Aero-engine vibration detection equipment

Abstract

The utility model belongs to the technical field of aero-engine detection, in particular to aero-engine vibration detection equipment, which comprises a base and further comprises a cartridge receiver mounting mechanism, a vibration detection mechanism and a vibration detection mechanism, 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 detection equipment provided by the utility model can be used for testing the total vibration amount of the aero-engine, can be used for independently testing the vibration of 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 utility model belongs to the technical field of aero-engine detection, and particularly relates to an aero-engine vibration detection device. BACKGROUND

[0002] During aero-engine test running, conventional vibration testing is to monitor the total engine vibration by using a preamplifier (the total vibration is the result of the square root of the sum of the square of each frequency peak value in the frequency bandwidth).

[0003] However, the engine blade, as a core working component, directly affects the running state, working efficiency and safety performance of the entire engine system. The engine blade needs to bear extremely complex exciting force in actual work, and thus is prone to vibration, thereby causing fatigue, and even cracks, breakage and other faults, resulting in serious safety accidents. Therefore, it is necessary to test the vibration of the engine blade.

[0004] In the prior art, a Chinese utility model patent with the authorization publication number CN221224140U discloses an "aero-engine blade vibration testing device", which comprises a bottom plate, a left support, a middle support, a right support, a horizontal transmission shaft, a casing, a testing sensor, a gas excitation application assembly, and the technical points are as follows: the gas excitation application assembly comprises 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 in communication with the hollow shaft, an annular distribution cavity in communication with the end of each radial hollow rod, a plurality of gas distribution outlets uniformly arranged on one side end face of the annular distribution cavity, a concentric shaft arranged at the front end of the hollow shaft, a plurality of radial arms uniformly arranged on the concentric shaft, and a movable nozzle arranged on the radial arm. The movable nozzle is in one-to-one correspondence with the gas distribution outlet, and a flexible connecting pipe is arranged between the movable nozzle and the gas distribution outlet.

[0005] The vibration testing device in the prior art including the above can meet general testing work, but in actual use, the testing parameter of the conventional vibration testing device is single, and the same device can only be used for testing the total engine vibration or the vibration performance of the blade, and cannot test the whole machine and the aero-engine blade. When different parts are tested, different testing devices need to be replaced, which is troublesome.

[0006] To solve the above problems, an aero-engine vibration detection device is provided in the present application. UTILITY MODEL CONTENTS

[0007] To solve the above problems in the prior art, the utility model provides an aero-engine vibration detection device, which has the characteristics of convenient use and wide testing range.

[0008] In order to achieve the above object, the utility model provides the following technical scheme: the aero-engine vibration detection equipment, including the base, still includes:

[0009] The machine case mounting mechanism includes a first support plate fixed on the base, a movable mounting seat movably connected to the first support plate, and a fixed flange fixed on the movable mounting seat.

[0010] Transmission rod, the transmission rod is through and rotationally connected to the movable mounting seat, and the transmission rod is coaxial with the fixed flange;

[0011] Drive mechanism, the drive mechanism is driveably connected to the movable mounting seat, for driving the movable mounting seat reciprocating movement along the vertical direction;

[0012] Excitation source mounting mechanism, the excitation source mounting mechanism includes a second support plate fixed on the base, a hollow rod through and rotationally installed on the second support plate and a gas excitation mechanism fixed to the end of the hollow rod, and the gas excitation mechanism is used for blowing high-pressure gas flow to the blade of aero-engine.

[0013] As a preferred technical scheme of the utility model, the drive mechanism includes:

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

[0015] Drive motor, the drive motor is fixed on the base;

[0016] Rotary disc, the rotary disc is fixed on the output shaft of the drive motor;

[0017] Dialling arm, one end of the dialling arm is rotationally connected to the eccentric position of the rotary disc, and the other end is rotationally connected to the lifting rod.

[0018] As a preferred technical scheme of the utility model, the lifting rod is through the dialling arm for forming the rotary structure.

[0019] As a preferred technical scheme of the utility model, further includes:

[0020] Threaded rod, the threaded rod is fixed at the eccentric position of the rotary disc, and the threaded rod has a through hole for the threaded rod to pass through on the dialling arm;

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

[0022] As a preferred technical scheme of the utility model, the through hole is distributed with multiple along the length direction of the dialling arm.

[0023] As a preferred technical scheme of the utility model, the movable hole is arranged on the first supporting plate, and the movable mounting base is movably arranged in the movable hole.

[0024] As a preferred technical scheme of the utility model, the utility model further comprises:

[0025] The guide rods are movably arranged in the movable hole and penetrate the movable mounting base.

[0026] The balance springs are arranged on the guide rods between the inner top surface of the movable hole and the top surface of the movable mounting base and between the inner bottom surface of the movable hole and the bottom surface of the movable mounting base.

[0027] As a preferred technical scheme of the utility model, the gas excitation mechanism comprises:

[0028] The shunt disc is provided with an air inlet, and the hollow rod is communicated with the air inlet.

[0029] The shunt disc is provided with a plurality of shunt channels which are equidistantly distributed along the circumferential direction and communicated with the air inlet, and the air jet nozzles are fixed to the ports of the shunt channels.

[0030] As a preferred technical scheme of the utility model, the excitation source mounting mechanism further comprises:

[0031] The rotary joint is fixed to the end of the hollow rod away from the gas excitation mechanism.

[0032] As a preferred technical scheme of the utility model, the two groups of machine case mounting mechanisms are equidistantly distributed, the lifting rods are fixed to the bottom ends of the two movable mounting bases, and the toggle arms are connected to the middle portions of the lifting rods.

[0033] Compared with the prior art, the utility model has the advantages that:

[0034] The detection equipment can be used for testing the total vibration of the aero-engine, and can also be used for testing the vibration of the blade of the aero-engine alone, and when the vibration performance of the blade is detected, the blade and the gas excitation mechanism can be simultaneously stationary, simultaneously rotated or only one of them is rotated, different detection requirements are met, the accuracy of the detection result is higher, and the detection equipment does not need to be replaced, and the use is more convenient.

[0035] Other additional advantages and beneficial effects of the application will be partially given in the following description, partially will become obvious from the following description, or will be understood by the practice of the application. BRIEF DESCRIPTION OF DRAWINGS

[0036] The accompanying drawings are used to provide further understanding of the present application, and constitute a part of the specification, and are used to explain the present application together with embodiments of the present application, and do not constitute a limitation to the present application. In the drawings:

[0037] Figure 1 is a structural schematic view of the present application;

[0038] Figure 2 is an axonometric structural schematic view of a driving mechanism in the present application;

[0039] Figure 3 is an axonometric structural schematic view of a machine case mounting mechanism in the present application;

[0040] Figure 4 is a sectional structural schematic view of a gas excitation mechanism in the present application.

[0041] In the drawings: 1, base; 2, machine case mounting mechanism; 21, No. 1 support plate; 211, movable hole; 22, movable mounting seat; 23, fixed flange; 24, guide rod; 25, balance spring; 3, transmission rod; 4, driving mechanism; 41, driving motor; 42, rotating disc; 43, threaded rod; 44, actuating 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, flow dividing disc; 5311, gas inlet; 5312, flow dividing passage; 532, gas jet nozzle; 54, rotating joint. DETAILED DESCRIPTION

[0042] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative work fall within the scope of protection of the present application.

[0043] Please refer to Figures 1-4 The present application provides the following technical solutions: an aero-engine vibration detection device, comprising a base 1, further comprising: a machine case mounting mechanism 2, a transmission rod 3, a driving mechanism 4 and an excitation source mounting mechanism 5.

[0044] Further, by Figure 1As shown, in the embodiment, the casing mounting mechanism 2 comprises 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 fixed flange 23 fixed on the movable mounting seat 22, the transmission rod 3 penetrates 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 for driving the movable mounting seat 22 to reciprocate in the vertical direction, the excitation source mounting mechanism 5 comprises 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 on the end of the hollow rod 52, and the gas excitation mechanism 53 is used for blowing high-pressure gas flow to the blades of the aero-engine, after the above scheme is adopted, in use, the casing of the aero-engine is fixed on the fixed flange 23, when the blades of the aero-engine are detected, the impeller casing is fixed on the fixed flange 23, and the main shaft of the blade is fixedly connected with the transmission rod 3, the hollow rod 52 is connected with the gas source, when the vibration total amount of the aero-engine is tested, the test sensor is fixed on the casing, and the test sensor is connected with 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, the casing is driven by the movable mounting seat 22 to reciprocate in the vertical direction, and the vibration performance of the aero-engine is monitored by the test sensor.

[0045] When the vibration performance of the blade is tested, 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 instrument device, the blade is driven to rotate by the transmission rod 3, and the vibration performance of the blade during rotation is monitored by the wireless vibration sensor.

[0046] When the vibration performance of the blade is tested, 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 instrument device, the blade is driven to rotate by the transmission rod 3, and the vibration performance of the blade during rotation is monitored by the wireless vibration sensor.

[0047] It should be noted that synchronous wheels are reserved on the transmission rod 3 and the hollow rod 52, and are shown in the drawings, and 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.

[0048] In addition, it should be further explained that, in the utility model, the transmission rod 3 and the hollow rod 52 are rotatably mounted through bearings, and the positions of the bearings are shown in the drawings.

[0049] Optionally, as shown in Figure 1 and Figure 2 In the embodiment, the driving mechanism 4 comprises a lifting rod 46, a driving motor 41, a rotating disc 42 and a poking 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 disc 42 is fixed on the output shaft of the driving motor 41, one end of the poking arm 44 is rotatably connected to the eccentric position of the rotating disc 42, and the other end is rotatably connected to the lifting rod 46. After the above scheme is adopted, in use, the driving motor 41 is started to drive the rotating disc 42 to rotate, the rotating disc 42 drives the poking arm 44 to swing and move up and down, the lifting rod 46 is driven by the poking arm 44 to move up and down, and the movable mounting seat 22 is driven to move up and down.

[0050] Optionally, as shown in Figure 1 and Figure 2 In the embodiment, the lifting rod 46 penetrates the poking arm 44 to form a rotating structure, and the rotating connection of the poking arm 44 and the lifting rod 46 is realized.

[0051] Preferably, as shown in Figure 1 and Figure 2 In the embodiment, it further comprises a threaded rod 43 and a locking nut 45, the threaded rod 43 is fixed at the eccentric position of the rotating disc 42, the poking arm 44 has a through hole 441 for the threaded rod 43 to penetrate, and the locking nut 45 is installed on the protruding end of the threaded rod 43 in a threaded screwing manner. After the above scheme is adopted, in use, the driving motor 41 is started to drive the rotating disc 42 to rotate, the rotating disc 42 drives the threaded rod 43 to do circular motion, and the threaded rod 43 drives the poking arm 44 to swing and move up and down.

[0052] Preferably, as shown in Figure 1 and Figure 2 In the embodiment, the through holes 441 are equally spaced along the length direction of the poking arm 44, so that the initial height of the movable mounting seat 22 can be adjusted by making the threaded rod 43 penetrate through the through holes 441 at different heights, and the accurate detection work is facilitated.

[0053] Preferably, as shown in Figures 1-3 In the embodiment, the first supporting plate 21 has a movable hole 211, and the movable mounting seat 22 is movable in the movable hole 211, the movable hole 211 is used for guiding and limiting the movable mounting seat 22, and the stability of the movable mounting seat 22 is ensured.

[0054] Preferably, as shown in Figures 1-3As shown, in the embodiment, further comprising: two guide rods 24, the two guide rods 24 are symmetrically fixed in the movable hole 211, and the guide rod 24 penetrates the movable mounting base 22, and the balance spring 25 is distributed between the inner top surface of the movable hole 211 and the top surface of the movable mounting base 22 and between the inner bottom surface of the movable hole 211 and the bottom surface of the movable mounting base 22 and is sleeved on the guide rod 24, after the above scheme is used, the guide rod 24 is used for guiding the movable mounting base 22, and the balance spring 25 has a reverse elastic force, so that the movement of the movable mounting base 22 is more stable, and the stability of the movable mounting base 22 is further improved.

[0055] Optionally, by Figure 1 and Figure 4 As shown, the gas excitation mechanism 53 comprises: a flow dividing disc 531 and a jet nozzle 532, the flow dividing disc 531 is provided with an air inlet 5311, the hollow rod 52 is communicated with the air inlet 5311, the flow dividing disc 531 is provided with a plurality of flow dividing channels 5312 which are equidistantly distributed in the circumferential direction and are communicated with the air inlet 5311, and the jet nozzle 532 is fixed at the port of the flow dividing channel 5312, after the above scheme is used, in use, the hollow rod 52 is connected with the gas source, the high-pressure gas enters the air inlet 5311 through the hollow rod 52, then is divided into each flow dividing channel 5312, and finally is discharged from the jet nozzle 532.

[0056] Preferably, by Figure 1 As shown, in the embodiment, the excitation source mounting mechanism 5 further comprises: a rotary joint 54, the rotary joint 54 is fixed at one end of the hollow rod 52 away from the gas excitation mechanism 53, after the above scheme is used, the hollow rod 52 is connected with the gas source through the rotary joint 54, so that the hollow rod 52 drives the gas excitation mechanism 53 to rotate in the test.

[0057] Preferably, by Figure 1 As shown, in the embodiment, the two groups of casing mounting mechanisms 2 are equidistantly distributed, the lifting rod 46 is fixed at the bottom end of the two movable mounting bases 22, and the poking arm 44 is connected to the middle part of the lifting rod 46, therefore, the detection equipment of the utility model supports the aero-engine casing by the two groups of casing mounting mechanisms 2, one group of casing mounting mechanisms 2 is directly fixedly connected with the casing, and the two groups of casing mounting mechanisms 2 indirectly support the aero-engine casing through the support transmission rod 3, so that the stability of the aero-engine casing is ensured, and the aero-engine casing also has high stability when reciprocating and oscillating in the vertical direction.

[0058] The circuit connection of the utility model relates to the common means adopted by the person skilled in the art, and the technical inspiration can be obtained through limited tests, and belongs to the prior art which is widely used.

[0059] The components not described in detail in the present application are the prior art.

[0060] The working principle and use process of the utility model: the detection equipment of the utility model, when using, the machine case of aero-engine is fixed on the fixed flange 23,

[0061] Firstly, when detecting the blade of aero-engine, the impeller machine case is fixed on the fixed flange 23, and the main shaft of the blade is fixedly connected with the transmission rod 3, the hollow rod 52 is connected with the gas source, and the sensor for testing is fixed on the blade, since the blade needs to rotate during testing, therefore the sensor for testing preferably adopts wireless vibration sensor, the transmission rod 3 is driven to rotate by external instrument equipment, the transmission rod 3 drives the blade to rotate, and the vibration performance of the blade during rotation is monitored through the wireless vibration sensor;

[0062] When testing the vibration performance of the blade of the impeller, the high-pressure gas flow can also be blown to the blade of aero-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 external instrument equipment, so that the blade rotates, the blade can also be tested in a static state, and the hollow rod 52 can also be driven to rotate by external instrument equipment, so that the gas excitation mechanism 53 blows the high-pressure gas flow to the blade during rotation, a plurality of tests are carried out under different states, the accuracy of the detection result is higher, and the detection equipment does not need to be replaced, and use is more convenient;

[0063] Secondly, when testing the total vibration of aero-engine, the sensor for testing is fixed on the machine case, and the sensor for testing is connected with the control host of the detection system, then the driving mechanism 4 is started to drive the movable mounting seat 22 to reciprocate along the vertical direction, the machine case is driven to reciprocate along the vertical direction through the movable mounting seat 22, and the vibration performance of aero-engine is monitored through the sensor for testing;

[0064] The detection equipment of the utility model can be used for testing the total vibration of aero-engine, can also be used for testing the vibration of the blade of aero-engine alone, and when testing the vibration performance of the blade, the blade and the gas excitation mechanism 53 can be simultaneously static, simultaneously rotate or only one of them rotates, different detection requirements are met, the accuracy of the detection result is higher, and the detection equipment does not need to be replaced, and use is more convenient.

[0065] Finally, it should be pointed out that: the above-mentioned only for preferred embodiment of the utility model, and does not limit the utility model, although the utility model has been described in detail with reference to the foregoing embodiments, for the person skilled in the art, still can modify the technical scheme recorded in the foregoing each embodiment, or equivalent replacement to part of technical features. Any modification, equivalent replacement, improvement etc. within the spirit and principle of the utility model should be included in the protection scope of the utility model.

Claims

1. An aeroengine vibration detection apparatus comprising a base (1), characterised in that, Also include: The machine case 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) penetrates and is rotatably connected to the movable mounting seat (22), and the transmission rod (3) is coaxial with the fixed flange (23); The drive mechanism (4) is drivably connected to the movable mounting seat (22) for driving the movable mounting seat (22) to reciprocate vertically; The excitation source mounting mechanism (5) includes a No. 2 support plate (51) fixed on the base (1), a hollow rod (52) penetrating 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 for blowing high-pressure gas flow to the blade of the aero-engine.

2. The aircraft engine vibration detection apparatus of claim 1, wherein: The drive mechanism (4) includes: The lifting rod (46) is fixed to the bottom end of the movable mounting seat (22); The drive motor (41) is fixed on the base (1); The rotating disc (42) is fixed on the output shaft of the drive motor (41); The toggle arm (44) is rotatably connected to the eccentric position of the rotating disc (42) at one end and rotatably connected to the lifting rod (46) at the other end.

3. The aircraft engine vibration detection apparatus of claim 2, wherein: The lifting rod (46) penetrates the toggle arm (44) to form a rotating structure.

4. The aircraft engine vibration detection apparatus of claim 2, wherein: Also include: The threaded rod (43) is fixed at the eccentric position of the rotating disc (42), and the threaded rod (43) has a through hole (441) penetrating the toggle arm (44); The locking nut (45) is installed on the protruding end of the threaded rod (43) by screwing.

5. The aircraft engine vibration detection apparatus of claim 4, wherein: The through hole (441) is equally spaced along the length direction of the toggle arm (44).

6. The aircraft engine vibration detection apparatus of claim 1, wherein: The No. 1 support plate (21) has a movable hole (211), and the movable mounting seat (22) is movably located in the movable hole (211).

7. The aircraft engine vibration detection apparatus of claim 6, wherein: Also include: The guide rod (24) is fixed symmetrically in the movable hole (211), and the guide rod (24) penetrates the movable mounting seat (22); The balance spring (25) is arranged on the guide rod (24) 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 apparatus of claim 1, wherein: The gas excitation mechanism (53) includes: The shunt disc (531) has an air inlet (5311), and the hollow rod (52) communicates with the air inlet (5311); A plurality of distribution channels (5312) are equidistantly distributed on the distribution disc (531) in a circumferential direction, and the distribution channels (5312) are communicated with the gas inlet (5311). The gas nozzle (532) is fixed at the end of the distribution channel (5312).

9. The aircraft engine vibration detection apparatus of claim 1, wherein: The excitation source mounting mechanism (5) further comprises: A rotary joint (54) is fixed at the end of the hollow rod (52) away from the gas excitation mechanism (53).

10. The aircraft engine vibration detection apparatus of claim 2, wherein: Two groups of the case mounting mechanisms (2) are equidistantly distributed, the lifting rod (46) is fixed at the bottom end of the two movable mounting seats (22), and the toggle arm (44) is connected to the middle part of the lifting rod (46).

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