CN106568568B - A kind of high-temperature fuel gas stream supersonic wind tunnel pilot system - Google Patents
A kind of high-temperature fuel gas stream supersonic wind tunnel pilot system Download PDFInfo
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- CN106568568B CN106568568B CN201610912736.5A CN201610912736A CN106568568B CN 106568568 B CN106568568 B CN 106568568B CN 201610912736 A CN201610912736 A CN 201610912736A CN 106568568 B CN106568568 B CN 106568568B
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- 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
Abstract
A kind of high-temperature fuel gas stream supersonic wind tunnel pilot system is related to aircraft solar heat protection ground experiment technical field；Including heater, supersonic nozzle, experimental cabin, diffuser and exhaust system；Wherein, one end of heater is connect with extra power system；Supersonic nozzle one end is fixedly connected with heater, and the other end of supersonic nozzle is fixedly connected with experimental cabin；Diffuser is fixedly mounted on one end of experimental cabin；One end of exhaust system is fixedly connected with diffuser, and the other end of exhaust system is connect with what external device；The present invention is the high-temperature fuel gas stream supersonic wind tunnel pilot system of hundred MW class power of one kind, meter level jet size, its power reaches 200 megawatts or more, jet size reaches 1.5m, can carry out the whole large scale model heat with part 1:1 of aircraft heat-protection system and examine.
Description
Technical field
The present invention relates to a kind of aircraft solar heat protection ground experiment technical field, especially a kind of high-temperature fuel gas stream supersonic speed wind
Hole pilot system.
Background technique
Hypersonic aircraft will receive harsh Aerodynamic Heating, heat-protection system is to aircraft development in flight course
Have the function of determining success or failure.Thermal environment simulation examination and verifying are carried out to aircraft heat-protection system using ground experiment, are winged
Essential link in the development process of row device heat-protection system.
The pilot system for carrying out the examination of aircraft heat-protection system heat domestic at present mainly has arc tunnel and combustion gas stream free
Fluidized bed.Arc tunnel power is in ten megawatts of magnitudes, and combustion gas stream free jet test platform scale is smaller, and nozzle exit pressure
Power is generally atmospheric pressure.The domestic hot tunnel climatic test system still without hundred megawatts of magnitude power at present.
Summary of the invention
It is an object of the invention to overcome the above-mentioned deficiency of the prior art, a kind of high-temperature fuel gas stream supersonic wind tunnel examination is provided
Check system, the system are the solar heat protection examination wind-tunnel that power reaches hundred megawatts of magnitudes, meet hypersonic aircraft heat-protection system
Whole and part 1:1 examines demand.
Above-mentioned purpose of the invention is achieved by following technical solution:
A kind of high-temperature fuel gas stream supersonic wind tunnel pilot system, including heater, supersonic nozzle, experimental cabin, diffuser
And exhaust system；Wherein, one end of heater is connect with extra power system；Supersonic nozzle one end and the fixed company of heater
It connects, the other end of supersonic nozzle is fixedly connected with experimental cabin；Diffuser is fixedly mounted on one end of experimental cabin；Exhaust system
One end is fixedly connected with diffuser, and the other end of exhaust system directly empties.
In a kind of above-mentioned high-temperature fuel gas stream supersonic wind tunnel pilot system, the exhaust system includes spray cooling dress
It sets, spray condensing unit, gas collecting apparatus and vacuum evacuation device；Wherein, spraying temperature lowering apparatus is fixedly connected with diffuser；It sprays cold
Solidifying device is fixedly connected with spraying temperature lowering apparatus；Gas collecting apparatus is fixedly mounted on the lower end of spray condensing unit；Vacuum evacuation device
It is fixedly connected with gas collecting apparatus.
In a kind of above-mentioned high-temperature fuel gas stream supersonic wind tunnel pilot system, high-temperature fuel gas stream supersonic wind tunnel pilot system
General power be greater than 200MW, temperature 2900-3700K；Stable work time is greater than 1000s.
In a kind of above-mentioned high-temperature fuel gas stream supersonic wind tunnel pilot system, the heater is that the burning of oxygen kerosene occurs
Device；Combustion gas total flow is more than being 29-31kg/s, and total heating power is greater than 200MW.
In a kind of above-mentioned high-temperature fuel gas stream supersonic wind tunnel pilot system, the supersonic nozzle is the spray of Laval face
The bore L1 of pipe, supersonic nozzle is 1.0-1.5m, replaces different bores according to actual needs.
In a kind of above-mentioned high-temperature fuel gas stream supersonic wind tunnel pilot system, the experimental cabin is rectangular water cooling cabin, including
Observation window, power supply flange, superpressure relief arrangement mouth, cooling water return pipe and cooling water inlet pipe；Wherein, observation window is fixedly mounted
In two middle side part of experimental cabin position on the lower side, and it is contour with the axis of supersonic nozzle；Power supply flange is fixedly mounted on experimental cabin
Lower section；Positioned at the top of observation window；The top rear of experimental cabin is arranged in superpressure relief arrangement mouth；Cooling water return pipe setting exists
Experimental cabin front end；Cooling water inlet pipe is arranged in experimental cabin rear end.
In a kind of above-mentioned high-temperature fuel gas stream supersonic wind tunnel pilot system, the straight two venturis formulas such as the diffuser (4) is
Diffuser；Including collector, contraction section, venturi and expansion segment；Collector, contraction section, venturi and expansion segment are fixedly connected sequentially；
The diffusion ratio of diffuser is greater than 10 times.
In a kind of above-mentioned high-temperature fuel gas stream supersonic wind tunnel pilot system, high-temperature fuel gas stream supersonic wind tunnel pilot system
The course of work are as follows: using oxygen and kerosene as fuel, burn in heater, the high-temperature fuel gas of generation total temperature 3700K；Through
The expansion for crossing supersonic nozzle accelerates, and forms supersonic speed high temperature gas flow, carries out hot examination to external model in experimental cabin；Test
Cabin interior air-flow pressure be far below atmospheric pressure, by diffuser slow down be pressurized, and by exhaust system cooling and further be pressurized after
Discharge.
In a kind of above-mentioned high-temperature fuel gas stream supersonic wind tunnel pilot system, the exhaust system passes through spraying temperature lowering apparatus
Fuel gas temperature is down to room temperature with spray condensing unit, combustion gas is pressurized by vacuum evacuation device and is discharged；Gas collecting apparatus provides one
Constant volume prevents pressure change in exhaust system too fast.
The invention has the following advantages over the prior art:
(1) core equipment of the present invention includes heater, supersonic nozzle, experimental cabin, diffuser, exhaust system, energy confession
Answer system etc..Wind tunnel system can realize status condition by modes such as replacement jet pipe, adjusting stagnation pressure, condition excess oxidizer coefficients, be vented
System can realize that the stable state under heavy traffic condition is vented, and general power is greater than 200MW, and total temperature reaches 3700K, and nozzle exit size reaches
To 1.5m, the time reaches 1000s；
(2) heater of the present invention is oxygen kerosene combustion generator, generates the big function of high temperature by the burning of oxygen and kerosene
Rate combustion gas, combustion gas total flow are more than 30kg/s, and total heating power is more than 200MW, pass through ejector filler design, the control in combustion reaction face
System and effective water cooling design the long-time steady-state operation to realize 1000s；
(3) supersonic nozzle of the present invention is Laval face jet pipe, and jet pipe 1.0~1.5m of bore can be according to operating condition needs
Replace different bore jet pipes；
(4) the straight two venturis formula diffusions such as experimental cabin of the present invention is rectangular water cooling cabin, and effective use volume is bigger, and diffuser is
Device is, it can be achieved that 10 times or more of diffusion ratio；
(5) wind-tunnel of the present invention can realize thermal environment state by modes such as replacement jet pipe, adjusting stagnation pressure, condition excess oxidizer coefficients
It adjusts.The jet pipe of compatible three sets of different bores, stagnation pressure adjustable range 30%, excess oxidizer coefficient adjustable range 40% is, it can be achieved that heat
The wide cut of environment is adjusted.
Detailed description of the invention
Fig. 1 is high-temperature fuel gas stream supersonic wind tunnel schematic diagram of the present invention；
Fig. 2 is experimental cabin schematic diagram of the present invention；
Fig. 3 is diffuser schematic diagram of the present invention.
Specific embodiment
The present invention is described in further detail in the following with reference to the drawings and specific embodiments:
The present invention provides a kind of high-power, large scale aircraft solar heat protection ground experiment examination wind-tunnel, and high-temperature fuel gas stream is super
The general power of velocity of sound wind tunnel test system is greater than 200MW, temperature 2900-3700K；Stable work time is greater than 1000s；It realizes
The high-power examination of large scale model of aircraft heat-protection system.
It is as shown in Figure 1 high-temperature fuel gas stream supersonic wind tunnel schematic diagram, as seen from the figure, a kind of high-temperature fuel gas stream supersonic speed wind
Hole pilot system, including heater 1, supersonic nozzle 2, experimental cabin 3, diffuser 4 and exhaust system 5；Wherein, heater 1
One end is connect with extra power system；2 one end of supersonic nozzle is fixedly connected with heater 1, the other end of supersonic nozzle 2 with
Experimental cabin 3 is fixedly connected；Diffuser 4 is fixedly mounted on one end of experimental cabin 3；One end of exhaust system 5 and the fixed company of diffuser 4
It connects, the other end of exhaust system 5 directly empties.
Wherein exhaust system 5 includes spraying temperature lowering apparatus 6, spray condensing unit 7, gas collecting apparatus 8 and vacuum evacuation device 9；
Wherein, spraying temperature lowering apparatus 6 is fixedly connected with diffuser 4；Spray condensing unit 7 is fixedly connected with spraying temperature lowering apparatus 6；Gas collection
Device 8 is fixedly mounted on the lower end of spray condensing unit 7；Vacuum evacuation device 9 is fixedly connected with gas collecting apparatus 8.
Heater 1 is oxygen kerosene combustion generator；Combustion gas total flow be more than be 29-31kg/s, total heating power is greater than
200MW。
The supersonic nozzle 2 is Laval face jet pipe, and the bore L1 of supersonic nozzle 2 is 1.0-1.5m, according to reality
Border needs replacing different bores.
It is illustrated in figure 2 experimental cabin schematic diagram, as seen from the figure, the experimental cabin 3 is rectangular water cooling cabin, including observation window
10, power supply flange 11, superpressure relief arrangement mouth 12, cooling water return pipe 13 and cooling water inlet pipe 14；Wherein, observation window 10 is solid
Dingan County position on the lower side mounted in 3 liang of middle side parts of experimental cabin, and it is contour with the axis of supersonic nozzle 2；The fixed peace of flange 11 of powering
Mounted in 3 lower section of experimental cabin；Positioned at the top of observation window 10；The top rear of experimental cabin 3 is arranged in superpressure relief arrangement mouth 12；It is cold
But water return pipe 13 is arranged in 3 front end of experimental cabin；Cooling water inlet pipe 14 is arranged in 3 rear end of experimental cabin.
It is illustrated in figure 3 diffuser schematic diagram, as seen from the figure, the straight two venturis formula diffusers such as the diffuser 4 is；Including
Collector 15, contraction section 16, venturi 17 and expansion segment 18；Collector 15, contraction section 16, venturi 17 and expansion segment 18 are successively fixed
Connection；The diffusion ratio of diffuser 4 is greater than 10 times.
The course of work of high-temperature fuel gas stream supersonic wind tunnel pilot system are as follows: using oxygen and kerosene as fuel, adding
Burning in hot device 1, generates the high-temperature fuel gas of total temperature 3700K；Accelerate by the expansion of supersonic nozzle 2, forms supersonic speed high temperature
Air-flow carries out hot examination to external model in experimental cabin 3；3 interior air-flow pressure of experimental cabin is far below atmospheric pressure, by diffuser
4, which slow down, is pressurized, and is cooled down by exhaust system 5 and be discharged after being further pressurized.
Fuel gas temperature is down to room temperature by spraying temperature lowering apparatus 6 and spray condensing unit 7 by exhaust system 5, true by taking out
Combustion gas is pressurized and is discharged by empty device 9；Gas collecting apparatus 8 provides a constant volume, prevents pressure change in exhaust system 5 too fast.It is described
Exhaust system is in the most downstream of wind tunnel system, including cooling device and vacuum evacuation device.Cooling device passes through spray cooling and spray
High-temperature fuel gas is reduced to room temperature using the latent heat of vaporization and sensible heat of water by the mode that leaching condensation combines, and vacuum evacuation device uses machine
Stream pressure is promoted to atmospheric pressure or more and is discharged by tool vacuum pump.
Wind-tunnel of the present invention can realize thermal environment shape by modes such as replacement jet pipe, adjusting stagnation pressure, condition excess oxidizer coefficients
State is adjusted.The jet pipe of compatible three sets of different bores, stagnation pressure adjustable range 30%, excess oxidizer coefficient adjustable range 40%, it can be achieved that
The wide cut of thermal environment is adjusted.
The content that description in the present invention is not described in detail belongs to the well-known technique of those skilled in the art.
Claims (3)
1. a kind of high-temperature fuel gas stream supersonic wind tunnel pilot system, it is characterised in that: including heater (1), supersonic nozzle
(2), experimental cabin (3), diffuser (4) and exhaust system (5)；Wherein, one end of heater (1) is connect with extra power system；
Supersonic nozzle (2) one end is fixedly connected with heater (1), the other end of supersonic nozzle (2) and experimental cabin (3) fixed company
It connects；Diffuser (4) is fixedly mounted on one end of experimental cabin (3)；One end of exhaust system (5) is fixedly connected with diffuser (4), row
The other end of gas system (5) directly empties；
The exhaust system (5) includes spraying temperature lowering apparatus (6), spray condensing unit (7), gas collecting apparatus (8) and vacuum means
Set (9)；Wherein, spraying temperature lowering apparatus (6) is fixedly connected with diffuser (4)；Spray condensing unit (7) and spraying temperature lowering apparatus
(6) it is fixedly connected；Gas collecting apparatus (8) is fixedly mounted on the lower end of spray condensing unit (7)；Vacuum evacuation device (9) and gas collection fill
(8) are set to be fixedly connected；
The general power of high-temperature fuel gas stream supersonic wind tunnel pilot system is greater than 200MW, temperature 2900-3700K；When steady operation
Between be greater than 1000s；
The heater (1) is oxygen kerosene combustion generator；Combustion gas total flow be more than be 29-31kg/s, total heating power is big
In 200MW；
The experimental cabin (3) be rectangular water cooling cabin, including observation window (10), power supply flange (11), superpressure relief arrangement mouth (12),
Cooling water return pipe (13) and cooling water inlet pipe (14)；Wherein, observation window (10) is fixedly mounted on (3) two middle side part of experimental cabin
Position on the lower side, and it is contour with the axis of supersonic nozzle (2)；Power supply flange (11) is fixedly mounted below experimental cabin (3)；Position
In the top of observation window (10)；The top rear in experimental cabin (3) is arranged in superpressure relief arrangement mouth (12)；Cooling water return pipe
(13) it is arranged in experimental cabin (3) front end；Cooling water inlet pipe (14) is arranged in experimental cabin (3) rear end；
The course of work of high-temperature fuel gas stream supersonic wind tunnel pilot system are as follows: using oxygen and kerosene as fuel, in heater
(1) burning in, generates the high-temperature fuel gas of total temperature 3700K；Accelerate by the expansion of supersonic nozzle (2), forms supersonic speed high temperature
Air-flow carries out hot examination to external model in experimental cabin (3)；Experimental cabin (3) interior air-flow pressure is far below atmospheric pressure, by expanding
Depressor (4), which slows down, to be pressurized, and is cooled down by exhaust system (5) and be discharged after being further pressurized；
Fuel gas temperature is down to room temperature by spraying temperature lowering apparatus (6) and spray condensing unit (7) by the exhaust system (5), is led to
It crosses vacuum evacuation device (9) and combustion gas is pressurized discharge；Gas collecting apparatus (8) provides a constant volume, prevents the interior pressure of exhaust system (5) from becoming
Change too fast.
2. a kind of high-temperature fuel gas stream supersonic wind tunnel pilot system according to claim 1, it is characterised in that: the Supersonic
Fast jet pipe (2) is Laval face jet pipe, and the bore L1 of supersonic nozzle (2) is 1.0-1.5m, is replaced according to actual needs not
Same bore.
3. a kind of high-temperature fuel gas stream supersonic wind tunnel pilot system according to claim 2, it is characterised in that: the diffusion
Device (4) be etc. straight two venturis formula diffuser；Including collector (15), contraction section (16), venturi (17) and expansion segment (18)；It collects
Device (15), contraction section (16), venturi (17) and expansion segment (18) are fixedly connected sequentially；The diffusion ratio of diffuser (4) is greater than 10 times.
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| CN201610912736.5A CN106568568B (en) | 2016-10-19 | 2016-10-19 | A kind of high-temperature fuel gas stream supersonic wind tunnel pilot system |
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| CN201610912736.5A CN106568568B (en) | 2016-10-19 | 2016-10-19 | A kind of high-temperature fuel gas stream supersonic wind tunnel pilot system |
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| CN106568568B true CN106568568B (en) | 2019-11-29 |
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