CN112282972A - Low-pressure sub-super shear flow experiment system with high-temperature subsonic air - Google Patents

Abstract

Translated fromChinese

本发明公开了一种具有高温亚声速空气的低压亚‑超剪切流实验系统，包括：实验模型段，为腔体结构，其前端和后端对应开设有气体入口和混合气体出口，且侧壁上开设有高温气体入口；在腔体内，其前段为并列且独立的多通道，多通道分别为亚声速气流通道和超声速气流通道；后段为与多通道相连通的单通道。进气管，与实验模型段的气体入口相连接，用于向所述亚声速气流通道内通入空气；空气流过亚声速气流通道后，与由超声速气流通道流出的高温气体在单通道内混合剪切。加热管，同轴套设在进气管内，与进气管的内壁间形成环缝，作为空气的输入通道。同时实现了模拟低背压及高温空气射流。

The invention discloses a low-pressure sub-supershear flow experiment system with high-temperature subsonic air, comprising: an experimental model section, which is a cavity structure, and its front and rear ends are correspondingly provided with a gas inlet and a mixed gas outlet, and side A high-temperature gas inlet is opened on the wall; in the cavity, the front section is a parallel and independent multi-channel, and the multi-channels are subsonic air flow channels and supersonic air flow channels respectively; the rear section is a single channel connected with the multi-channel. The air intake pipe is connected to the gas inlet of the experimental model section, and is used to introduce air into the subsonic airflow channel; after the air flows through the subsonic airflow channel, it is mixed with the high-temperature gas flowing out from the supersonic airflow channel in a single channel. cut. The heating pipe is coaxially sleeved in the air inlet pipe, and forms a ring seam with the inner wall of the air inlet pipe as an air input channel. Simultaneously, the simulated low back pressure and high temperature air jet are realized.

Description

Low-pressure sub-super shear flow experiment system with high-temperature subsonic air

Technical Field

The invention belongs to the technical field of rocket engine experimental systems, and particularly relates to a low-pressure sub-super shear flow experimental system with high-temperature subsonic air.

Background

The research of sub-super-shear mixing flow is one of the important research fields in the study of turbulent flow, for example, the mixing of main rocket gas and incoming air in a combustion chamber of a rocket-ramjet combined engine is a typical shear mixing flow. The shear mixing flow field is a turbulent flow structure developed by shearing and mixing air flows with the same direction, one flow speed is supersonic speed, and the other flow speed is subsonic speed, and has the characteristics of strong compressibility, high temperature, high speed, large gradient and the like. As one of the classical representatives of turbulent flow fields, the turbulent flow field has the macroscopic sequence similarity and the microscopic randomness.

In recent years, the embedded rocket type ramjet has good and wide application in repeatable carrier rockets and supersonic aircrafts, has the advantages of rocket engines and ramjets, solves the problems that the ramjet cannot take off by itself and has poor high altitude performance, and has the advantages of light take-off quality and high specific impulse. The interaction of high-temperature high-speed incoming flow and low-temperature low-speed incoming flow of air in the main combustion chamber has extremely high incoming flow speed, the size of the combustion chamber is very limited, and the gas residence time is basically in the millisecond order. The mixing of the fuel gas and the air is sequentially subjected to the processes of large-scale entrainment, small-scale dissipation, molecular diffusion and the like, so that the chemical reaction can be carried out when the mixing reaches the molecular level.

However, the structure of the embedded rocket type ramjet is complex, and the establishment of a complete embedded rocket type ramjet system is technically difficult and expensive. Therefore, it is very difficult to carry out experimental research directly aiming at the sub-super shear mixed flow in the combustion chamber of the embedded rocket type ramjet combined engine, so that only the sub-super shear mixed flow is considered to be researched, namely, a set of sub-super shear mixed flow test system is set up for researching the mixing process of the engine under the condition of not considering the engine. The existing test system has the capability of simulating cold and high-temperature fuel gas, can simulate the mixing state of supersonic jet and subsonic jet at room temperature, and adopts a small rocket to generate high-temperature supersonic fuel gas and mix the supersonic jet and the subsonic jet. However, the engine is in high altitude in an actual flight state, the backpressure is a low backpressure state, and the flow field and the mixing efficiency of the sub-ultra-shear mixed flow are changed under the low backpressure condition. The air jet flow at the subsonic side is in a high-temperature state after being compressed, and the temperature can reach 800K at most. High temperatures can change the physical parameters of the fluid, thereby affecting subsequent blending flow. The high-speed airflow is limited, the heating temperature of the heating subsonic air does not exceed 500K in the existing test scheme, and the difference between the heating temperature and the actual use temperature is large. Furthermore, the visual diagnosis of sub-shear layers in confined spaces is limited by the difficulty that optical glasses are not available at high temperatures, making it difficult to quantify the sub-shear layer thickness and its growth rate.

Disclosure of Invention

The technical problem to be solved by the present invention is to provide a low-pressure sub-super shear flow experimental system with high-temperature subsonic air, which can simulate low back pressure and high-temperature air jet.

In order to solve the technical problems, the invention adopts the technical scheme that a low-pressure sub-super shear flow experiment system with high-temperature subsonic air comprises:

the experimental model section is of a cavity structure, the front end and the rear end of the experimental model section are correspondingly provided with a gas inlet and a mixed gas outlet, and the side wall of the experimental model section is provided with a high-temperature gas inlet; in the cavity, the front section of the cavity is provided with a plurality of parallel and independent channels which are respectively a subsonic airflow channel and a supersonic airflow channel; the rear section is a single channel communicated with the multiple channels.

The air inlet pipe is connected with the air inlet of the experimental model section and is used for introducing air into the subsonic airflow channel; after the air flows through the subsonic airflow channel, the air is mixed and sheared with the high-temperature gas flowing out of the supersonic airflow channel in the single channel.

And the heating pipe is coaxially sleeved in the air inlet pipe, and forms a circular seam with the inner wall of the air inlet pipe to be used as an air input channel.

The induction copper pipe is spirally wound on the outer wall of the heating pipe.

The high-frequency induction microwave electric heater is connected with the induction copper pipe, matched with the induction copper pipe and used for heating the heating pipe through magnetic induction so as to heat subsonic airflow.

Furthermore, the heating tube also comprises fins which are spiral metal wire rings, the heating tube is coaxially sleeved with the fins, and each metal wire is attached to the outer wall of the heating tube.

Furthermore, the side plates of the experimental model section are made of high silica phenolic materials. .

Furthermore, a thermocouple array is arranged on the side plate and close to the high-temperature gas inlet, the thermocouple array at least comprises three rows of thermocouple groups arranged at intervals along the airflow direction, each thermocouple group comprises a plurality of thermocouples, and each thermocouple vertically penetrates through the side plate.

Furthermore, the rear end of the experimental model section is connected with a vacuum tank through a connecting pipe, and the pipeline on the vacuum tank is connected with at least three vacuum pumps.

Furthermore, a snake-shaped cooling pipe is arranged in the connecting pipe, and the cooling pipe is communicated with the cooling water tank.

Furthermore, a divider is arranged in the experimental model section to realize the division of multiple channels in the cavity, the divider is a cavity which is enclosed by a shell and has openings at the front end and the rear end, and the rear end of the shell is integrally connected with a spray pipe with the front end contracted and the rear end expanded; two independent subsonic channels are formed between the upper plate and the lower plate of the shell and the corresponding upper plate and lower plate of the experimental model section, and the front ends of the two subsonic channels are communicated with the air inlet pipe; the inner cavity of the shell is a supersonic air flow channel, and one side wall of the shell is provided with an air flow inlet corresponding to the position of the high-temperature air inlet.

The invention has the following advantages: 1. the low-backpressure subsonic velocity air flow test system has the advantages that the low-backpressure subsonic velocity air flow test system capable of generating high-temperature subsonic velocity air is provided, and low-backpressure conditions and high-temperature subsonic velocity air flows are provided for researching the subsonic velocity air flow in a real state. 2. Quantitatively obtaining the thickness growth rule of the sub-super shear mixed layer.

Drawings

FIG. 1 is a diagram of a sub-super shear flow experimental system for high temperature subsonic air in accordance with the present invention;

FIG. 2 is a view showing the inner structure of an intake pipe according to the present invention;

FIG. 3 is a diagram of thermocouple site placement in the present invention;

wherein: 1. the device comprises an air inlet pipe, 2 parts of heat preservation cotton, 3 parts of an induction copper pipe, 4 parts of an air-air rocket, 5 parts of an experimental model section, 6 parts of a cooling water tank, 7 parts of a vacuum tank, 8 parts of a vacuum pump, 9 parts of a heater cooling water tank, 10 parts of a high-frequency induction microwave electric heater, 11 parts of fins, 12 parts of a heating pipe and 13 parts of a thermocouple array.

Detailed Description

In the invention, a low back pressure experiment system with high-temperature subsonic air and high-temperature supersonic gas mixed is established to simulate the state of the embedded rocket ramjet in a real working environment, and further research the flow field structure and the growth characteristics of the mixed layer in the environment. The experimental system has the following difficulties that firstly, the subsonic air speed is over 100m/s, the convection heat exchange difficulty of air in a high-speed flowing state is very high, a conventional electric heating system can only heat to be about 473K, and the real ram air temperature is difficult to simulate; secondly, the ground environment pressure is one standard atmospheric pressure, and the ignition working back pressure environment under the condition of about 0.1atm when high space is provided on the ground is very difficult; thirdly, the growth of the shear mixing layer is difficult to measure in the thermal state experiment, and the information of the mixing layer can hardly be captured in the visual optical diagnosis mode.

The invention discloses a low-pressure sub-super shear flow experimental system with high-temperature subsonic air, as shown in figure 1, comprising: theexperimental model section 5 is of a cavity structure, the front end and the rear end of the experimental model section are correspondingly provided with a gas inlet and a mixed gas outlet, and the side wall of the experimental model section is provided with a high-temperature gas inlet; in the cavity, the front section of the cavity is provided with a plurality of parallel and independent channels which are respectively a subsonic airflow channel and a supersonic airflow channel; the rear section is a single channel communicated with the multiple channels. Theair inlet pipe 1 is connected with an air inlet of theexperimental model section 5 and used for introducing air into the subsonic airflow channel; after the air flows through the subsonic airflow channel, the air is mixed and sheared with the high-temperature gas flowing out of the supersonic airflow channel in the single channel. Theheating pipe 12 is coaxially sleeved in theair inlet pipe 1, and forms a circular seam with the inner wall of theair inlet pipe 1 to be used as an air input channel. Theinduction copper pipe 3 is spirally wound on the outer wall of theheating pipe 12. The high-frequency induction microwaveelectric heater 10 is connected with theinduction copper pipe 3, matched with theinduction copper pipe 3 and used for heating theheating pipe 12 through magnetic induction heating so as to heat subsonic airflow.

As shown in fig. 2, the low-pressure sub-shear flow experimental system with high-temperature subsonic air further includes afin 11, which is a spiral wire ring coaxially sleeved outside theheating tube 12, and each wire is attached to the outer wall of theheating tube 12.

As shown in fig. 3, the side plates of theexperimental model section 5 were made of high silica phenolic material. On the curb plate, and be close to the high temperature gas entrance and be provided with thermocouple array 13, thermocouple array 13 includes the thermocouple group that the three rows set up along the gas flow direction interval at least, all includes a plurality of thermocouples in each thermocouple group, and each thermocouple all passes the curb plate perpendicularly. The thermocouple and the side cover plate are bonded through high-temperature-resistant glue to achieve the effects of fastening and sealing.

The rear end of theexperimental model section 5 is connected with avacuum tank 7 through a connecting pipe, and the pipeline on thevacuum tank 7 is connected with at least threevacuum pumps 8. A snake-shaped cooling pipe is arranged in the connecting pipe and is communicated with thecooling water tank 6.

A divider is arranged in theexperimental model section 5 to divide multiple channels in the cavity, the divider is a cavity which is enclosed by a shell and is provided with openings at the front end and the rear end, and the rear end of the shell is integrally connected with a spray pipe with the front end contracted and the rear end expanded; two independent subsonic channels are formed between the upper plate and the lower plate of the shell and the corresponding upper plate and lower plate of theexperimental model section 5, and the front ends of the two subsonic channels are communicated with theair inlet pipe 1; the inner cavity of the shell is a supersonic air flow channel, and one side wall of the shell is provided with an air flow inlet corresponding to the position of the high-temperature air inlet.

The invention relates to a low-pressure sub-super shear flow experiment system with high-temperature subsonic air.Aheating pipe 12 is coaxially sleeved in anair inlet pipe 1, and a circular seam is formed between the heating pipe and the inner wall of theair inlet pipe 1 and is used as an input channel of air; the difference between the inner diameter of theheating pipe 12 and the inner diameter of theair inlet pipe 1 is about 20mm, namely the size of the gap of the circular seam is about 20 mm. Theheating pipe 12 is coaxially sleeved with a spiral wire ring, the wire ring is afin 11, each wire of the wire ring is tightly attached to the outer wall of theheating pipe 12, a gap is reserved between the wire ring and the inner wall of theair inlet pipe 1, and the gap is about 3mm and used for gas circulation.

Theair inlet pipe 1 is heated by a high-frequency induction microwaveelectric heater 10, aninduction copper pipe 3 of the high-frequency induction microwaveelectric heater 10 is in a spiral shape formed by annularly winding copper wires, theinduction copper pipe 3 is coaxially sleeved outside theair inlet pipe 1, and two ends of theinduction copper pipe 3 are connected with a power supply. Theinduction copper pipe 3 is wound on theair inlet pipe 1 uniformly, and theheating pipe 12 is heated and heated rapidly in an electromagnetic induction mode, exchanges heat with thefins 11, and transfers heat to thefins 11 through heat conduction. Thefins 11 can slow down the speed of the entering high-speed air, increase the retention time in the pipe, and greatly increase the heat exchange area, so that the convection heat exchange efficiency is improved, the temperature can reach 800K, the heating of the subsonic airflow is realized, and the required temperature is reached. The outer wall of theair inlet pipe 1 is wound with heat insulation cotton to reduce the heat dissipation loss between the pipeline and the external environment and maintain the temperature of high-speed airflow in the pipe. The microwaveelectric heater 10 is communicated with the heatercooling water tank 9 to realize cooling.

The front end of theair inlet pipe 1 is connected with an air inlet joint, the air inlet joint adopts a quick joint, the air inlet joint is convenient and quick, and different models can be replaced when different low back pressures are needed. Is connected with an air supply device pipeline through a quick coupling.

The rear end of theair inlet pipe 1 is connected with anexperimental model section 5 which is of a cavity structure, the front end and the rear end of the air inlet pipe are provided with a gas inlet and a mixed gas outlet, and the side wall of the air inlet pipe is provided with a high-temperature gas inlet; in the cavity, the front section of the cavity is parallel to independent multiple channels which are a subsonic airflow channel and a supersonic airflow channel respectively; the rear section is a single channel communicated with the multiple channels.

Specifically, theexperiment model section 5 adopts a cuboid cavity, in order to realize the division of multiple channels in the cavity, a divider is axially arranged in the cavity, the divider is a cavity which is enclosed by a shell and is open at the front end and the rear end, and the rear end of the shell is integrally connected with a spray pipe which is contracted at the front end and expanded at the rear end. Two independent subsonic channels are formed between the upper plate and the lower plate of the shell and the corresponding upper plate and lower plate of theexperimental model section 5, and the front ends of the two subsonic channels are communicated with theair inlet pipe 1. The inner cavity of the shell is a supersonic airflow channel, an airflow inlet is arranged on the side wall of the shell and corresponds to the position of the high-temperature gas inlet, and the high-temperature gas inlet is connected with the outlet of the spray pipe of the gas-gas rocket 4. Supersonic gas is provided by a combustion chamber of the gas-gas rocket 4 and vertically enters a supersonic airflow channel, then the vertical supersonic airflow is converted into axial flow and flows out from the tail end of the supersonic airflow channel, and the supersonic airflow flowing out from an upper subsonic airflow channel and a lower subsonic airflow channel enters a single channel and is mixed to form a shear layer. The gas introduced into the combustion chamber of the gas-gas rocket 4 is oxygen and ethylene, an external oxygen pipeline and an ethylene pipeline are connected, each pipeline is connected with a gas source device, each pipeline is provided with an electromagnetic valve and a flowmeter, each electromagnetic valve is controlled by a PLC control box, and a data collector is also arranged, connected with the PLC control box, and used for collecting data flowing through each electromagnetic valve and the flowmeter and transmitting the data to the PLC control box.

The rear end mixed gas outlet of theexperimental model section 5 is connected with avacuum tank 7 through a connecting pipe, and thevacuum tank 7 is at least connected with threevacuum pumps 8. The back pressure of the experiment system is adjusted in a vacuumizing mode in the experiment process, so that the environmental requirement of low back pressure of 0.1atm can be met, and the working environment of the combined engine can be better simulated. Meanwhile, the subsonic airflow is sucked in a sucking mode. And a cooling pipe is axially arranged in the connecting pipe and is communicated with a coolingwater tank 6, and the mixed air flow discharged from the rear end of theexperimental model section 5 is cooled by adopting a water cooling mode. The cooling pipe adopts the coiled pipe to increase the area of contact of mist and condenser pipe, and then promote cooling efficiency.

More specifically, thevacuum tank 7 has a volume of 3m³Selecting the volumeThe reason for thevacuum tank 7 with the specification is that the pressure of thevacuum tank 7 is extremely difficult to maintain in the test process due to the small volume; the volume is too large, so that the pumping time of the vacuum tank is too long, and the pressure control of the vacuum tank is difficult to realize; furthermore, thevacuum tank 7 is too large, the sealing conditions become more and more severe, and a great deal of effort is required for equipment maintenance.

The side plates on at least one side of theexperimental model section 5 are stacked externally and are provided with side plates, and the side plates are made of high-silica phenolic materials, so that the heat loss of thermocouple measuring points is reduced, and the measuring precision is improved. On the side, a thermocouple array 13 is arranged close to the high-temperature gas inlet along the direction of the flow direction of the gas flow, the thermocouple array 13 is specifically at least three rows of heat discharge couples arranged at intervals along the direction of the gas flow, the number of each row of heat discharge couples is 17, and each thermocouple vertically penetrates through the side plate and extends into the cavity. The distances from the three heat discharge couples to the high-temperature gas inlet are respectively 30mm, 60mm and 90mm, and the distance between every two adjacent heat discharge couples is 2.5 mm.

The working process of the low-pressure sub-super shear flow experimental system with the high-temperature subsonic air is as follows: the high-frequency induction microwaveelectric heater 10 and the coolingwater tank 6 are turned on, and the high-frequency induction microwaveelectric heater 10 starts to work. Preheat 60s back, open 3 vacuum pumps in proper order and take outvacuum tank 7 to low back pressure environment, later open vacuum tank ball valve and subsonic inlet vacuum ball valve, undervacuum tank 7's suction effect, the air gets intoexperiment model section 5 from atmospheric environment through subsonic inlet vacuum ball valve, inintake pipe 1,heating pipe 12heats fin 11, the subsonic air current that flows through heaies up through high temperature fin heat transfer, flow inexperiment model section 5, flow out along the axial byexperiment model section 5's upper and lower both sides.

After the subsonic velocity airflow is stable, opening an electromagnetic valve of an oxygen and ethylene pipeline through a PLC control box, introducing mixed gas into a fuel gas generator of a gas-gas rocket 4, opening a high-frequency igniter to ignite the mixed gas, enabling high-temperature and high-pressure airflow generated after combustion to flow into a spray pipe of anexperimental model section 5, generating supersonic velocity airflow through an outlet of a built-in spray pipe, enabling the subsonic velocity airflow and the supersonic velocity airflow to be subjected to shearing mixing at the rear end of theexperimental model section 5, enabling the mixed airflow to flow out of the rear end of theexperimental model section 5, enabling the mixed airflow to enter a cooling connecting pipe to be cooled, introducing the cooled gas into avacuum tank 7, and enabling the experimental duration to be 20 s.

More specifically, the test procedure through the test system is as follows:

(1) and testing whether the acquisition system is normal.

(2) And cutting off the gas source valves of the oxygen path and the ethylene path, and checking whether the two paths of electromagnetic valves work normally.

(3) Before each ignition test of the gas-gas rocket 4, whether the firearm works normally is checked.

(4) The pressure of the oxygen path gas source is adjusted to be between 1.95 and 2.17MPa, and the pressure of the ethylene path gas source is adjusted to be between 0.97 and 1.15 MPa.

(5) Before the test starts, the subsonic inlet valve is closed, and the valve of thevacuum tank 7 is opened for checking to determine that the test system is good in air tightness.

(6) The connecting line between theexperimental model section 5 and thevacuum tank 7 was cooled in advance.

(7) And (3) starting the heatercooling water tank 9 and maintaining the high-frequency induction microwaveelectric heater 10 to work for a long time.

(8) The high frequency induction microwave electric heater power supply is started, and the high frequency induction microwaveelectric heater 10 starts to heat theheating tube 12 and thefin 11.

(7) Thevacuum pump 8 is started to pump the pressure in thevacuum tank 7 to below 1000 Pa.

(8) Starting a test section acquisition system and starting to acquire data;

(9) manually opening a control valve and a subsonic inlet valve between thevacuum tank 7 and theexperimental model section 5;

(10) and opening an oxygen path electromagnetic valve, opening an ethylene path electromagnetic valve after 1s, and opening an igniter for ignition after 1 s.

(11) After the ignition is successfully finished, the electromagnetic valves of the oxygen path and the ethylene path are closed after 7s, the supply of ethylene and oxygen is cut off, and the combustion is stopped.

(12) And (4) continuously opening the subsonic inlet valve, and pumping ambient air by thevacuum pump 8 to blow away the fuel gas in thevacuum tank 7.

(13) Thevacuum pump 8 is turned off and the subsonic inlet valve andvacuum tank 7 valve are closed.

(14) And (4) turning off the power supply of the high-frequency induction microwave electric heater, and turning off the heater cooling system after 60 s.

(15) And (3) exporting the acquired data from a test system, reading the voltage values of all thermocouples through Origin post-processing software, converting the voltage values into temperature values, obtaining a temperature distribution curve of the shear layer, and calculating to obtain the thickness and the thickness growth rate of the shear mixing layer.

The experimental system provides high-temperature subsonic air and a low back pressure environment for ground test of the large-gradient sub-shear-super-shear mixed flow, and solves the problem of quantitative test of the thickness of the high-temperature sub-shear-super-shear mixed flow layer. Therefore, the induction of the high-frequency induction microwave electric heater to heat the air jet flow at the subsonic velocity side is one of the key points, and the subsonic velocity air can be heated to be more than 600K under the condition, so that the temperature is increased by 130K compared with the temperature of the existing electric heating system; the key point is that a low-pressure vacuum system formed by combining threevacuum pumps 8 is introduced, and the low-back-pressure environment is realized and the back pressure is flexibly adjusted by controlling the pumping time and the starting number of thevacuum pumps 8; in addition, thermocouples are densely distributed at different positions along the flow direction of theexperimental model section 5, and the thickness of the sub-super shear mixed layer is obtained by measuring the temperature gradient distribution.

The experiment system is a large-gradient sub-shear-layer experiment system capable of providing high-temperature subsonic air and a low back pressure environment on the ground, the temperature of the subsonic air can be adjusted by controlling the power of the high-frequency induction microwaveelectric heater 10, and the experiment system can be used for researching the influence rule of the subsonic incoming flow temperature on the large-gradient sub-shear-layer. The ignition backpressure is changed by controlling the pumping time and the opening number of thevacuum pump 8, and the method can be used for researching the influence rule of different backpressure on the large-gradient sub-super shear layer; the thickness of the sub-super shear mixed layer at different flow direction positions is obtained through the measurement of the thermocouple arranged on the side wall, and the method can be used for researching the growth characteristics of the large-gradient sub-super shear layer.

Claims (7)

Translated fromChinese

1.一种具有高温亚声速空气的低压亚-超剪切流实验系统，其特征在于，包括：1. a low pressure sub-supershear flow experiment system with high temperature subsonic air, is characterized in that, comprises:实验模型段(5)，为腔体结构，其前端和后端对应开设有气体入口和混合气体出口，且侧壁上开设有高温气体入口；在腔体内，其前段为并列且独立的多通道，多通道分别为亚声速气流通道和超声速气流通道；后段为与多通道相连通的单通道；The experimental model section (5) is a cavity structure, its front and rear ends are correspondingly provided with a gas inlet and a mixed gas outlet, and a high-temperature gas inlet is provided on the side wall; in the cavity, its front section is a parallel and independent multi-channel , the multi-channels are the subsonic airflow channel and the supersonic airflow channel respectively; the rear section is a single channel connected with the multi-channel;进气管(1)，与所述实验模型段(5)的气体入口相连接，用于向所述亚声速气流通道内通入空气；空气流过亚声速气流通道后，与由超声速气流通道流出的高温气体在单通道内混合剪切；The air inlet pipe (1) is connected with the gas inlet of the experimental model section (5), and is used for introducing air into the subsonic airflow channel; The high temperature gas is mixed and sheared in a single channel;加热管(12)，同轴套设在所述进气管(1)内，与所述进气管(1)的内壁间形成环缝，作为空气的输入通道；a heating pipe (12), which is coaxially sleeved in the air inlet pipe (1), and forms an annular seam with the inner wall of the air inlet pipe (1), serving as an air input channel;感应铜管(3)，螺旋环绕缠绕在所述加热管(12)的外壁；an induction copper tube (3), spirally wound around the outer wall of the heating tube (12);高频感应微波电加热器(10)，与所述感应铜管(3)相连接，并与所述感应铜管(3)相配合，通过磁感应加热所述加热管(12)，以实现对亚声速气流的加热。A high-frequency induction microwave electric heater (10) is connected to the induction copper tube (3), and is matched with the induction copper tube (3) to heat the heating tube (12) by magnetic induction, so as to realize the Heating of subsonic airflow.2.根据权利要求1所述的一种具有高温亚声速空气的低压亚-超剪切流实验系统，其特征在于，还包括翅片(11)，其为螺旋状的金属丝环，同轴套设在所述加热管(12)外，且各金属丝与所述加热管(12)的外壁相贴合。2. a kind of low pressure sub-supershear flow experimental system with high temperature subsonic air according to claim 1, is characterized in that, also comprises fin (11), it is helical wire ring, coaxial The utility model is sleeved outside the heating pipe (12), and each metal wire is attached to the outer wall of the heating pipe (12).3.根据权利要求2所述的一种具有高温亚声速空气的低压亚-超剪切流实验系统，其特征在于，所述实验模型段(5)的侧板采用高硅氧酚醛材料。3 . The low-pressure sub-supershear flow experimental system with high-temperature subsonic air according to claim 2 , wherein the side plate of the experimental model section ( 5 ) is made of high-silica phenolic material. 4 .4.根据权利要求3所述的一种具有高温亚声速空气的低压亚-超剪切流实验系统，其特征在于，在所述侧板上，且靠近高温气体入口处设置有热电偶阵列(13)，所述热电偶阵列(13)至少包括三列沿气流流向方向间隔设置的热电偶组，各所述热电偶组中均包括多个热电偶，且各热电偶均垂直穿过侧板。4. a kind of low pressure sub-supershear flow experimental system with high temperature subsonic air according to claim 3, is characterized in that, on described side plate, and near the high temperature gas inlet place is provided with thermocouple array ( 13), the thermocouple array (13) includes at least three rows of thermocouple groups arranged at intervals along the airflow direction, each of the thermocouple groups includes a plurality of thermocouples, and each thermocouple vertically passes through the side plate .5.根据权利要求4所述的一种具有高温亚声速空气的低压亚-超剪切流实验系统，其特征在于，所述实验模型段(5)的后端通过连接管连接有一真空罐(7)，所述真空罐(7)上管路连接有至少三个真空泵(8)。5. a kind of low pressure sub-supershear flow experimental system with high temperature subsonic air according to claim 4, is characterized in that, the rear end of described experimental model section (5) is connected with a vacuum tank (5) by connecting pipe. 7), at least three vacuum pumps (8) are connected to the pipeline on the vacuum tank (7).6.根据权利要求5所述的一种具有高温亚声速空气的低压亚-超剪切流实验系统，其特征在于，在所述连接管内设置有蛇形冷却管，所述冷却管与冷却水罐(6)相连通。6. a kind of low pressure sub-supershear flow experiment system with high temperature subsonic air according to claim 5, is characterized in that, in described connecting pipe, be provided with serpentine cooling pipe, described cooling pipe and cooling water The tank (6) is connected.7.根据权利要求5或6所述的一种具有高温亚声速空气的低压亚-超剪切流实验系统，其特征在于，在所述实验模型段(5)内设置有一分割器实现腔体内多通道的分割，所述分割器为由一壳体围成的前后两端敞口的腔体，壳体的后端一体连接有前端收缩，后端外扩的喷管；壳体的上下板与实验模型段(5)的对应的上下板间形成两个独立的亚声速通道，两个亚声速通道的前端均与进气管(1)相连通；壳体内腔为超声速气流通道，壳体的一侧壁上开设有一气流入口，与高温气体入口的位置相对应。7. A kind of low pressure sub-supershear flow experiment system with high temperature subsonic air according to claim 5 or 6, is characterized in that, in described experimental model section (5) is provided with a divider to realize in cavity Multi-channel splitting, the splitter is a cavity enclosed by a casing with open front and rear ends, and the rear end of the casing is integrally connected with a nozzle that contracts at the front end and expands at the rear end; the upper and lower plates of the casing Two independent subsonic channels are formed between the upper and lower plates corresponding to the experimental model section (5), and the front ends of the two subsonic channels are connected with the air intake pipe (1). A gas inlet is provided on one side wall, which corresponds to the position of the high temperature gas inlet.

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