Aircraft engine vibration detection equipment and detection method

Abstract

The present invention belongs to the technical field of aircraft engine detection, wherein the aircraft engine vibration detection equipment includes a base and also includes: a casing mounting mechanism, including a No. 1 support plate, a movable mounting seat and a fixed flange; a transmission rod, the transmission rod passes through and is rotatably connected to the movable mounting seat; a driving mechanism, the driving mechanism is drivably connected to the movable mounting seat; an excitation source mounting mechanism, including a No. 2 support plate, a hollow rod and a gas excitation mechanism, the gas excitation mechanism is used to blow a high-pressure airflow to the blades of the aircraft engine; the present invention can be used to test the total vibration of the aircraft engine, and can also perform vibration tests on the blades of the aircraft engine separately, and when detecting 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 the two can rotate, so as to meet different detection requirements, so that the detection results are more accurate, and there is no need to replace the detection equipment, so it is more convenient to use.

Description

Technical Field

[0001] The present 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 from the prior art that 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 assembly. The technical key points are: the gas excitation application assembly includes a hollow shaft arranged on the right support, a plurality of radial hollow rods arranged on the outer circumference of the hollow shaft and connected thereto, an annular distribution chamber connected to the end of each radial hollow rod, a plurality of gas distribution outlets evenly arranged on one side end face 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 needs, in actual use, the test parameters of traditional vibration testing devices are single. The same device can only be used to detect the total amount of engine vibration or the vibration performance of the blades, and cannot 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 more 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 range of testing characteristics.

[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 includes:

[0009] A casing mounting mechanism, the casing mounting mechanism comprising a first support plate fixed to the base, a movable mounting seat movably connected to the first support plate, and a fixing flange fixed to the movable mounting seat;

[0010] a transmission rod, the transmission rod passing through and rotatably connected to the movable mounting seat, and the transmission rod and the fixing flange are coaxial;

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

[0012] An excitation source mounting mechanism includes a No. 2 support plate fixed on the base, a hollow rod penetrating and rotatably mounted on the No. 2 support plate, and a gas excitation mechanism fixed to the end of the hollow rod, wherein 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 being 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 being 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 has a through hole for the threaded rod to pass through;

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

[0022] As a preferred technical solution of the present invention, a plurality of through holes are distributed at equal intervals 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 located and moves 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 pass through the movable mounting seat;

[0026] A balancing 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. A balancing spring is provided 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 has a plurality of diversion channels distributed at equal intervals along the circumferential direction on the diversion plate, and the diversion channels are communicated with the air inlet, and the air jet is fixed at the port of the diversion channel.

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

[0031] A rotary 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 is distributed in two groups 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 further provides a detection method for the aircraft engine vibration detection device according to any one of the above technical solutions, comprising the following steps:

[0034] Step 1: When the blades of the aircraft engine are at rest, a high-pressure airflow is blown toward the blades through a gas excitation mechanism, and the vibration performance of the blades at rest is monitored by a test sensor.

[0035] Step 2: An external device drives the transmission rod to rotate, thereby driving the blades of the aircraft engine to rotate. At the same time, a gas excitation mechanism blows high-pressure airflow toward the blades of the aircraft engine, thereby monitoring the vibration performance of the blades during rotation through test sensors.

[0036] Step 3: Transfer the test sensor from the blade to the casing, and drive the movable mounting base to move back and forth in the vertical direction through the driving mechanism, so that the movable mounting base 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 vibration of an aircraft engine, and can also perform vibration tests on the 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, thereby meeting different testing requirements, making the test results more accurate, and eliminating the need to replace the testing equipment, making it more convenient to use.

[0039] Other additional advantages and benefits 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 learned 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 This is a schematic structural diagram of an aircraft engine vibration detection device according to the present invention;

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

[0043] Figure 3 This is a schematic diagram of the axonometric structure of the casing mounting mechanism of 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 plate; 5311. air inlet; 5312. diverter channel; 532. jet nozzle; 54. rotary joint. DETAILED DESCRIPTION

[0046] The following will clearly and completely describe the technical solutions in the embodiments of the present invention in conjunction with the accompanying drawings. 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 making creative efforts 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 and is used 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 toward the blades of the aircraft engine. After adopting the above solution, when in use, the casing of the aircraft engine is fixed on the fixed flange 23. When testing 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 vibration of the aircraft engine, the test sensor is fixed on the casing and connected to the control host of the detection system. Then, the driving mechanism 4 is started to drive the movable mounting seat 22 to move back and forth in the vertical direction. The casing is driven to oscillate back and forth 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 is preferably 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. The wireless vibration sensor is still fixed on the blade. At this time, the transmission rod 3 can be driven to rotate by an external device to rotate the blade. The blade 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 blade during the rotation process. Multiple groups of tests can be performed under different conditions. The test results are more accurate and there is no need to replace the test equipment, which 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 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 accompanying 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, and 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 up and down by the toggle arm 44, and the movable mounting seat 22 is driven up and down at the same time.

[0054] Optionally, by Figure 1 and Figure 2 As shown, in this embodiment, the lifting rod 46 passes through 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 perform 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, there are multiple through holes 441 distributed at equal intervals 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, this embodiment 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 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. 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 has an air inlet 5311, and the hollow rod 52 is communicated with the air inlet 5311. The diverter disk 531 has a plurality of diverter channels 5312 evenly spaced along the circumferential direction, and the diverter channels 5312 are communicated with the air inlet 5311. 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 gas 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 rotary 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 using the rotary 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 this embodiment, there are two groups of casing mounting mechanisms 2 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. Therefore, the detection equipment of the present invention uses 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 through the supporting transmission rod 3, thereby ensuring the stability of the aircraft engine casing and also making the aircraft engine casing 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 limited experiments. It belongs to the widely used existing technology.

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

[0064] The working principle and use process of the present invention: When using the detection device of the present invention, 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 to 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 to the blade. Since the blade needs to be rotated during the test, the test sensor is preferably 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 wireless vibration sensor monitors the vibration performance of the blade during rotation.

[0066] When testing the vibration performance of the impeller blades, the gas excitation mechanism 53 can also be used to blow high-pressure airflow toward the blades of the aircraft engine. 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. 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 high-pressure airflow toward the blades during the rotation process. Multiple groups of tests can be performed under different conditions. The test results are more accurate and there is no need to replace the test equipment, which is more convenient to use.

[0067] Secondly, when testing the total vibration of an aircraft engine, a test sensor is fixed to the casing and connected to the control host of the detection system. Then, the drive mechanism 4 is activated to drive the movable mounting seat 22 to move back and forth in the vertical direction. 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.

[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, making the detection results more accurate, and there is no need to replace the detection equipment, making it more convenient to use.

[0069] Finally, it should be noted that the above descriptions are merely preferred embodiments of the present invention and are 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 will be able to modify the technical solutions described in the aforementioned embodiments or substitute equivalents for some of the technical features. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of the present invention shall be included within the scope of protection 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) passes 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 configured to drive the movable mounting seat (22) to reciprocate in a vertical direction; An excitation source mounting mechanism (5) includes 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), wherein the gas excitation mechanism (53) is used to blow a high-pressure airflow toward the blades of the 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), the lifting rod (46) being fixed to the bottom end of the movable mounting seat (22); a drive motor (41), wherein the drive motor (41) is fixed on the base (1); a rotating disk (42), wherein the rotating disk (42) is fixed on the output shaft of the driving motor (41); A toggle arm (44) has one end rotatably connected to an eccentric position of the rotating disk (42) and the other end 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 mounted on the protruding end of the threaded rod (43) by screwing.

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.

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) is provided 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). The balance spring (25) is sleeved on the guide rod (24).

8. The aircraft engine vibration detection device according to claim 1, characterized in that: The gas excitation mechanism (53) comprises: A diverter plate (531), having an air inlet (5311) on the diverter plate (531), 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 disk (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) is spaced apart and has two groups. 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 in a stationary state; 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 that the vibration performance of the blades during rotation is monitored 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 at the same time, the vibration performance of the aircraft engine is monitored by the test sensor.

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