Microtube vibration wind tunnel test section and test method

Abstract

The microtube vibration wind tunnel test section and test method belong to the technical field of heat exchange equipment. The main body of the test section consists of five parts: a stabilization section, a flow guide section, a test section, a microtube core, and a test system. It is a complex microtube bundle structure with a spiral periodic arrangement, providing a vibration wind tunnel test. The flow guide section allows incoming air to flow into the test section from all sides and then into the microtube core. The microtube core is an annular cylindrical core with microtube rows installed. The incoming air passes across the microtube bundle within the core, causing disturbances and vibrations. Finally, it passes through the exhaust guide cone and is discharged along the channel. The entire process simulates the air flow conditions of real flow. At the same time, a laser displacement sensor is used to measure the vibration displacement and test the structural vibration of the microtube. This test section can realize the vibration displacement measurement of complex spiral microtube structures, providing a reference for the structural reliability assessment of heat exchange microtube structures in complex flow fields.

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, hypersonic propulsion technology at high Mach numbers has become increasingly important. However, as aerospace vehicles increase in speed, the stagnation temperature of the engine airflow gradually increases, making it difficult to compress the air, and the power system performance drops sharply. At the same time, the thermal protection problem becomes more serious. Placing a cooling device (pre-cooling heat exchanger) in the engine inlet duct to reduce the temperature can effectively solve this problem.

[0003] While significantly improving aircraft performance, pre-cooling heat exchangers also present numerous challenges that require further improvement, one of which is the vibration of the heat exchange microtubes within the heat exchanger core. As heat exchangers become increasingly lightweight and efficient, and as they face increased reliability demands for long-term operation, the microtube bundles experience structural vibration during operation due to disturbances from the incoming high-temperature airflow outside the tubes, the pressure of the helium within the tubes, and the thermal stresses caused by high temperatures. This is an unstable phenomenon that can severely damage the microtube structure, creating significant safety hazards and impacting the normal operation of aerospace vehicles. Therefore, research on the vibration of microtube bundles is necessary. Summary of the Invention

[0004] The purpose of the present invention is to provide a microtube vibration wind tunnel test section to meet the needs of microtube vibration research. By constructing an air circulation channel, a microtube 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 microtube structure under different flow rate conditions is completed, providing a reference for the structural reliability evaluation of the heat exchange microtube structure in complex flow fields.

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

[0006] A micro-tube vibration wind tunnel test section comprises 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 container, 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 provided 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 includes a test section shell and a test cavity. A micro heat exchange tube bundle and a core support seat are arranged in the test cavity. The micro heat exchange tube bundle is arranged on the core support seat, and the core support seat is fixed to the support platform. One end of the micro heat exchange tube of the micro heat exchange tube bundle is arranged on the helium inlet manifold, and the other end is arranged on the helium outlet manifold. The helium inlet manifold and the helium 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 provided on the micro heat exchange tube bundle.

[0011] An exhaust guide cone is provided at the center of the core support seat, with the tip of the exhaust guide cone facing 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 provided on the test section housing, and a laser displacement sensor is provided in the measuring outlet;

[0013] The interior of the stabilizing section is in communication with one end of the diversion cavity, the other end of the diversion cavity is in communication with the periphery of the test cavity in the test section, and the outlet of the test cavity is in communication with 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 provided 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 the wind tunnel air inlet channel, and the exhaust port is connected to the exhaust channel.

[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 to scan and monitor the static and total pressures at the inlet of the stable section, and to collect the vibration displacement of sample point P1 on the micro-heat exchange tube bundle. Then, start the wind tunnel fan to supply air to the test device.

[0021] S4. By adjusting the valve opening of the wind tunnel inlet passage and monitoring pressure data, the valve opening is adjusted to test condition 1. Incoming air enters the test apparatus, stabilizes in the stabilization section, and then flows into the guide section, where it is divided by a conical guide cone, allowing the airflow to flow from all sides into the test cavity of the test section. After entering the test cavity from all sides, the air flows across the micro heat exchange tube bundle. The exhaust guide cone guides the air to the exhaust section and flows out of the exhaust port. After stabilization, vibration displacement acquisition is started, and test data acquisition is repeated at regular intervals.

[0022] The laser displacement sensor emits a high-frequency laser through a 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 the displacement at the sampling point is then obtained by the change in distance at different times.

[0023] S5. After collecting the vibration displacement data for test condition 1, adjust the valve opening of the wind tunnel ventilation channel to 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 collection for all test conditions of the upper sample point P1 is completed;

[0024] S6. Loosen the bolts securing the guide section to the test section, and the test section to the exhaust section. Rotate the test section housing and re-tighten the bolts, thereby moving the vibration measurement point of the micro heat exchange tube bundle to the next sample point, P2. Repeat the above test steps to complete the vibration test data collection for all test conditions at 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 on the cylinder; the flow guide section is a conical cylinder with flanges at both ends, a flow guide cone being installed inside the cylinder via six flow guide cone support plates; the test section is a combination of a cylinder and a conical cylinder, a measurement window being opened on its cavity shell for installing a laser displacement sensor; the exhaust section is composed of a cover plate with bolt through holes and an 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, allowing the airflow to flow into the test section from all sides; after the 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 micro-heat exchange tube bundle were installed in the test section, bolted to the core support and secured to the support platform at the bottom of the guide cone within the guide section. The micro-heat exchange tube bundle was mounted and secured to the core support. An exhaust guide cone was located at the bottom of the core support, allowing air to pass across the micro-tube bundle, converge through the guide, and then flow to the exhaust section before exiting. The micro-heat exchange tube bundle consists of four rows of staggered micro-tubes. The micro-tubes are spiral-shaped, with their ends welded to the helium inlet and outlet manifolds, respectively.

[0029] The guide cone of the guide section serves as the inner liner, secured to the outer cavity of the guide section via six guide cone support plates. The core support is bolted to the support platform extending from the inner liner. The upper ends of the helium inlet and outlet manifolds of the micro heat exchange tube bundle extend through holes in the exhaust end plate and are secured with bolts. The micro heat exchange tube bundle is installed between the core support and the exhaust section cover, securing it within the test section. The core support and the exhaust section cover are fixed together by 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 in the pressure measuring hole on the stable section. The pressure scanning valve collects data and measures the total static pressure of the incoming flow in the stable section, thereby obtaining the incoming flow velocity. The vibration measurement system includes a laser displacement sensor, a computer, and supporting displacement testing 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 can be calculated.

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

[0032] During the test, the incoming air flow rate can be adjusted to carry out tests under different speed conditions. At the same time, 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. There are total pressure and static pressure measuring holes on the probe. It is connected to the pressure scanning valve through a fine pressure measuring tube. The pressure data can be transmitted to the computer through the data line. The real-time pressure data in the stable channel can be scanned and obtained through the supporting pressure scanning detection software, 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. The laser displacement sensor is installed on the outer shell of the test section cavity and is fixed to the measurement window of the test section 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, and the light 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. Then, the displacement at the measuring point can be obtained by the distance change at different times.

[0034] When the measurement 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 measurement 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 vibration testing of complex spiral heat exchange micro-tube structures. Through the guide channel, the air flow is uniformly directed into the micro-tube core from all sides, thereby sweeping across the micro-tube bundle, so that the entire air flow process simulates the real flow conditions 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 a transparent window of a transparent acrylic plate, thereby calculating and obtaining the vibration data of the micro-tube. Moreover, by rotating the test section shell, the measuring point position of the laser displacement sensor on the micro-tube can be changed, realizing vibration measurement of different circumferential positions of the micro-heat exchange tube bundle, thereby obtaining the vibration law of the micro-tube under different working conditions, and providing 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 the microtube 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 microtube vibration wind tunnel test of the present invention.

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

[0041] Figure 5 It is a schematic diagram of measuring points for 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. Stable 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 section outer 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 plans.

[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 stabilizing section 1, a flow guide section 2, a test section 3, and an exhaust section 6. The incoming air enters the test device, stabilizes in the stabilizing section 1, and then flows into the flow guide section 2, where it is divided by a conical flow guide cone, allowing the airflow to flow from all sides into the test section 3. After the air flows into the cavity of the test section 3 from all sides, it flows within the microtube core and crosses the microheat exchange tube bundle 5. After crossing the microheat exchange tube bundle 5, the air flows out from the exhaust section 6.

[0047] S2, the microtube core includes a core support 4 and a microheat exchange tube bundle 5; the microtube core is installed in the test section 3 and is bolted to the bottom platform of the guide cone inside the guide section 2 via the core support 4; the microtube core is fixed to the core support 4 via the microheat exchange tube bundle 5; a guide cone is provided at the bottom of the core support 4, so that after air passes through the microtube bundle 5, it is combined through the guide and then flows to the exhaust section 6 for outflow; the microheat exchange tube bundle 5 is composed of four rows of microtubes arranged in an alternating pattern. The microtubes are spiral-shaped, and their ends are welded and fixed to 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 consists of a pressure probe, a micro-pressure tube, a pressure scanning valve, a computer, and a supporting pressure scanning detection system. The pressure probe is installed and fixed in the pressure measuring hole 7 on the stable section 1. The pressure scanning valve is used to collect data, measuring the total pressure and static pressure of the incoming flow in the stable section 1, thereby obtaining the incoming flow velocity. The vibration measurement system consists of a laser displacement sensor 8, a computer, and supporting displacement testing software. The laser displacement sensor 8 is installed on the test section housing 3c. By measuring the displacement change of the laser displacement sensor 8 from the measuring point on the micro-tube, the vibration data of the micro-tube is calculated.

[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 the 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 vibrations 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 stabilization section 1 is a cylinder with flanges at both ends, and there is a pressure measuring hole 7 on the cylinder. The diversion section 2 is a conical cylinder with flanges at both ends, and a diversion cone 2a is installed inside it through six diversion cone support plates 2e. The test section 3 is a combination of a cylinder and a conical cylinder, and a measuring window 8a is opened on its cavity shell to facilitate the installation of the laser displacement sensor 8. The exhaust section 6 consists 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 The stabilizing section 1 and the guide section 2 are installed sequentially, with the stabilizing section 1 being connected to the guide section 2 by bolts. There is a guide cone 2a in the guide section 2, which is welded to the outer cavity 2d of the guide section through the rib baffles on all sides. The testing section 3 is then connected to the guide section 2 by bolts as well. The microtube core in the testing section 3 is composed of a core support 4 and a microheat exchange tube bundle 5, and is installed on the supporting platform 2b connected to the guide cone in the guide section 2 by bolts. At the same time, the upper ends of the helium inlet and outlet manifolds of the microheat exchange tube bundle 5 extend from the holes in the exhaust end plate 6a and are fixed by bolts, so that the microtube core can be fixed in the testing 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. 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. 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, and the inlet flow rate of the stable section can be obtained by calculating the total pressure and static pressure.

[0056] On the test section 3, there is a measurement window 8a, in which an acrylic transparent window 8b is installed. At the same time, the laser displacement sensor 8 is fixed to the measurement window 8a by bolts. When the measurement 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 measurement point of the laser displacement sensor 8 can be changed, thereby measuring the vibration of different positions of the micro heat exchange tube bundle 5 in the circumferential direction, such as Figure 5 、 Figure 6 shown.

[0057] The laser displacement sensor 8 emits high-frequency laser light through the transparent acrylic window 8b, which is reflected back to the laser receiver at each measuring point on the capillary tube, thereby using the triangulation method to measure the distance between the laser displacement sensor 8 and the measuring point. The displacement at the measuring point can then be obtained by 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, allowing the airflow to 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 micro heat exchange tube bundle 5. After sweeping across the micro heat exchange tube bundle 5, the air is guided by the guide cone on the core support 4 and flows out from the exhaust section 6.

[0059] Figure 4 This is a photo of the heat exchange tube bundle test piece inside the heat exchange core. It consists of four staggered rows of heat exchange tube bundles 5a. The horizontal tube spacing between the heat exchange tube bundles is 2.5 mm, the vertical tube spacing is 2 mm, and the center-to-center distance between adjacent rows is 1.25 mm. The tubes have an outer diameter of 1 mm and an inner diameter of 0.8 mm. The ends of the tube bundle are connected to the helium inlet and outlet manifolds 5b and 5c, respectively. Each heat exchange tube is inserted through a small hole in the helium inlet and outlet manifolds. Each heat exchange tube is welded to the surface of the helium inlet and outlet manifolds and then connected to the manifolds at both ends. Each row of heat exchange tubes is connected and secured by 13 support plates 5d. The angle between two adjacent support plates and the center line is 30°. The heat exchange tubes are made of 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. Complete the debugging of the relevant settings of the laser displacement sensor 8 in a static state, and also check and debug the pressure monitoring system. At this point, 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 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 test officially begins.

[0063] Step (3) starts the pressure monitoring system and the displacement acquisition system, starts scanning and monitoring the static pressure and total pressure at the inlet 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, adjust the valve opening to test condition 1, wait for a period of stabilization, start vibration displacement collection, and repeat the test data collection at intervals of 1 minute to reduce the test error.

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

[0066] Step (6) Undo 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 measuring 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 laws 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 content should be regarded as equivalent valid embodiments and 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 by: It comprises a stabilizing section (1), a flow guide section (2), a testing section (3) and an exhaust section (6), with two adjacent sections 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 container, and the guide cone (2a) is connected to the guide section outer cavity (2d) via a guide cone support plate (2e), forming a guide cavity (2c) between the guide cone (2a) and the guide section outer cavity (2d); a support platform (2b) is provided at the tail end of the guide cone (2a); The exhaust section (6) adopts an exhaust port (6b) provided at the center of the exhaust end plate (6a); The test section (3) comprises a test section shell (3c) and a test cavity (3a); a micro heat exchange tube bundle (5) and a core support seat (4) are arranged in the test cavity (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 inlet manifold (5b), and the other end is arranged on the helium outlet manifold (5c); the helium inlet manifold (5b) and the helium 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 provided at the center of the core support seat (4), with the tip of the exhaust guide cone (3b) facing the exhaust port (6b); the fine heat exchange tube bundle (5) is spirally shaped and surrounds the outside of the exhaust guide cone (3b); A measuring window (8a) equipped with a transparent window (8b) is provided on the test section housing (3c), and a laser displacement sensor (8) is provided in the measuring window (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 the vibration of the micro heat exchange tube bundle (5) at different circumferential positions is measured.

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

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

4. The test method for a micro-tube vibration wind tunnel test section according to claim 1, 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 displacement acquisition system, start scanning and monitoring the static pressure and total pressure at the inlet 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 wind tunnel fan to supply air to the test device; S4. By adjusting the valve opening of the wind tunnel air inlet channel and the monitored pressure data, the valve opening is adjusted to test condition 1, and the incoming air enters the test device, stabilizes the airflow in the stabilization section (1), and then flows into the guide section (2), where it is divided by the conical guide cone (2a), 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 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 obtained by the change in distance at different times. S5. After collecting the vibration displacement data for test condition 1, adjust the valve opening of the wind tunnel ventilation channel to 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 collection for all test conditions of the upper sample point P1 is completed; S6. Undo 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 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 vibration test data collection 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 various test conditions is completed, and the test process is now completed.

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