CN201149539Y - Two phase flow ground simulation test device under flight load function - Google Patents
Two phase flow ground simulation test device under flight load function Download PDFInfo
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- CN201149539Y CN201149539Y CNU2008200312959U CN200820031295U CN201149539Y CN 201149539 Y CN201149539 Y CN 201149539Y CN U2008200312959 U CNU2008200312959 U CN U2008200312959U CN 200820031295 U CN200820031295 U CN 200820031295U CN 201149539 Y CN201149539 Y CN 201149539Y
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Abstract
Disclosed is a two-phase flow ground simulation test device under the function of flight load, which belongs to the two-phase flow measuring technique field. The device simulates the flight dynamic loading condition by a flight dynamic loading platform and flight loading condition by adjusting revolving speed of a turntable to get different centripetal accelerations. The device consists of the dynamic loading platform and a two-phase flow test system, wherein the two-phase flow test system is composed of a flowing water circulation system, a fluid parameter measurement system and a data acquisition and saving system. The method and device can achieve the two-phase flow ground simulation test under the function of flight load.
Description
Technical field
Two phase flow ground simulation test device under the flight load function belongs to the two-phase flow measurement technical field, relates to the ground simulation platform of flight load state, the new technology of fluid parameter measuring method.
Background technology
Biphase gas and liquid flow is the flow process of gas, two kinds of fluid mixing of liquid or boiling, heat of condensation fluid, also is a kind of heat and mass transfer process that is accompanied by gas-liquid phase transition usually.Flow boiling and heat transfer in the horizontal tube, be widely used in the heat transmission equipment and refrigeration air-conditioner of power, nuclear energy, chemistry, Aero-Space and various processing industry, it has important practical value for energy savings, the consumption that reduces precious metal, minimizing equipment volume and reducing production costs etc.
In the aircraft industry field, the installation of high-power high integrated electronic electric equipment, though improved the overall performance and the fight capability of aircraft, but brought tens kilowatts heating load to fuselage, its thermal value is tens times of original thermal force, cause air circulation system to be difficult to reach the cooling requirement of its equipment, need better energy management and refrigeration system; In the space industry field, the space science development of technology more and more develops spacecraft to the high-power and high direction that becomes more meticulous, and then will be more and more higher to the fluid of spacecraft and heat management, power supply, environment control also with the requirement of life-support systems, this also requires to design and build to have more high-power, more advanced energy supply and heat delivered and control system.The heat transferred and the energy deliverability of two-phase flow medium fully satisfy this demand in the sweat cooling circulation.
The acceleration of aircraft is flown or is swerved and will certainly bring bigger movement load to fuselage, and the overload that fuselage bears numerically can reach 6～9g.When the sweat cooling circulation system is applied in the aeronautical and space technology, in the airborne sweat cooling circulation system cold-producing medium condense, evaporate and flow and diabatic process all can be subjected to the influence of dynamic load effect, and then influence the performance of refrigeration part and system.Like this, the reliability of the design and running of the sweat cooling circulation system will depend on fully realizing biphase gas and liquid flow mechanism under the dynamic load effect to a great extent.Therefore, the research of Two-phase flow and heat transfer characteristic just seems particularly important under the dynamic load effect.
Present stage, the experimental study of two-phase flow aspect rested on the ground stationary state mostly, the experimental result that obtains like this can not satisfy aircraft and do the requirement that produces the dynamic load state in the dangerous plays such as acceleration, deceleration, tempo turn, roll, quick pull-out, the appearance of dynamic load, make ground a lot of achievement in research might not still set up aboard, the defective of the experimental technique of sleep mode is to realize the influence of dynamic load for two-phase flow, therefore we will obtain still suitable aboard experimental result, and experimental situation must have the dynamic load effect.For the boiling heat transfer under the effect of flight dynamic load and the research aspect of biphase gas and liquid flow, rarely seen relevant research report.This mainly is because the realization of flight dynamic load state has certain difficulty.
In order to realize the dynamic load state, many now experiments that comprise the flight load state often need equipment set and surveying instrument all be installed to follows the machine experiment on the aircraft.Because being the centripetal force that is produced of turning when being flown by the aircraft high-speed maneuver, causes flight load, so during the experiment under carrying out the flight load state, the overload that aircraft has only dangerous plays such as doing acceleration, deceleration, tempo turn, roll, quick pull-out for a long time just can obtain to continue.The security that experimentizes in this case is poor, aircraft accident takes place easily and damage experimental facilities.Aircraft could go up to the sky to fly when occurring owing to the weather that has only suitable flying condition in addition, causes following the machine experiment to be subjected to the influence of weather bigger; Be exactly many more with the machine experiment number in addition, the flight number of times is also just many more, and experimental cost will be corresponding very high.
Though the someone imagines and utilizes long straight rail to quicken with simulated flight dynamic load state on ground now, can follow the machine experiment, but because this method need go up the long acceleration orbit of km, taken very big lab space, implement very and be not easy, and the size of dynamic load also is difficult to carry out real-time regulated according to experimental requirements.The ground simulation method of two-phase flow is not also realized under the dynamic load effect, and the method that can carry out two-phase flow data acquisition and detection in real time under moving load condition effectively is still in exploration.
Summary of the invention
The object of the present invention is to provide a kind of foundation also on the ground can realize two phase flow ground simulation test method and device under the flight load function.
Two phase flow ground simulation test method under a kind of flight load function is characterized in that comprising following process:
(1) utilization flight dynamic load analog platform simulated aircraft dynamic load state wherein obtains different centripetal accelerations by the rotational speed of adjusting rotating disk, with the flight load state under simulated aircraft acceleration, deceleration, tempo turn, roll, the quick pull-out action;
(2) the two-phase flow test macro is installed on the flight dynamic load analog platform, with real-time measurement fluid parameter and preservation experimental data.
Two phase flow ground simulation test device under a kind of flight load function is characterized in that: be made up of the two-phase flow test macro that flies the dynamic load analog platform and be installed on the flight dynamic load analog platform; The dynamic load of wherein flying analog platform is made up of rotating disk, motor, arrangements for speed regulation, frame; Wherein the two-phase flow test macro is made up of the circulating water circulation system, fluid parameter measuring system and data acquisition saved system; Wherein the circulating water circulation system comprises water tank, water pump, pre-heater, after-heater, transparent testing tube, wherein water outlet of water tank links to each other with water pump, pre-heater, after-heater successively by pipeline, the after-heater other end stretches in the transparent testing tube, and the transparent testing tube other end links to each other with the water tank water return outlet by pipeline; Wherein the fluid parameter measuring system comprises voidage tester, flowmeter, pressure gauge, differential manometer, temperature sensor; Wherein the data acquisition saved system is made up of data acquisition module that links to each other with sensor and notebook computer.
Principle of work: the pre-heater heating of flowing through after circulating water is extracted out in the water tank by water pump, flow into the transparent testing tube of two-phase flow again, since pre-heater add shortage of heat so that water is heated to fluidized state, therefore in transparent testing tube, be provided with after-heater, water is arrived boiling gas-liquid two-phase stream mode at transparent testing tube by post bake, by the pipeline reflow tank, form a circulation then.The sensor of setting pressure, pressure reduction, flow, voidage, temperature before and after the transparent test pipeline section.All sensors of measuring fluid parameter are connected with notebook computer by 3 data modules, and experimental data just can be got off in real-time preservation like this.By adjusting the velocity of rotation of universal stage, obtain different horizontal centripetal accelerations in the experimentation, to simulate different flight overloads.Two-phase flow flows and test macro all is fixed on the rotation platform, and then realizes the experiment of dynamic load effect Two-phase flow and heat exchange property.
Between water pump and pre-heater, can also be connected to a T-valve formula air and liquid mixer in the above-mentioned circulating water circulation system, an inlet of this T-valve formula air and liquid mixer is connected with described water pump, another inlet links to each other with air compressor machine, and its outlet is connected with described pre-heater.Form an air inlet branch road like this.Its effect is when pre-heater and after-heater are closed, and mixes to reach and mixes the gas-liquid two-phase state because this air inlet branch road is introduced water in the portion gas and the circulation system.
Two phase flow ground simulation test device under the above-mentioned flight load function, transparent test pipeline section can be radially or circumferential arrangement, and the angle of its inclination of scalable.Fluid flow direction is consistent with the turntable diameter direction in the time of radially, and is identical or opposite with the overload direction, but simulated flight device straight line quickens or the situation when slowing down.The experiment test pipeline section arranges that along the circumferential direction fluid flow direction is consistent with the tangent to periphery direction of turntable along pipeline section in the time of circumferentially, and direction is vertical with transshipping, but the simulated flight device is turned fast, the situation when underriding or pull-up.
Two phase flow ground simulation test device under the above-mentioned flight load function is provided with Digital Video near transparent testing tube, can take Two-phase flow state in the record transparent tube.
Utilize the rotation platform can be in ground load.It is combined with two-phase flow system, realized that two-phase flow under the flight dynamic load flows and the ground experiment of heat transfer property.
Utilize the rotation platform can be in ground load, solved the problem that the flight load experiment must be boarded a plane and be done, the dangerous play motor-driven with do height for a long time by aircraft produces the method for dynamic load state and compares, security will be got well, be not easy to damage experimental facilities, aircraft accident can not take place.Very high experimental expenses with respect to flight experiment, saved very big cost, the dynamic load size can change rotating speed according to requirement of experiment and regulate, the dynamic load size can be controlled, the dynamic load direction can be regulated by the putting position that changes transparent test pipeline section, and test and just can carry out indoor, be not subjected to the influence of weather conditions.
Utilize rotation platform simulation dynamic load state very big advantage to be arranged with respect to dynamic load analogy method with straight rail accelerated motion.The dynamic load simulation of rotatable platform can be carried out in common lab, does not need very long acceleration orbit, quickens to go up the long track of km with respect to straight line, and rotation platform has been saved space and expense, than being easier to realization and affected by environment less.
Two-phase flow proving installation under the dynamic load can be realized control and measure in the dynamic load change procedure well, carry out real-time data acquisition and preservation, the contrast of result and stationary state can obtain the influence of dynamic load state for two-phase flow by experiment, has solved the power delivery that is difficult to realize under the dynamic load status condition, has circulated, heats and control and measuring problem in real time.This system has two-phase flow and generates and test function.Can measure flow voidage and the data in real time of test is kept in the notebook computer of gas-liquid two-phase in real time.The experiment test pipe adopts the transparent organic glass pipe, can see the mobility status of internal flow, can take Two-phase flow state in the record transparent tube by HD digital Camcorder.
In sum, quicken to compare with flight experiment with straight rail, this invention makes under the dynamic load effect two-phase flow flow and heat transfer characteristic is tested easier control, more economical, safer.Two-phase flow proving installation controllability is strong, and real-time is good.
Description of drawings
Fig. 1 is a flight dynamic load analog platform synoptic diagram.Wherein Fig. 1 (a) is a front view, and Fig. 1 (b) is a vertical view.
Fig. 2 is the two-phase flow measurement system schematic.
Fig. 3 is transparent test pipeline section synoptic diagram.
Number in the figure title: 1, frame; 2, protection network; 3, rotating disk; 4, brushgear; 5, motor; 9, guardrail; 12, water tank; 13, water pump; 14, flowmeter; 15, T-valve formula air and liquid mixer; 16, pre-heater; 17, after-heater; 18, thermometric face; 19, transparent testing tube; 20, differential manometer; 21, pressure gauge; 22, air compressor machine; 23, oil separator; 24, data acquisition module; 25, notebook computer; 26, voidage tester; 27, panel box; 28, valve; 29, video camera; 32, temperature sensor; 33, voidage test surfaces; 34, wing flats; 35, water tank water return outlet; 36, water outlet of water tank.
Specific embodiments
Further introduce the composition of flight dynamic load simulation experiment platform in conjunction with Fig. 1.The high speed rotating of experiment porch requires experimental provision that very firm cement ground will be arranged.Motor 5 and rotating disk 3 all are fixed on the frame 1, can guarantee that so just whole platform is firm in operation, steady.Rotating disk 3 is connected with frame 1 by bearing, and the axis of rotating disk 3 couples together by belt and motor 5, and motor 5 drives the platform high speed rotating by belt, and the rotating speed of motor 5 is controlled and regulated by frequency converter, and frequency converter is installed in the outside of platform.Because motor 5 usefulness is the three-phase power line, so the electric wire of whole platform will have ground protection.Because rotating disk 3 high speed rotating, experiment inevitably has certain danger.For ensureing the safety of experimentation, having under the situation of fender wall, the protection network of stainless steel has been installed.
Further introduce the composition of two phase flow ground simulation test device in conjunction with Fig. 2.Circulating water is flowed into the transparent testing tube 19 of two-phase flow again by water pump 13 pre-heater 16 heating of flowing through after 12 li extractions of water tank.Since pre-heater 16 add shortage of heat so that water is heated to fluidized state, therefore in transparent testing tube 19, be provided with after-heater 17, water is arrived boiling gas-liquid two-phase stream mode at transparent testing tube 19 by post bake, by pipeline reflow tank 12, forms a circulation then.The sensor of transparent testing tube 19 front and back setting pressures, pressure reduction, flow, voidage, temperature.All sensors of measuring fluid parameter are connected with notebook computer 25 by 3 data modules, and experimental data just can be got off in real-time preservation like this.By adjusting the velocity of rotation of rotating disk 3, obtain different horizontal centripetal accelerations in the experimentation, to simulate the flight overload of different sizes.Transparent test pipeline section can be radially or circumferential arrangement, and the angle of its inclination of scalable.Fluid flow direction is consistent with the turntable diameter direction in the time of radially, and is identical or opposite with the overload direction, but simulated flight device straight line quickens or the situation when slowing down.The experiment test pipeline section arranges that along the circumferential direction fluid flow direction is consistent with the tangent to periphery direction of turntable along pipeline section in the time of circumferentially, and direction is vertical with transshipping, but the simulated flight device is turned fast, the situation when underriding or pull-up.
Two-phase flow flows and test macro all is fixed on the flight dynamic load simulation experiment platform, and then realizes the experiment of dynamic load effect Two-phase flow and heat exchange property.
Between water pump and pre-heater, can also be connected to a T-valve formula air and liquid mixer 15 in the above-mentioned circulating water circulation system, an inlet of this T-valve formula air and liquid mixer 15 is connected with described water pump 13, another inlet links to each other with air compressor machine 22, and its outlet is connected with described pre-heater 16.Form an air inlet branch road like this.Its effect is when pre-heater 16 and after-heater 17 are closed, and introduces water in the portion gas and the circulation system by this air inlet branch road and mixes to reach and mix the gas-liquid two-phase state.The all devices electricity consumption is supplied with by panel box.
Shown in Fig. 2 and 3, further introduce transparent testing tube 19 inner sensor positions.Inwall at transparent testing tube 19 is respectively equipped with 4 thermometric faces 18 as shown in the figure, and the probe of temperature sensor 32 stretches into transparent testing tube 19 inwalls.First is used for measuring fluid temperature (F.T.) before the boiling 4 thermometric faces, second fluid temperature (F.T.) that is used for measuring in the boiling, all the other two fluid temperature (F.T.)s that are used for measuring after the boiling.
Claims (4)
1, two phase flow ground simulation test device under a kind of flight load function is characterized in that: be made up of the two-phase flow test macro that flies the dynamic load analog platform and be installed on the flight dynamic load analog platform;
The dynamic load of wherein flying analog platform is made up of rotating disk (3), motor (5), arrangements for speed regulation, frame (10);
Wherein the two-phase flow test macro is made up of the circulating water circulation system, fluid parameter measuring system and data acquisition saved system;
Wherein the circulating water circulation system comprises water tank (12), water pump (13), pre-heater (16), after-heater (17), transparent testing tube (19), wherein water outlet of water tank (36) links to each other with water pump (13), pre-heater (16), after-heater (17) successively by pipeline, after-heater (17) other end stretches in the transparent testing tube (19), and transparent testing tube (19) other end links to each other with water tank water return outlet (35) by pipeline;
Wherein the fluid parameter measuring system comprises voidage tester (26), flowmeter (14), pressure gauge (21), differential manometer (20), temperature sensor (32);
Wherein the data acquisition saved system is made up of data acquisition module that links to each other with sensor (24) and notebook computer (25).
2, two phase flow ground simulation test device under the flight load function according to claim 1, it is characterized in that: between water pump (13) and pre-heater (16), also be connected to a T-valve formula air and liquid mixer (15) in the described circulating water circulation system, an inlet of this T-valve formula air and liquid mixer (15) is connected with described water pump (13), another inlet links to each other with air compressor machine (22), and its outlet is connected with described pre-heater (16).
3, according to two phase flow ground simulation test device under the described flight load function of claim 1-2, it is characterized in that: described transparent testing tube (19) is radially circumferential or arbitrarily angled layout on rotating disk (3).
4, according to two phase flow ground simulation test device under the described flight load function of claim 1-2, it is characterized in that: near described transparent testing tube (19), be provided with the Digital Video (29) that is used for taking record transparent tube Two-phase flow state.
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| Application Number | Priority Date | Filing Date | Title |
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| CNU2008200312959U CN201149539Y (en) | 2008-01-22 | 2008-01-22 | Two phase flow ground simulation test device under flight load function |
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| Application Number | Priority Date | Filing Date | Title |
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| CNU2008200312959U CN201149539Y (en) | 2008-01-22 | 2008-01-22 | Two phase flow ground simulation test device under flight load function |
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| CN201149539Y true CN201149539Y (en) | 2008-11-12 |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN100585360C (en) * | 2008-01-22 | 2010-01-27 | 南京航空航天大学 | Two phase flow ground simulation test method and device under flight load function |
| CN109060288A (en) * | 2018-09-17 | 2018-12-21 | 西南石油大学 | A kind of testing tube section apparatus of the interior stream two phase flow Flow vibration experiment of development |
-
2008
- 2008-01-22 CN CNU2008200312959U patent/CN201149539Y/en not_active Expired - Lifetime
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN100585360C (en) * | 2008-01-22 | 2010-01-27 | 南京航空航天大学 | Two phase flow ground simulation test method and device under flight load function |
| CN109060288A (en) * | 2018-09-17 | 2018-12-21 | 西南石油大学 | A kind of testing tube section apparatus of the interior stream two phase flow Flow vibration experiment of development |
| CN109060288B (en) * | 2018-09-17 | 2020-09-18 | 西南石油大学 | Test pipe section device for developing internal flow two-phase flow induced vibration experiment |
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Effective date of abandoning: 20080122 |
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| C25 | Abandonment of patent right or utility model to avoid double patenting |