CN211740626U - A combined power multi-channel nozzle test device - Google Patents

Abstract

The utility model discloses a combined power multi-channel nozzle test device, which simulates the multi-channel nozzle of a turbine-based combined cycle engine and can observe the air flow mixing. The utility model can carry out a simulation experiment of injecting indicators with different colors and observing their mixing conditions, and explores the basic law of airflow mixing of multi-channel combined nozzles under low-speed flight conditions and different pipeline working conditions. The three channels of the utility model simulate the turbine engine, the rocket engine and the ramjet respectively. The opening and closing of the upper and middle channels are controlled by the adjustment device to simulate the situation when the TBCC mode is switched. Observe and calculate the air flow speed through the differential pressure gauge as the basis to control the motor to reach the corresponding speed. Observe the mixing of air flow by spraying different colored indicators through different channels. Studying the flow variation law of multi-channel nozzles during modal transition is beneficial to the research and development of combined power nozzles.

Description

A combined power multi-channel nozzle test device

technical field

The utility model belongs to the field of aircraft, and relates to a combined power multi-channel nozzle test device (a turbine-based combined power cycle multi-channel nozzle that can be used at different flight speeds).

Background technique

The characteristics of hypersonic aircraft are specific impulse, wide speed range, vertical take-off and landing, low cost, and have a wide range of application value in the study of future aircraft. At present, the operating speed range of the existing air-breathing engine is narrow. The working Mach number of turbojet engine and turbofan engine is between 0-3, and the working Mach number of ramjet engine is between 2-6. It can be seen that any kind of air-breathing engine cannot meet the requirements of the wide speed range of hypersonic aircraft. Although the rocket engine can work between Mach 0-10, it needs to carry fuel and oxygen, the specific impulse is small, it cannot be reused, and the economy is low. Therefore, since the 1960s, extensive and in-depth research has been carried out on combined cycle engines at home and abroad.

Turbine-Based-Combined-Cycle (TBCC) is a type of combined-cycle engine. The TBCC engine is a wide-speed hypersonic power system formed by a scientific combination based on a turbine engine, integrating ramjet, rocket engine and other power forms. It has the advantages of specific impulse, wide flight speed range, and reusability. It is an ideal power propulsion system for full-speed hypersonic flight.

In order to realize the conversion under different working modes, the TBCC power system needs to have an adjustment mechanism with simple structure, stable operation, reliability and safety, and convenient maintenance. The current structure has many movable parts, the structure is complex, and it is difficult to set the driving parts.

Utility model content

In order to solve the above problems, the purpose of this utility model is to provide a combined power multi-channel nozzle test device.

The technical scheme adopted by the utility model to solve its technical problems is:

A combined power multi-channel nozzle test device includes a power module, an airflow velocity measurement module, a rectifier module, a pipeline module, a color indicator module, an adjustment mechanism and a support structure; the power module includes: a motor, an electronic governor, Electric wire, receiver, power supply and remote control; the rectification module includes: rectification pipe, straw array, barbed wire; the color indicator module includes: feeding funnel, feeding hose, colored powder; the air velocity measurement The module includes: thick hose, U-shaped pipe, adapter, thin hose and thin metal pipe; the pipeline module is a square pipe, a tail nozzle; the adjustment mechanism includes: a triangular adjustment plate, a bearing, a square rotating shaft and A steering gear; the support structure includes: a motor support and a steering gear support.

Further, the test device is composed of upper, middle, and lower channels. Motors are arranged on the three channels. The motor is connected to the rectifier pipe through the motor support. The rectifier pipe is connected to the square pipe, and the square pipe is connected to the tail spray. There is an adjusting device at the connection between the upper and middle passages and the tail nozzle. The adjusting device is fixed on the tail nozzle and is used to control the opening and closing of the upper and middle square pipes. The first hole is fixed with a feeding hose, the feeding hose is connected with the feeding funnel, and two small holes are provided above the square pipe for connecting the air velocity measurement module.

Further, a suction pipe array is arranged in the rectification pipe, and both ends of the suction pipe array are provided with a wire mesh, and the wire mesh fixes the suction pipe array in the rectification pipe.

Further, the airflow velocity measurement module includes a thick hose, a U-shaped pipe, an adapter, a thin hose and a metal pipe, and each of the thick hose, the adapter, the thin hose and the metal pipe has two, one of which is one The metal pipe is inserted into the middle position of the square pipe through a small hole, and is bent 90 degrees to the horizontal, so that the nozzle of the metal pipe faces the direction of the incoming airflow, and the end of the metal pipe outside the square pipe is connected with a thin hose, a rotating One end of fittings, thick hoses and U-tubes;

The other metal pipe is connected to the square pipe through another small hole 2. One port of the metal pipe is flush with the inner side of the square pipe, and the other port of the other metal pipe is sequentially connected with another thin hose, another turn Fittings, another thick hose, and the other end of the U-tube.

Further, the adjusting device is a triangular adjusting plate, and the steering gear drives the triangular adjusting plate to rotate around a square rotating shaft fixed on the tail nozzle to control the opening and closing of the pipe; the triangular adjusting plate is hollow design.

Further, the rotation speed of the motor is controlled by a power control module, and the power control module includes an electronic governor, a receiver, a power supply and a remote control.

Further, the shape of the motor support is a shrunk round and square shape.

Further, the U-shaped pipe is provided with a scale line, and the rectification pipe, the square pipe and the tail nozzle are all transparent square pipes made of acrylic material.

Further, the tail nozzle is in the shape of an inverted triangle, which is a unilateral expansion tail nozzle designed by the characteristic line method.

Further, the rectifying pipe and the square pipe are connected by a concave-convex table nesting structure.

The utility model simulates a multi-channel nozzle of a turbine-based combined cycle engine (Turbine-Based-Combined-Cycle, TBCC), and is a device that can observe the air flow mixing. The TBCC engine is based on a turbine engine and integrates a ramjet and a rocket engine to form a wide-speed hypersonic power system. The utility model can carry out a simulation experiment of introducing indicators of different colors and observing their mixing conditions, so as to explore the basic laws of airflow mixing of multi-channel combined nozzles under low-speed flight conditions and different pipeline working conditions. The utility model is provided with three channels, respectively simulating a turbine engine, a rocket engine and a ramjet engine. The opening and closing of the upper two channels are controlled by the adjustment device to simulate the situation when the TBCC mode is switched. Observe and calculate the airflow speed through the differential pressure measuring meter, and control the motor to reach the corresponding speed based on this. Observe the air flow mixing by spraying different colored indicators through different channels. Studying the flow variation law of multi-channel nozzles during modal transition is beneficial to the research and development of combined power nozzles.

The beneficial effects of the utility model are: compared with most existing engine nozzles, the combined power multi-channel nozzle of the present utility model has the following functions: 1. Working in a wide speed range, it can simulate Mach numbers from 0 to 10 The combined cycle of the turbine engine, rocket engine and ramjet engine in the TBCC system for full-speed flight; 2. To study the airflow conditions during mode switching, this nozzle can explore the airflow conditions at the moment of starting and stopping switching of the three engines; 3. To study the airflow mixing in the tail nozzle, the airflow mixing situation in the tail nozzle caused by the difference in the airflow velocity in each pipe can be observed according to the different colors of airflow ejected by different motors.

Description of drawings

Fig. 1 is the overall structure front view of the utility model;

Fig. 2 is the overall structure sectional view of the utility model;

Fig. 3 is the left side view of the overall structure of the utility model;

Fig. 4 is the utility model round-turn square motor support;

Fig. 5 is the triangular adjustment plate of the utility model;

Fig. 6 is the limit position of the triangular adjustment plate of the present invention in the tail nozzle (the left side of Fig. 6 is that the triangular adjustment plate is opened, and the right side is closed);

Fig. 7 is the utility model pipeline connection mode;

Fig. 8 is the array arrangement of the straws of the rectifier module of the present invention;

Fig. 9 is the barbed wire placement position of the utility model;

10 is a schematic diagram of the connection between the U-shaped pipe and the pipeline of the present invention;

11 is a schematic diagram of the three-dimensional structure of the present invention;

In the figure, the square rectifier pipe 1, the round-to-square motor support 2, the rectifier suction pipe 3, the wire mesh 4, the square pipe 5, the triangular adjustment plate 6, the bearing 7, the tail nozzle 8, the square shaft 9, the duct motor 10, the rudder Engine 11, steering gear support 12, feeding funnel 13, ESC 14, feeding hose 15, electric wire 16, power battery 17, thick hose 18, U-shaped tube 19, adapter 20, thin hose 21, thin metal tube twenty two.

Detailed ways

The specific structure details and working conditions of the combined power multi-channel nozzle test device proposed by the present utility model are described in detail below with reference to the schematic diagrams.

A combined power multi-channel nozzle test device includes a power module, an airflow velocity measurement module, a rectifier module, a pipeline module, a color indicator module, an adjustment mechanism and a support structure; the power module includes: a motor 10, an electronic governor 14. Electric wire 16, receiver, power supply 17 and remote control; the rectification module includes: a rectification pipe 1, a straw array 3, and a barbed wire 4; the color indicator module includes: a feeding funnel 13, a feeding hose 15, a belt Color powder; the airflow velocity measurement module (ie the differential pressure gauge) includes: a thick hose 18, a U-shaped pipe 19, an adapter 20, a thin hose 21 and a thin metal pipe 22; the pipe module is a square pipe 5. The tail nozzle 8; the adjustment mechanism includes: a triangular adjustment plate 6, a bearing 7, a square rotating shaft 9 and a steering gear 11; the support structure includes: a motor support 2 and a steering gear support 12.

The test device is composed of upper, middle and lower channels. Motors 10 are arranged on the three channels. The motor 10 is connected to the rectifier pipe 1 through the motor support 2 . The rectifier pipe 1 is connected to the square pipe 5 and the square pipe 5 . The tail nozzle 8 is connected together, and an adjustment device is provided at the connection between the upper and middle passages and the tail nozzle 8. The adjustment device is fixed on the tail nozzle 8 to control the opening and closing of the upper and middle square pipes 5, and the motor Above the square pipe section of the support 2, a feeding hose 15 is fixed through a small hole, the feeding hose 15 is connected with the feeding funnel 13, and two small holes are opened above the square pipe 5 for connecting the airflow velocity measurement module (ie Differential Pressure Gauge).

The rectification pipe 1 is provided with a suction pipe array 3 , and both ends of the suction pipe array 3 are provided with a wire mesh 4 , and the wire mesh 4 fixes the suction pipe array 3 in the rectification pipe 1 .

The airflow velocity measurement module (ie the differential pressure gauge) includes a thick hose 18, a U-shaped pipe 19, an adapter 20, a thin hose 21 and a metal pipe 22. The thick hose 18, the adapter 20, the thin hose 21 and two metal pipes, one of the metal pipes 22 is inserted into the middle position of the square pipe 5 through a small hole, and is bent 90 degrees to the horizontal, so that the mouth of the metal pipe faces the direction of the incoming airflow, and the metal pipe 22 is in the middle position. The outer end of the square pipe 5 is sequentially connected with the thin hose 21, the adapter 20, the thick hose 18 and one end of the U-shaped pipe 19;

Another metal pipe 22 is connected to the square pipe 5 through another small hole 2, one port of the metal pipe 22 is flush with the inner side of the square pipe 5, and another port of the other metal pipe 22 is connected with another thin pipe in turn. Tube 21 , another adapter 20 , another thick hose 18 and the other end of the U-shaped tube 19 .

The adjusting device is a triangular adjusting plate 6, and the steering gear 11 drives the triangular adjusting plate 6 to rotate around a square shaft fixed on the tail nozzle 8 to control the opening and closing of the pipe; the triangular adjusting plate 6 is hollowed out.

The rotation speed of the motor 10 is controlled by a power control module, and the power control module includes an electronic speed governor 14, a receiver, a power supply 17 and a remote controller.

The shape of the motor support 2 is a shrunk round and square shape.

The U-shaped pipe 19 is provided with a scale line, and the rectification pipe 1 , the square pipe 5 and the tail nozzle 8 are all transparent square pipes made of acrylic material.

The tail nozzle 8 is in the shape of an inverted triangle, and is a unilateral expansion tail nozzle designed by the characteristic line method.

The rectifying pipe 1 and the square pipe 5 are connected by a concave-convex table nesting structure.

The power module is controlled by the remote controller to simultaneously control the motors 10 of the upper, middle and lower channels to achieve different rotational speeds, so as to control different intake speeds and realize the function of simulating turbine engines, rocket engines and jet engines with different Mach numbers.

The airflow velocity measurement module simulates a pitot tube, and according to the principle of Bernoulli equation, the difference between the measured total pressure and the static pressure is the dynamic pressure, and the function of calculating the airflow velocity is realized.

The rectification module realizes the function of converting the air flow from a swirling and unstable turbulent flow state to a relatively stable laminar flow state.

The pipeline module is designed by the characteristic line method to design the unilateral expansion tail nozzle 8, which realizes the functions of mixing the airflows of different engine modules and increasing the gas impulse.

The color indicator module enables observation of airflow mixing.

The adjustment mechanism is controlled by the steering gear 11 to control the triangular adjustment plate 6 to rotate around the square shaft 9 fixed on the tail nozzle 8 to adjust the throat area and the opening and closing channels to control the flow of air, so as to realize the conversion function of different modules of the TBCC engine system. . The adjustment mechanism is controlled by the remote control to rotate the steering gear 11 to realize the rotation adjustment function of the triangular adjustment plate 6 .

The support structure is composed of a 3D-printed circular rotary motor support 2, a steering gear support 12, a rectifier pipe 1 and a test device support frame (not shown) to realize the wrapping and supporting functions of the entire test device.

In one embodiment, the present invention is based on a parallel turbine-based combined cycle power engine and a unilateral expansion nozzle, the upper channel is the turbojet engine channel, the middle channel is the rocket engine channel, and the lower channel is the ramjet engine channel. At the tail of both the turbojet channel and the rocket channel, a circular-turned-square channel is set, which is finally connected to the tail nozzle.

The utility model is provided with a square rectifier pipe, a circular-rotating square motor support, a suction pipe array, a barbed wire, a square pipe, a triangular adjusting plate, a bearing, a tail nozzle, a square rotating shaft, a ducted motor, a steering gear, a steering gear support, a feeding funnel, Electronic governor, feeding hose, wire, power battery, thick hose, U-shaped tube, adapter, thin hose, thin metal tube.

The ducted motor 10 is installed and embedded in the circular-to-square motor support 2. The motor support 2 is a transitional structure of a circular-to-square section printed with a 3D printer. The circular inner diameter matches the outer diameter of the ducted motor, and the square size matches the rear rectifier module square tube. There is a small hole. Insert the feeding hose 15 into the colored powder. The motor support 2 is followed by a square rectifier pipe 1. The square rectifier pipe 1 is filled with a rectifier straw array 3 to form a honeycomb structure, and wire mesh is placed at both ends of the rectifier straw array 3. 4 Fix, the square rectifier pipe 1 is then connected to a section of square pipe 5, there are two small holes on the square pipe 5, and the thick hose 18, the adapter 20, the thin hose 21, and the thin metal pipe 22 are connected through the U-shaped pipe 19. Measure the gas pressure and calculate the gas flow rate. The square pipe 5 is followed by the tail nozzle 8. The upper and middle square pipes 5 and the tail nozzle 8 are connected with a bearing 7 and a square rotating shaft 9. The triangular adjustment plate 6 is fixed on the tail through the square rotating shaft 9. Inside the nozzle 8, the side wall of the tail nozzle 8 is provided with a steering gear support 12, and the steering gear 11 in the steering gear support 12 is fixed to the square rotating shaft 9.

Power module: It consists of a ducted motor 10 with a diameter of 90mm, an electronic governor 14, an electric wire 16, a receiver, a 12V power battery 17, and a remote control. Control the speed of the three motors with the remote control. The function is: to provide a steady stream of air intake.

Air velocity measurement module, simulating a pitot tube, punch two circular holes above the square tube in the pipe module, insert a metal tube, and insert one into the square tube and bend it 90° to the horizontal at the middle position (make the metal nozzle face the direction of incoming flow) To measure the static pressure, an inserted square tube is flush with the lower wall of the upper surface of the square tube, and then sealed. A small piece of thin hose is connected to the upper end of the metal pipe, and the thin hose is connected to the adapter and then the thick hose, which is also sealed, and the other end of the thick hose is connected to the U-shaped pipe. Use thin hose, thick hose, and adapter to connect the two thin metal pipes to the U-shaped pipe. The dynamic pressure and then the airflow velocity are calculated by Bernoulli's equation.

The rectification module consists of a straw array 3, a wire mesh 4 and an axial 100mm acrylic splicing pipe. The connection method between the rectifier module and the pipes at both ends is shown in Figure 7. The outer side of the front and rear pipes is cut with a square shell with a thickness of 3mm and a height of 10mm to form an inner boss with a thickness of 7mm and a height of 10mm. The inner side of the rectifier module is cut with a thickness of 7mm and a height of 10mm. The shell forms an outer boss with a thickness of 3mm and a height of 10mm, and the two bosses can be assembled together; the rectifier pipe is filled with straws with a diameter of 10mm to form the straw array shown in Figure 8; the connection between the two ends of the straw is densely placed As shown in Figure 9, the mesh width of the wire mesh is slightly smaller than the diameter of the suction pipe, so when the pipes are connected, the position of the wire mesh is fixed, and then the position of the suction pipe is fixed. The function is to organize the airflow entering the pipeline. The rotation of the motor will generate a rotating airflow, and the direction will be irregular, which will affect the follow-up observation effect. After passing through a length of straight straws, the direction of the air flow is the same level and smooth.

In the pipeline module, a unilateral expansion tail nozzle 8 is designed using the feature line method. The function is: the airflow of different channels is mixed in the tail nozzle and discharged. In the actual aero-engine, in addition to the exhaust function, the tail nozzle can also continue to accelerate the gas from the combustion chamber or turbine, convert the pressure energy and thermal energy in the gas into kinetic energy, and increase the impulse of the gas, thereby increasing the engine's power. thrust.

The adjustment module is composed of a square shaft 9 , a bearing 7 and a triangular adjustment plate 6 . The cross-sectional shape of the triangular adjustment plate is similar to a fan shape, and is composed of a larger diameter arc, a smaller diameter arc, and two straight lines. In order to reduce the load on the steering gear, the triangle plate is made hollow, and the rib structure is added on both sides to increase the strength of the triangle plate. Since the TBCC tail nozzle needs to work within a wide range of pressure drop ratio, and the mass flow rate through which it passes is also greatly changed, a geometrically variable adjustment structure must be adopted to achieve a larger throat area and outlet area of the tail nozzle. Range adjustment. The triangular regulating plate is respectively installed in the rocket channel and the turbojet channel, and the triangular regulating plate rotates around the rotating shaft fixed on the tail nozzle, so as to realize the purpose of adjusting the throat area and opening and closing the channel. The upper and lower plates of the triangular adjustment plate are straight plates, and the intersection of the lower plate and the side wall of the unilateral expansion tail nozzle and the upper expansion surface is the same. It is always tangent to the upper plate of the constricted section of the tail nozzle during the rotation. The drive components of the triangle adjustment plate and its accessories are placed in the side space outside the channel. There is no adjustment structure installed in the ram channel nozzle, and it is always kept open. The function is to adjust the opening and closing of the baffle through the action of the steering gear, so as to adjust the air flow of different pipes, so as to realize the mode conversion of the TBCC engine and the purpose of changing the flight speed. The mechanism is simple, reliable and easy to maintain.

The color indicator module is composed of a feeding funnel 13, a feeding hose 15, and powders with three different colors: green, red, and purple. The green, red, and purple powders are used as color indicators to indicate the flow conditions of the upper, middle, and lower channels, respectively. . During the experiment, the powder was continuously added to the feeding funnel, and the motor was rotated to allow it to flow with the airflow through the pipe to realize mixing in the tail nozzle, so as to observe the mixing of the airflow.

The adjustment mechanism drive module is composed of the steering gear 11 (the steering gear, the steering gear disk and the transition part between the steering gear disk and the shaft). The remote control controls the steering gear to drive the adjusting triangle to rotate around the shaft fixed on the tail nozzle.

The support structure consists of two parts, namely the motor support 2 and the steering gear support 12. The motor support is mainly that the motor has a circular cross-section, and the back pipe is a square cross-section, and a round-to-square structure is required in the middle. By 3D printing a piece of round-to-square parts, one end can be embedded with the motor, and the other end is connected to the rear square tube with a tenon-and-mortise structure; the steering gear support is also 3D printed, and a groove-shaped structure is printed into the rudder. machine, and two small cylinders protruding from the bottom are embedded in it by drilling holes on the side of the tail nozzle.

The whole process of utilizing the utility model to carry out the experiment is given below:

1) Record the local atmospheric pressure Pa and ambient temperature Ta before the experiment.

2) Connect the differential pressure gauge (that is, the airflow velocity measurement module) to the measuring point (hole 2), adjust the liquid level at both ends of the U-shaped tube to the same level, and record the initial indication; debugging the motor and steering gear through the remote control can be done. The state required by the experiment is met: the motor speed ratio of the upper, middle and lower channels is 1:2:4, and the steering gear can be freely opened and closed to any specified position.

3) Open the upper triangle adjustment plate, close the lower triangle adjustment plate, and start the motor of the upper channel. During the operation of the motor, keep adding yellow powder at a uniform speed, and observe the airflow in the tail nozzle until the air flow is stable; observe the connection of the upper channel The change of the differential pressure meter (that is, observe the change of the liquid level of the U-shaped pipe 19 connected to the upper channel), and record the differential pressure meter (calculate the differential pressure);

4) Open the middle triangle adjustment plate, slowly start the motor in the middle channel, increase the speed to about 2 times the speed of the motor in the upper channel, and keep adding red powder evenly during the operation of the motor, and pass the powder of yellow and red colors. For the mixing situation, observe the mixing of the airflow at the tail of the nozzle during the motor of the upper channel and the motor of the middle channel, until the airflow is stable; observe the change of the differential pressure gauge connected to the middle channel (observe the liquid in the U-tube 19 connected to the middle channel). Surface change), record the differential pressure count (ie, calculate the differential pressure).

5) Slowly turn off the motor of the upper channel. During the motor off process, through the mixing of yellow and red powders, observe the mixing of the airflow at the tail of the nozzle when the motor in the upper channel is slowly turned off and the motor in the middle channel is normally on. The upper channel motor is completely turned off, and the upper channel triangle adjustment plate is closed.

6) Slowly start the motor of the lower channel and increase the speed to about twice the speed of the motor in the middle channel. During the operation of the motor, keep adding blue powder evenly, and observe the middle channel through the mixing of red and blue powders. When the motor is normally turned on and the lower channel motor is turned on, the air flow at the end of the nozzle is mixed until the air flow is stable; observe the change of the differential pressure gauge connected to the lower channel (that is, observe the liquid level change of the U-shaped tube 19 connected to the lower channel), record Differential pressure count (ie, calculate the differential pressure).

7) Slowly turn off the motor in the middle channel. During the motor off process, through the mixing of red and blue powders, observe the mixing of the airflow at the tail of the nozzle when the motor in the middle channel is slowly turned off and the motor in the lower channel is normally on. The middle channel motor is completely turned off, and the lower channel triangle adjustment plate is closed.

8) Slowly turn off the motor of the lower channel, and the experiment ends; organize the experimental data and analyze the airflow mixing in each state.

The beneficial effects of the utility model are: compared with most existing engine nozzles, the combined power multi-channel nozzle of the present utility model has the following functions: 1. Working in a wide speed range, it can simulate Mach numbers from 0 to 10 The combined cycle of the turbine engine, rocket engine and ramjet engine in the TBCC system for full-speed flight; 2. To study the airflow conditions during mode switching, this nozzle can explore the airflow conditions at the moment of starting and stopping switching of the three engines; 3. To study the airflow mixing in the tail nozzle, the airflow mixing situation in the tail nozzle caused by the difference in the airflow velocity in each pipe can be observed according to the different colors of airflow ejected by different motors.

Claims (6)

1. a combined power multi-channel nozzle test device is characterized in that: comprise a power module, an airflow velocity measurement module, a rectifier module, a pipeline module, a color indicator module, an adjustment mechanism and a support structure; The power module comprises: a motor (10), a power control module and an electric wire (16); The rectification module comprises: a rectification pipe (1), a suction pipe array (3), and a wire mesh (4); The color indicator module includes: a feeding funnel (13), a feeding hose (15), and colored powder; The airflow velocity measurement module includes: a thick hose (18), a U-shaped pipe (19), an adapter (20), a thin hose (21) and a thin metal pipe (22); The pipeline module is a square pipeline (5) and a tail nozzle (8); The adjusting mechanism comprises: a triangular adjusting plate (6), a bearing (7), a square rotating shaft (9) and a steering gear (11); The support structure includes: a motor support (2) and a steering gear support (12); The test device is composed of upper, middle and lower channels. Motors (10) are arranged on the three channels. The motor (10) is connected to the rectifier pipe (1) through the motor support (2), and the power control module is connected to the rectifier pipe (1) through the electric wire (16). ) controls the speed of the motor (10), the rectifier pipe (1) is connected to the square pipe (5), and the square pipe (5) is connected to the tail nozzle (8) together, The shape of the motor support (2) is round and square, and a feeding hose (15) is fixed on the top of the square pipe section of the motor support (2) through a small hole, and the feeding hose (15) is connected with the feeding funnel (13), Two small holes are provided above the square pipe (5) for connecting the airflow velocity measurement module, and the thick hose (18), the adapter (20), the thin hose (21) and the thin metal pipe all have two holes. One of the thin metal pipes (22) is inserted into the middle position of the square pipe (5) through a small hole, and is bent 90 degrees to the horizontal, so that the orifice of the thin metal pipe faces the direction of the incoming air flow, and the thin metal pipe (22) The end on the outside of the square pipe (5) is sequentially connected with one end of the thin hose (21), the adapter (20), the thick hose (18) and the U-shaped pipe (19); The other thin metal pipe (22) is connected to the square pipe (5) through another small hole 2, one port of the thin metal pipe (22) is flush with the inner side of the square pipe (5), and the other thin metal pipe (22) ) is sequentially connected with another thin hose (21), another adapter (20), another thick hose (18) and the other end of the U-shaped pipe (19), A suction pipe array (3) is arranged in the rectification pipe (1), and both ends of the suction pipe array (3) are provided with a wire mesh (4), and the wire mesh (4) fixes the suction pipe array (3) on the rectification pipe (1) Inside, An adjustment device is provided at the connection between the upper and middle passages and the tail nozzle (8), and the adjustment device is a triangular adjustment plate (6). The bearing (7) and the square shaft (9), the side wall of the tail nozzle (8) is equipped with a steering gear support (12), and the steering gear (11) in the steering gear support (12) is fixed with the square shaft (9). (11) Drive the triangular adjustment plate (6) to rotate around the square rotating shaft (9) fixed on the tail nozzle (8) to control the opening and closing of the upper and middle square pipes (5). 2 . The combined power multi-channel nozzle test device according to claim 1 , wherein the triangular adjustment plate ( 6 ) has a hollow design. 3 . 3. A combined power multi-channel nozzle test device as claimed in claim 2, characterized in that: the U-shaped pipe (19) is provided with a scale line, the rectifier pipe (1), the square pipe (5) ) and the tail nozzle (8) are all transparent square pipes made of acrylic material. 4. A combined power multi-channel nozzle test device as claimed in claim 3, characterized in that: the tail nozzle (8) is an inverted triangle shape, and is a unilateral expansion tail nozzle designed by the characteristic line method . 5 . The combined power multi-channel nozzle test device according to claim 4 , wherein the rectifying pipe ( 1 ) and the square pipe ( 5 ) are connected by a concave-convex platform nesting structure. 6 . 6. A combined power multi-channel nozzle test device according to claim 5, wherein the power control module comprises an electronic governor (14), a receiver, a power supply (17) and a remote control.

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