Microtube vibration wind tunnel test test section and test method

Abstract

The invention discloses a microtube vibration wind tunnel test test section and a test method, and belongs to the technical field of heat exchange equipment. The main body of the test section comprises five parts, namely a stable section, a flow guide section, a test section, a microtube core body and a test system, is of a spiral periodic arrangement complex microtube bundle structure, and provides a vibration wind tunnel test. Incoming flow air flows into the testing section from the periphery through the flow guide section and then enters the microcapillary core body. The micropipe core body is an annular cylindrical core body provided with the micropipe row, incoming air flows across the micropipe row in the core body, disturbs the micropipe row and vibrates the micropipe row, finally, the air flows through the exhaust flow guide cone and is exhausted along a channel, and the whole process enables air flow to simulate the real flowing condition. Meanwhile, a laser displacement sensor is adopted to measure vibration displacement, and the structural vibration of the microcapillary is tested. The test section can realize vibration displacement measurement of the complex spiral microcapillary structure, and provides reference for structural reliability evaluation of the heat exchange microcapillary structure in a complex flow field.

Description

Technical Field

[0001] The invention relates to a device for testing micro heat exchange tubes in the field of heat exchange equipment, and in particular to a micro tube vibration wind tunnel test section. Background Art

[0002] With the development of aerospace industry, hypersonic propulsion technology at high Mach numbers has become increasingly important. However, as the flight speed of aerospace vehicles increases, the stagnation temperature of the engine flow gradually increases, the air is difficult to compress, and the performance of the power system drops sharply. At the same time, the thermal protection problem is becoming more serious. Arranging a cooling device (precooling heat exchanger) in the engine intake duct to cool down and cool can effectively solve this problem.

[0003] While the precooling heat exchanger has greatly improved the performance of the aircraft, there are still many problems that need to be further improved, one of which is the vibration of the heat exchange micro-tubes in the heat exchanger core. As the heat exchanger is required to be lightweight and efficient, and the reliability requirements for long-term service are greatly improved, the micro heat exchange tube bundle will vibrate when it is working due to the disturbance of the high-temperature air flow outside the tube, the pressure of the helium in the tube, and the thermal stress caused by the high temperature. This is an unstable phenomenon that will seriously damage the micro-tube structure, causing great safety hazards and affecting the normal operation of the aerospace vehicle. Therefore, it is necessary to study the vibration of the micro-tube bundle. Summary of the invention

[0004] The purpose of the present invention is to provide a micro-tube vibration wind tunnel test section to meet the needs of micro-tube vibration research. By building an air circulation channel, a micro-tube core and an experimental test data acquisition system, and adjusting the incoming air flow rate, the vibration displacement test of the complex spiral heat exchange micro-tube structure under different flow rate conditions is completed, providing a reference for the structural reliability evaluation of the heat exchange micro-tube structure in a complex flow field.

[0005] The purpose of the present invention can be achieved through the following technical solutions:

[0006] A micro-tube vibration wind tunnel test section, comprising a stabilizing section, a flow guide section, a test section and an exhaust section, wherein two adjacent sections are fixedly connected;

[0007] The stabilizing section is provided with a pressure measuring hole for installing a pressure monitoring system;

[0008] The guide cone in the guide section serves as an inner liner, and the guide cone is connected to the outer cavity of the guide section through a guide cone support plate, so that a guide cavity is formed between the guide cone and the outer cavity of the guide section; a support platform is arranged at the tail end of the guide cone;

[0009] The exhaust section adopts an exhaust port arranged at the center of the exhaust end plate;

[0010] The test section comprises a test section shell and a test cavity, wherein a micro heat exchange tube bundle and a core support seat are arranged in the test cavity, wherein the micro heat exchange tube bundle is arranged on the core support seat, and the core support seat is fixed on the support platform; one end of the micro heat exchange tube of the micro heat exchange tube bundle is arranged on the helium gas inlet manifold, and the other end is arranged on the helium gas outlet manifold; the helium gas inlet manifold and the helium gas outlet manifold are arranged on the core support base and the exhaust end plate of the exhaust section; a support plate for supporting and fixing the micro heat exchange tube is arranged on the micro heat exchange tube bundle;

[0011] An exhaust guide cone is arranged at the center of the core support seat, and the tip of the exhaust guide cone faces the exhaust port; the fine heat exchange tube bundle is spirally shaped and surrounds the outside of the exhaust guide cone;

[0012] A measuring window with a transparent window is arranged on the shell of the test section, and a laser displacement sensor is arranged in the measuring outlet;

[0013] The inside of the stabilizing section is connected to one end of the flow guiding cavity, the other end of the flow guiding cavity is connected to the periphery of the test cavity in the test section, and the outlet of the test cavity is connected to the exhaust port;

[0014] By rotating the test section shell and changing the circumferential position of the laser displacement sensor, the vibration of the micro heat exchange tube bundle at different circumferential positions is measured.

[0015] Furthermore, a plurality of groups of support plates are arranged on the micro heat exchange tube bundle, and the central angle between two adjacent groups of support plates is 30°-60°.

[0016] Furthermore, the stabilizing section is communicated with an air inlet passage of the wind tunnel, and the exhaust port is connected to the exhaust passage.

[0017] A test method for a micro-tube vibration wind tunnel test section comprises the following steps:

[0018] S1. Build the displacement acquisition system and pressure monitoring system, complete the debugging of the laser displacement sensor in a static state, and then calibrate and debug the pressure monitoring system;

[0019] S2. Select different sampling frequencies and sampling points for vibration displacement acquisition debugging, select the laser displacement sensor sampling frequency and sampling points P1, P2...Pn;

[0020] S3. Start the pressure monitoring system and displacement acquisition system, start scanning and monitoring the inlet static pressure and total pressure of the stable section, and start collecting the vibration displacement of the sample point P1 on the micro heat exchange tube bundle; then start the fan of the wind tunnel to supply air to the test device;

[0021] S4. By adjusting the valve opening of the wind tunnel air inlet channel and the monitored pressure data, the valve opening is adjusted to the test condition 1. The incoming air enters the test device, stabilizes the airflow in the stable section, and then flows into the guide section, where it is diverted by the conical guide cone so that the airflow can flow into the test cavity of the test section from all sides; after the incoming air flows into the test cavity from all sides, it sweeps across the fine heat exchange tube bundle; it is guided to the exhaust section by the exhaust guide cone and flows out from the exhaust port; after stabilization, the vibration displacement collection is started, and the test data collection is repeated at equal time intervals;

[0022] The laser displacement sensor emits high-frequency laser through the transparent window, which is reflected back to the laser receiver at the sampling point of the micro heat exchange tube bundle. The distance between the laser displacement sensor and the sampling point is measured using the triangulation method, and then the displacement at the sampling point is obtained by the distance change at different times.

[0023] S5. After collecting the vibration displacement data of the test condition 1, adjust the valve opening of the wind tunnel ventilation channel to the test condition 2 again, repeat step S4 to collect data, and then adjust the valve opening to other conditions again until the vibration test data of all test conditions of the upper sample point P1 are collected;

[0024] S6. Unfasten the fixing bolts between the guide section and the test section, and between the test section and the exhaust section, rotate the test section housing, and re-tighten the bolts, thereby changing the vibration measurement point of the micro heat exchange tube bundle to the next sample point P2; repeat the test process of the above steps to complete the vibration test data collection of all test conditions of the sample point P2 on the micro heat exchange tube bundle;

[0025] S7. Repeat step S6 until the micro-tube vibration test of all sample points under various test conditions is completed, and the test process is now completed.

[0026] A micro-tube vibration wind tunnel test section comprises an air circulation channel, a micro-tube core body and a test data acquisition system; the air circulation channel comprises a stabilizing section, a flow guide section, a test section and an exhaust section; the stabilizing section is a cylinder with flanges at both ends, and a pressure measuring hole is provided on the cylinder; the flow guide section is a conical cylinder with flanges at both ends, and a flow guide cone is installed in the interior thereof through six flow guide cone support plates connected thereto; the test section is a combination of a cylinder and a conical cylinder, and a measuring window is provided on the cavity shell thereof for installing a laser displacement sensor; the exhaust section is composed of a cover plate with bolt through holes and a section of exhaust channel.

[0027] The incoming air enters the test device, stabilizes the airflow in the stabilization section, and then flows into the guide section, where it is diverted by the conical guide cone so that the airflow can flow into the test section from all sides; after the incoming air flows into the test cavity from all sides, it sweeps across the micro heat exchange tube bundle; after sweeping across the micro heat exchange tube bundle, the air flows out from the exhaust section.

[0028] The core support and the micro heat exchange tube bundle are installed in the test section, which are fixed by bolts connected between the core support and the support platform on the bottom of the guide cone inside the guide section; the micro heat exchange tube bundle is installed and fixed on the core support; there is an exhaust guide cone on the bottom of the core support, so that the air passes through the micro tube bundle, merges through the guide, and then flows to the exhaust section and out. The micro heat exchange tube bundle is composed of four rows of micro tubes arranged in an alternating manner. The micro tubes are spiral-shaped, and the two ends are welded and fixed on the helium inlet header and the helium outlet header.

[0029] The guide cone of the guide section is used as the inner tank, which is fixed to the outer cavity of the guide section through six guide cone support plates, while the core support is fixed to the support platform extending from the inner tank through bolts. At the same time, the upper ends of the helium inlet manifold and the helium outlet manifold of the micro heat exchange tube bundle extend from the holes on the exhaust end plate and are fixed by bolts; the micro heat exchange tube bundle is installed between the core support and the exhaust section outer cover and fixed in the test section; the core support and the exhaust section outer cover are fixedly connected through five support columns.

[0030] The test system includes a pressure test system and a vibration measurement system; the pressure test system consists of a pressure probe, a micro pressure tube, a pressure scanning valve, a computer and supporting pressure scanning detection software. The pressure probe is installed and fixed in the pressure measuring hole on the stable section. The pressure scanning valve is used to collect data and measure the total static pressure of the incoming flow in the stable section, so as to obtain the incoming flow velocity. The vibration measurement system includes a laser displacement sensor, a computer and supporting displacement test software. The laser displacement sensor is installed on the test section housing. By measuring the displacement change of the laser displacement sensor from the measuring point on the micro tube, the vibration data of the micro tube is calculated.

[0031] In the present invention, the spiral complex microtube bundle model used as the test object is composed of staggered arrangement of microtubes with a longitudinal diameter of 1.0 mm.

[0032] In the test, the incoming air flow rate can be adjusted to carry out different speed conditions test, and the total pressure and static pressure can be measured by the pressure test system to obtain the inlet flow rate condition; the pressure probe is installed on the stable section, and there are total pressure and static pressure measuring holes on the probe, which is connected to the pressure scanning valve through a fine pressure measuring tube, and then the pressure data can be transmitted to the computer through the data line. Through the matching pressure scanning detection software, the real-time pressure data in the stable channel can be scanned and obtained, so that the inlet flow rate of the stable pressure section can be calculated by the total pressure and static pressure;

[0033] The micro-tube vibration test sensor is a laser displacement sensor, which is installed on the outer shell of the test section cavity and fixed with the measurement window of the test section outer shell. The vibration displacement of the heat exchange tube is measured through the transparent window of the acrylic plate. The laser displacement sensor emits a high-frequency laser through the acrylic transparent window, which is reflected back to the laser receiver at each measuring point on the tube, thereby using the triangulation measurement method to complete the distance measurement between the laser displacement sensor and the measuring point, and then the displacement at the measuring point can be obtained through the distance change at different times.

[0034] When the measuring point needs to be changed, the position of the laser displacement sensor relative to the test section shell remains unchanged. By loosening the bolts connecting the test section and the guide section and rotating the test section shell, the measuring point of the laser displacement sensor can be changed, thereby measuring the vibration of different circumferential positions of the micro heat exchange tube bundle.

[0035] Compared with the prior art, the present invention has the following beneficial effects:

[0036] The present invention is aimed at the vibration test of the complex spiral heat exchange micro-tube structure. The airflow is made to flow into the micro-tube core evenly from all sides through the guide channel, thereby sweeping across the micro-tube bundle, so that the whole process of air flow simulates the real flow situation as much as possible; at the same time, the present invention uses a laser displacement sensor to measure the displacement change of the laser displacement sensor from the measuring point on the micro-tube through the transparent window of the transparent acrylic plate, so as to calculate and obtain the vibration data of the micro-tube, and by rotating the test section shell, the measuring point position of the laser displacement sensor on the micro-tube can be changed, and the vibration measurement of different positions of the micro-heat exchange tube bundle in the circumferential direction can be realized, so as to obtain the vibration law of the micro-tube under different working conditions, and provide a reference for the structural reliability evaluation of the heat exchange micro-tube structure in a complex flow field. BRIEF DESCRIPTION OF THE DRAWINGS

[0037] Figure 1 It is a structural schematic diagram of a micro-tube vibration wind tunnel test section of the present invention.

[0038] Figure 2 It is a schematic diagram of the exploded structure of the micro-tube vibration wind tunnel test section of the present invention.

[0039] Figure 3 It is a cross-sectional view of a test section of a micro-tube vibration wind tunnel test of the present invention.

[0040] Figure 4 It is a schematic diagram of the micro-tube bundle structure of the micro-tube vibration wind tunnel test section of the present invention.

[0041] Figure 5 It is a schematic diagram of measuring points of the microtube vibration test of the present invention.

[0042] Figure 6 It is a schematic diagram of the measuring point conversion operation of the microtube vibration test of the present invention.

[0043] In the figure: 1. stabilizing section, 1a. air inlet, 2. guide section, 2a. guide cone, 2b. support platform, 2c. guide cavity, 2d. guide section outer cavity, 2e. guide cone support plate, 3. test section, 3a. test cavity, 3b. exhaust guide cone, 3c. test cavity shell, 4. core support plate, 5. micro heat exchange tube bundle, 5a. micro heat exchange tube, 5b. helium inlet manifold, 5c. helium outlet manifold, 6. exhaust section, 6a. exhaust end plate, 6b. exhaust port, 7. pressure measuring hole, 8. laser displacement sensor, 9. wind tunnel inlet channel, 10. exhaust channel. DETAILED DESCRIPTION

[0044] The micro-tube vibration wind tunnel test section of the present invention is described in detail below with reference to the accompanying drawings and specific implementation schemes.

[0045] The micro-tube vibration wind tunnel test section includes an air circulation channel, a micro-tube core body and a test data acquisition system.

[0046] S1, the air flow channel includes a stable section 1, a guide section 2, a test section 3 and an exhaust section 6; the incoming air enters the test device, stabilizes the airflow in the stable section 1, and then flows into the guide section 2, where it is divided by a conical guide cone so that the airflow can flow into the test section 3 from all sides; after the incoming air flows into the cavity of the test section 3 from all sides, it flows in the micro-tube core and crosses the micro-heat exchange tube bundle 5; after the air crosses the micro-heat exchange tube bundle 5, it flows out from the exhaust section 6;

[0047] S2, the micro-tube core includes a core support 4 and a micro-heat exchange tube bundle 5; the micro-tube core is installed in the test section 3, and is bolted and fixed to the bottom surface platform of the guide cone inside the guide section 2 through the core support 4; the micro-tube core is installed and fixed on the core support 4 through the micro-heat exchange tube bundle 5; there is a guide cone at the bottom of the core support 4, so that the air passes through the micro-tube bundle 5, merges through the guide, and then flows to the exhaust section 6 to flow out; the micro-heat exchange tube bundle 5 is composed of four rows of micro-tubes arranged in an alternating manner, and the micro-tubes are spiral-shaped, and both ends are welded and fixed on the helium inlet and outlet manifolds;

[0048] S3, the test data acquisition system includes a pressure test system and a vibration measurement system; the pressure test system is composed of a pressure probe, a micro pressure tube, a pressure scanning valve, a computer and a matching pressure scanning detection system. The pressure probe is installed and fixed in the pressure measuring hole 7 on the stable section 1, and data is collected through the pressure scanning valve to measure the total static pressure of the incoming flow in the stable section 1, so as to obtain the incoming flow velocity; the vibration measurement system is composed of a laser displacement sensor 8, a computer and matching displacement test software. The laser displacement sensor 8 is installed on the test section housing 3c, and the vibration data of the micro tube is calculated by measuring the displacement change of the laser displacement sensor 8 from the measuring point on the micro tube;

[0049] By adjusting the incoming air flow rate to carry out tests under different speed conditions, the pressure test system can obtain the inlet flow rate condition by measuring the total static pressure of the stable section 1 through a pressure probe.

[0050] The microtube vibration test sensor is a laser displacement sensor 8.

[0051] By rotating the test section housing 3 c , the circumferential position of the laser displacement sensor can be changed, thereby measuring the vibration of the micro heat exchange tube bundle 5 at different circumferential positions.

[0052] like Figures 1 to 3 As shown, a micro-tube vibration wind tunnel test section includes a stabilizing section 1, a flow guide section 2, a test section 3, a core support 4, a micro heat exchange tube bundle 5, an exhaust section 6, a pressure measuring hole 7 on the stabilizing section, a laser displacement sensor 8, a pressure probe, and a computer.

[0053] The stabilizing section 1 is a cylinder with flanges at both ends, and a pressure measuring hole 7 is provided on the cylinder. The diversion section 2 is a conical cylinder with flanges at both ends, and a diversion cone 2a is installed inside the cylinder through six diversion cone support plates 2e. The testing section 3 is a combination of a cylinder and a conical cylinder, and a measuring window 8a is provided on the cavity shell thereof for convenient installation of a laser displacement sensor 8. The exhaust section 6 is composed of a cover plate with bolt through holes and an exhaust channel.

[0054] The test equipment in the micro-tube vibration wind tunnel test section is as follows: Figure 2 Installed sequentially, the stabilizing section 1 and the guide section 2 are connected by bolts, wherein the guide section 2 has a guide cone 2a, which is welded to the outer cavity 2d of the guide section through the rib baffles around it; then the test section 3 and the guide section 2 are also connected by bolts, the micro-tube core in the test section 3 is composed of a core support 4 and a micro-heat exchange tube bundle 5, and is installed on the supporting platform 2b connected to the guide cone in the guide section 2 by bolt connection, and at the same time, the upper end of the helium inlet and outlet gas collecting pipes of the micro-heat exchange tube bundle 5 extends from the hole of the exhaust end plate 6a and is fixed by bolt connection, so that the micro-tube core can be fixed in the test section 3.

[0055] The stable section 1 is connected to the laboratory wind tunnel ventilation channel. During the experiment, the test conditions are adjusted by controlling the flow opening of the laboratory wind tunnel ventilation channel, and the pressure probe is installed on the stable section 1. There are total pressure and static pressure measuring holes on the probe. It is connected to the pressure scanning valve through a micro pressure measuring tube, and then the pressure data can be transmitted to the computer through a data cable. Through the supporting pressure scanning detection software, the real-time pressure data in the stable channel can be scanned and obtained, so that the inlet flow rate of the stable section can be calculated by the total pressure and static pressure.

[0056] There is a measuring window 8a on the test section 3, and an acrylic transparent window 8b is installed in the measuring window. At the same time, the laser displacement sensor 8 is fixedly installed on the measuring window 8a by bolts. When the measuring point needs to be changed, the position of the laser displacement sensor 8 relative to the cavity of the test section 3 remains unchanged. By loosening the bolts connecting the test section 3 and the guide section 2 and rotating the test section shell 3c, the measuring point of the laser displacement sensor 8 can be changed, thereby measuring the vibration of the micro heat exchange tube bundle 5 at different circumferential positions, such as Figure 5 , Figure 6 shown.

[0057] The laser displacement sensor 8 emits high-frequency laser through the transparent acrylic window 8b, which is reflected back to the laser receiver at each measuring point on the capillary, thereby using the triangulation measurement method to measure the distance between the laser displacement sensor 8 and the measuring point, and then the displacement at the measuring point can be obtained through the distance change at different times.

[0058] The incoming air enters the test device, stabilizes the airflow in the stabilizing section 1, and then flows into the guide section 2, where it is diverted by the conical guide cone so that the airflow can flow into the test section 3 from all sides; after the incoming air flows into the cavity of the test section 3 from all sides, it sweeps across the fine heat exchange tube bundle 5. After sweeping across the fine heat exchange tube bundle 5, the air is guided by the guide cone on the core support 4 to flow out from the exhaust section 6.

[0059] Figure 4 The actual picture of the heat exchange tube bundle experimental part in the heat exchange core is shown in Figure 1. It consists of 4 rows of heat exchange tube bundles 5a arranged in a staggered manner. The horizontal tube spacing between the heat exchange tube bundles is 2.5 mm, the longitudinal tube spacing is 2 mm, the center distance between two adjacent rows is 1.25 mm, the outer diameter of the tube is 1 mm, and the inner diameter is 0.8 mm. The two ends of the tube bundle are connected to the helium inlet and outlet gas collecting pipes 5b and 5c respectively. Each heat exchange tube is inserted into the small hole on the helium inlet and outlet gas collecting pipes, and each heat exchange tube is welded and connected on the surface of the helium inlet and outlet main pipe, and then connected to the gas collecting pipes at both ends. Each row of heat exchange tubes is connected and fixed by 13 support plates 5d. The angle between two adjacent support plates and the center line is 30°. The material of the heat exchange tube is GH4169.

[0060] The test steps of the micro-tube vibration wind tunnel test section provided by the present invention are as follows:

[0061] Step (1) According to the test plan, assemble the experimental device components, and build the displacement acquisition system and pressure monitoring system to form a vibration test system. In addition, complete the debugging of the laser displacement sensor 8 related settings in a static state, and also check and debug the pressure monitoring system. Thus, the construction of the microtube vibration wind tunnel test section is completed.

[0062] Step (2) selects different sampling frequencies and sampling points for vibration displacement acquisition debugging, so as to select the appropriate sampling frequency and sampling points of the laser displacement sensor 8, thereby avoiding the loss of some information due to inappropriate sampling frequency and sampling points. At this point, the preparation work is completed and the experiment officially begins.

[0063] Step (3) starts the pressure monitoring system and the displacement acquisition system, starts scanning and monitoring the inlet static pressure and total pressure of the stable section 1, and starts collecting the vibration displacement of the measuring point P1 on the micro heat exchange tube bundle 5; then starts the fan of the large flow wind tunnel to supply air to the test device.

[0064] Step (4) By adjusting the valve opening of the wind tunnel ventilation channel and the monitored pressure data, the valve opening is adjusted to test condition 1, and after stabilization for a period of time, vibration displacement collection is started, and repeated test data collection is performed at intervals of 1 minute to reduce test errors.

[0065] After the vibration displacement data of test condition 1 is collected in step (5), the valve opening of the wind tunnel ventilation channel is adjusted to test condition 2 again, and the vibration displacement collection of step (4) is repeated, and then the valve opening is adjusted again to other conditions until the micro-tube vibration test data of all test conditions of the upper measuring point P1 are collected.

[0066] Step (6) Unfasten the fixing bolts between the guide section 2 and the test section 3, and between the test section 3 and the exhaust section 6, rotate the test section shell 3c clockwise by 30°, and re-tighten the bolts, thereby changing the vibration measurement point of the micro heat exchange tube bundle 5 to point P2; repeat the test process of steps (3) to (5) to complete the micro tube vibration test data collection of all test conditions at the measurement point P1 on the micro heat exchange tube bundle 5.

[0067] Step (7) replaces the vibration measuring point of the micro heat exchange tube bundle 5 again, and performs micro tube vibration test under various test conditions, until data collection is completed at the five vibration measuring points on the selected micro heat exchange tube bundle 5. At this point, the test process is completed, and the test data is processed and analyzed to obtain the vibration law and vibration characteristics of the micro heat exchange tube bundle 5 under different working conditions, thereby meeting the test requirements.

[0068] The above description is only a description of the preferred embodiments of the present invention, and is not intended to limit the scope of the present invention. Any changes or modifications made by any person skilled in the art based on the above disclosed technical contents shall be regarded as equivalent effective embodiments and shall fall within the scope of protection of the technical solution of the present invention.

Claims

1. A micro-tube vibration wind tunnel test section, characterized in that: It comprises a stabilizing section (1), a flow guide section (2), a testing section (3) and an exhaust section (6), wherein two adjacent sections are fixedly connected; The stabilizing section (1) is provided with a pressure measuring hole (7) for installing a pressure monitoring system; The guide cone (2a) in the guide section (2) serves as an inner liner; the guide cone (2a) is connected to the guide section outer cavity (2d) via a guide cone support plate (2e); a guide cavity (2c) is formed between the guide cone (2a) and the guide section outer cavity (2d); a support platform (2b) is provided at the rear end of the guide cone (2a); The exhaust section (6) adopts an exhaust port (6b) arranged at the center of the exhaust end plate (6a); The test section (3) comprises a test section shell (3c) and a test chamber (3a); a micro heat exchange tube bundle (5) and a core support seat (4) are arranged in the test chamber (3a); the micro heat exchange tube bundle (5) is arranged on the core support seat (4), and the core support seat (4) is fixed on the support platform (2b); one end of the micro heat exchange tube (5a) of the micro heat exchange tube bundle (5) is arranged on the helium gas inlet manifold (5b), and the other end is arranged on the helium gas outlet manifold (5c); the helium gas inlet manifold (5b) and the helium gas outlet manifold (5c) are arranged on the core support seat (4) and the exhaust end plate (6a) of the exhaust section (6); a support plate (5d) for supporting and fixing the micro heat exchange tube (5a) is arranged on the micro heat exchange tube bundle (5); An exhaust guide cone (3b) is arranged at the center of the core support seat (4), and the tip of the exhaust guide cone (3b) faces the exhaust port (6b); the fine heat exchange tube bundle (5) is spirally shaped and surrounds the outside of the exhaust guide cone (3b); The test section housing (3c) is provided with a measuring window (8a) equipped with a transparent window (8b), and a laser displacement sensor (8) is provided in the measuring outlet (8a); The interior of the stabilizing section (1) is in communication with one end of the flow guiding cavity (2c), the other end of the flow guiding cavity (2c) is in communication with the periphery of the test cavity (3a) in the test section (3), and the outlet of the test cavity (3a) is in communication with the exhaust port (6b); By rotating the test section housing (3c), the circumferential position of the laser displacement sensor (8) is changed, and vibrations of the micro heat exchange tube bundle (5) at different circumferential positions are measured.

2. A micro-tube vibration wind tunnel test section according to claim 1, characterized in that: A plurality of groups of support plates (5d) are arranged on the fine heat exchange tube bundle (5), and the central angle between two adjacent groups of support plates (5d) is 30°-60°.

3. A micro-tube vibration wind tunnel test section according to claim 1, characterized in that: The stabilizing section (1) is in communication with a wind tunnel air inlet passage (9), and the exhaust port (6b) is connected to an exhaust passage (10).

4. The test method for a micro-tube vibration wind tunnel test section according to claim 1 is characterized in that: The following steps are involved: S1, build a displacement acquisition system and a pressure monitoring system, complete the debugging of the laser displacement sensor (8) in a static state, and then calibrate and debug the pressure monitoring system; S2. Select different sampling frequencies and sampling points for vibration displacement acquisition debugging, select the laser displacement sensor (8) sampling frequency and sampling points P1, P2 ... ... Pn; S3. Start the pressure monitoring system and the displacement acquisition system, start scanning and monitoring the inlet static pressure and total pressure of the stable section (1), and start collecting the vibration displacement of the sample point P1 on the micro heat exchange tube bundle (5); then start the fan of the wind tunnel to supply air to the test device; S4. By adjusting the valve opening of the wind tunnel air inlet passage and the monitored pressure data, the valve opening is adjusted to the test condition 1, the incoming air enters the test device, stabilizes the airflow in the stabilizing section (1), and then flows into the guide section (2), where the conical guide cone (2a) divides the airflow, so that the airflow can flow from all sides into the test cavity (3a) of the test section (3); After the air flows into the test chamber (3a) from all sides, it sweeps across the fine heat exchange tube bundle (5); it is guided to the exhaust section (6) by the exhaust guide cone (3b) and flows out from the exhaust port (6b); after stabilization, vibration displacement collection is started, and test data collection is repeated at equal time intervals; The laser displacement sensor (8) emits a high-frequency laser through the transparent window (8b), which is reflected back to the laser receiver at the sampling point of the micro heat exchange tube bundle. The distance between the laser displacement sensor and the sampling point is measured using a triangulation method, and the displacement at the sampling point is then obtained by the change in distance at different times. S5. After collecting the vibration displacement data of the test condition 1, adjust the valve opening of the wind tunnel ventilation channel to the test condition 2 again, repeat step S4 to collect data, and then adjust the valve opening to other conditions again until the vibration test data of all test conditions of the upper sample point P1 are collected; S6. Unfasten the fixing bolts between the flow guide section (2) and the test section (3), and between the test section (3) and the exhaust section (6), rotate the test section housing (3c), and re-tighten the bolts, thereby changing the vibration measurement point of the micro heat exchange tube bundle (5) to the next sample point P2; repeat the test process of the above steps to complete the collection of vibration test data of all test conditions of the sample point P2 on the micro heat exchange tube bundle (5); S7. Repeat step S6 until the micro-tube vibration test of all sample points under each test condition is completed, and the test process is now completed.

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