Aero-engine rotor system sudden unbalance test device

Abstract

The application relates to the field of machine component testing, and discloses an aero-engine rotor system sudden imbalance testing device, which comprises a balance testing frame and a balance testing mechanism, the balance testing mechanism is arranged on the upper surface of the balance testing frame, the balance testing mechanism is used for testing the sudden imbalance of an aero-engine rotor, an auxiliary marking mechanism is arranged above the balance testing mechanism, the balance testing mechanism is used for marking the imbalance position while testing the aero-engine rotor and issuing a shaking sound to assist in judging the sudden imbalance of the rotor, through the double feedback mechanisms of vision and hearing, the application realizes accurate and rapid judgment of the imbalance state of the aero-engine rotor, improves the efficiency and accuracy of the rotor balance testing, and provides a powerful guarantee for the safe operation of the aero-engine.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of machine component testing, in particular to a sudden unbalance test device for aero-engine rotor system. BACKGROUND

[0002] An aero-engine is a core component of a modern aircraft, and its performance directly determines the safety and reliability of the aircraft. As a key component of the engine, the rotor system bears the core task of converting mechanical energy into thrust. In the actual operation of the aero-engine, the rotor system may suddenly produce unbalanced load due to reasons such as blade fracture, foreign object impact or component failure. This sudden unbalance will have a significant impact on the vibration characteristics, structural integrity and operation stability of the engine. Therefore, it is of great significance to study the dynamic response of the rotor system under the condition of sudden unbalance for evaluating the reliability and safety of the engine.

[0003] According to the authorized patent announcement number CN111947836B, a test device and method for simulating rotor system sudden unbalance fault are disclosed, which comprises a motor, a first coupling, a bearing seat, a rotating shaft, a balancing iron block, a wheel disc, a conductive ring, an insulating sheet, an electric brush and a vibration sensor. The output end of the motor is connected with the first coupling, the other end of the first coupling is connected with the rotating shaft, the rotating shaft passes through the shaft center of the wheel disc and is fixed with the wheel disc, the wheel disc has the balancing iron block, the two ends of the rotating shaft are provided with the bearing seat, the balancing iron block is sleeved with a coil, the coil is connected with the conductive ring, the outer wall of the rotating shaft is connected with the insulating sheet, and the insulating sheet is fixedly connected with the electric brush. The sensor is used for collecting the vibration signals of the power end of the rotating shaft and the rotating shaft on the bearing seat.

[0004] The above disclosed technical scheme has the advantages of simple structure, convenient disassembly and assembly, and reduced labor consumption in the test process compared with the previous one. However, the test device still has some deficiencies. The device relies on the vibration sensor to collect the vibration signals to determine the unbalance state of the rotor. This way has limited information and it is difficult to directly determine the specific position and severity of the unbalance. In addition, complex analysis and processing of the collected vibration signals are required to draw a conclusion, which requires high professional knowledge and experience of the operator and takes a long time for analysis, which is not conducive to rapid judgment and timely handling of faults. SUMMARY

[0005] In view of the deficiencies of the prior art, the present application provides an aero-engine rotor system sudden unbalance test device to solve the above problems.

[0006] To achieve the above purpose, the present application realizes the following technical scheme: an aero-engine rotor system sudden unbalance test device, comprising:

[0007] a balancing test frame;

[0008] The balance test mechanism is arranged on the upper surface of the balance test frame and is used for testing the sudden imbalance of the aero-engine rotor;

[0009] The auxiliary marking mechanism is arranged above the balance test mechanism and is used for marking the imbalance position and issuing a shaking sound to assist in judging the sudden imbalance of the rotor when the aero-engine rotor is tested;

[0010] The auxiliary marking mechanism comprises a linkage ring, a conical protruding end, a movable rod, a marking chalk, a swing arm, a swing support, a swing blade and a square protruding end, a rough surface test shaft is vertically arranged in the middle of the linkage ring, square protruding ends are arranged on the left and right sides of the linkage ring, conical protruding ends are arranged on the front and back sides of the linkage ring, a marking chalk is arranged in the middle of the left square protruding end and is used for leaving marks on the surface of the rough surface test shaft, movable rods are rotatably connected to the outer sides of the two conical protruding ends, one end of each of the two movable rods away from the corresponding conical protruding end is rotatably connected to one end of a swing arm, the two swing arms are fixedly connected to the front and back sides of a swing support, swing blades are movably connected to the left and right ends of the swing support, in the process of testing the aero-engine rotor, the motor in the balance test mechanism drives the up-and-down moving ring and the linkage ring to move up and down on the surface of the rough surface test shaft connected to the aero-engine rotor through a coupling, if the rotor in the aero-engine body shakes when rotating due to unbalanced load, the rough surface test shaft shakes and rubs or collides with the marking chalk, thereby leaving marks on the surface of the rough surface test shaft, in the case of severe imbalance, the marks on the surface of the rough surface test shaft are no longer limited to slight friction marks, but may form obvious scratches, spots or continuous lines, in this way, the position of the sudden imbalance of the rotor is directly indicated, and an accurate basis is provided for subsequent rotor balance correction, in addition, the conical protruding ends push the movable rods to reciprocate when the linkage ring moves up and down, the other end of the movable rod is connected to the swing arm, therefore, the swing arm also reciprocates, the swing motion of the swing arm is transmitted to the swing blade through the swing support, so that the swing blade also reciprocates, since there is a gap between the swing blade and the swing support, when the swing blade reciprocates, the gap causes the swing blade to collide with or rub against the support or other components, thereby emitting a sound, as the shaking amplitude increases, a louder or higher frequency sound is produced, the change in the sound provides intuitive auditory feedback for the operator, so that the operator can quickly judge the severity of the rotor imbalance;

[0011] The application realizes accurate and rapid judgment of the unbalanced state of the aero-engine rotor through the dual feedback mechanism of vision and hearing, improves the efficiency and accuracy of the rotor balance test, provides a strong guarantee for the safe operation of the aero-engine, and utilizes the collision sound principle of the simple mechanical transmission mechanism and loose parts, has a relatively simple structure, is easy to realize and control, and reduces the manufacturing cost and maintenance difficulty.

[0012] Preferably, the lower end of the swing support is clamped and connected with the rough surface test shaft, an aero-engine body is arranged below the rough surface test shaft, and a shaft coupling is keyed between the lower end of the rough surface test shaft and the rotor of the aero-engine body.

[0013] Preferably, the balance test mechanism comprises fixing supports, motors, rotating arms one, rotating arms two, swing rods, connecting arms and up-and-down moving rings, the number of the fixing supports is three, the three fixing supports are distributed around the upper surface of the balance test stand, and the upper surfaces of the three fixing supports are all fixedly connected with the motors.

[0014] Preferably, the output end of each motor is drivingly connected with the rotating arm one, one end of the rotating arm one away from the output end of the motor is rotationally connected with the rotating arm two, and one end of the rotating arm two away from the rotating arm one is rotationally connected with the swing rod.

[0015] Preferably, the upper end of the swing rod is rotationally connected with the outer end of the connecting arm, the inner end of the connecting arm is fixedly connected with the outside of the up-and-down moving ring, and the up-and-down moving ring is sleeved outside the rough surface test shaft.

[0016] Preferably, the outside of the right square protruding end is rotationally connected with a limiting swing arm one, the upper end of the limiting swing arm one is rotationally connected with the lower end of a limiting swing arm two, and one end of the limiting swing arm two away from the limiting swing arm one is rotationally connected with the outside of the lower end of the swing support.

[0017] Preferably, the upper surface of the aero-engine body is provided with four engine mounting rods, and each engine mounting rod is threadedly connected with the aero-engine body.

[0018] Preferably, the upper end of each engine mounting rod penetrates the balance test stand, and each engine mounting rod is threadedly connected with a mounting nut at the upper end, and the mounting nut is arranged on the upper surface of the balance test stand.

[0019] Preferably, the upper surface of the left square protruding end is provided with a fastening nut, and the lower end of the fastening nut penetrates the square protruding end and is threadedly connected with the square protruding end.

[0020] Preferably, one side of the up-and-down moving ring is fixedly connected with a connecting rod, one end of the connecting rod away from the up-and-down moving ring penetrates the inside of a limiting support, and a limiting groove is formed in the inside of the limiting support. Advantages

[0021] The application provides a sudden imbalance test device for an aero-engine rotor system, and has the following advantages compared with the prior art:

[0022] 1、In the application, the auxiliary marking mechanism is arranged, in the process of testing the aero-engine rotor, the motor in the balance test mechanism drives the up-down moving ring to move up and down on the surface of the rough test shaft connected with the aero-engine rotor through the coupling, if the rotor in the aero-engine body shakes when rotating due to the unbalanced load, the rough test shaft shakes and rubs or collides with the marking powder, and then leaves marks on the surface of the rough test shaft, in the case of serious imbalance, the marks on the surface of the rough test shaft are no longer limited to slight friction marks, but may form obvious scratches, spots or continuous lines, in this way, the position of the sudden imbalance of the rotor is directly indicated, and an accurate basis is provided for subsequent rotor balance correction, in addition, with the up-down movement of the linkage ring, the conical protruding end pushes the movable rod to reciprocate in the up-down movement process, the other end of the movable rod is connected with the swing arm, so that the swing arm also reciprocates, the swing movement of the swing arm is transmitted to the swing blade through the swing support, so that the swing blade also reciprocates, since there is a gap at the connection between the swing blade and the swing support, when the swing blade reciprocates, the gap causes the swing blade to collide or rub with the support or other components, thereby emitting a sound, with the increase of the shaking amplitude, a louder or higher frequency sound is produced, the change of the sound provides intuitive auditory feedback for the operator, so that the operator can quickly judge the severity of the rotor imbalance, the application realizes accurate and rapid judgment of the imbalance state of the aero-engine rotor through the double feedback mechanism of vision and hearing, improves the efficiency and accuracy of the rotor balance test, provides a powerful guarantee for the safe operation of the aero-engine, and utilizes the collision sound emission principle of the simple mechanical transmission mechanism and the loose parts, the structure is relatively simple, easy to realize and control, and the manufacturing cost and maintenance difficulty are reduced;

[0023] 2、The present application, by setting the balance test mechanism, before testing the rotor system of the aero-engine body, the aero-engine body is placed in the balance test bench under the surface, and the four engine installation rod lower end is screwed into the screw hole of the aero-engine body, then the four engine installation rod upper end is screwed into the installation nut of the balance test bench surface, finally the motor drives the rotation arm one rotation, and then drives the rotation arm two and the swing rod swing, finally makes the up and down moving ring moves up and down along the rough surface test shaft, the linkage ring also moves up and down on the surface of the rough surface test shaft under the action of the up and down moving hall, when the rotor in the aero-engine body shakes due to unbalanced load, the shaking of the rough surface test shaft will rub or collide with the marking powder, thereby leaving marks on the surface of the shaft. BRIEF DESCRIPTION OF DRAWINGS

[0024] Figure 1 The three-dimensional structure schematic diagram of the aero-engine rotor system sudden added unbalance test device provided by the present application is shown in the figure.

[0025] Figure 2 The structure schematic diagram of the other side view of the aero-engine rotor system sudden added unbalance test device provided by the present application is shown in the figure.

[0026] Figure 3 The structure schematic diagram of the bottom view of the aero-engine rotor system sudden added unbalance test device provided by the present application is shown in the figure.

[0027] Figure 4 The front structure schematic diagram of the auxiliary marking mechanism in the aero-engine rotor system sudden added unbalance test device provided by the present application is shown in the figure.

[0028] Figure 5 The side structure schematic diagram of the auxiliary marking mechanism in the aero-engine rotor system sudden added unbalance test device provided by the present application is shown in the figure.

[0029] Figure 6 The structure schematic diagram of the balance test mechanism in the aero-engine rotor system sudden added unbalance test device provided by the present application is shown in the figure.

[0030] Figure 7 The structure schematic diagram of the linkage ring in the aero-engine rotor system sudden added unbalance test device provided by the present application is shown in the figure.

[0031] Figure 8 The Figure 6 The enlarged view of A in the figure.

[0032] Legend:

[0033] 1, balance test frame; 2, aero-engine body;

[0034] 3. Balance testing mechanism; 301. Fixed support; 302. Motor; 303. Rotary arm 1; 304. Rotary arm 2; 305. Rocking lever; 306. Connecting arm; 307. Up and down moving ring; 308. Connecting rod; 309. Limiting support; 310. Limiting groove;

[0035] 4. Auxiliary marking mechanism; 401. Linkage ring; 402. Conical convex end; 403. Movable rod; 404. Fastening nut; 405. Marking chalk; 406. Rocking arm; 407. Rocking support; 408. Rocking blade; 409. Limiting swing arm 1; 410. Limiting swing arm 2; 411. Square convex end;

[0036] 5. Mounting nut; 6. Engine mounting rod; 7. Coupling; 8. Rough surface testing shaft. DETAILED DESCRIPTION

[0037] The technical solutions of the present application will be described clearly and completely below in combination with the drawings of the present application. Obviously, the described embodiments are only some of the embodiments of the present application, but not all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of protection of the present application.

[0038] Please refer to Figures 1-8 The present application provides two technical solutions, specifically including the following embodiments:

[0039] Embodiment 1

[0040] The application discloses an aero-engine rotor system sudden imbalance test device, which comprises a balance test frame 1, a balance test mechanism 3 arranged on the upper surface of the balance test frame 1, an auxiliary marking mechanism 4 arranged above the balance test mechanism 3, and an aero-engine body 2. The balance test mechanism 3 is used for testing the sudden imbalance of the rotor of the aero-engine body 2, the auxiliary marking mechanism 4 is used for marking the imbalance position and issuing a shaking sound to assist in judging the sudden imbalance of the rotor when the aero-engine body 2 rotor is tested, and the auxiliary marking mechanism 4 comprises a linkage ring 401, a conical protruding end 402, a movable rod 403, a marking chalk 405, a swing arm 406, a swing support 407, a swing blade 408 and a square protruding end 411. The middle part of the linkage ring 401 is vertically penetrated by a rough surface test shaft 8, the left and right sides of the linkage ring 401 are provided with the square protruding end 411, and the front and rear sides of the linkage ring 401 are provided with the conical protruding end 402. The middle part of the left square protruding end 411 is penetrated by the marking chalk 405, the marking chalk 405 is used for leaving traces on the surface of the rough surface test shaft 8, the outer sides of the two conical protruding ends 402 are rotationally connected with the movable rods 403, the ends, away from the corresponding conical protruding ends 402, of the two movable rods 403 are rotationally connected with the ends of the two swing arms 406, the two swing arms 406 are fixedly connected with the front and rear sides of the swing support 407, the left and right ends of the swing support 407 are movably connected with the swing blades 408, the swing blades 408 are connected with the swing support 407 with a gap, the lower end of the swing support 407 is clampedly connected with the rough surface test shaft 8, the rough surface test shaft 8 is made of wear-resistant coated alloy steel plate and is commonly used for manufacturing blackboard materials, the aero-engine body 2 is arranged below the rough surface test shaft 8, the shaft coupling 7 is arranged between the lower end of the rough surface test shaft 8 and the rotor of the aero-engine body 2, the outer side of the right square protruding end 411 is rotationally connected with a limiting swing arm one 409, the upper end of the limiting swing arm one 409 is rotationally connected with the lower end of a limiting swing arm two 410, the end, away from the limiting swing arm one 409, of the limiting swing arm two 410 is rotationally connected with the outer side of the lower end of the swing support 407, and the upper surface of the left square protruding end 411 is provided with a fastening nut 404.

[0041] When working, in the process of testing the rotor of the aero-engine, the motor 302 in the balance testing mechanism 3 drives the up-and-down moving ring 307 to move up and down on the surface of the rough surface test shaft 8 connected with the rotor of the aero-engine through the coupling 7, if the rotor in the aero-engine body 2 shakes when rotating due to unbalanced load, the rough surface test shaft 8 shakes and rubs or collides with the marking powder in the process of shaking, and then leaves marks on the surface of the rough surface test shaft 8, in the case of serious imbalance, the marks on the surface of the rough surface test shaft 8 will no longer be limited to slight rubbing marks, but may form obvious scratches, spots or continuous lines, in this way, the position of the suddenly unbalanced rotor is directly indicated, and accurate basis is provided for subsequent rotor balance correction, in addition, as the linkage ring 401 moves up and down, the conical protruding end 402 pushes the movable rod 403 to reciprocate in the process of moving up and down, the other end of the movable rod 403 is connected with the swing arm 406, so the swing arm 406 also swings reciprocally, the swing movement of the swing arm 406 is transmitted to the swing blade 408 through the swing support 407, so that the swing blade 408 also swings reciprocally, as there is a gap between the swing blade 408 and the swing support 407, when the swing blade 408 swings reciprocally, the looseness will cause the swing blade 408 to collide or rub with the support or other components, thereby producing sound, as the shaking amplitude increases, louder or higher frequency sound is produced, the change of the sound provides intuitive auditory feedback for the operator, so that he can quickly judge the severity of the rotor imbalance.

[0042] Example two

[0043] On the basis of the first embodiment, the balance test mechanism 3 comprises a fixed support 301, a motor 302, a rotating arm one 303, a rotating arm two 304, a swing rod 305, a connecting arm 306, and an up-down moving ring 307. The number of the fixed supports 301 is three, which are distributed around the upper surface of the balance test stand 1. The upper surface of each fixed support 301 is fixedly connected with a motor 302. The output end of each motor 302 is drivingly connected with a rotating arm one 303. One end of the rotating arm one 303 away from the output end of the motor 302 is rotatably connected with a rotating arm two 304. One end of the rotating arm two 304 away from the rotating arm one 303 is rotatably connected with a swing rod 305. The upper end of the swing rod 305 is rotatably connected with the outer end of the connecting arm 306. The inner end of the connecting arm 306 is fixedly connected with the outer side of the up-down moving ring 307. The up-down moving ring 307 is sleeved on the outer side of the rough surface test shaft 8. The upper surface of the aero-engine body 2 is provided with four engine mounting rods 6. Each engine mounting rod 6 is threadedly connected with the aero-engine body 2. The upper end of each engine mounting rod 6 penetrates the balance test stand 1 and is threadedly connected with a mounting nut 5 on the upper surface of the balance test stand 1. One side of the up-down moving ring 307 is fixedly connected with a connecting rod 308. One end of the connecting rod 308 away from the up-down moving ring 307 penetrates the inside of a limiting support 309. A limiting groove 310 is formed in the inside of the limiting support 309. It should be noted that when marking or drawing with tools such as paint sprayer, chalk, and marker pen, if the tool or the marked surface shakes during the movement, the greater the shaking amplitude, the longer and more irregular the traces left. Essentially, the shaking increases the effective moving distance, prolongs the contact time, and changes the force condition, so the balance test mechanism 3 drives the up-down moving ring 307 to move up and down along the rough surface test shaft 8;

[0044] Before testing the rotor system of the aero-engine body 2, the aero-engine body 2 is placed on the lower surface of the balance test stand. The lower ends of the four engine mounting rods 6 are screwed into the threaded holes of the aero-engine body 2. Then the mounting nuts 5 are screwed onto the upper ends of the four engine mounting rods 6 and the surface of the balance test stand. Finally, the motor 302 drives the rotating arm one 303 to rotate, which in turn drives the rotating arm two 304 and the swing rod 305 to swing, and finally drives the up-down moving ring 307 to move up and down along the rough surface test shaft 8. The linkage ring 401 also moves up and down on the surface of the rough surface test shaft 8 under the action of the up-down moving ring 307. When the rotor in the aero-engine body 2 shakes due to unbalanced load during rotation, the shaking of the rough surface test shaft 8 will rub or collide with the marked powder, leaving traces on the surface of the shaft.

[0045] The above only describes preferred embodiments of the present application and is not used to limit the present application, and any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the application should be included in the protection scope of the present application.

Claims

1. An aero-engine rotor system sudden imbalance test device, comprising: a balance test frame (1); a balance test mechanism (3); characterized in that the balance test mechanism (3) is arranged on the upper surface of the balance test frame (1), and the balance test mechanism (3) is used for testing the sudden imbalance of the rotor of the aero-engine body (2); an auxiliary marking mechanism (4); the auxiliary marking mechanism (4) is located above the balance test mechanism (3), and the balance test mechanism (3) is used for marking the imbalance position while testing the rotor of the aero-engine body (2) and issuing a shaking sound to assist in judging the sudden imbalance of the rotor; the auxiliary marking mechanism (4) comprises a linkage ring (401), a conical protruding end (402), a movable rod (403), a marking chalk (405), a swing arm (406), a swing support (407), a swing blade (408) and a square protruding end (411), a rough surface test shaft (8) is vertically arranged in the middle of the linkage ring (401), square protruding ends (411) are arranged on the left and right sides of the linkage ring (401), conical protruding ends (402) are arranged on the front and back sides of the linkage ring (401), wherein a marking chalk (405) is arranged in the middle of the left square protruding end (411), the marking chalk (405) is used for leaving marks on the surface of the rough surface test shaft (8), movable rods (403) are rotatably connected to the outer sides of the two conical protruding ends (402), one ends of the two movable rods (403) away from the corresponding conical protruding ends (402) are rotatably connected to one ends of two swing arms (406), the two swing arms (406) are fixedly connected to the front and back sides of a swing support (407), and swing blades (408) are movably connected to the left and right ends of the swing support (407); the swing support (407) is clamped and connected to the rough surface test shaft (8), and the aero-engine body (2) is arranged below the rough surface test shaft (8); the balance test mechanism (3) comprises a fixed support (301), a motor (302), a rotating arm one (303), a rotating arm two (304), a swing rod (305), a connecting arm (306) and an up-down moving ring (307), the number of the fixed supports (301) is three, the three fixed supports (301) are distributed around the upper surface of the balance test frame (1), and the upper surfaces of the three fixed supports (301) are fixedly connected with the motors (302); one side of the up-down moving ring (307) is fixedly connected with a connecting rod (308), one end of the connecting rod (308) away from the up-down moving ring (307) is arranged in a limiting support (309), and a limiting groove (310) is formed in the limiting support (309).

2. The test apparatus of claim 1, wherein: A shaft coupling (7) is connected between the lower end of the rough surface test shaft (8) and the rotor of the aero-engine body (2).

3. The test apparatus of claim 1, wherein: The output end of each motor (302) is drivingly connected with a rotating arm one (303), one end of the rotating arm one (303) away from the output end of the motor (302) is rotatably connected with a rotating arm two (304), one end of the rotating arm two (304) away from the rotating arm one (303) is rotatably connected with a swing rod (305).

4. The test apparatus of claim 3, wherein: The upper end of the swing rod (305) is rotatably connected with the outer end of a connecting arm (306), the inner end of the connecting arm (306) is fixedly connected with the outer side of an up-down moving ring (307), the up-down moving ring (307) is sleeved on the outer side of the rough surface test shaft (8).

5. The test apparatus of claim 1, wherein: The outer side of the right square protruding end (411) is rotatably connected with a limiting swing arm one (409), the upper end of the limiting swing arm one (409) is rotatably connected with the lower end of a limiting swing arm two (410), one end of the limiting swing arm two (410) away from the limiting swing arm one (409) is rotatably connected with the outer side of the lower end of a swing bracket (407).

6. The test apparatus of claim 1, wherein: The upper surface of the aero-engine body (2) is provided with four engine mounting rods (6), each engine mounting rod (6) is in threaded connection with the aero-engine body (2).

7. The test apparatus of claim 6, wherein: The upper end of each engine mounting rod (6) penetrates the balance test frame (1), and the upper end of each engine mounting rod (6) is in threaded connection with a mounting nut (5), and the mounting nut (5) is arranged on the upper surface of the balance test frame (1).

8. The test apparatus of claim 1, wherein: The upper surface of the left square protruding end (411) is provided with a fastening nut (404), the lower end of the fastening nut (404) penetrates the square protruding end (411) and is in threaded connection with the square protruding end (411).

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