CN115837292A - High-flow high-temperature heating system of hypersonic wind tunnel - Google Patents
High-flow high-temperature heating system of hypersonic wind tunnel Download PDFInfo
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- CN115837292A CN115837292A CN202310173140.8A CN202310173140A CN115837292A CN 115837292 A CN115837292 A CN 115837292A CN 202310173140 A CN202310173140 A CN 202310173140A CN 115837292 A CN115837292 A CN 115837292A
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Abstract
A high-flow high-temperature heating system of a hypersonic wind tunnel belongs to the technical field of wind tunnel test equipment. The invention aims to realize that the hypersonic wind tunnel heats gas in the test process so as to meet the temperature increase requirements of different Mach numbers. The heat storage device comprises an inlet section, a first heating section, a second heating section and an outlet section, wherein the inlet section, the first heating section, the second heating section and the outlet section are sequentially connected and installed in a flange mode, the first heating section and the second heating section are cylindrical container shells, heat insulation layers are installed on the inner walls of the first heating section and the second heating section and are tightly pressed through lining plates, specifically, the heat insulation layers are tightly installed on the inner walls of the first heating section and the second heating section through the lining plates, a plurality of heat storage bodies are respectively arranged in the first heating section and the second heating section, the heat storage bodies are of honeycomb structures, and a plurality of electric heating pipes are uniformly distributed and installed in the heat storage bodies. The invention can meet the operation and use requirements of the wind tunnel on long-time high-temperature clean airflow.
Description
Technical Field
The invention relates to a high-flow high-temperature heating system of a hypersonic wind tunnel, belonging to the technical field of wind tunnel test equipment.
Background
Hypersonic wind tunnels generally need to heat test gases, and heating gases according to different wind tunnel types mainly has two purposes: firstly, prevent the air condensation, in conventional hypersonic wind tunnel, the air is at the accelerating expansion of spray tube, and airflow temperature descends rapidly, and the quiet temperature is extremely low in experimental section, at this moment not only vapor and carbon dioxide can take place to condense, and air component itself also can take place to condense, and this is that the wind tunnel test does not allow. In order to delay or eliminate condensation, the temperature of test air needs to be increased, so a hypersonic wind tunnel taking air as a medium needs to be provided with a heating system, the temperature increase requirements for different Mach numbers are different, the test Mach number is about 800K when the air is tested to ensure that the air is not condensed, and the test Mach number is about 1000K when the air is tested to ensure that the air is not condensed. The other purpose of heating the test gas is to simulate the actual total temperature condition of a flight envelope, mainly aiming at a long-time high-temperature high-enthalpy wind tunnel, hypersonic flight bears a very severe high-temperature high-pressure environment in the high-speed flight process, and in order to reproduce the flight environment in a ground test so as to accurately evaluate the performance of an aircraft and an engine, the temperature simulation capability of a ground test is particularly important, so a heating system is required to be configured for the high-temperature wind tunnel, the temperature to be simulated at the moment is far higher than the temperature for preventing air from being uncondensed, if the total temperature of simulated flight Mach number 5 reaches 1300K, and the total temperature heating temperature of simulated Mach number 8 exceeds 3000K.
According to different heating purposes, the conventional heating modes of the super wind tunnel mainly comprise direct electric heating, combustion type and heat accumulation type, wherein the direct electric heating has the advantages of high efficiency, cleanness, high controllability and the like, but the direct electric heating is mainly used for heating with small flow and low temperature rise and cannot meet the requirement of large flow and high temperature rise; the combustion mode mainly adopts fuels such as kerosene, alcohol, liquid hydrogen, liquid oxygen and the like or fuels and combustion improver to combust and release heat to directly heat the airflow, and has the advantages that higher temperature rise can be obtained, the high-temperature heating requirement of 2000K and above is met, and the combustion mode has the defects that combustion products can pollute the test airflow and the uncertainty of test data is introduced; the heat accumulation type heating device can be divided into electric heat accumulation and combustion heat accumulation according to a heating mode, and can be divided into metal heat accumulation, pebble bed heat accumulation, molten salt heat accumulation and the like according to a heat accumulation medium, the heat accumulation type heater can complete the transfer of heat to test gas through a high-temperature heat accumulation medium, the heating device is suitable for the heating requirement of high flow rate, medium and low temperature rise, wherein the metal electric heat accumulation is the optimal scheme which meets the use requirement of a large-caliber high-super wind tunnel of about 1000K of the heating requirement at present and can take manufacturing cost, use energy consumption, long operation time, land occupation scale, air flow cleanliness and other factors into consideration.
Disclosure of Invention
The invention aims to realize that the hypersonic wind tunnel heats gas in the test process so as to meet the temperature increase requirements of different Mach numbers. The following presents a simplified summary of the invention in order to provide a basic understanding of some aspects of the invention. It should be understood that this summary is not an exhaustive overview of the invention. It is not intended to determine the key or critical elements of the present invention, nor is it intended to limit the scope of the present invention.
The technical scheme adopted by the invention for solving the technical problems is as follows:
the utility model provides a large-traffic high temperature heating system of hypersonic wind tunnel, includes inducer, first heating section, second heating section and export section, and inducer, first heating section, second heating section and export section adopt flange mode to connect the installation in proper order, first heating section and second heating section are cylindrical container shell, and the heat preservation is installed to the inner wall of first heating section and second heating section, and the heat preservation compresses tightly through the welt, specifically the heat preservation compresses tightly through the welt and installs on the inner wall of first heating section and second heating section, has arranged a plurality of heat accumulators respectively in first heating section and the second heating section, and the heat accumulator is honeycomb structure, and evenly distributed installs a plurality of electric heating pipe in the heat accumulator.
Preferably: the inlet section and the outlet section are both of water-cooling jacket structures. The inlet section and the outlet section are of the same structure and are of water-cooling jacket structures, and circulating cooling water can be introduced to cool the interface flange, so that the flange is not over-heated in the heating process, and the temperature rise of an upstream connecting piece and the temperature deformation caused by high temperature due to heat transfer of the flange are avoided.
Preferably: the heat preservation includes aerogel and ceramic fiber cotton, and the aerogel distributes on the inner wall of first heating section and second heating section, and the inboard ceramic fiber cotton that distributes of aerogel, ceramic fiber cotton compress tightly on the inner wall of first heating section and second heating section through interior welt.
The inner wall of first heating section and second heating section is coated with the aerogel, and the inboard ceramic fiber cotton that distributes of aerogel compresses tightly on the inner wall of first heating section and second heating section through interior welt. The outer side of the ceramic fiber cotton is wrapped by two layers of silk screens, and the outer side of each silk screen is tightly pressed by an inner lining plate.
Preferably, the following components: 14 heat accumulators are respectively arranged in the first heating section and the second heating section. 28 heat accumulators are arranged in 4 groups in the first heating section and the second heating section, and each group of the heat accumulators is 7.
Preferably: the heat accumulator is circular, and evenly processing has a plurality of air vents on the heat accumulator, 8 two C type support pieces are arranged to heat accumulator circumference, and the heat accumulator passes through two C type support pieces and welds with the inner wall of first heating section and second heating section respectively.
Preferably: the heat accumulator is circumferentially processed with 8 built-in mounting seats, each built-in mounting seat is provided with a T-shaped mounting seat through a sliding screw, and the double C-shaped supporting pieces are welded on the T-shaped mounting seats.
Preferably: the heat accumulators are provided with cylindrical pins and bar-shaped pins, the adjacent two heat accumulators are positioned by the cylindrical pins and guided by the bar-shaped pins.
Preferably, the following components: a plurality of electrodes are arranged on the first heating section and the second heating section, and the plurality of electrodes are connected with the plurality of electric heating pipes in a one-to-one correspondence manner.
The invention has the beneficial effects that: a high-flow high-temperature heating system of a hypersonic wind tunnel is characterized in that a first heating section main body and a second heating section main body are designed by adopting a multi-layer shell structure, an outer shell is used for bearing pressure, and a heat insulation layer and an inner lining plate are used for blocking high-temperature heat transfer; the heat accumulator adopts a porous honeycomb structure made of high-temperature steel materials, so that the requirements of high heat storage capacity and high flow through characteristic are met; import and export and adopt water-cooling jacket structure, guarantee that flange temperature is not super-warm, this system has following advantage:
1. the high-temperature heating system has the advantages that the high temperature and the high pressure are decoupled, the outer shell bears pressure, the inner layer is heat-insulating, and the inner lining plate bears temperature, so that the problems that a high-temperature and high-pressure container is not easy to design and has high cost are solved;
2. in the high-temperature heating system, the heat accumulator is designed by adopting a porous honeycomb structure, so that heat storage is large, and flowing pressure loss is low;
3. in the high-temperature heating system, the inlet section and the outlet section adopt the water-cooling jacket design, so that the high-temperature heat transfer and deformation of the flange are avoided;
4. the high-temperature heating system has an integral distributed heating design, high temperature control precision and good temperature adjustability.
Drawings
FIG. 1 is a front view of the present invention;
FIG. 2 is a cross-sectional view of the present invention;
FIG. 3 is a cross-sectional view of an inducer/exducer;
FIG. 4 is a schematic view of the arrangement of insulation on the first/second heating zones;
FIG. 5 is a perspective view of a thermal mass;
FIG. 6 is an enlarged view at A in FIG. 5;
FIG. 7 is a main body view of a heat accumulator;
FIG. 8 is a schematic view of the arrangement of the heat accumulator within the first heating section;
in the figure, 1-inlet section, 2-first heating section, 3-second heating section, 4-outlet section, 5-insulating layer, 6-lining plate, 7-heat accumulator, 8-electric heating pipe, 9-aerogel, 10-ceramic fiber cotton, 11-vent hole, 12-double C type support piece, 13-built-in mounting seat, 14-sliding screw rod, 15-T type mounting seat, 16-cylindrical pin, 17-bar pin, 18-electrode and 19-water cooling cover.
Detailed Description
The present invention is further illustrated by the following examples, which are intended to be purely exemplary and are not intended to limit the scope of the invention, as various equivalent modifications of the invention will occur to those skilled in the art upon reading the present disclosure and fall within the scope of the appended claims.
The first embodiment is as follows:
the embodiment is described by combining with accompanying drawings 1-8 of the specification, and discloses a high-flow high-temperature heating system of a hypersonic wind tunnel, which comprises an inlet section 1, a first heating section 2, a second heating section 3 and an outlet section 4, wherein the inlet section 1, the first heating section 2, the second heating section 3 and the outlet section 4 are sequentially connected and installed in a flange mode, the first heating section 2 and the second heating section 3 are cylindrical container shells, heat preservation layers 5 are installed on the inner walls of the first heating section 2 and the second heating section 3, the heat preservation layers 5 are tightly pressed through lining plates 6, specifically, the heat preservation layers 5 are tightly pressed and installed on the inner walls of the first heating section 2 and the second heating section 3 through the lining plates 6, a plurality of heat accumulators 7 are respectively arranged in the first heating section 2 and the second heating section 3, the heat accumulators 7 are of a honeycomb structure, and a plurality of electric heating pipes 8 are uniformly distributed and installed in the heat accumulators 7.
In the embodiment, the lining plate 6 is used for compacting the heat-insulating layer and ensuring that the heat-insulating layer does not have the phenomenon of wire drawing or slag falling under the air current scouring;
when the device is used, firstly, the heat accumulator 7 of the heater is heated to a preset temperature through the electric heating pipes 8 distributed and installed on the heat accumulator 7, after a test is started, after test gas enters the heater, the test gas is firstly subjected to flow equalization and impact reduction through the rectifying pore plate of the inlet section 1, the gas is subjected to through-flow of the gas holes of the heat accumulator 7 and is subjected to sufficient heat exchange with the heat accumulator 7, the test gas reaches the preset test temperature at the outlet section 4 of the heater through the temperature control adjustment of the four heat accumulators, and the high-temperature gas enters the main structure of the wind tunnel and passes through the spray pipe to establish a hypersonic flow field; after the test is finished, the heat accumulator 7 is heated and temperature-compensated for the next test. The system is applied to long-time pollution-free heating of the test gas of the hypersonic wind tunnel.
The second embodiment is as follows:
the embodiment is described by combining the attached drawings 1-8 in the specification, and discloses a high-flow high-temperature heating system of a hypersonic wind tunnel, wherein an inlet section 1 and an outlet section 4 are both of water-cooling jacket structures. The inlet section 1 and the outlet section 4 have the same structure, are both conical section structures and are both water-cooling jacket structures, and specifically comprise: taking the inlet section 1 as an example, a layer of water cooling cover 19 is welded on the outer wall of the inlet section 1, the water cooling cover 19 and the outer wall of the inlet section 1 form a water cooling circulation cavity, and the water cooling cover 19 is provided with a water inlet and a water outlet, so that circulating cooling water can be introduced to cool the interface flange, the flange is not over-temperature in the heating process, and the temperature rise of the upstream and downstream connecting pieces and the deformation caused by high temperature due to the heat transfer of the flange are avoided.
The third concrete implementation mode:
the embodiment is described with reference to fig. 1 to 8 in the specification, and discloses a high-flow high-temperature heating system for a hypersonic wind tunnel, where the heat insulation layer 5 includes aerogel 9 and ceramic fiber cotton 10, the aerogel 9 is distributed on the inner walls of the first heating section 2 and the second heating section 3, the ceramic fiber cotton 10 is distributed on the inner side of the aerogel 9, and the ceramic fiber cotton 10 is pressed against the inner walls of the first heating section 2 and the second heating section 3 through the lining plate 6. Specifically, the coating has the aerogel on the inner wall of first heating section 2 and second heating section 3, and the inboard ceramic fiber cotton that distributes of aerogel compresses tightly on the inner wall of first heating section 2 and second heating section 3 through interior welt 6. The outer side of the ceramic fiber cotton is wrapped by two layers of silk screens, and the outer side of the silk screens is tightly pressed by the lining plate 6. So set up, heat preservation 5 can tolerate not less than 1000K high temperature air current and erode and guarantee that the shell body (first heating section 2 and second heating section 3) temperature is not higher than 60 ℃.
The fourth concrete implementation mode:
the embodiment is described with reference to fig. 1 to fig. 8 in the specification, and discloses a high-flow high-temperature heating system for a hypersonic wind tunnel, wherein 14 heat accumulators 7 are respectively arranged in the first heating section 2 and the second heating section 3. Namely, 28 heat accumulators are arranged in 4 groups in the first heating section 2 and the second heating section 3, and 7 heat accumulators 7 are arranged in 7 groups.
The electric heating pipes 8 are arranged on the cross section of the heat accumulator 7 in two half-areas, 4 groups of heat accumulators 7 are arranged in the first heating section 2 and the second heating section 3 (2 groups of heat accumulators 7 are respectively arranged in the first heating section 2 and the second heating section 3), the electric heating pipes 8 are respectively installed on each group of heat accumulator 7, each electric heating pipe 8 can independently control heating power, the heat accumulator 7 is heated through a resistor firstly in the using process, when the temperature of the heat accumulator is close to a preset temperature, PID (proportion integration differentiation) regulation is started by electric control until the preset target temperature is reached, and temperature compensation can be carried out at a test interval.
The fifth concrete implementation mode is as follows:
the embodiment is described with reference to fig. 1 to 8 in the specification, and discloses a high-flow high-temperature heating system for a hypersonic wind tunnel, wherein a heat accumulator 7 is a circular body, a plurality of vent holes 11 are uniformly processed on the heat accumulator 7, 8 double C-shaped supporting pieces 12 are circumferentially arranged on the heat accumulator 7, and the heat accumulator 7 is respectively welded with the inner walls of a first heating section 2 and a second heating section 3 through the double C-shaped supporting pieces 12. Two C type support piece 12 are the support piece structure that two C type support piece formed side by side, this structure not only can realize the installation of heat accumulator 7 in first heating section 2 and second heating section 3, and has the advantage that structural strength is high, can effectively improve heat accumulator 7 installation structural strength in first heating section 2 and second heating section 3, avoid carrying out the heating process to test gas, receive gas heat flow impact and lead to the position of heat accumulator 7 inflation in first heating section 2 and second heating section 3 to take place to warp or the drunkenness, indirectly improve whole high temperature heating system's operating stability.
Furthermore, 8 built-in mounting seats 13 are machined in the circumferential direction of the heat accumulator 7, a T-shaped mounting seat 15 is mounted on each built-in mounting seat 13 through a sliding screw 14, and the double C-shaped supporting pieces 12 are welded on the T-shaped mounting seats 15. According to the arrangement, the heat accumulator 7 is made of 316L stainless steel, grooves are machined in the circumferential direction of the heat accumulator 7, 8 built-in mounting seats 13 are formed in the circumferential direction of the heat accumulator 7, the T-shaped mounting seats 15 are welded to the double C-shaped supporting pieces 12, the T-shaped mounting seats 15 are screwed and mounted on the built-in mounting seats 13 through the sliding screw rods 14, and compared with the fact that the heat accumulator 7 and the double C-shaped supporting pieces 12 are integrally formed, the structure is convenient to mount and low in manufacturing cost.
Furthermore, the heat accumulators 7 are provided with cylindrical pins 16 and strip pins 17, the adjacent two heat accumulators 7 are positioned by the cylindrical pins 16 and guided by the strip pins 17, and the heat expansion direction of the heat accumulators 7 can be limited by the cylindrical pins 16 and the strip pins 17.
Furthermore, a plurality of electrodes 18 are installed on the first heating section 2 and the second heating section 3, and the plurality of electrodes 18 are connected with the plurality of electric heating pipes 8 in a one-to-one correspondence manner.
While the present invention has been described with reference to the particular illustrative embodiments, it is to be understood that the invention is not limited to the disclosed embodiments, but is intended to cover various modifications, equivalent arrangements, and equivalents thereof, which may be made by those skilled in the art without departing from the spirit and scope of the invention as defined by the appended claims.
Claims (8)
1. The utility model provides a large-traffic high temperature heating system of hypersonic wind tunnel, includes inducer (1), first heating section (2), second heating section (3) and export section (4), and inducer (1), first heating section (2), second heating section (3) and export section (4) adopt flange mode to connect the installation in proper order, its characterized in that: first heating section (2) and second heating section (3) are cylindrical vessel shell, and heat preservation (5) are installed to the inner wall of first heating section (2) and second heating section (3), and heat preservation (5) compress tightly through interior welt (6), have arranged a plurality of heat accumulators (7) in first heating section (2) and the second heating section (3) respectively, and heat accumulator (7) are honeycomb, and evenly distributed installs a plurality of electric heating pipe (8) in heat accumulator (7).
2. The high-flow high-temperature heating system of the hypersonic wind tunnel according to claim 1, characterized in that: the inlet section (1) and the outlet section (4) are both of water-cooling jacket structures.
3. The high-flow high-temperature heating system of the hypersonic wind tunnel according to claim 1, characterized in that: heat preservation (5) include aerogel (9) and ceramic fiber cotton (10), and aerogel (9) distribute on the inner wall of first heating section (2) and second heating section (3), and aerogel (9) inboard distribution ceramic fiber cotton (10), and ceramic fiber cotton (10) compress tightly on the inner wall of first heating section (2) and second heating section (3) through interior welt (6).
4. The high-flow high-temperature heating system of the hypersonic wind tunnel according to claim 1, characterized in that: 14 heat accumulators (7) are respectively arranged in the first heating section (2) and the second heating section (3).
5. The high-flow high-temperature heating system of the hypersonic wind tunnel according to claim 1, characterized in that: the heat accumulator (7) is a round body, a plurality of vent holes (11) are uniformly processed in the heat accumulator (7), 8 double-C-shaped supporting pieces (12) are circumferentially arranged in the heat accumulator (7), and the heat accumulator (7) is welded with the inner walls of the first heating section (2) and the second heating section (3) through the double-C-shaped supporting pieces (12).
6. The high-flow high-temperature heating system of the hypersonic wind tunnel according to claim 5, characterized in that: the heat accumulator (7) is circumferentially provided with 8 built-in mounting seats (13), each built-in mounting seat (13) is provided with a T-shaped mounting seat (15) through a sliding screw (14), and the double C-shaped supporting pieces (12) are welded on the T-shaped mounting seats (15).
7. The high-flow high-temperature heating system of the hypersonic wind tunnel according to claim 1, characterized in that: the heat accumulators (7) are provided with cylindrical pins (16) and strip-shaped pins (17), and the adjacent two heat accumulators (7) are positioned by the cylindrical pins (16) and guided by the strip-shaped pins (17).
8. The high-flow high-temperature heating system of the hypersonic wind tunnel according to claim 1, characterized in that: a plurality of electrodes (18) are arranged on the first heating section (2) and the second heating section (3), and the electrodes (18) are connected with the electric heating pipes (8) in a one-to-one correspondence manner.
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116222951A (en) * | 2023-05-09 | 2023-06-06 | 中国航空工业集团公司沈阳空气动力研究所 | External heating system for high-temperature tube of tube wind tunnel |
| CN116776453A (en) * | 2023-08-25 | 2023-09-19 | 中国空气动力研究与发展中心超高速空气动力研究所 | High-temperature wind tunnel equipment body layout method |
| CN117782507A (en) * | 2024-02-23 | 2024-03-29 | 中国航空工业集团公司沈阳空气动力研究所 | Porous pressure equalizing and filament drawing preventing heat protection structure for hypersonic wind tunnel |
Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH07286936A (en) * | 1994-04-19 | 1995-10-31 | Mitsubishi Heavy Ind Ltd | Airflow heater for wind tunnel |
| JPH09324623A (en) * | 1996-06-07 | 1997-12-16 | Nippon Steel Corp | Manufacture of catalyst converter |
| DE10151494A1 (en) * | 2001-10-18 | 2003-04-30 | Emitec Emissionstechnologie | Honeycomb structure, used as carrier for exhaust gas catalyst for automobile IC engine, has open spring damper system formed by sleeve joints in mantle pipe |
| CN203177465U (en) * | 2013-01-29 | 2013-09-04 | 中国航天空气动力技术研究院 | Electric preheating high-temperature high-pressure heat storing air heating device |
| CN104019958A (en) * | 2013-08-23 | 2014-09-03 | 中国人民解放军国防科学技术大学 | Wind tunnel rectification device |
| CN206140911U (en) * | 2016-09-29 | 2017-05-03 | 天津大格科技有限公司 | Sectional type heating 3D beats printer head |
| CN107166392A (en) * | 2017-06-20 | 2017-09-15 | 马鞍山蓝信环保科技有限公司 | A kind of thermal-storage burning device utilizing radiant tube |
| CN206637838U (en) * | 2017-03-16 | 2017-11-14 | 东方电气集团东方锅炉股份有限公司 | A kind of electric-heating container for being used to obtain HTHP air |
| CN108759093A (en) * | 2018-03-08 | 2018-11-06 | 西北工业大学 | A kind of hollow brick storage heater |
| CN111412650A (en) * | 2020-04-02 | 2020-07-14 | 中国航空工业集团公司北京长城计量测试技术研究所 | Large-flow pure air heater |
| CN214052895U (en) * | 2020-12-17 | 2021-08-27 | 常州瑞玛环保科技有限公司 | Automatic cleaning device for RTO ceramic bed |
| CN113701982A (en) * | 2021-08-26 | 2021-11-26 | 中国科学院力学研究所 | Measurement and control method of heat storage heater for wind tunnel experiment |
| CN115371260A (en) * | 2022-07-22 | 2022-11-22 | 中国航天空气动力技术研究院 | Series connection partition heating high-temperature high-pressure heater |
-
2023
- 2023-02-28 CN CN202310173140.8A patent/CN115837292B/en active Active
Patent Citations (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH07286936A (en) * | 1994-04-19 | 1995-10-31 | Mitsubishi Heavy Ind Ltd | Airflow heater for wind tunnel |
| JPH09324623A (en) * | 1996-06-07 | 1997-12-16 | Nippon Steel Corp | Manufacture of catalyst converter |
| DE10151494A1 (en) * | 2001-10-18 | 2003-04-30 | Emitec Emissionstechnologie | Honeycomb structure, used as carrier for exhaust gas catalyst for automobile IC engine, has open spring damper system formed by sleeve joints in mantle pipe |
| CN203177465U (en) * | 2013-01-29 | 2013-09-04 | 中国航天空气动力技术研究院 | Electric preheating high-temperature high-pressure heat storing air heating device |
| CN104019958A (en) * | 2013-08-23 | 2014-09-03 | 中国人民解放军国防科学技术大学 | Wind tunnel rectification device |
| CN206140911U (en) * | 2016-09-29 | 2017-05-03 | 天津大格科技有限公司 | Sectional type heating 3D beats printer head |
| CN206637838U (en) * | 2017-03-16 | 2017-11-14 | 东方电气集团东方锅炉股份有限公司 | A kind of electric-heating container for being used to obtain HTHP air |
| CN107166392A (en) * | 2017-06-20 | 2017-09-15 | 马鞍山蓝信环保科技有限公司 | A kind of thermal-storage burning device utilizing radiant tube |
| CN108759093A (en) * | 2018-03-08 | 2018-11-06 | 西北工业大学 | A kind of hollow brick storage heater |
| CN111412650A (en) * | 2020-04-02 | 2020-07-14 | 中国航空工业集团公司北京长城计量测试技术研究所 | Large-flow pure air heater |
| CN214052895U (en) * | 2020-12-17 | 2021-08-27 | 常州瑞玛环保科技有限公司 | Automatic cleaning device for RTO ceramic bed |
| CN113701982A (en) * | 2021-08-26 | 2021-11-26 | 中国科学院力学研究所 | Measurement and control method of heat storage heater for wind tunnel experiment |
| CN115371260A (en) * | 2022-07-22 | 2022-11-22 | 中国航天空气动力技术研究院 | Series connection partition heating high-temperature high-pressure heater |
Non-Patent Citations (1)
| Title |
|---|
| 刘燕燕, pages: 291 * |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116222951A (en) * | 2023-05-09 | 2023-06-06 | 中国航空工业集团公司沈阳空气动力研究所 | External heating system for high-temperature tube of tube wind tunnel |
| CN116222951B (en) * | 2023-05-09 | 2023-07-04 | 中国航空工业集团公司沈阳空气动力研究所 | External heating system for high-temperature tube of tube wind tunnel |
| CN116776453A (en) * | 2023-08-25 | 2023-09-19 | 中国空气动力研究与发展中心超高速空气动力研究所 | High-temperature wind tunnel equipment body layout method |
| CN116776453B (en) * | 2023-08-25 | 2023-10-24 | 中国空气动力研究与发展中心超高速空气动力研究所 | High-temperature wind tunnel equipment body layout method |
| CN117782507A (en) * | 2024-02-23 | 2024-03-29 | 中国航空工业集团公司沈阳空气动力研究所 | Porous pressure equalizing and filament drawing preventing heat protection structure for hypersonic wind tunnel |
| CN117782507B (en) * | 2024-02-23 | 2024-05-14 | 中国航空工业集团公司沈阳空气动力研究所 | Porous pressure equalizing and filament drawing preventing heat protection structure for hypersonic wind tunnel |
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| CN115837292B (en) | 2023-06-02 |
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