CN204346806U - For the gas mixer of high-altitude flight atmospheric temperature simulated experiment - Google Patents
For the gas mixer of high-altitude flight atmospheric temperature simulated experiment Download PDFInfo
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- CN204346806U CN204346806U CN201520017073.1U CN201520017073U CN204346806U CN 204346806 U CN204346806 U CN 204346806U CN 201520017073 U CN201520017073 U CN 201520017073U CN 204346806 U CN204346806 U CN 204346806U
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Abstract
The utility model discloses a kind of gas mixer for the simulated experiment of high-altitude flight atmospheric temperature, wherein mixing chamber urceolus, measuring chamber urceolus, mixing chamber inner core and measuring chamber inner core are cylinder type hollow tube-in-tube structure, and together constitute the double-layer cavity structure possessing four inner spaces; Heat-source spraying gun inserts in mixing chamber inner core, and sprays into plasma high-temperature gas for high/low temperature gas and vapor permeation space wherein; Mixing chamber urceolus offers gas access, the wall of mixing chamber inner core offers circumferentially uniform hole, make cryogenic gas perform Homogeneous phase mixing with jet mixing mode and high-temperature gas thus, then enter mixed gas measurement space; The Probe arrangement of temperature sensor in mixed gas measurement space, and is measured for performing real time temperature to mixed gas.By the utility model, rapid mixing and the measurement of high/low temperature flowing gas can be reached, and obtain the servo-actuated temperature simulation system of high precision and response fast.
Description
Technical field
The utility model belongs to ground high-altitude flight hardware-in-the-loop simulation field, more specifically, relate to a kind of gas mixer for the simulated experiment of high-altitude flight atmospheric temperature, it is suitable for realizing high precision, the high/low temperature gas and vapor permeation responded fast and servo-actuated temperature simulation and test-purpose for flowing gas.
Background technology
In order to meet the demand of Current terrestrial hardware-in-the-loop experiment, usually need the experimental provision of simulated flight device high-altitude flight atmospheric temperature, and the part material object accessing aircraft in temperature simulation emulation loop is tested.It can access in kind as far as possible in environmental simulation system when conditions permit, to replace the mathematical model of appropriate section, like this closer to actual conditions, and accurately reflect actual characteristic and the problem of aircraft, thus grasp aircraft in the condition of Space-Work and characteristic, eliminate the in-flight hidden danger of aircraft.
For above-mentioned high-altitude flight atmospheric temperature analog machine, high and low temperature gas mixer is one of its core component, and its performance quality directly has influence on the reliability of temperature simulator.But further research shows, current temperature simulation equipment majority is humidity control system, and temperature simulation scope is lower, and there is the defects such as the low or position control low precision of response speed when applying to dynamic High Temperature Simulation; Especially, for flowing gas in high-altitude flight atmospheric environment, be difficult to the servo-actuated temperature simulation system obtaining high precision, response fast.
Utility model content
For above defect or the Improvement requirement of prior art, the utility model provides a kind of gas mixer for the simulated experiment of high-altitude flight atmospheric temperature, wherein by the feature in conjunction with high-altitude flight atmospheric temperature simulation self, the unitary construction of its high/low temperature gas mixer and set-up mode are improved, especially to configuration mixing chamber urceolus wherein, mixing chamber inner core, the concrete structure of the key components such as measuring chamber urceolus and measuring chamber inner core and be interconnected mode design, double-layer cavity structure should be able to be utilized to reach rapid mixing and the measurement of high/low temperature flowing gas mutually, and obtain the servo-actuated temperature simulation system of high precision and response fast, thus the application scenario of high-altitude flight atmospheric temperature simulated experiment is particularly useful for.
For achieving the above object, according to the utility model, provide a kind of gas mixer for the simulated experiment of high-altitude flight atmospheric temperature, it is characterized in that, this gas mixer comprises mixing chamber urceolus, measuring chamber urceolus, mixing chamber inner core, measuring chamber inner core, heat-source spraying gun and temperature sensor, wherein:
Described mixing chamber urceolus, measuring chamber urceolus, mixing chamber inner core and measuring chamber inner core are cylinder type hollow tube-in-tube structure, wherein installed by flange coaxial between mixing chamber urceolus and measuring chamber urceolus and jointly form the first cavity, between mixing chamber inner core and measuring chamber inner core, threadedly coaxial installation forms the second cavity jointly, and the second cavity is distributed in its center of inside along the whole length direction of the first cavity, forms double-layer cavity structure thus; In addition, in the inside and outside cylinder junction of this double-layer cavity structure, correspondence is provided with the first heat insulation loop and the second heat insulation loop respectively, double-layer cavity structure is divided into four spaces further thus, namely be in cryogenic gas on the left of outer cavity to import space, be in high/low temperature gas and vapor permeation space on the left of internal layer cavity, be in mixed gas measurement space on the right side of internal layer cavity, and be in the heat insulation packing space on the right side of outer cavity;
The side of described first cavity is Closed End, and described heat-source spraying gun runs through this Closed End and inserts in described mixing chamber inner core, and for spraying into high-temperature gas to described high/low temperature gas and vapor permeation space; Described mixing chamber urceolus offers gas access, the wall of described mixing chamber inner core offers circumferentially uniform hole; In this way, cryogenic gas enters cryogenic gas via gas access and imports space, cooling performed to mixing chamber inner core and continues to enter high/low temperature gas and vapor permeation space via hole, then performing jet mixing with described high-temperature gas, and after mixing, enter described mixed gas measurement space;
The Probe arrangement of described temperature sensor in described mixed gas measurement space, and is measured for performing real time temperature to the mixed gas imported from described high/low temperature gas and vapor permeation space.
As further preferably, for described high/low temperature gas and vapor permeation space, preferably present 90 ° of angles between high-temperature gas and cryogenic gas and perform jet mixing.
As further preferably, described heat insulation packing space preferably adopts heat-barrier material to fill completely, to guarantee the heat-energy losses of mixed gas in described mixed gas measurement space.
As further preferably, the whole Closed End of described first cavity is also provided with the 3rd heat insulation loop; And described first, second, and third heat insulation loop is preferably made up of high-temperature ceramic materials.
As further preferably, the probe of described temperature sensor is 2, and they are arranged vertically in described mixed gas measurement space up and down symmetrically.
As further preferably, described heat-source spraying gun is preferably high-temperature plasma body heat source, and can be connected with high frequency controller and perform adjustment to its power; Described cryogenic gas is provided by low temperature source of the gas, and serving volume valve can be equipped with to control its flow velocity.
As further preferably, for above-mentioned double-layer cavity structure, do not exist between its internal layer cavity with outer cavity and directly contact.
In general, the above technical scheme conceived by the utility model compared with prior art, mainly possesses following technological merit:
1, by its key component as the concrete structure of mixing chamber urceolus, mixing chamber inner core, measuring chamber urceolus and measuring chamber inner core etc. and be interconnected mode design, without directly contact between the double-layer cavity structure inside and outside sleeve formed, adopt heat insulation loop to carry out supporting and thermal insulation simultaneously, effectively prevent hot loss of energy, ensure that the high precision of measurement result;
2, by adopting above-mentioned double-layer cavity structure and coordinating the mode of the direct jet mixing of high/low temperature gas, substantially increase the speed of gas and vapor permeation, but also can by controlling the power of high temperature heat source and the flow of cryogenic gas and flow velocity, correspondingly to reach fast, accurately control export the object of gas temperature, and whole dynamic characteristic of the course is excellent;
3, owing to adopting plasma high temperature heat source, thermal source gas flow temperature is high, speed fast, concentration of energy, heat distributes very fast to external world, and this high-temperature gas combines with above double-layer cavity structure and jet mixing mode, can obtain the servo-actuated temperature simulation system of high precision and response fast further;
4, according to gas mixer compact overall structure of the present utility model, be convenient to manipulation and also be easy to disassemble and later maintenance, actual test shows to avoid heat transfer and thermal loss well, especially corresponding and position control precision high is fast possessed for dynamic gas and vapor permeation simulation, be thus particularly useful for the application scenario of high-altitude flight atmospheric temperature simulated experiment.
Accompanying drawing explanation
Fig. 1 is the agent structure schematic diagram according to the high/low temperature gas mixer constructed by the utility model preferred embodiment;
In all of the figs, identical Reference numeral is used for representing identical element or structure, wherein:
1-heat-source spraying gun, 2-flange, 3-mixing chamber urceolus, 4-cryogenic gas entrance, 5-measuring chamber urceolus, 6-heat-barrier material, 7-measuring chamber inner core, 8-mixing chamber inner core, 9-12 is temperature-resistance thermal-insulation pottery, the probe of 13-temperature sensor, and A-cryogenic gas imports space, B-high/low temperature gas and vapor permeation space, C-mixed gas measurement space
Embodiment
In order to make the purpose of this utility model, technical scheme and advantage clearly understand, below in conjunction with drawings and Examples, the utility model is further elaborated.Should be appreciated that specific embodiment described herein only in order to explain the utility model, and be not used in restriction the utility model.In addition, if below in described each embodiment of the utility model involved technical characteristic do not form conflict each other and just can mutually combine.
Fig. 1 is the agent structure schematic diagram according to the high/low temperature gas mixer constructed by the utility model preferred embodiment.As shown in fig. 1, this mixing arrangement mainly comprises the assemblies such as mixing chamber urceolus 3, measuring chamber urceolus 5, mixing chamber inner core 8, measuring chamber inner core 7, heat-source spraying gun 1 and temperature sensor 13.
Specifically, mixing chamber urceolus 3, measuring chamber urceolus 5, mixing chamber inner core 8 and measuring chamber inner core 7 are cylinder type hollow tube-in-tube structure, wherein installed by flange coaxial between mixing chamber urceolus 3 and measuring chamber urceolus 5 that jointly to form the first cavity be also outer cavity, between mixing chamber inner core 8 and measuring chamber inner core 7, threadedly coaxial common formation the second cavity of installing also is internal layer cavity, and the second cavity is distributed in its center of inside along the whole length direction of the first cavity, forms double-layer cavity structure thus, in addition, same intracardiac at this double-layer cavity structure, urceolus junction, also be between the mixing chamber urceolus 3 of outer cavity and measuring chamber urceolus 5, the heat insulation loop be for example made up of refractory ceramics is all vertically provided with between the mixing chamber inner core 8 of internal layer cavity and measuring chamber inner core 7, this first heat insulation loop 10 and the second heat insulation loop 11 make, between inside and outside sleeve, direct contact does not occur, and double-layer cavity structure is divided into four spaces further, namely the cryogenic gas be on the left of outer cavity imports space A, be in the high/low temperature gas and vapor permeation space B on the left of internal layer cavity, be in the mixed gas measurement space C on the right side of internal layer cavity, and the heat insulation packing space be on the right side of outer cavity, in this way, be actually and constitute mixing chamber by two concentric cylinders, wherein inner chamber is the high-temperature gas of flowing, and exocoel is the cryogenic gas of flowing, and the cryogenic gas of exocoel enters inner chamber by the perforate on inner core and carries out mixed process, equally, constitute measuring chamber by two concentric cylinders, wherein inner chamber is the temperature flowing gas after mixing, and exocoel is the heat-barrier material of filling.
Be Closed End in the side (be shown as in figure left side) of the first cavity, it is positioned by joint flange 2, then adopts the 3rd heat insulation loop 9 that for example refractory ceramics is made to fit within it; In addition, other side (being shown as right side in the figure) hatch frame ringwise of the first cavity, and the inner side of this annular opening is provided with the heat insulation loop made with for example refractory ceramics equally, not only guarantee that inside and outside sleeve direct contact does not occur in any position yet in its interior volume further in endface position thus.
Heat-source spraying gun 1 is connected with joint flange 2 by screw thread, and it runs through this Closed End and inserts in mixing chamber inner core 8, and for spraying into high-temperature gas to high/low temperature gas and vapor permeation space B; Mixing chamber urceolus 3 offers gas access 4, the wall of mixing chamber inner core 8 then offers circumferentially uniform large number of orifices; In this way, cryogenic gas enters cryogenic gas via gas access 4 and imports space A, cooling performed to mixing chamber inner core 8 and continues to enter high/low temperature gas and vapor permeation space B via hole, then performing jet mixing with high-temperature gas, and after mixing, enter mixed gas measurement space C.
To specifically describe below according to principle of work of the present utility model.
The high temperature gas flow that high-temperature plasma generator produces enters mixing chamber inner core 8 by heat-source spraying gun 1, low temperature source gas enters mixing chamber urceolus 3 through low-temperature inlet 4, cryogenic gas has cooling effect at the internal tube wall surface of the flowing of mixing chamber exocoel, is then preferably that 90 ° of angles carry out jet mixing with high temperature gas flow by the aperture of the circumference uniform distribution of mixing chamber inner core 8 wall.Gas mixes laggard measuring chamber at mixing chamber, and measuring chamber inner core 7 has vertically arranged temperature sensor probe 13 to carry out temperature survey.Fill with heat-barrier material 6 between measuring chamber inner core 7 and measuring chamber urceolus 5, and support by heat insulation loop 9,10,11.
In addition, described high-temperature plasma thermal source comprises plasma direct-current power supply, high frequency controller, cooling circulation water tank and high-temperature plasma jetting gun.Described cryogenic gas is connected with cryogenic gas source via pipeline, and is equipped with serving volume valve.Like this, quick adjustment can be carried out to the power of high temperature heat source by high frequency controller, by serving volume valve, cryogenic gas flow be controlled, the corresponding object reaching accurately control output gas temperature fast.
To sum up, in the utility model, by taking high-temperature plasma as thermal source, utilizing double-layer cavity structure, high and low temperature gas rapid mixing can be reached, avoid the high-temperature gas of flowing in chamber by wall thermal loss to external world simultaneously.This device compact overall structure, be convenient to manipulation and also be easy to disassemble and later maintenance, actual test shows to avoid heat transfer and thermal loss well, especially corresponding and position control precision high is fast possessed for dynamic gas and vapor permeation simulation, be thus particularly useful for the application scenario of high-altitude flight atmospheric temperature simulated experiment.
Those skilled in the art will readily understand; the foregoing is only preferred embodiment of the present utility model; not in order to limit the utility model; all do within spirit of the present utility model and principle any amendment, equivalent to replace and improvement etc., all should be included within protection domain of the present utility model.
Claims (6)
1. the gas mixer for the simulated experiment of high-altitude flight atmospheric temperature, it is characterized in that, this gas mixer comprises mixing chamber urceolus (3), measuring chamber urceolus (5), mixing chamber inner core (8), measuring chamber inner core (7), heat-source spraying gun (1) and temperature sensor (13), wherein:
Described mixing chamber urceolus (3), measuring chamber urceolus (5), mixing chamber inner core (8) and measuring chamber inner core (7) are cylinder type hollow tube-in-tube structure, wherein installed by flange coaxial between mixing chamber urceolus (3) and measuring chamber urceolus (5) and jointly form the first cavity, between mixing chamber inner core (8) and measuring chamber inner core (7), threadedly coaxial installation forms the second cavity jointly, and the second cavity is distributed in its center of inside along the whole length direction of the first cavity, forms double-layer cavity structure thus; In addition, in the inside and outside cylinder junction of this double-layer cavity structure, correspondence is provided with the first heat insulation loop (10) and the second heat insulation loop (11) respectively, double-layer cavity structure is divided into four spaces further thus, namely be in cryogenic gas on the left of outer cavity to import space (A), be in high/low temperature gas and vapor permeation space (B) on the left of internal layer cavity, be in mixed gas measurement space (C) on the right side of internal layer cavity, and be in the heat insulation packing space on the right side of outer cavity;
The side of described first cavity is Closed End, and described heat-source spraying gun (1) runs through this Closed End and inserts in described mixing chamber inner core (8), and for spraying into high-temperature gas to described high/low temperature gas and vapor permeation space (B); Described mixing chamber urceolus (3) offers gas access (4), the wall of described mixing chamber inner core (8) offers circumferentially uniform hole; In this way, cryogenic gas enters cryogenic gas via gas access (4) and imports space (A), cooling is performed to mixing chamber inner core (8) and continues to enter high/low temperature gas and vapor permeation space (B) via hole, then perform jet mixing with described high-temperature gas, and after mixing, enter described mixed gas measurement space (C);
The probe (13) of described temperature sensor is arranged in described mixed gas measurement space (C), and measures for performing real time temperature to the mixed gas imported from described high/low temperature gas and vapor permeation space (B).
2. gas mixer as claimed in claim 1, is characterized in that, for described high/low temperature gas and vapor permeation space (B), presents 90 ° of angles and perform jet mixing between high-temperature gas and cryogenic gas.
3. gas mixer as claimed in claim 1 or 2, is characterized in that, described heat insulation packing space adopts heat-barrier material (6) to fill completely.
4. gas mixer as claimed in claim 3, is characterized in that, the whole Closed End of described first cavity is also provided with the 3rd heat insulation loop (9).
5. gas mixer as claimed in claim 4, it is characterized in that, the probe (13) of described temperature sensor is 2, and they are arranged vertically in described mixed gas measurement space (C) up and down symmetrically.
6. gas mixer as claimed in claim 1 or 2, it is characterized in that, described heat-source spraying gun (1) is high-temperature plasma body heat source.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520017073.1U CN204346806U (en) | 2015-01-12 | 2015-01-12 | For the gas mixer of high-altitude flight atmospheric temperature simulated experiment |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201520017073.1U CN204346806U (en) | 2015-01-12 | 2015-01-12 | For the gas mixer of high-altitude flight atmospheric temperature simulated experiment |
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| CN204346806U true CN204346806U (en) | 2015-05-20 |
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| CN201520017073.1U Expired - Fee Related CN204346806U (en) | 2015-01-12 | 2015-01-12 | For the gas mixer of high-altitude flight atmospheric temperature simulated experiment |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104689734A (en) * | 2015-01-12 | 2015-06-10 | 华中科技大学 | Gas mixing device for atmospheric environment temperature simulation experiment in high-altitude flight |
| CN106679924A (en) * | 2017-02-24 | 2017-05-17 | 中国航天空气动力技术研究院 | High frequency induction plasma heating wind tunnel |
| CN110057591A (en) * | 2019-04-15 | 2019-07-26 | 中国航发湖南动力机械研究所 | Turboaxle motor air inlet heating system |
| RU2767554C2 (en) * | 2020-08-25 | 2022-03-17 | Российская Федерация, от имени которой выступает Министерство промышленности и торговли Российской Федерации (Минпромторг России) | Gas dynamic testing unit |
-
2015
- 2015-01-12 CN CN201520017073.1U patent/CN204346806U/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104689734A (en) * | 2015-01-12 | 2015-06-10 | 华中科技大学 | Gas mixing device for atmospheric environment temperature simulation experiment in high-altitude flight |
| CN104689734B (en) * | 2015-01-12 | 2016-08-24 | 华中科技大学 | Gas mixer for high-altitude flight atmospheric temperature simulation experiment |
| CN106679924A (en) * | 2017-02-24 | 2017-05-17 | 中国航天空气动力技术研究院 | High frequency induction plasma heating wind tunnel |
| CN106679924B (en) * | 2017-02-24 | 2019-08-09 | 中国航天空气动力技术研究院 | A kind of high-frequency induction heating plasma wind-tunnel |
| CN110057591A (en) * | 2019-04-15 | 2019-07-26 | 中国航发湖南动力机械研究所 | Turboaxle motor air inlet heating system |
| RU2767554C2 (en) * | 2020-08-25 | 2022-03-17 | Российская Федерация, от имени которой выступает Министерство промышленности и торговли Российской Федерации (Минпромторг России) | Gas dynamic testing unit |
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| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150520 Termination date: 20190112 |