CN102519704A - Pulse wind tunnel thermal jet flow experiment gas source feed platform - Google Patents
Pulse wind tunnel thermal jet flow experiment gas source feed platform Download PDFInfo
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- CN102519704A CN102519704A CN2011103491711A CN201110349171A CN102519704A CN 102519704 A CN102519704 A CN 102519704A CN 2011103491711 A CN2011103491711 A CN 2011103491711A CN 201110349171 A CN201110349171 A CN 201110349171A CN 102519704 A CN102519704 A CN 102519704A
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Abstract
The invention discloses a pulse wind tunnel thermal jet flow experiment gas source feed platform. The platform comprises a gas blending tank, and hydrogen, oxygen and nitrogen are uniformly mixed according to a predetermined proportion to form combustible mixed gas which is filled into a pipeline. The mixed gas is filled into the pipeline according to predetermined pressure. A metal membrane and a jet pipe are arranged at a pipe end of the pipeline in order. A position close to the metal membrane at the pipe end also is provided with an ignition unit. When the ignition unit ignites the mixed gas, by utilizing instant raising of temperature and pressure of combustion gas after combustion, the metal membrane is broken through, the gas sprays out of the jet pipe to form combustion gas jet flow which satisfies a thermal jet flow experiment state, and the combustion gas jet flow is ensured to have a segment of stable flow time. According to the invention, by utilizing a hydrogen and oxygen combustion pipeline method, a transient combustion gas thermal jet flow gas source with a total temperature of 1000K about can be provided, a complex cooling system is not needed, and the platform has the characteristics of a short experiment period, small environmental pollution, low energy demand.
Description
Technical field
The present invention relates to the hot jet flow experiment of a kind of impulse wind tunnel source of the gas air feed platform.
Background technology
Aircraft causes aircraft control rudder face efficient to reduce greatly because high-altitude hypopycnal flow kinetic energy sharply descends when high speed flight at high altitude.In order to improve the maneuvering characteristics of aircraft, adopt the jet flow engine control in a large number, the jet flow of employing mainly is the higher gaseous jet of stagnation temperature (a hot jet flow).The interference meeting of hot jet flow and main flow produces remarkable influence to aircraft body and the pneumatic thermal environment of structure member.
At present, less for hot jet flow experimental study both at home and abroad, there is following several respects problem from see hot jet flow experiment of existing technical development:
1, there is not the pneumatic heat experiment of nozzle inside/outside stream coupling
In the existing experimental technique, only carry out stream experiment in the engine mostly, mainly comprise: the heat structure of the pneumatic performance of research engine, thermodynamic cycle performance, firing chamber internal combustion efficient and engine to engine chamber.These experimental techniques all can not be engaged in outflow coupling experiment research in the nozzle, can not study the pneumatic thermal environment experiment of body behind the engine.
2, there is not the experiment of hot jet flow inside/outside stream coupled characteristic
In the jet flow control wind tunnel experiment; Basically all be outflow coupling experiment in carrying out according to similar parameters such as blow down ratio, Mach number and geometric parameters with gases at high pressure; Real gas influence for engine has only the work of some numerical evaluation, and carries out hot jet flow experiment also rare report both at home and abroad.
3, there is not the synchronous experimental technique of hot jet flow and impulse wind tunnel
Impulse wind tunnel system and hot jet flow system all are the operational systems of millisecond magnitude, have caused the difficulty of synchronous operation.
Summary of the invention
To the problem that prior art exists, the object of the present invention is to provide a kind of hot jet flow experiment of impulse wind tunnel source of the gas air feed platform that good experimental situation can be provided for outflow coupling experiment in the engine of scale model.
The hot jet flow experiment of a kind of impulse wind tunnel provided by the invention source of the gas air feed platform comprises:
The gas mixing tank mixes hydrogen, oxygen and nitrogen according to predetermined ratio, form combustible mixed gas, and said mixed gas is filled in the pipeline;
Pipeline charges into said mixed gas according to predetermined pressure;
Pipe end at said pipeline is disposed with metallic membrane and jet pipe, near the position of said metallic membrane igniting unit is installed also at said pipe end;
When said igniting unit is lighted said mixed gas; Utilize raising moment of burning back fuel gas temperature and pressure that said metallic membrane is broken through; And from said jet pipe ejection, form and satisfy hot jet flow experimental state gaseous jet, guarantee that gaseous jet has one section stable flowing time.
Preferably, said metallic membrane has suitable thickness, also offers the groove with suitable length and degree of depth on the surface of said metallic membrane.
Preferably, said groove is a cross recess.
Preferably, the blending ratio of said hydrogen, oxygen and nitrogen is: the nitrogen of hydrogen 50～60%, oxygen 5～15% and surplus, very being weight percentage here.
The present invention has following advantage:
1, the present invention utilizes the hot jet flow source of the gas of transient state combustion gas about the method for oxyhydrogen combustion pipeline can provide stagnation temperature for 1000K, does not need more complicated cooling system, and it is short therefore to have experimental period, and environmental pollution is little, the characteristics that energy demand is few;
2, can to obtain to satisfy the hot jet flow source of the gas of different stagnation temperatures, conveniently satisfy jet flow experiment similarity criterion through the different proportion of allotment mixed gas;
3, the present invention tests and has realized the pneumatic heat experiment of platform nozzle inside/outside stream coupling, can carry out the experiment of hot jet flow inside/outside stream coupled characteristic, thereby be convenient to utilize the inside and outside flow disturbance of laboratory facilities exploratory flight device pneumatic hot;
4, the present invention can also realize hot jet flow and the synchronous experiment of impulse wind tunnel.
Characteristics such as it is short that 5, the present invention also has experimental period, and experimental cost is low, and the pollution that experimental situation is caused is little.
Description of drawings
Fig. 1 is a structural representation of the present invention.
Fig. 2 is the structural representation of metallic membrane.
Embodiment
As shown in Figure 1; The present invention includes: gas mixing tank 2, pipeline 3, metallic membrane 5 and jet pipe 6; Gas mixing tank 2 is used for hydrogen, oxygen and nitrogen are mixed according to predetermined ratio, forms combustible mixed gas, and mixed gas is filled in the pipeline 3.In embodiments of the present invention, can utilize draft tube 1 that above-mentioned three kinds of gases are filled in the gas mixing tank 2 according to predetermined ratio.Pipeline 3 is used for charging into mixed gas according to predetermined pressure.In embodiments of the present invention, pipeline 3 can adopt length L=7～10m, the sealing of the high pressure resistant pipeline of caliber Φ=100mm and assurance pipeline.Metallic membrane 5 and jet pipe 6 are successively set on the pipe end of pipeline 3, near the position of metallic membrane 5 igniting unit 4 are installed also at pipe end.In the embodiment of the invention, igniting unit 4 adopts electric spark.
Like this; After igniting unit 4 is lighted mixed gas, utilize raising moment of burning back fuel gas temperature and pressure that metallic membrane 5 is broken through, and spray from jet pipe 6; Satisfy hot jet flow experimental state gaseous jet thereby form; Its Main physical state comprises the gaseous jet stagnation temperature, stagnation pressure and Mach number, and can guarantee that gaseous jet has one section stable flowing time.
In addition, the blending ratio of above-mentioned hydrogen, oxygen and nitrogen is preferably: the nitrogen of hydrogen 50～60%, oxygen 5～15% and surplus, very being weight percentage here.
The present invention adopts oxyhydrogen combustion, and the mode of end face igniting produces the hot gas source, and the component of mixed gas is: hydrogen H
2, oxygen O
2And nitrogen N
2Reach the experimental state of testing required hot jet flow gas through the proportioning of regulating the mixed gas different component, before the experiment these three kinds of gases are poured gas mixing tank 2 by predetermined ratio, make it in gas mixing tank 2, fully mix after 10～15 minutes; Mixed gas is poured in the pipeline 3; Utilize spark ignition to make mixed gas burning, utilize pressure and the raising of temperature after the gaseous combustion to break through metallic membrane 5, and from jet pipe 6 ejections.
Because the present invention adopts the burning burning mixture to drive pipeline 3 work; The raising of utilization burning back fuel gas temperature and pressure is broken through metallic membrane 5 and is sprayed from jet pipe 6; Realize the smooth combustion of mixed gas at normal temperatures and pressures, avoided the generation of phenomenon of detonation.Especially adopt the mode of rich hydrogen burning heated nitrogen; The blending ratio of hydrogen, oxygen and nitrogen is: the proportioning of the nitrogen of hydrogen 50～60%, oxygen 5～15% and surplus, further better proportioning is: the nitrogen of hydrogen 50%～60%, oxygen about 10% and surplus.Here very be weight percent hundred.Experimental result shows: adopt the method effectively to avoid the generation of phenomenon of detonation, from lighting a fire the perfect combustion time 10ms～20ms, not only reduced while burning time but also can produce high temperature with the mode of stablizing smoulder, the gas of high pressure simultaneously.
In addition; The concrete mode of control spark ignition can adopt following mode: the power isolation transformer auxiliary winding of controller has 5 taps; Switching through waver and toggle switch; The different voltages with different value can be obtained,, totally 9 grades of magnitudes of voltage can be obtained about DC70-600V again through 2 voltage multiplying rectifiers, capacitance energy storage.The on-off element of IGNITION CONTROL adopts the up-to-date semiconductor devices IGBT pipe of the third generation, and switching speed is 0.1～1 μ s.There is computer-controlled ignition signal to be added to time base circuit through optic coupling element; After timing controlled, output to the G utmost point of IGBT; Make its conducting, the electric capacity of energy storage has been very soon through heated filament discharge, and the high voltage on the electric capacity, big electric current make the heated filament blast and produce high-energy burning mixture is lighted.
The basic mechanical design feature of heated filament discharge igniting controller: power supply is suppressed AC220V, and inverter DC12V, 7Ah are output as AC220V, continuous working 10 hours.Ignition voltage divides high and low two grades of totally 9 kinds of different voltages with different values, voltage-regulation scope DC70V～600V.External trigger ignition signal DC3.5～10V, the trigger pip electric current is greater than 3mA.Ignition signal to the heated filament electric detonation time less than 0.1ms, the ignition timing time is 5ms.Every 470 μ F450VDC of storage capacitor, IGBT manages 60A1KV, ignition wire diameter of phi 0.08～0.15mm, instrument continuous working for a long time.
The method of application of heated filament discharge igniting controller is: the control signal of computing machine output is connected with lighter with the Q9 head, and Q9 center is that pulse signal is anodal, all can between signal amplitude DC3.5～10V.The adjusting of voltage should be regulated after discharging as if voltage is too high by hanging down to lofty tone again.The adjusting of voltage just can obtain 9 kinds of magnitudes of voltage by the switching of 1～6 of waver and " height " " low " position of toggle switch.Two positive and negative polar curves that inverter is drawn are connected with the accumulator positive and negative electrode, just can produce the AC220V power supply, as long as the attaching plug access inverter socket of lighter is got final product operate as normal.Show when on the low side when magnitude of voltage occurring, should be in time and charge in batteries.
Can the igniting position choice be obtain one of gordian technique of smooth combustion among the present invention.The mode of lighting a fire through the single-point end face among the present invention can obtain comparatively stable, the burning wave system of good reproducibility.Specific practice is that electric spark is placed near metallic membrane 5 front ends, utilizes the IGNITION CONTROL element to trigger igniting.
In addition, the present invention adopts has the metallic membrane of suitable thickness, and offers the groove with appropriate depth, to reach the purpose of nature rupture of membranes.For example, in the embodiment of the invention, adopt the aluminium film that has " ten " font groove, the aluminium film thickness is 0.32mm, and groove depth is 0.22mm, and is as shown in Figure 2.Be sealed between the pipe end and jet pipe 6 of pipeline 3.Utilize the nature rupture of membranes, promptly, metallic membrane 5 is broken through near the HTHP of burning back gas.
Claims (4)
1. the hot jet flow experiment of an impulse wind tunnel source of the gas air feed platform is characterized in that, comprising:
The gas mixing tank mixes hydrogen, oxygen and nitrogen according to predetermined ratio, form combustible mixed gas, and said mixed gas is filled in the pipeline;
Pipeline charges into said mixed gas according to predetermined pressure;
Pipe end at said pipeline is disposed with metallic membrane and jet pipe, near the position of said metallic membrane igniting unit is installed also at said pipe end;
When said igniting unit is lighted said mixed gas; Utilize raising moment of burning back fuel gas temperature and pressure that said metallic membrane is broken through; And from said jet pipe ejection, form and satisfy hot jet flow experimental state gaseous jet, guarantee that gaseous jet has one section stable flowing time.
2. platform as claimed in claim 1 is characterized in that said metallic membrane has suitable thickness, also offers the groove with suitable length and degree of depth on the surface of said metallic membrane.
3. platform as claimed in claim 2 is characterized in that, said groove is a cross recess.
4. like the arbitrary described platform of claim 1 to 3, it is characterized in that the blending ratio of said hydrogen, oxygen and nitrogen is: the nitrogen of hydrogen 50～60%, oxygen 5～15% and surplus, very being weight percentage here.
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| CN2011103491711A CN102519704A (en) | 2011-11-08 | 2011-11-08 | Pulse wind tunnel thermal jet flow experiment gas source feed platform |
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| CN2011103491711A CN102519704A (en) | 2011-11-08 | 2011-11-08 | Pulse wind tunnel thermal jet flow experiment gas source feed platform |
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2582805C2 (en) * | 2014-09-22 | 2016-04-27 | Федеральное государственное автономное образовательное учреждение высшего образования "Новосибирский национальный исследовательский государственный университет" (Новосибирский государственный университет, НГУ) | Device for gas sampling in high-enthalpy plants of short-term action and method of measuring flow gas rate with use of said device |
| RU2582805C9 (en) * | 2014-09-22 | 2016-06-27 | Федеральное государственное автономное образовательное учреждение высшего образования "Новосибирский национальный исследовательский государственный университет" (Новосибирский государственный университет, НГУ) | Device for gas sampling in high-enthalpy plants of short-term action and method of measuring flow gas rate with use of said device |
| CN106402865A (en) * | 2016-09-29 | 2017-02-15 | 中国科学院力学研究所 | Heater igniter of high-ultrasonic-velocity high-enthalpy ground simulation equipment |
| CN106441793A (en) * | 2016-11-14 | 2017-02-22 | 北京航空航天大学 | Adjusting method and apparatus of air-flow temperature in calibration wind tunnel |
| CN107143849A (en) * | 2017-04-20 | 2017-09-08 | 南京理工大学 | Aero-engine ground direct-connect test air heating apparatus |
| CN108051176A (en) * | 2017-11-29 | 2018-05-18 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of high enthalpy tube wind tunnel driving tube body of width Mach number |
| CN109765030A (en) * | 2019-03-12 | 2019-05-17 | 中国空气动力研究与发展中心超高速空气动力研究所 | A kind of wind-tunnel hot exhaust interference test device |
| CN111649904A (en) * | 2020-06-12 | 2020-09-11 | 中国空气动力研究与发展中心超高速空气动力研究所 | Film clamping method based on screw temperature control |
| CN113375889A (en) * | 2021-05-14 | 2021-09-10 | 中国科学院力学研究所 | Thermal jet flow experimental method for shock tunnel |
| CN113375890A (en) * | 2021-05-14 | 2021-09-10 | 中国科学院力学研究所 | Thermal jet flow experimental device for shock tunnel |
| CN113884267A (en) * | 2021-12-07 | 2022-01-04 | 中国空气动力研究与发展中心超高速空气动力研究所 | Transient jet flow test device for pulse wind tunnel |
| CN114166455A (en) * | 2021-12-07 | 2022-03-11 | 中国空气动力研究与发展中心超高速空气动力研究所 | Transient jet flow test method for pulse wind tunnel |
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Cited By (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2582805C9 (en) * | 2014-09-22 | 2016-06-27 | Федеральное государственное автономное образовательное учреждение высшего образования "Новосибирский национальный исследовательский государственный университет" (Новосибирский государственный университет, НГУ) | Device for gas sampling in high-enthalpy plants of short-term action and method of measuring flow gas rate with use of said device |
| RU2582805C2 (en) * | 2014-09-22 | 2016-04-27 | Федеральное государственное автономное образовательное учреждение высшего образования "Новосибирский национальный исследовательский государственный университет" (Новосибирский государственный университет, НГУ) | Device for gas sampling in high-enthalpy plants of short-term action and method of measuring flow gas rate with use of said device |
| CN106402865A (en) * | 2016-09-29 | 2017-02-15 | 中国科学院力学研究所 | Heater igniter of high-ultrasonic-velocity high-enthalpy ground simulation equipment |
| CN106402865B (en) * | 2016-09-29 | 2018-11-09 | 中国科学院力学研究所 | A kind of heater igniter of hypersonic high enthalpy ground-based simulation equipment |
| CN106441793A (en) * | 2016-11-14 | 2017-02-22 | 北京航空航天大学 | Adjusting method and apparatus of air-flow temperature in calibration wind tunnel |
| CN106441793B (en) * | 2016-11-14 | 2018-02-13 | 北京航空航天大学 | The adjusting method of gas flow temperature suitable for calibration wind tunnel |
| CN107143849B (en) * | 2017-04-20 | 2023-04-11 | 南京理工大学 | Ground direct-connected test air heating device for aero-engine |
| CN107143849A (en) * | 2017-04-20 | 2017-09-08 | 南京理工大学 | Aero-engine ground direct-connect test air heating apparatus |
| CN108051176A (en) * | 2017-11-29 | 2018-05-18 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of high enthalpy tube wind tunnel driving tube body of width Mach number |
| CN108051176B (en) * | 2017-11-29 | 2019-11-15 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of high enthalpy tube wind tunnel of width Mach number drives tube body |
| CN109765030A (en) * | 2019-03-12 | 2019-05-17 | 中国空气动力研究与发展中心超高速空气动力研究所 | A kind of wind-tunnel hot exhaust interference test device |
| CN109765030B (en) * | 2019-03-12 | 2024-04-19 | 中国空气动力研究与发展中心超高速空气动力研究所 | Wind tunnel thermal jet interference test device |
| CN111649904A (en) * | 2020-06-12 | 2020-09-11 | 中国空气动力研究与发展中心超高速空气动力研究所 | Film clamping method based on screw temperature control |
| CN113375889A (en) * | 2021-05-14 | 2021-09-10 | 中国科学院力学研究所 | Thermal jet flow experimental method for shock tunnel |
| CN113375890A (en) * | 2021-05-14 | 2021-09-10 | 中国科学院力学研究所 | Thermal jet flow experimental device for shock tunnel |
| CN113884267A (en) * | 2021-12-07 | 2022-01-04 | 中国空气动力研究与发展中心超高速空气动力研究所 | Transient jet flow test device for pulse wind tunnel |
| CN113884267B (en) * | 2021-12-07 | 2022-02-25 | 中国空气动力研究与发展中心超高速空气动力研究所 | Transient jet flow test device for pulse wind tunnel |
| CN114166455A (en) * | 2021-12-07 | 2022-03-11 | 中国空气动力研究与发展中心超高速空气动力研究所 | Transient jet flow test method for pulse wind tunnel |
| CN114166455B (en) * | 2021-12-07 | 2023-03-31 | 中国空气动力研究与发展中心超高速空气动力研究所 | Transient jet flow test method for pulse wind tunnel |
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Application publication date: 20120627 |