CN103630325A - Thermal deformation compensation device for high-temperature thermal-structure wind tunnel - Google Patents
Thermal deformation compensation device for high-temperature thermal-structure wind tunnel Download PDFInfo
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- CN103630325A CN103630325A CN201310682462.1A CN201310682462A CN103630325A CN 103630325 A CN103630325 A CN 103630325A CN 201310682462 A CN201310682462 A CN 201310682462A CN 103630325 A CN103630325 A CN 103630325A
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- thermal deformation
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Abstract
The invention provides a thermal deformation compensation device for a high-temperature thermal-structure wind tunnel. The thermal deformation compensation device comprises a wind tunnel diffusion section, a test section and a corrugated pipe, wherein the wind tunnel diffusion section stretches into the test section, the corrugated pipe is sleeved on the outer side of the wind tunnel diffusion section, one end of the corrugated pipe is connected to the outer side of the wind tunnel diffusion section, and the other end of the corrugated pipe is connected to one end part of the test section. According to the thermal deformation compensation device, the large-size corrugated pipe is mounted between the test section and the diffusion section of the high-temperature wind tunnel, and the size of the corrugated pipe is larger than that of the diffusion section, so that the axial displacement generated in the operation process of the wind tunnel is transferred to the corrugated pipe, and the axial thermal deformation of the whole wind tunnel is compensated by virtue of the elastic deformation capacity of the corrugated pipe.
Description
Technical field
The present invention relates to for aerospace large-scale ground high-temperature tunnel testing equipment, particularly a kind of high temperature heat structure wind-tunnel thermal deformation compensating device.
Background technology
Large scale high temperature heat structure wind-tunnel is the ground simulation test equipment for the examination of Aero-Space high-speed aircraft heat structure, high-speed aircraft is due to shock wave heating and air-flow and aircraft surface rubbing action, kinetic transformation is heat energy and aircraft is produced to Aerodynamic Heating phenomenon, serious Aerodynamic Heating even can cause burning and disintegrating of aircraft, so the thermal protection struc ture of aircraft designs and examination is the gordian technique of high-speed aircraft design.
Large scale high temperature heat structure wind-tunnel is according to the different minute arc-heated wind tunnels of type of heating and gas heating wind-tunnel etc., and its heating-up temperature is from several thousand degree to degree up to ten thousand.No matter adopt which kind of type of heating, effect due to high temperature gas flow, the temperature of wind tunnel body can significantly rise, the wind-tunnel deflection causing due to thermal expansion axially can reach tens millimeters, if do not carried out the safe operation of effective compensation meeting serious threat wind-tunnel, cause catastrophic consequence, therefore compensation system is one of gordian technique of large scale high temperature heat structure wind-tunnel design reliably.
Summary of the invention
The object of the present invention is to provide a kind of high temperature heat structure wind-tunnel thermal deformation compensating device, with solve wind-tunnel in when operation because the high temperature gas flow larger axis that heating causes to hole body is to bit shift compensation problem, guarantee wind-tunnel safe operation.
To achieve these goals, the invention provides a kind of high temperature heat structure wind-tunnel thermal deformation compensating device, its technical scheme is as follows:
A kind of high temperature heat structure wind-tunnel thermal deformation compensating device, comprise wind-tunnel diffuser and test section, it is inner that described wind-tunnel diffuser stretches into described test section, wherein, also comprise: corrugated tube, be sheathed on described wind-tunnel diffuser outside, one end is connected in described wind-tunnel diffuser outside, and the other end is connected in described test section end.
In a kind of preferred implementation of above-mentioned high temperature heat structure wind-tunnel thermal deformation compensating device, the bore of described corrugated tube is 1.5～2 times of described wind-tunnel diffuser bore.
In a kind of preferred implementation of above-mentioned high temperature heat structure wind-tunnel thermal deformation compensating device, one end of described corrugated tube is connected in described wind-tunnel diffuser outside by flange, and the other end of described corrugated tube is also connected in described test section end by flange.
In a kind of preferred implementation of above-mentioned high temperature heat structure wind-tunnel thermal deformation compensating device, the other end of described corrugated tube is connected in the edge of opening of described test section end.
The present invention by installing large scale corrugated tube between high-temperature tunnel test section and diffuser, corrugated tube size is greater than diffuser, the axial displacement producing in the time of can making wind tunnel operation is delivered on corrugated tube by diffuser, utilizes the elastic deformability of corrugated tube to compensate the Axial Thermal distortion of whole wind-tunnel.
Accompanying drawing explanation
Fig. 1 is the axial sectional structure schematic diagram of the embodiment of the present invention.
Embodiment
Below in conjunction with the drawings and specific embodiments, the present invention is described in further details.
As shown in Figure 1, the embodiment of the present invention mainly comprises wind-tunnel diffuser 1, test section 2 and corrugated tube 3.Wind-tunnel diffuser 1 stretches into the inside of test section 2 by open-ended 20 of test section 2.Corrugated tube 3 is sheathed on wind-tunnel diffuser 1 outside, and one end is connected in wind-tunnel diffuser 1 outside, and the other end is connected in test section 2 ends.
For fear of high temperature gas flow, corrugated tube 3 is caused to damage, except corrugated tube 3 being set in to wind-tunnel diffuser 1 outside, the present embodiment is also set with suitable distance between corrugated tube 3 and wind-tunnel diffuser 1, and preferably, the bore of corrugated tube 3 is 1.5～2 times of bore of wind-tunnel diffuser 1.
For the connection corrugated tube 3 of simple, stable, sealing and wind-tunnel diffuser 1, test section 2, one end of the corrugated tube 3 of the present embodiment is connected in wind-tunnel diffuser 1 outside by flange, and the other end is also connected in open-ended 20 edge of test section 2 by flange.For example, in the outside of wind-tunnel diffuser 1, be provided with vertical ring flange 11, the end of corrugated tube 3 is connected with ring flange 31, between ring flange 11, ring flange 31, by bolt 4 and nut (unmarked), locks.
When application, the wind-tunnel axial displacement that high temperature causes is passed to corrugated tube 3 by wind-tunnel diffuser 1, and corrugated tube 3 stretches, and with the Axial Thermal distortion to whole wind-tunnel, compensates.
To sum up, the present invention by installing large scale corrugated tube between high-temperature tunnel test section and diffuser, the axial displacement producing in the time of can making wind tunnel operation is delivered on corrugated tube by diffuser, utilizes the elastic deformability of corrugated tube to compensate the Axial Thermal distortion of whole wind-tunnel.
Compare with wind-tunnel global displacement scheme, the present invention adopts corrugated tube can meet the more compensation of big displacement quantity, also can avoid the long-term use of wind-tunnel due to the lubricated bad potential safety hazard causing of gearshift.
Compare with sleeve sealing circle scheme, the present invention adopts corrugated tube can avoid large-size axis parts covering device machining precision and a sealing difficult problem, also can avoid the long-term gas leak phenomenon that lost efficacy and cause due to O-ring seal that uses of wind-tunnel.
As known by the technical knowledge, the present invention can realize by other the embodiment that does not depart from its Spirit Essence or essential feature.Therefore, above-mentioned disclosed embodiment, with regard to each side, all just illustrates, and is not only.Change within the scope of the present invention all or within being equal to scope of the present invention is all included in the invention.
Claims (4)
1. a high temperature heat structure wind-tunnel thermal deformation compensating device, comprises wind-tunnel diffuser and test section, and it is inner that described wind-tunnel diffuser stretches into described test section, it is characterized in that, also comprises:
Corrugated tube, is sheathed on described wind-tunnel diffuser outside, and one end is connected in described wind-tunnel diffuser outside, and the other end is connected in described test section end.
2. high temperature heat structure wind-tunnel thermal deformation compensating device according to claim 1, is characterized in that, the bore of described corrugated tube is 1.5～2 times of described wind-tunnel diffuser bore.
3. high temperature heat structure wind-tunnel thermal deformation compensating device according to claim 1, it is characterized in that, one end of described corrugated tube is connected in described wind-tunnel diffuser outside by flange, and the other end of described corrugated tube is also connected in described test section end by flange.
4. high temperature heat structure wind-tunnel thermal deformation compensating device according to claim 1, is characterized in that, the other end of described corrugated tube is connected in the edge of opening of described test section end.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310682462.1A CN103630325A (en) | 2013-12-12 | 2013-12-12 | Thermal deformation compensation device for high-temperature thermal-structure wind tunnel |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310682462.1A CN103630325A (en) | 2013-12-12 | 2013-12-12 | Thermal deformation compensation device for high-temperature thermal-structure wind tunnel |
Publications (1)
| Publication Number | Publication Date |
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| CN103630325A true CN103630325A (en) | 2014-03-12 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
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| CN201310682462.1A Pending CN103630325A (en) | 2013-12-12 | 2013-12-12 | Thermal deformation compensation device for high-temperature thermal-structure wind tunnel |
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| CN (1) | CN103630325A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104458189A (en) * | 2014-10-17 | 2015-03-25 | 北京航天益森风洞工程技术有限公司 | Process layout method for conventional hypersonic speed wind tunnel |
| CN106802225A (en) * | 2016-12-31 | 2017-06-06 | 中国工程物理研究院激光聚变研究中心 | The six degree of freedom non-decoupling mechanism end position and attitude error penalty method in time varying temperature |
| CN111272291A (en) * | 2020-03-19 | 2020-06-12 | 中国科学院长春光学精密机械与物理研究所 | Large-stroke opening and closing device for low-temperature vacuum environment |
| CN113074174A (en) * | 2021-04-21 | 2021-07-06 | 中国科学院力学研究所 | Shock tunnel test cabin and corrugated pipe connecting method |
| CN113758672A (en) * | 2021-08-26 | 2021-12-07 | 中国航天空气动力技术研究院 | High-efficient water-cooling diffuser of electric arc wind-tunnel |
| CN114942117A (en) * | 2022-07-25 | 2022-08-26 | 沈阳鼓风机集团股份有限公司 | Wind tunnel displacement compensation device |
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| GB769373A (en) * | 1954-04-27 | 1957-03-06 | Snecma | Improvements in or relating to high-speed wind tunnels |
| CN101832443A (en) * | 2010-06-01 | 2010-09-15 | 陈墅庚 | Compound compensator for high pressure pipeline |
| CN102252818A (en) * | 2011-06-23 | 2011-11-23 | 中国人民解放军国防科学技术大学 | Supersonic wind tunnel with variable quality of flow field |
| CN102359683A (en) * | 2011-10-12 | 2012-02-22 | 陈墅庚 | Plunger-type double-safety pipeline compensator |
| CN202598914U (en) * | 2011-12-26 | 2012-12-12 | 陕西长岭电子科技有限责任公司 | Double corrugated pipe solar energy metal direct connection vacuum heat-collection pipe |
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| GB769373A (en) * | 1954-04-27 | 1957-03-06 | Snecma | Improvements in or relating to high-speed wind tunnels |
| CN101832443A (en) * | 2010-06-01 | 2010-09-15 | 陈墅庚 | Compound compensator for high pressure pipeline |
| CN102252818A (en) * | 2011-06-23 | 2011-11-23 | 中国人民解放军国防科学技术大学 | Supersonic wind tunnel with variable quality of flow field |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104458189A (en) * | 2014-10-17 | 2015-03-25 | 北京航天益森风洞工程技术有限公司 | Process layout method for conventional hypersonic speed wind tunnel |
| CN104458189B (en) * | 2014-10-17 | 2017-05-17 | 北京航天益森风洞工程技术有限公司 | Process layout method for conventional hypersonic speed wind tunnel |
| CN106802225A (en) * | 2016-12-31 | 2017-06-06 | 中国工程物理研究院激光聚变研究中心 | The six degree of freedom non-decoupling mechanism end position and attitude error penalty method in time varying temperature |
| CN111272291A (en) * | 2020-03-19 | 2020-06-12 | 中国科学院长春光学精密机械与物理研究所 | Large-stroke opening and closing device for low-temperature vacuum environment |
| CN111272291B (en) * | 2020-03-19 | 2021-10-08 | 中国科学院长春光学精密机械与物理研究所 | Large-stroke opening and closing device for low-temperature vacuum environment |
| CN113074174A (en) * | 2021-04-21 | 2021-07-06 | 中国科学院力学研究所 | Shock tunnel test cabin and corrugated pipe connecting method |
| CN113758672A (en) * | 2021-08-26 | 2021-12-07 | 中国航天空气动力技术研究院 | High-efficient water-cooling diffuser of electric arc wind-tunnel |
| CN113758672B (en) * | 2021-08-26 | 2024-03-26 | 中国航天空气动力技术研究院 | High-efficient water-cooling diffuser of electric arc wind tunnel |
| CN114942117A (en) * | 2022-07-25 | 2022-08-26 | 沈阳鼓风机集团股份有限公司 | Wind tunnel displacement compensation device |
| CN114942117B (en) * | 2022-07-25 | 2022-10-21 | 沈阳鼓风机集团股份有限公司 | Wind tunnel displacement compensation device |
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Application publication date: 20140312 |