body is determined that the ratio of tube body overall length and each section needs to consider two kinds by tube wind tunnel operational modal
Operational modal.
As shown in Fig. 2, the additional hot systems of pipe in 5. high temperature section in the present invention include 9. internal layer high-temperature heating body and 10.
Outer layer insulating layer.Internal layer high-temperature heating body is directly contacted with heating tube surfaces, and bread wraps up in insulating layer outside it.High-temperature heating
Body generally uses electrical heating form, is preheated to heat storage by high temperature resistance element.
Program specific implementation design method is divided into the following aspects：
1) diameter of tube body
The diameter of tube body is determined that the selection of value is limited by two aspects by tube wind tunnel operational modal：On the one hand, in order to subtract
Reflection of the weak dilatational wave on cold heat section interface can theoretically derive cold section of caliber from flow Conservation Relationship
There are following relationships with high temperature section caliber：
Wherein, dhotFor high temperature section internal diameter of tube body, dcoldFor cold section of internal diameter of tube body, ThotFor high temperature section tubular body gas temperature
It spends (being determined by experimental condition), TcoldFor cold section of tubular body gas temperature (being usually room temperature).
On the other hand, it is contemplated that tube wall boundary-layer influences, and tubular body flows Mach number M1Generally between 0.02~0.2 it
Between, which depends on nozzle exit size and high temperature section caliber ratio, and specific relationship is as follows：
Wherein, d*For nozzle throat size, r is specific heats of gases ratio.Meanwhile in test gas total temperature, stagnation pressure and high temperature section
Gas total temperature, stagnation pressure have following relationship：
Wherein, subscript t, 1 indicates that test gas parameter, subscript 0 indicate gas parameter in high temperature section.
By taking Mach number 3.5, test section gas total temperature 750K, nozzle exit size Φ 300mm as an example, cold section of caliber (including
High drive section, double film sections, low pressure are by drive section 1) Φ 255mm are can be taken as, high temperature section caliber can be taken as Φ 200mm, low pressure quilt
2 caliber of drive section is identical as cold section of caliber.
2) length of tube body
The ratio of tube body overall length and each section needs to consider two kinds of operational modals.Under tube wind tunnel operational mode, operation
There are following relationship between time and tube body overall length and high temperature section tube length：
Wherein, t1For run time, L is tube body overall length, and Δ L is high temperature section tube length, and a is the velocity of sound in pipe, and u is in pipe
Flow velocity.Subscript 1 indicate initial bubble wave by but reflect Bottomhole pressure parameter when dilatational wave does not reach, subscript 0 indicates initial
Pipe's flow parameter.
It is required according to tube wind tunnel run time, it may be determined that tube body overall length and high temperature segment length are rationally divided on this basis
With shock tunnel mode high drive section and low pressure by drive section ratio, theoretical longest test period can be obtained, if this has
Effect experiment test period cannot meet shock tunnel modal test demand, choose tube body overall length (can equal proportion extend) again, with
Ensure the efficiency test time of wide range of Mach numbers.By taking the tube wind tunnel 200ms efficiency test times as an example, wind-tunnel overall length can be taken as
35m, high temperature segment length 10m；The corresponding high drive section of shock tunnel mode can be taken as 10m, and low pressure can be taken as by drive section 1
15m, low pressure are 10m by drive section 2, it is ensured that the 30ms efficiency test times in 5~8 range of Mach number.Following table is theory analysis
Test parameters of the different driving than under when obtained Mach number 6 (low pressure is by drive section pressure 1bar).
| Driving pressure P4(bar) | 20 | 40 | 60 | 100 |
| Efficiency test time tr(ms) | 37.0 | 37.5 | 31.6 | 35.4 |
| The peak value of gas pressure in room (bar) | 18.4 | 35.0 | 48.2 | 78.6 |
| The valley of gas pressure in room (bar) | 16.5 | 33.7 | 49.4 | 73.4 |
| Gas pressure in room fluctuates (%) | - 5.4~+5.4 | - 1.9~+1.9 | - 1.2~+1.2 | - 3.4~+3.4 |
| The peak value of gas temperature in room (K) | 743.4 | 946.8 | 1085.2 | 1304.0 |
| The valley of gas temperature in room (K) | 720.7 | 936.1 | 1077.6 | 1278.9 |
| Gas temperature in room fluctuates (%) | - 1.6~+1.6 | - 0.6~+0.6 | - 0.4~+0.4 | - 1.0~+1.0 |
The detailed process of the present invention：
Under shock tunnel pattern, respectively 2 and second low pressure of double film sections by 4 end of drive section place diaphragm, experiment before
Diaphragm both sides (high drive section and low pressure are by drive section) are filled with the gas of different pressures.After the rupture of diaphragm of upstream, at diaphragm
It generates one of Shock-Motion to propagate to by drive section, be used for test gas temperature-pressure, when shock propagation to the second low pressure quilt
4 end of drive section, high-temperature high-pressure air flow break through two diaphragms, on-test；
Under tube wind tunnel pattern, the second low pressure is mutually replaced by drive section 4 and high temperature section 5, wherein high drive section 1, double films
Section 2 and the first low pressure form cold section of tube body by drive section 3.Upstream high temperature isolating device 6 and the fast open system 9 of downstream high temperature are closed,
The gas of different pressures is filled with to cold section and high temperature section respectively, gas in pipe is heated by pipe additional hot systems.When up to
To after specified temperature and pressure, upstream high temperature isolating device 6, the fast open system 9 of downstream high temperature, on-test are successively opened.
Combination type of drive proposed by the invention has operability in practical implementation.The present invention is in structure
Upper similar to traditional pulse wind-tunnel, the not no start control mechanism of complexity, the heating temperature and length of high temperature section tube body can be by examinations
Requirement design is tested by pneumatic operation logic to be met, it is simple in structure, reliable.The tube wind tunnel method of operation is used under middle low mach,
Effective run time, while the quality in guarantee test section flow field can be extended.
Above example is only that a kind of parameter of the present invention chooses reference, is not intended to limit the protection model of the present invention
Enclose, it is all within the principle of the present invention, made by it is any modification, replace or improve etc., protection scope of the present invention it
It is interior.
Claims (2)
1. a kind of high enthalpy impulse wind tunnel pipe structure of the wide Mach number of combined type, including：High drive section (1), double film sections (2),
One low pressure by drive section (4), is sequentially connected between each section using form of flanges, feature exists by drive section (3), the second low pressure
In second low pressure can be replaced mutually between drive section (4) and high temperature section (5), and wherein high temperature section (5) includes upstream high temperature
Isolating device (6), heating tube (7) and the additional hot systems (8) of pipe and the fast open system of downstream high temperature (9), manage additional hot systems (8) paving
Set on heating tube (7) periphery, upstream high temperature isolating device (6), periphery be cased with the additional hot systems of pipe (8) heating tube (7) and under
It is sequentially connected using form of flanges between the trip fast open system of high temperature (9).
2. the high enthalpy impulse wind tunnel pipe structure of the wide Mach number of combined type as described in claim 1, which is characterized in that outside the pipe
Heating system (8) high-temperature heating body containing internal layer (10) and outer layer insulating layer (11), internal layer high-temperature heating body (10) directly with heating
(7) the body surface face of pipe contact, in interior floor height temperature calandria (10) outer surface package outer layer insulating layer (11).
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107806977A (en) * | 2017-11-29 | 2018-03-16 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of high enthalpy impulse wind tunnel pipe structure of the wide Mach number of combined type |
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- 2017-11-29 CN CN201721632690.8U patent/CN208043384U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107806977A (en) * | 2017-11-29 | 2018-03-16 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of high enthalpy impulse wind tunnel pipe structure of the wide Mach number of combined type |
| 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 |
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