Aero-engine vibration detection equipment and detection method

Abstract

The invention belongs to the technical field of aero-engine detection, and relates to aero-engine vibration detection equipment which comprises a base and further comprises a cartridge receiver mounting mechanism which comprises a first supporting plate, a movable mounting seat and a fixed flange; the transmission rod penetrates through and is rotationally connected to the movable mounting seat; the driving mechanism is connected to the movable mounting seat in a drivable manner; the excitation source mounting mechanism comprises a second supporting plate, a hollow rod and a gas excitation mechanism, and the gas excitation mechanism is used for blowing high-pressure airflow to blades of the aero-engine; the device can be used for testing the total vibration amount of the aero-engine, can also independently perform vibration testing on the blade of the aero-engine, and can enable the blade and the gas excitation mechanism to be static at the same time, rotate at the same time or only rotate one of the blade and the gas excitation mechanism when the vibration performance of the blade is detected, thereby meeting different detection requirements. And moreover, the detection equipment does not need to be replaced, and the use is more convenient.

Description

Technical Field

[0001] The invention belongs to the technical field of aero-engine detection, and in particular relates to an aero-engine vibration detection device and a detection method. Background Art

[0002] During the aircraft engine test, conventional vibration testing uses a preamplifier to monitor the total amount of engine vibration (the total amount of vibration is the square root of the sum of the squares of the peak values ​​of each frequency within the frequency bandwidth).

[0003] As the core working component, the engine blades directly affect the operating state, working efficiency and safety performance of the entire engine system. In actual work, the engine blades need to withstand extremely complex exciting forces, so they are prone to vibration, which leads to fatigue and even cracks, breakage and other failures, causing serious safety accidents. It is very necessary to conduct vibration testing on engine blades.

[0004] It was retrieved that in the prior art, a Chinese invention patent with authorization announcement number CN221224140U disclosed "an aircraft engine blade vibration test device", including a base plate, a left support, a middle support, a right support, a horizontal transmission shaft, a casing, a test sensor, and a gas excitation application component. Its technical highlights are: the gas excitation application component includes a hollow shaft arranged on the right support, a plurality of radial hollow rods arranged on the outer circumferential surface of the hollow shaft and connected thereto, an annular distribution chamber connected to the ends of each radial hollow rod, a plurality of gas distribution outlets evenly arranged on one side end surface of the annular distribution chamber, a concentric shaft arranged at the front end of the hollow shaft, a plurality of radial support arms evenly arranged on the concentric shaft, and a movable nozzle arranged on the radial support arm, the movable nozzle corresponds to the gas distribution outlet one by one, and a flexible connecting pipe is provided between the movable nozzle and the gas distribution outlet.

[0005] Although the vibration testing devices in the prior art, including those mentioned above, can meet general testing work, in actual use, the test parameters of traditional vibration testing devices are single, and the same device can only be used to detect the total amount of engine vibration or the vibration performance of the blades. It is unable to take into account the testing of the entire machine and the blades of the aircraft engine. When testing different parts, different test equipment needs to be replaced, which is rather troublesome. Summary of the invention

[0006] In order to solve the above problems existing in the prior art, the present invention provides an aircraft engine vibration detection device and a detection method, which are easy to use and have a wide test range.

[0007] To achieve the above object, the present invention provides the following technical solutions:

[0008] Aircraft engine vibration detection equipment, including a base, and also including:

[0009] A casing mounting mechanism, the casing mounting mechanism comprising a No. 1 support plate fixed on the base, a movable mounting seat movably connected to the No. 1 support plate, and a fixing flange fixed on the movable mounting seat;

[0010] A transmission rod, the transmission rod passes through and is rotatably connected to the movable mounting seat, and the transmission rod is coaxial with the fixing flange;

[0011] A driving mechanism, the driving mechanism is drivably connected to the movable mounting seat, and is used to drive the movable mounting seat to reciprocate in a vertical direction;

[0012] An excitation source installation mechanism, the excitation source installation mechanism includes a No. 2 support plate fixed on the base, a hollow rod penetrating and rotatably installed on the No. 2 support plate, and a gas excitation mechanism fixed to the end of the hollow rod, the gas excitation mechanism is used to blow high-pressure airflow toward the blades of the aircraft engine.

[0013] As a preferred technical solution of the present invention, the driving mechanism includes:

[0014] A lifting rod, the lifting rod is fixed to the bottom end of the movable mounting seat;

[0015] A driving motor, wherein the driving motor is fixed on the base;

[0016] A rotating disk, the rotating disk is fixed on the output shaft of the driving motor;

[0017] A toggle arm, one end of which is rotatably connected to the eccentric position of the rotating disk, and the other end of which is rotatably connected to the lifting rod.

[0018] As a preferred technical solution of the present invention, the lifting rod passes through the toggle arm to form a rotating structure.

[0019] As a preferred technical solution of the present invention, it also includes:

[0020] A threaded rod, the threaded rod is fixed at an eccentric position of the rotating disk, and the toggle arm is provided with a through hole for the threaded rod to penetrate;

[0021] A locking nut is installed on the protruding end of the threaded rod by threaded engagement.

[0022] As a preferred technical solution of the present invention, a plurality of through holes are evenly spaced along the length direction of the toggle arm.

[0023] As a preferred technical solution of the present invention, a movable hole is provided on the No. 1 support plate, and the movable mounting seat is movable in the movable hole.

[0024] As a preferred technical solution of the present invention, it also includes:

[0025] Guide rods, two of which are symmetrically fixed in the movable hole, and the guide rods pass through the movable mounting seat;

[0026] A balance spring is provided between the inner top surface of the movable hole and the top surface of the movable mounting seat, and between the inner bottom surface of the movable hole and the bottom surface of the movable mounting seat. The balance spring is sleeved on the guide rod.

[0027] As a preferred technical solution of the present invention, the gas excitation mechanism includes:

[0028] A diverter plate, wherein the diverter plate has an air inlet, and the hollow rod is connected to the air inlet;

[0029] The air jet nozzle has a plurality of flow diversion channels which are evenly spaced along the circumferential direction on the flow diversion plate, and the flow diversion channels are communicated with the air inlet, and the air jet nozzle is fixed at the port of the flow diversion channel.

[0030] As a preferred technical solution of the present invention, the excitation source installation mechanism further includes:

[0031] A rotating joint is fixed to an end of the hollow rod away from the gas excitation mechanism.

[0032] As a preferred technical solution of the present invention, the casing mounting mechanism has two groups distributed at intervals, the lifting rod is fixed to the bottom ends of the two movable mounting seats, and the toggle arm is connected to the middle of the lifting rod.

[0033] The present invention also provides a detection method of the aircraft engine vibration detection device based on any one of the above technical solutions, comprising the following steps:

[0034] Step 1: When the blades of the aircraft engine are in a stationary state, a high-pressure airflow is blown toward the blades of the aircraft engine through a gas excitation mechanism, and at the same time, the vibration performance of the blades when stationary is monitored by a test sensor;

[0035] Step 2: The transmission rod is driven to rotate by an external device to drive the blades of the aircraft engine to rotate, and at the same time, a high-pressure airflow is blown to the blades of the aircraft engine by a gas excitation mechanism, so that the vibration performance of the blades during rotation is monitored by a test sensor;

[0036] Step 3: Transfer the test sensor from the blade to the casing, and drive the movable mounting seat to move back and forth in the vertical direction through the driving mechanism, so that the movable mounting seat drives the casing to oscillate back and forth in the vertical direction, and at the same time monitor the vibration performance of the aircraft engine through the test sensor.

[0037] Compared with the prior art, the present invention has the following beneficial effects:

[0038] The present invention can be used to test the total amount of vibration of an aircraft engine, and can also perform vibration tests on blades of an aircraft engine individually. When testing the vibration performance of the blades, the blades and the gas excitation mechanism can be made stationary at the same time, rotate at the same time, or only one of them can rotate, so as to meet different testing requirements, thereby making the test results more accurate and more convenient to use without having to replace the testing equipment.

[0039] Other additional advantages and beneficial effects of the present application will be given in part in the following description, and in part will become apparent from the following description, or will be understood through the practice of the present application. BRIEF DESCRIPTION OF THE DRAWINGS

[0040] The accompanying drawings are used to provide a further understanding of the present invention and constitute a part of the specification. Together with the embodiments of the present invention, they are used to explain the present invention and do not constitute a limitation of the present invention. In the accompanying drawings:

[0041] Figure 1 It is a structural schematic diagram of the aircraft engine vibration detection device of the present invention;

[0042] Figure 2 It is a schematic diagram of the axonometric structure of the driving mechanism in the present invention;

[0043] Figure 3 It is a schematic diagram of the axonometric structure of the casing mounting mechanism in the present invention;

[0044] Figure 4 It is a schematic diagram of the cross-sectional structure of the gas excitation mechanism in the present invention.

[0045] In the figure: 1. base; 2. casing mounting mechanism; 21. No. 1 support plate; 211. movable hole; 22. movable mounting seat; 23. fixing flange; 24. guide rod; 25. balance spring; 3. transmission rod; 4. driving mechanism; 41. driving motor; 42. rotating disk; 43. threaded rod; 44. toggle arm; 441. through hole; 45. locking nut; 46. lifting rod; 5. excitation source mounting mechanism; 51. No. 2 support plate; 52. hollow rod; 53. gas excitation mechanism; 531. diverter disk; 5311. air inlet; 5312. diverter channel; 532. jet nozzle; 54. rotary joint. DETAILED DESCRIPTION

[0046] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0047] See also Figure 1-Figure 4 The present invention provides the following technical solution: an aircraft engine vibration detection device includes a base 1, and also includes: a casing mounting mechanism 2, a transmission rod 3, a driving mechanism 4 and an excitation source mounting mechanism 5.

[0048] Further, by Figure 1 As shown, in this embodiment, the casing mounting mechanism 2 includes a No. 1 support plate 21 fixed on the base 1, a movable mounting seat 22 movably connected to the No. 1 support plate 21, and a fixed flange 23 fixed on the movable mounting seat 22. The transmission rod 3 passes through and is rotatably connected to the movable mounting seat 22, and the transmission rod 3 is coaxial with the fixed flange 23. The driving mechanism 4 is drivably connected to the movable mounting seat 22 to drive the movable mounting seat 22 to reciprocate in the vertical direction. The excitation source mounting mechanism 5 includes a No. 2 support plate 51 fixed on the base 1, a hollow rod 52 passing through and rotatably mounted on the No. 2 support plate 51, and a gas excitation mechanism 53 fixed to the end of the hollow rod 52. The gas excitation mechanism 53 is used to blow high-pressure airflow to the blades of the aircraft engine. After adopting the above scheme, when in use, the casing of the aircraft engine is fixed on the fixed flange 23. When detecting the blades of the aircraft engine, the impeller casing is fixed on the fixed flange 23, and the main shaft of the blade is fixedly connected to the transmission rod 3. The hollow rod 52 is connected to the air source. When testing the total amount of vibration of the aircraft engine, the test sensor is fixed on the casing, and the test sensor is connected to the control host of the detection system. Then, the driving mechanism 4 is started to drive the movable mounting seat 22 to reciprocate in the vertical direction, and the casing is driven to oscillate reciprocally in the vertical direction through the movable mounting seat 22, and the vibration performance of the aircraft engine is monitored by the test sensor.

[0049] When testing the vibration performance of the blade, the test sensor is fixed on the blade. Since the blade needs to be rotated during the test, the test sensor preferably adopts a wireless vibration sensor. The transmission rod 3 is driven to rotate by an external device, and the transmission rod 3 drives the blade to rotate. The vibration performance of the blade during rotation is monitored by the wireless vibration sensor.

[0050] When testing the vibration performance of the impeller blades, the high-pressure airflow can also be blown toward the blades of the aircraft engine through the gas excitation mechanism 53, and the wireless vibration sensor is still fixed on the blades. At this time, the transmission rod 3 can be driven to rotate by an external device to rotate the blades, and the blades can also be kept in a stationary state for testing. The hollow rod 52 can also be driven to rotate by an external device to make the gas excitation mechanism 53 blow the high-pressure airflow toward the blades during the rotation process. Multiple groups of tests can be performed under different conditions, and the test results are more accurate. There is no need to replace the test equipment, and it is more convenient to use.

[0051] It should be noted that synchronous wheels are reserved on the transmission rod 3 and the hollow rod 52, and as shown in the accompanying drawings, the transmission rod 3 and the hollow rod 52 can be driven to rotate by means of a motor, a synchronous wheel and a synchronous belt.

[0052] It should be further explained that, in the present invention, the transmission rod 3 and the hollow rod 52 are both rotatably mounted via bearings, and the positions of the bearings are shown in the drawings.

[0053] Optionally, by Figure 1 and Figure 2 As shown, in this embodiment, the driving mechanism 4 includes: a lifting rod 46, a driving motor 41, a rotating disk 42 and a toggle arm 44, the lifting rod 46 is fixed to the bottom end of the movable mounting seat 22, the driving motor 41 is fixed on the base 1, the rotating disk 42 is fixed on the output shaft of the driving motor 41, one end of the toggle arm 44 is rotatably connected to the eccentric position of the rotating disk 42, and the other end is rotatably connected to the lifting rod 46. After adopting the above scheme, when in use, the driving motor 41 is started to drive the rotating disk 42 to rotate, and the rotating disk 42 drives the toggle arm 44 to swing and move up and down, and the lifting rod 46 is driven to move up and down through the toggle arm 44, and at the same time drives the movable mounting seat 22 to move up and down.

[0054] Optionally, by Figure 1 and Figure 2 As shown, in this embodiment, the lifting rod 46 penetrates the toggle arm 44 to form a rotating structure, thereby realizing a rotational connection between the toggle arm 44 and the lifting rod 46 .

[0055] Preferably, by Figure 1 and Figure 2 As shown, in this embodiment, it also includes: a threaded rod 43 and a locking nut 45. The threaded rod 43 is fixed at an eccentric position of the rotating disk 42. A through hole 441 is provided on the toggle arm 44 for the threaded rod 43 to pass through. The locking nut 45 is installed on the protruding end of the threaded rod 43 by threaded engagement. After adopting the above scheme, when in use, the drive motor 41 is started to drive the rotating disk 42 to rotate, the rotating disk 42 drives the threaded rod 43 to make a circular motion, and the threaded rod 43 drives the toggle arm 44 to swing and move up and down.

[0056] Preferably, by Figure 1 and Figure 2 As shown, in this embodiment, a plurality of through holes 441 are evenly spaced along the length direction of the toggle arm 44. Therefore, by passing the threaded rod 43 through the through holes 441 at different heights, the initial height of the movable mounting seat 22 can be adjusted to facilitate accurate detection work.

[0057] Preferably, by Figure 1-Figure 3 As shown, in this embodiment, a movable hole 211 is provided on the No. 1 support plate 21 , and the movable mounting seat 22 is movable in the movable hole 211 . The movable hole 211 is used to guide and limit the movable mounting seat 22 to ensure the stability of the movable mounting seat 22 .

[0058] Preferably, by Figure 1-Figure 3 As shown, in this embodiment, it also includes: a guide rod 24 and a balance spring 25. The two guide rods 24 are symmetrically fixed in the movable hole 211, and the guide rods 24 pass through the movable mounting seat 22. Balance springs 25 mounted on the guide rods 24 are distributed between the inner top surface of the movable hole 211 and the top surface of the movable mounting seat 22, and between the inner bottom surface of the movable hole 211 and the bottom surface of the movable mounting seat 22. After adopting the above scheme, the guide rods 24 are used to guide the movable mounting seat 22, and the balance springs 25 have a reverse elastic force to ensure that the movement of the movable mounting seat 22 is smoother, thereby further improving the stability of the movable mounting seat 22.

[0059] Optionally, by Figure 1 and Figure 4 As shown, the gas excitation mechanism 53 includes: a diverter disk 531 and an air nozzle 532. The diverter disk 531 is provided with an air inlet 5311, and the hollow rod 52 is communicated with the air inlet 5311. The diverter disk 531 is provided with a plurality of diverter channels 5312 evenly spaced along the circumferential direction, and the diverter channels 5312 are communicated with the air inlet 5311, and the air nozzle 532 is fixed at the port of the diverter channel 5312. After adopting the above scheme, when in use, the hollow rod 52 is connected to the air source, and the high-pressure gas passes through the hollow rod 52 into the air inlet 5311, and then is diverted into each diverter channel 5312, and finally discharged from the air nozzle 532.

[0060] Preferably, by Figure 1 As shown, in this embodiment, the excitation source mounting mechanism 5 also includes: a rotating joint 54, which is fixed to one end of the hollow rod 52 away from the gas excitation mechanism 53. After adopting the above scheme, the hollow rod 52 is connected to the gas source by the rotating joint 54, which is convenient for using the hollow rod 52 to drive the gas excitation mechanism 53 to rotate during testing.

[0061] Preferably, by Figure 1As shown, in the present embodiment, there are two groups of casing mounting mechanisms 2 spaced apart from each other, the lifting rod 46 is fixed to the bottom ends of the two movable mounting seats 22, and the toggle arm 44 is connected to the middle of the lifting rod 46. Therefore, the detection equipment of the present invention utilizes two groups of casing mounting mechanisms 2 to support the aircraft engine casing, one group of casing mounting mechanisms 2 is directly fixedly connected to the casing, and the two groups of casing mounting mechanisms 2 indirectly support the aircraft engine casing by supporting the transmission rod 3, thereby ensuring the stability of the aircraft engine casing and also enabling the aircraft engine casing to have higher stability when oscillating back and forth in the vertical direction.

[0062] The circuit connection involved in the present invention is a common method used by those skilled in the art, and technical inspiration can be obtained through a limited number of experiments, and it belongs to the widely used existing technology.

[0063] Components not described in detail herein are prior art.

[0064] Working principle and use process of the present invention: When the detection device of the present invention is used, the casing of the aircraft engine is fixed on the fixing flange 23;

[0065] First, when testing the blades of an aircraft engine, the impeller casing is fixed on the fixed flange 23, and the main shaft of the blade is fixedly connected to the transmission rod 3, the hollow rod 52 is connected to the air source, and the test sensor is fixed on the blade. Since the blade needs to be rotated during the test, the test sensor preferably adopts a wireless vibration sensor, and the transmission rod 3 is driven to rotate by an external device, and the transmission rod 3 drives the blade to rotate, and the vibration performance of the blade during rotation is monitored by the wireless vibration sensor;

[0066] When testing the vibration performance of the impeller blades, the high-pressure airflow can also be blown toward the blades of the aircraft engine through the gas excitation mechanism 53, and the wireless vibration sensor is still fixed on the blades. At this time, the transmission rod 3 can be driven to rotate by an external device to rotate the blades, and the blades can also be kept in a stationary state for testing. The hollow rod 52 can also be driven to rotate by an external device to make the gas excitation mechanism 53 blow the high-pressure airflow toward the blades during the rotation process. Multiple groups of tests can be performed under different conditions, and the accuracy of the test results is higher. There is no need to replace the test equipment, and it is more convenient to use.

[0067] Secondly, when testing the total amount of vibration of the aircraft engine, the test sensor is fixed on the casing, and the test sensor is connected to the control host of the detection system, and then the driving mechanism 4 is started to drive the movable mounting seat 22 to move back and forth in the vertical direction, and the casing is driven to reciprocate and oscillate in the vertical direction through the movable mounting seat 22, and the vibration performance of the aircraft engine is monitored by the test sensor;

[0068] The detection equipment of the present invention can be used to test the total vibration of an aircraft engine, and can also perform vibration tests on the blades of an aircraft engine individually. When detecting the vibration performance of the blades, the blades and the gas excitation mechanism 53 can be made stationary at the same time, rotate at the same time, or only one of them can rotate, to meet different detection requirements, thereby making the detection results more accurate and more convenient to use without having to replace the detection equipment.

[0069] Finally, it should be noted that the above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Although the present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art can still modify the technical solutions described in the aforementioned embodiments or replace some of the technical features therein by equivalents. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. An aircraft engine vibration detection device, comprising a base (1), characterized in that: Also includes: A casing mounting mechanism (2), the casing mounting mechanism (2) comprising a first support plate (21) fixed on the base (1), a movable mounting seat (22) movably connected to the first support plate (21), and a fixing flange (23) fixed on the movable mounting seat (22); A transmission rod (3), the transmission rod (3) penetrates through and is rotatably connected to the movable mounting seat (22), and the transmission rod (3) and the fixing flange (23) are coaxial; A driving mechanism (4), the driving mechanism (4) being drivably connected to the movable mounting seat (22) and used for driving the movable mounting seat (22) to reciprocate in a vertical direction; An excitation source mounting mechanism (5), the excitation source mounting mechanism (5) comprising a second support plate (51) fixed on the base (1), a hollow rod (52) penetrating and rotatably mounted on the second support plate (51), and a gas excitation mechanism (53) fixed to the end of the hollow rod (52), the gas excitation mechanism (53) being used to blow a high-pressure airflow toward the blades of an aircraft engine.

2. The aircraft engine vibration detection device according to claim 1, characterized in that: The driving mechanism (4) comprises: A lifting rod (46), wherein the lifting rod (46) is fixed to the bottom end of the movable mounting seat (22); A driving motor (41), wherein the driving motor (41) is fixed on the base (1); A rotating disk (42), wherein the rotating disk (42) is fixed on an output shaft of the driving motor (41); A toggle arm (44), one end of which is rotatably connected to an eccentric position of the rotating disk (42) and the other end of which is rotatably connected to the lifting rod (46).

3. The aircraft engine vibration detection device according to claim 2, characterized in that: The lifting rod (46) passes through the toggle arm (44) to form a rotating structure.

4. The aircraft engine vibration detection device according to claim 2, characterized in that: Also includes: A threaded rod (43), the threaded rod (43) being fixed at an eccentric position of the rotating disk (42), and the toggle arm (44) having a through hole (441) for the threaded rod (43) to pass through; A locking nut (45) is installed on the protruding end of the threaded rod (43) by means of threaded engagement.

5. The aircraft engine vibration detection device according to claim 4, characterized in that: A plurality of through holes (441) are distributed at equal intervals along the length direction of the toggle arm (44).

6. The aircraft engine vibration detection device according to claim 1, characterized in that: The first support plate (21) is provided with a movable hole (211), and the movable mounting seat (22) is located in the movable hole (211) and moves therein.

7. The aircraft engine vibration detection device according to claim 6, characterized in that: Also includes: Guide rods (24), two guide rods (24) are symmetrically fixed in the movable hole (211), and the guide rods (24) pass through the movable mounting seat (22); A balance spring (25) sleeved on the guide rod (24) is distributed between the inner top surface of the movable hole (211) and the top surface of the movable mounting seat (22), and between the inner bottom surface of the movable hole (211) and the bottom surface of the movable mounting seat (22).

8. The aircraft engine vibration detection device according to claim 1, characterized in that: The gas excitation mechanism (53) comprises: A diverter plate (531), wherein the diverter plate (531) has an air inlet (5311), and the hollow rod (52) is in communication with the air inlet (5311); The air jet (532) has a plurality of diversion channels (5312) distributed at equal intervals along the circumferential direction on the diversion plate (531), and the diversion channels (5312) are communicated with the air inlet (5311), and the air jet (532) is fixed at the port of the diversion channel (5312).

9. The aircraft engine vibration detection device according to claim 2, characterized in that: The casing mounting mechanism (2) has two groups distributed at intervals, the lifting rod (46) is fixed to the bottom ends of the two movable mounting seats (22), and the toggle arm (44) is connected to the middle of the lifting rod (46).

10. A detection method based on the aircraft engine vibration detection device according to any one of claims 1 to 9, characterized in that: The steps include: Step 1: When the blades of the aircraft engine are in a stationary state, a high-pressure airflow is blown toward the blades of the aircraft engine through a gas excitation mechanism (53), and at the same time, a test sensor is used to monitor the vibration performance of the blades when they are stationary; Step 2: The transmission rod (3) is driven to rotate by an external device to drive the blades of the aircraft engine to rotate, and at the same time, a high-pressure airflow is blown toward the blades of the aircraft engine by a gas excitation mechanism (53), so as to monitor the vibration performance of the blades during rotation by a test sensor; Step 3: The test sensor is transferred from the blade to the casing, and the movable mounting seat (22) is driven to move back and forth in the vertical direction by the driving mechanism (4), so that the movable mounting seat (22) drives the casing to oscillate back and forth in the vertical direction, and the vibration performance of the aircraft engine is monitored by the test sensor at the same time.

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