CN115837292B - 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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- CN115837292B CN115837292B CN202310173140.8A CN202310173140A CN115837292B CN 115837292 B CN115837292 B CN 115837292B CN 202310173140 A CN202310173140 A CN 202310173140A CN 115837292 B CN115837292 B CN 115837292B
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
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- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
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Abstract
A hypersonic wind tunnel high-flow high-temperature heating system belongs to the technical field of wind tunnel test equipment. The invention aims to realize that the hypersonic wind tunnel heats the gas in the test process so as to meet the temperature increasing requirements of different Mach numbers. The invention 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 preservation layers are installed on the inner walls of the first heating section and the second heating section and are tightly pressed through lining plates, particularly the heat preservation layers are tightly pressed and installed on the inner walls of the first heating section and the second heating section through lining plates, a plurality of heat accumulators are respectively arranged in the first heating section and the second heating section, the heat accumulators are of honeycomb structures, and a plurality of electric heating pipes are uniformly distributed in the heat accumulators. The invention can meet the operation and use requirements of long-time high-temperature clean airflow of the wind tunnel.
Description
Technical Field
The invention relates to a hypersonic wind tunnel high-flow high-temperature heating system, and belongs to the technical field of wind tunnel test equipment.
Background
Hypersonic wind tunnels generally require heating of test gases, which mainly serve two purposes depending on the type of tunnel: firstly, prevent the air condensation, in conventional hypersonic wind tunnel, the air is in the expansion of spray tube acceleration, and air current temperature drops rapidly, and the static temperature is extremely low in the test section, and at this moment not only vapor and carbon dioxide can take place to condense, and the air composition can take place to condense by oneself, and this is not allowed in wind tunnel test. In order to delay or eliminate condensation, the temperature of test air needs to be increased, so that a hypersonic wind tunnel taking air as a medium needs to be provided with a heating system, and the heating requirements for different Mach numbers are different, and in order to ensure that the air is not condensed, the test Mach number 8 needs to be heated to about 800K, and the Mach number 10 needs to be heated to above 1000K. Another purpose of heating the test gas is to simulate the actual total temperature conditions of the flight envelope, mainly for a long-time high Wen Gaohan wind tunnel, hypersonic flight is subjected to very severe high temperature and high pressure environment in the high-speed flight process, in order to reproduce this flight environment in the ground test to facilitate accurate assessment of the performance of the aircraft and the engine, the temperature simulation capability of the ground test is particularly important, so that the high-temperature wind tunnel needs to be provided with a heating system, at this time, the simulated temperature needs to be far higher than the temperature for preventing the air from being condensed, for example, the total temperature of the simulated flight mach number 5 reaches 1300K, and the total temperature heating temperature of the simulated mach number 8 exceeds 3000K.
According to different heating purposes, the conventional heating modes of the current hypersonic tunnel mainly comprise direct electric heating, combustion type and heat accumulating type, wherein the direct electric heating has the advantages of high efficiency, cleanliness, high controllability and the like, but is mainly used for heating with low flow and low temperature rise, and cannot meet the use of high flow and high temperature rise; the combustion type direct heating device mainly adopts the fuel such as kerosene, alcohol, liquid hydrogen and liquid oxygen or the fuel and combustion improver to burn and release heat to directly heat the air flow, has the advantages of obtaining higher temperature rise, meeting the high-temperature heating requirement of 2000K and above, and has the disadvantages that combustion products can pollute the test air flow and introduce uncertainty of test data; the heat accumulation type heater 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, heat is transferred to test gas through a high-temperature heat accumulation medium, and the heat accumulation type heater is suitable for the heating requirement of high-flow medium-low temperature rise, wherein the metal electric heat accumulation is a preferable scheme capable of meeting the use requirement of a large-caliber high-altitude tunnel with the heating requirement of about 1000K at present and considering various factors such as manufacturing cost, use energy consumption, operation duration, occupation scale, air flow cleanliness and the like.
Disclosure of Invention
The invention aims to realize that the hypersonic wind tunnel heats the gas in the test process so as to meet the temperature increasing 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 identify key or critical elements of the invention or to delineate the scope of the invention.
The technical scheme adopted by the invention for solving the technical problems is as follows:
the utility model provides a hypersonic wind tunnel high-flow high temperature heating system, includes entrance, first heating section, second heating section and export section, and entrance, 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 casing, 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 interior welt, and specifically the heat preservation compresses tightly through interior welt and installs on the inner wall of first heating section and second heating section, has arranged a plurality of heat accumulators in first heating section and the second heating section respectively, and the heat accumulator is honeycomb structure, evenly distributed installs a plurality of electric heating pipes in the heat accumulator.
Preferably: the inlet section and the outlet section are both water-cooling jacket structures. The inlet section and the outlet section have the same structure and are both water-cooling jacket structures, and the flange of the interface can be cooled by circulating cooling water, so that the flange is not over-heated in the heating process, and the temperature rise of an upstream connecting piece and a downstream connecting piece caused by heat transfer of the flange and deformation caused by high temperature 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 compresses tightly on the inner wall of first heating section and second heating section through interior welt.
The inner walls of the first heating section and the second heating section are coated with aerogel, ceramic cellucotton is distributed on the inner sides of the aerogel, and the ceramic cellucotton is tightly pressed on the inner walls of the first heating section and the second heating section through the inner lining plate. The outside of the ceramic fiber cotton is wrapped by two layers of silk screens, and the outside of the silk screens is tightly pressed by the inner lining plate.
Preferably: 14 heat accumulators are respectively arranged in the first heating section and the second heating section. And 28 heat accumulators are respectively arranged in 4 groups in the first heating section and the second heating section, and 7 heat accumulators are respectively arranged in each group.
Preferably: the heat accumulator is a circular body, a plurality of vent holes are uniformly formed in the heat accumulator, 8 double-C-shaped supporting pieces are circumferentially arranged on the heat accumulator, and the heat accumulator is welded with the inner walls of the first heating section and the second heating section through the double-C-shaped supporting pieces.
Preferably: the heat accumulator circumference processing has 8 built-in mount pads, installs T type mount pad through the sliding screw on every built-in mount pad, double C type support piece welded mounting is on T type mount pad.
Preferably: the heat accumulator is provided with cylindrical pins and strip pins, and the adjacent two heat accumulator bodies are positioned by the cylindrical pins and guided by the strip pins.
Preferably: the first heating section and the second heating section are provided with a plurality of electrodes, and the electrodes are connected with the electric heating pipes in a one-to-one correspondence manner.
The invention has the beneficial effects that: the hypersonic wind tunnel high-flow high-temperature heating system 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 an insulating 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; the inlet and the outlet adopt a water-cooling jacket structure, so that the temperature of the connecting flange is not over-temperature, and the system has the following advantages:
1. the high-temperature heating system of the invention adopts a high-temperature and high-pressure decoupling design, the outer shell of the high-temperature and high-pressure heating system bears pressure, the inner layer of the high-temperature and high-pressure heating system bears temperature, and the problems that the high-temperature and high-pressure container is not easy to design and the cost is high are solved;
2. in the high-temperature heating system, the heat accumulator adopts a porous honeycomb structure design, so that the heat accumulation is large, and the flow pressure loss is low;
3. in the high-temperature heating system, the inlet section and the outlet section adopt a water-cooling jacket design, so that the flange is prevented from high-temperature heat transfer and deformation;
4. the high-temperature heating system has the advantages of integrally 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 the inducer/exducer portion;
FIG. 4 is a schematic view of the arrangement of the insulation layer on the first heating section/the second heating section;
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 view of a heat accumulator;
FIG. 8 is a schematic view of the mounting structure of the heat reservoir within the first heating section;
in the figure, the heat-insulating material comprises a 1-inlet section, a 2-first heating section, a 3-second heating section, a 4-outlet section, a 5-heat-insulating layer, a 6-inner lining plate, a 7-heat accumulator, an 8-electric heating pipe, 9-aerogel, 10-ceramic fiber cotton, 11-vent holes, 12-double C-shaped supporting pieces, 13-built-in mounting seats, 14-sliding screws, 15-T-shaped mounting seats, 16-cylindrical pins, 17-bar pins, 18-electrodes and 19-water cooling covers.
Detailed Description
The present invention is further illustrated below in conjunction with specific embodiments, it being understood that these embodiments are meant to be illustrative of the invention only and not limiting the scope of the invention, and that modifications of the invention, which are equivalent to those skilled in the art to which the invention pertains, will fall within the scope of the invention as defined in the claims appended hereto.
The first embodiment is as follows:
referring to fig. 1-8 of the accompanying drawings, this embodiment is described, this embodiment discloses a hypersonic wind tunnel high-flow high-temperature heating system, including entrance section 1, first heating section 2, second heating section 3 and exit section 4, entrance section 1, first heating section 2, second heating section 3 and exit section 4 adopt flange mode to connect the installation in proper order, first heating section 2 and second heating section 3 are cylindrical container shell, and heat preservation 5 is installed to the inner wall of first heating section 2 and second heating section 3, and heat preservation 5 compresses tightly through interior welt 6, and specifically heat preservation 5 compresses tightly through interior welt 6 and installs on the inner wall of first heating section 2 and second heating section 3, and a plurality of heat accumulator 7 have been arranged respectively in first heating section 2 and second heating section 3, and heat accumulator 7 is honeycomb structure, installs a plurality of electric heating pipes 8 in the heat accumulator 7 evenly distributed.
In this embodiment, the inner lining 6 is used to compact the insulation layer and ensure that the insulation layer is not drawn or broken under the airflow brushing;
when the hypersonic flow field test device is used, firstly, the heat accumulator 7 of the heater is heated to a preset temperature through electric heating pipes 8 distributed and arranged on the heat accumulator 7, after a test is started, test gas enters the heater, flow equalization and impact reduction are carried out through a rectifying pore plate of the inlet section 1, the gas exchanges heat with the heat accumulator 7 fully through the air hole through flow of the heat accumulator 7, the temperature of the heat accumulator is controlled and adjusted to reach the preset test temperature through four groups of heat accumulator, and high-temperature gas enters a wind tunnel main structure and a hypersonic flow field is established through a spray pipe; after the test, the heat accumulator 7 was heated and warmed, and the next test was prepared. The system is applied to long-time pollution-free heating of the hypersonic tunnel test gas.
The second embodiment is as follows:
referring to fig. 1-8 of the accompanying drawings, the embodiment discloses a hypersonic wind tunnel high-flow high-temperature heating system, and the inlet section 1 and the outlet section 4 are both water-cooling jacket structures. The inlet section 1 and the outlet section 4 have the same structure, are both cone section structures and are both water-cooling jacket structures, and specifically are: 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, a water cooling circulation cavity is formed by the water cooling cover 19 and the outer wall of the inlet section 1, and a water inlet and a water outlet are formed in the water cooling cover 19, so that a circulating cooling water cooling interface flange can be introduced, the flange is ensured not to be overtemperature in the heating process, and the temperature rise of an upstream connecting piece and a downstream connecting piece caused by heat transfer of the flange and deformation caused by high temperature are avoided.
And a third specific embodiment:
referring to fig. 1-8 of the accompanying drawings, the embodiment discloses a hypersonic wind tunnel high-flow high-temperature heating system, the heat insulation layer 5 comprises 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 tightly pressed on the inner walls of the first heating section 2 and the second heating section 3 through the inner lining plate 6. Specifically, aerogel is coated on the inner walls of the first heating section 2 and the second heating section 3, ceramic fiber cotton is distributed on the inner sides of the aerogel, and the ceramic fiber cotton is tightly pressed on the inner walls of the first heating section 2 and the second heating section 3 through the inner lining plate 6. The outside of the ceramic fiber cotton is wrapped by two layers of silk screens, and the outside of the silk screens is tightly pressed by the inner lining plate 6. So arranged, the heat-insulating layer 5 can withstand high temperature air flow scouring not lower than 1000K to ensure that the temperature of the outer shell (the first heating section 2 and the second heating section 3) is not higher than 60 ℃.
The specific embodiment IV is as follows:
referring to fig. 1-8 of the drawings, the present embodiment discloses a hypersonic wind tunnel high-flow high-temperature heating system, and 14 heat storages 7 are respectively arranged in the first heating section 2 and the second heating section 3. Namely, 28 blocks of heat accumulator bodies 7 are arranged in groups of 4 in the first heating section 2 and the second heating section 3.
The electric heating pipes 8 are arranged in the section of the heat accumulator 7 in an upper half area and a lower half area, 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 arranged on each group of heat accumulators 7, heating power of each electric heating pipe 8 can be independently controlled, in the use process, the heat accumulator 7 is firstly heated through a resistor, when the temperature of the heat accumulator approaches to a preset temperature, PID (proportion integration differentiation) adjustment is started by electric appliance until the preset target temperature is reached, and temperature compensation can be carried out in a test gap.
Fifth embodiment:
referring to fig. 1-8 of the accompanying drawings, the embodiment discloses a hypersonic wind tunnel high-flow high-temperature heating system, the heat accumulator 7 is a round body, a plurality of ventilation holes 11 are uniformly formed in 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 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. The double-C-shaped supporting piece 12 is a supporting piece structure formed by two C-shaped supporting pieces in parallel, the structure not only can realize the installation of the heat accumulator 7 in the first heating section 2 and the second heating section 3, but also has the advantage of high structural strength, can effectively improve the structural strength of the heat accumulator 7 installed in the first heating section 2 and the second heating section 3, avoids the heat accumulator 7 expanding in the first heating section 2 and the second heating section 3 due to the impact of gas heat flow in the heating process of test gas, and indirectly improves the operation stability of the whole high-temperature heating system.
Further, 8 built-in mounting seats 13 are circumferentially machined on the heat accumulator 7, T-shaped mounting seats 15 are mounted on each built-in mounting seat 13 through sliding screws 14, and the double-C-shaped supporting piece 12 is mounted on the T-shaped mounting seats 15 in a welding mode. So set up, heat accumulator 7 adopts 316L stainless steel, and its circumference processing has the recess, and then forms 8 built-in mount pad 13 in the circumference of heat accumulator 7, and double C type support piece 12 welds has T type mount pad 15, and T type mount pad 15 screws through sliding screw 14 and installs on built-in mount pad 13, compares with "heat accumulator 7 and double C type support piece 12 adoption integrated into one piece technology", this kind of structure simple to operate, and low in manufacturing cost.
Further, the cylindrical pins 16 and the bar pins 17 are arranged on the heat storages 7, the adjacent two heat storages 7 are positioned by adopting the cylindrical pins 16, and the heat storages 7 can be limited in the thermal expansion direction by adopting the bar pins 17 through the cylindrical pins 16 and the bar pins 17.
Further, a plurality of electrodes 18 are arranged 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.
The embodiments of the present invention have been described above with reference to the accompanying drawings, but the present invention is not limited to the above-described embodiments, which are merely illustrative and not restrictive, and many forms may be made by those having ordinary skill in the art without departing from the spirit of the present invention and the scope of the claims, which are to be protected by the present invention.
Claims (6)
1. The utility model provides a hypersonic wind tunnel high-flow high temperature heating system, includes entrance (1), first heating section (2), second heating section (3) and export section (4), entrance (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: the first heating section (2) and the second heating section (3) are cylindrical container shells, an insulating layer (5) is arranged on the inner walls of the first heating section (2) and the second heating section (3), the insulating layer (5) is tightly pressed by an inner lining plate (6), a plurality of heat storages (7) are respectively arranged in the first heating section (2) and the second heating section (3), the heat storages (7) are of honeycomb structures, and a plurality of electric heating pipes (8) are uniformly distributed in the heat storages (7);
the heat accumulator (7) is a circular body, a plurality of vent holes (11) are uniformly formed in 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 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) respectively;
the double C-shaped supporting piece (12) is a supporting piece structure formed by two C-shaped supporting pieces in parallel;
the heat accumulator (7) is made of 316L stainless steel, grooves are formed in the circumferential direction of the heat accumulator, 8 built-in mounting seats (13) are formed in the circumferential direction of the heat accumulator (7), T-shaped mounting seats (15) are mounted on each built-in mounting seat (13) through sliding screws (14), and double-C-shaped supporting pieces (12) are mounted on the T-shaped mounting seats (15) in a welding mode.
2. The hypersonic wind tunnel high-flow high-temperature heating system as claimed in claim 1, wherein: the inlet section (1) and the outlet section (4) are both water-cooling jacket structures.
3. The hypersonic wind tunnel high-flow high-temperature heating system as claimed in claim 1, wherein: the heat preservation (5) include aerogel (9) and ceramic fibre cotton (10), and aerogel (9) distribute on the inner wall of first heating section (2) and second heating section (3), and ceramic fibre cotton (10) are distributed to aerogel (9) inboard, and ceramic fibre cotton (10) compress tightly on the inner wall of first heating section (2) and second heating section (3) through interior welt (6).
4. The hypersonic wind tunnel high-flow high-temperature heating system as claimed in claim 1, wherein: 14 heat accumulators (7) are respectively arranged in the first heating section (2) and the second heating section (3).
5. The hypersonic wind tunnel high-flow high-temperature heating system as claimed in claim 1, wherein: the heat accumulator bodies (7) are provided with cylindrical pins (16) and strip-shaped pins (17), the adjacent two heat accumulator bodies (7) are positioned by the cylindrical pins (16), and the heat accumulator bodies are guided by the strip-shaped pins (17).
6. The hypersonic wind tunnel high-flow high-temperature heating system as claimed in claim 1, wherein: 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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| CN202310173140.8A CN115837292B (en) | 2023-02-28 | 2023-02-28 | High-flow high-temperature heating system of hypersonic wind tunnel |
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| CN202310173140.8A CN115837292B (en) | 2023-02-28 | 2023-02-28 | High-flow high-temperature heating system of hypersonic wind tunnel |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| 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 |
| 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 |
| 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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| CN115837292A (en) | 2023-03-24 |
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