Aero-engine rotor system sudden loading unbalance test device

Abstract

The invention relates to the field of machine part testing, and discloses an aero-engine rotor system sudden loading unbalance test device, which comprises a balance test rack and a balance test mechanism, and is characterized in that the balance test mechanism is arranged on the upper surface of the balance test rack, and is used for testing the sudden loading unbalance condition of an aero-engine body rotor; the auxiliary marking mechanism is located above the balance testing mechanism, and the balance testing mechanism is used for marking an unbalanced position and making a shaking sound to assist in judging the sudden unbalance condition of the rotor while testing the rotor of the aero-engine body. The method achieves the precise and rapid judgment of the unbalance state of the aero-engine rotor, improves the efficiency and accuracy of the balance test of the rotor, and provides a powerful guarantee for the safe operation of the aero-engine.

Description

Technical Field

[0001] The present invention relates to the field of machine component testing, and particularly to a sudden unbalance test device for an aero-engine rotor system. Background Art

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

[0003] According to the Chinese authorized patent publication number: CN111947836B, a test device and method for simulating sudden unbalance faults of a rotor system are disclosed, including a motor, a first coupling, a bearing seat, a rotating shaft, balance iron blocks, a wheel disc, a slip ring, an insulating sheet, a carbon brush, and a vibration sensor. The output end of the motor is connected to the first coupling, the other end of the first coupling is connected to the rotating shaft, the rotating shaft passes through the center of the wheel disc and is fixed to the wheel disc. There are balance iron blocks on the wheel disc, coils are sleeved on the balance iron blocks, the coils are connected to the slip ring, an insulating sheet is connected to the outer wall of the rotating shaft, and the insulating sheet is fixedly connected to the carbon brush; the sensor is used to collect the vibration signals at the power end of the rotating shaft and the vibration signals of the rotating shaft on the bearing seat.

[0004] The above-disclosed technical solution has a simple structure, is convenient for disassembly and assembly, and the test process reduces a large amount of labor consumption compared with the past. However, this test device still has deficiencies. This device relies on vibration sensors to collect vibration signals to judge the unbalance state of the rotor. This method has limited information and it is difficult to intuitively determine the specific location and severity of the unbalance. Moreover, complex analysis and processing of the collected vibration signals are required to draw conclusions, which requires high professional knowledge and experience of the operators, and the analysis time is long, which is not conducive to quickly judging and timely handling faults. Summary of the Invention

[0005] In view of the deficiencies of the prior art, the present invention provides a sudden unbalance test device for an aero-engine rotor system, which solves the above problems.

[0006] To achieve the above object, the present invention is realized through the following technical solutions: A sudden unbalance test device for an aero-engine rotor system, including: A balance test stand; Balance test mechanism; the balance test mechanism is arranged on the upper surface of the balance test stand, and the balance test mechanism is used to test the sudden unbalance condition of the rotor of the aero-engine body; Auxiliary marking mechanism; the auxiliary marking mechanism is located above the balance test mechanism, and the balance test mechanism is used to mark the unbalanced position and emit a shaking sound to assist in judging the sudden unbalance condition of the rotor while testing the rotor of the aero-engine body; The auxiliary marking mechanism includes a linkage ring, a conical protruding end, a movable rod, a marking chalk, a rocking arm, a rocking bracket, a rocking leaf and a square protruding end. A rough surface test shaft is vertically penetrated through the middle of the linkage ring. Square protruding ends are arranged on both the left and right sides of the linkage ring, and conical protruding ends are arranged on both the front and back sides of the linkage ring. Among them, the middle of the left square protruding end is penetrated with a marking chalk, and the marking chalk is used to leave 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 ends of the two movable rods far away from the corresponding conical protruding ends are respectively rotatably connected to one ends of the two rocking arms. The two rocking arms are fixedly connected to the front and back sides of the rocking bracket. Rocking leaves are movably connected to both the left and right ends of the rocking bracket. During the process of testing the aero-engine rotor, the motor in the balance test mechanism drives the upper and lower 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 generates shaking due to unbalanced load during rotation, the shaking rough surface test shaft will generate friction or collision with the marking powder during the shaking process, and thus leave marks on the surface of the rough surface test shaft. In a severely unbalanced state, the marks on the surface of the rough surface test shaft will no longer be limited to slight friction marks, but may form obvious scratches, spots or continuous lines, indicating the position of the sudden unbalance of the rotor in this way and providing an accurate basis for subsequent rotor balance correction. In addition, as the linkage ring moves up and down, the conical protruding end will push the movable rod to make a reciprocating motion during the up and down movement. The other end of the movable rod is connected to the rocking arm, so the rocking arm will also make a reciprocating swing. This swinging motion of the rocking arm is transmitted to the rocking leaf through the rocking bracket, causing the rocking leaf to also perform a reciprocating rotational swing. Since there is a gap at the connection between the rocking leaf and the rocking bracket, when it performs a reciprocating rotational swing, this looseness will cause the rocking leaf to collide or rub against the bracket or other components, thereby generating a sound. As the shaking amplitude increases, a louder or higher-frequency sound will be generated. This sound change provides intuitive auditory feedback for the operator, enabling them to quickly judge the severity of the rotor unbalance; Through a dual feedback mechanism of vision and audition, the present invention realizes accurate and rapid judgment of the unbalanced state of an aero-engine rotor, improves the efficiency and accuracy of rotor balance testing, provides strong guarantee for the safe operation of the aero-engine, and utilizes a simple mechanical transmission mechanism and the principle of collision sound generation of loose components, with relatively simple structure, easy to implement and control, reducing the manufacturing cost and maintenance difficulty.

[0007] Preferably, the lower end of the swing bracket is snap-connected to the rough surface test shaft, an aero-engine body is arranged below the rough surface test shaft, and a coupling is key-connected between the lower end of the rough surface test shaft and the rotor of the aero-engine body.

[0008] Preferably, the balance test mechanism includes fixed brackets, motors, a first rotating arm, a second rotating arm, a swing rod, a connecting arm and an up-and-down moving ring. The number of the fixed brackets is three, and the three fixed brackets are distributed around the upper surface of the balance test stand, and motors are fixedly connected to the upper surfaces of the three fixed brackets.

[0009] Preferably, the output end of each motor is drivingly connected to a first rotating arm, one end of the first rotating arm far away from the output end of the motor is rotatably connected to a second rotating arm, and one end of the second rotating arm far away from the first rotating arm is rotatably connected to a swing rod.

[0010] Preferably, the upper end of the swing rod is rotatably connected to the outer end of the connecting arm, the inner end of the connecting arm is fixedly connected to the outside of the up-and-down moving ring, and the up-and-down moving ring is sleeved outside the rough surface test shaft.

[0011] Preferably, a limiting swing arm one is rotatably connected to the outside of the right square convex end, the upper end of the limiting swing arm one is rotatably connected to the lower end of the limiting swing arm two, and one end of the limiting swing arm two far away from the limiting swing arm one is rotatably connected to the outside of the lower end of the swing bracket.

[0012] Preferably, four engine mounting rods are arranged on the upper surface of the aero-engine body, and each engine mounting rod is threadedly connected to the aero-engine body.

[0013] Preferably, the upper end of each engine mounting rod penetrates through the balance test stand, and an installation nut is threadedly connected to the upper end of each engine mounting rod, and the installation nut is arranged on the upper surface of the balance test stand.

[0014] Preferably, a fastening nut is arranged on the upper surface of the left square convex end, and the lower end of the fastening nut penetrates through the square convex end and is threadedly connected to the square convex end.

[0015] Preferably, a connecting rod is fixedly connected to one side of the up-and-down moving ring, the end of the connecting rod far away from the up-and-down moving ring penetrates through the inside of the limiting bracket, and a limiting groove is formed in the inside of the limiting bracket. Beneficial effects

[0016] The present invention provides a sudden addition unbalance test device for an aero-engine rotor system, which has the following beneficial effects compared with the prior art: 1. In the present invention, through the provided auxiliary marking mechanism, during the process of testing the aero-engine rotor, the motor in the balance test mechanism drives the upper and lower moving rings 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 during rotation due to unbalanced load, the shaking rough-surface test shaft will rub or collide with the marking powder during the shaking process, and thus leave marks on the surface of the rough-surface test shaft. In a severely unbalanced state, the marks on the surface of the rough-surface test shaft will no longer be limited to slight friction marks, but may form obvious scratches, spots or continuous lines, thereby intuitively indicating the position of the sudden addition unbalance of the rotor, providing an accurate basis for subsequent rotor balance correction. In addition, as the linkage ring moves up and down, the conical convex end will push the movable rod to make a reciprocating motion during the up and down movement. The other end of the movable rod is connected to the rocking arm, so the rocking arm will also make a reciprocating swing accordingly. This swinging motion of the rocking arm is transmitted to the rocking leaf through the rocking bracket, causing the rocking leaf to also perform a reciprocating rotational swing. Since there is a gap at the connection between the rocking leaf and the rocking bracket, when it performs a reciprocating rotational swing, this looseness will cause the rocking leaf to collide or rub with the bracket or other components, thereby generating a sound. As the shaking amplitude increases, a louder or higher-frequency sound will be generated. This sound change provides intuitive auditory feedback to the operator, enabling them to quickly judge the severity of the rotor unbalance. The present invention realizes the precise and rapid judgment of the unbalance state of the aero-engine rotor through a 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 simple mechanical transmission mechanism and the principle of collision sound generation of loose components, with a relatively simple structure, easy to implement and control, reducing the manufacturing cost and maintenance difficulty; 2. In the present invention, through the provided balance test mechanism, before testing the rotor system of the aero-engine body, place the aero-engine body on the lower surface of the balance test bench, and screw the lower ends of the four engine mounting rods into the screw holes of the aero-engine body. Then, screw the mounting nuts into the upper ends of the four engine mounting rods and the surface of the balance test bench. Finally, the motor drives the rotation of the first rotating arm, thereby driving the second rotating arm and the swing rod to swing, and finally causing the upper and lower moving rings to move 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 movement. When the rotor in the aero-engine body shakes during rotation 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 shaft surface. Description of the drawings

[0017] Figure 1 This is a three-dimensional structural schematic diagram of the sudden addition of unbalance test device for the aero-engine rotor system proposed by the present invention; Figure 2 This is a structural schematic diagram of the other perspective of the sudden addition of unbalance test device for the aero-engine rotor system proposed by the present invention; Figure 3 This is a bottom view structural schematic diagram of the sudden addition of unbalance test device for the aero-engine rotor system proposed by the present invention; Figure 4 This is a front view structural schematic diagram of the auxiliary marking mechanism in the sudden addition of unbalance test device for the aero-engine rotor system proposed by the present invention; Figure 5 This is a side view structural schematic diagram of the auxiliary marking mechanism in the sudden addition of unbalance test device for the aero-engine rotor system proposed by the present invention; Figure 6 This is a structural schematic diagram of the balance test mechanism in the sudden addition of unbalance test device for the aero-engine rotor system proposed by the present invention; Figure 7 This is a structural schematic diagram of the linkage ring in the sudden addition of unbalance test device for the aero-engine rotor system proposed by the present invention; Figure 8 is Figure 6 an enlarged view of part A in

[0018] Legend: 1. Balance test stand; 2. Aero-engine body; 3. Balance test mechanism; 301. Fixed bracket; 302. Motor; 303. Rotating arm one; 304. Rotating arm two; 305. Rocking rod; 306. Connecting arm; 307. Up and down moving ring; 308. Connecting rod; 309. Limit bracket; 310. Limit groove; 4. Auxiliary marking mechanism; 401. Linkage ring; 402. Conical protruding end; 403. Moving rod; 404. Fastening nut; 405. Marking chalk; 406. Rocking arm; 407. Rocking bracket; 408. Rocking blade; 409. Limit swing arm one; 410. Limit swing arm two; 411. Square protruding end; 5. Installation nut; 6. Engine installation rod; 7. Coupling; 8. Rough surface test shaft. Detailed implementation manners

[0019] The technical solutions of the present invention will be clearly and completely described below in conjunction with the accompanying drawings of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all of the embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without making creative efforts belong to the scope of protection of the present invention.

[0020] Please refer to Figures 1-8 , the present invention provides two technical solutions, specifically including the following embodiments: Embodiment 1 An aero-engine rotor system sudden unbalance test device, comprising: a balance test stand 1; a balance test mechanism 3, the balance test mechanism 3 is arranged on the upper surface of the balance test stand 1, and the balance test mechanism 3 is used to test the sudden unbalance 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 to mark the unbalanced position and emit a shaking sound to assist in judging the sudden unbalance of the rotor while testing the rotor of the aero-engine body 2. The auxiliary marking mechanism 4 includes a linkage ring 401, a conical protruding end 402, a movable rod 403, a marking chalk 405, a rotating arm 406, a swinging bracket 407, a swinging leaf 408 and a square protruding end 411. A rough surface test shaft 8 is vertically penetrated through the middle of the linkage ring 401. Square protruding ends 411 are arranged on both the left and right sides of the linkage ring 401, and conical protruding ends 402 are arranged on both the front and back sides of the linkage ring 401. Among them, a marking chalk 405 is penetrated through the middle of the left square protruding end 411, and the marking chalk 405 is used to leave a mark on the surface of the rough surface test shaft 8. The outer sides of the two conical protruding ends 402 are respectively rotatably connected with movable rods 403, and the ends of the two movable rods 403 far away from the corresponding conical protruding ends 402 are respectively rotatably connected to one ends of the two rotating arms 406. The two rotating arms 406 are fixedly connected to the front and back sides of the swinging bracket 407. Swing leaves 408 are movably connected to both the left and right ends of the swinging bracket 407. There is a gap at the connection between the swing leaf 408 and the swinging bracket 407. The lower end of the swinging bracket 407 is snap-connected to the rough surface test shaft 8. The rough surface test shaft 8 is made of an alloy steel plate with a wear-resistant coating, which is commonly used for making blackboard materials. An aero-engine body 2 is arranged below the rough surface test shaft 8. A coupling 7 is key-connected between the lower end of the rough surface test shaft 8 and the rotor of the aero-engine body 2. A limiting swing arm 409 is rotatably connected to the outside of the right square protruding end 411. The upper end of the limiting swing arm 409 is rotatably connected to the lower end of the limiting swing arm 410. The end of the limiting swing arm 410 far away from the limiting swing arm 409 is rotatably connected to the outside of the lower end of the swinging bracket 407. A fastening nut 404 is arranged on the upper surface of the left square protruding end 411. The lower end of the fastening nut 404 penetrates through the square protruding end 411 and is threadedly connected to the square protruding end 411.

[0021] During operation, in the process of testing an aero-engine rotor, the motor 302 in the balance testing mechanism 3 drives the up-and-down moving ring 307 and the linkage ring 401 to move up and down on the surface of the rough-surface testing shaft 8 connected to the aero-engine rotor through the coupling 7. If the rotor in the aero-engine body 2 generates wobbling during rotation due to unbalanced loads, the wobbling rough-surface testing shaft 8 will rub against or collide with the marking powder during the wobbling process, thereby leaving marks on the surface of the rough-surface testing shaft 8. In a severely unbalanced state, the marks on the surface of the rough-surface testing shaft 8 will no longer be limited to slight friction marks, but may form obvious scratches, spots or continuous lines, thus intuitively indicating the position of sudden unbalance of the rotor and providing an accurate basis for subsequent rotor balance correction. Additionally, as the linkage ring 401 moves up and down, the conical protruding end 402 will push the movable rod 403 to make a reciprocating motion during the up-and-down movement. The other end of the movable rod 403 is connected to the rocking arm 406. Therefore, the rocking arm 406 will also make a reciprocating swing accordingly. This swinging motion of the rocking arm 406 is transmitted to the rocking leaf 408 through the rocking bracket 407, causing the rocking leaf 408 to also perform a reciprocating rotational swing. Since there is a gap at the connection between the rocking leaf 408 and the rocking bracket 407, when it performs a reciprocating rotational swing, this looseness will cause the rocking leaf 408 to collide with or rub against the bracket or other components, thereby generating a sound. As the amplitude of the wobbling increases, a louder or higher-frequency sound will be generated. This change in sound provides intuitive auditory feedback to the operator, enabling them to quickly judge the severity of rotor unbalance.

[0022] Embodiment Two On the basis of Embodiment 1, the balance test mechanism 3 includes a fixed bracket 301, a motor 302, a first rotating arm 303, a second rotating arm 304, a swing rod 305, a connecting arm 306, and an up-and-down moving ring 307. The number of fixed brackets 301 is set to three. The three fixed brackets 301 are distributed around the upper surface of the balance test stand 1. The upper surfaces of the three fixed brackets 301 are fixedly connected with motors 302. The output end of each motor 302 is drivingly connected with a first rotating arm 303. One end of the first rotating arm 303 away from the output end of the motor 302 is rotatably connected with a second rotating arm 304. One end of the second rotating arm 304 away from the first rotating arm 303 is rotatably connected with a swing rod 305. The upper end of the swing rod 305 is rotatably connected to the outer end of the connecting arm 306. The inner end of the connecting arm 306 is fixedly connected to the outside of the up-and-down moving ring 307. The up-and-down moving ring 307 is sleeved outside the rough surface test shaft 8. Four engine mounting rods 6 are arranged on the upper surface of the aero-engine body 2. Each engine mounting rod 6 is threadedly connected to the aero-engine body 2. The upper end of each engine mounting rod 6 penetrates through the balance test stand 1, and an installation nut 5 is threadedly connected to the upper end of each engine mounting rod 6. The installation nut 5 is arranged on the upper surface of the balance test stand 1. One side of the up-and-down moving ring 307 is fixedly connected with a connecting rod 308. One end of the connecting rod 308 away from the up-and-down moving ring 307 penetrates through and is arranged inside the limit bracket 309. A limit groove 310 is opened inside the limit bracket 309. It should be noted that when using tools such as spray paint, chalk, and marker pens for marking or painting, if there is shaking during the movement of the tool or the marked surface, the greater the shaking amplitude, the longer and more irregular the traces left are. Essentially, this is because the shaking increases the effective moving distance, extends the contact time, and changes the force application situation. Therefore, it is necessary for the balance test mechanism 3 to drive the up-and-down moving ring 307 to move up and down along the rough surface test shaft 8; Before testing the rotor system of the aero-engine body 2, place the aero-engine body 2 on the lower surface of the balance test stand, screw the lower ends of the four engine mounting rods 6 into the screw holes of the aero-engine body 2, then screw the installation nuts 5 onto the upper ends of the four engine mounting rods 6 and the surface of the balance test stand. Finally, drive the first rotating arm 303 to rotate by the motor 302, thereby driving the second rotating arm 304 and the swing rod 305 to swing, and finally making the up-and-down moving ring 307 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-and-down moving ring. When the rotor in the aero-engine body 2 shakes due to unbalanced loads during rotation, the shaking of the rough surface test shaft 8 will cause friction or collision with the marking powder, leaving traces on the shaft surface.

[0023] The above are only the preferred embodiments of the present application and are not intended to limit the present application. Any modifications, equivalent replacements, and improvements made within the spirit and principle of the application shall be included in the protection scope of the present application.

Claims

1. Sudden unbalance test device for aircraft engine rotor system, including: Balance test frame (1); A balancing test mechanism (3); characterized in that the balancing test mechanism (3) is arranged on the upper surface of the balancing test frame (1), and the balancing test mechanism (3) is used to test the sudden imbalance of the rotor of the aircraft engine body (2); An auxiliary marking mechanism (4); the auxiliary marking mechanism (4) is located above the balancing test mechanism (3), and the balancing test mechanism (3) is used to mark the unbalanced position and emit a shaking sound to assist in judging the sudden unbalance of the rotor while testing the rotor of the aircraft engine body (2); 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 bracket (407), a swing leaf (408) and a square protruding end (411); a rough surface test shaft (8) is vertically penetrated through the middle of the linkage ring (401); square protruding ends (411) are provided on both the left and right sides of the linkage ring (401); and conical protruding ends (402) are provided on both the front and rear sides of the linkage ring (401); wherein the left square protruding end (411) is provided on the left side of the linkage ring (401); ) is provided with a marking chalk (405) penetrating through the middle of the test shaft (8), and the marking chalk (405) is used to leave a mark on the surface of the rough test shaft (8). The outer sides of the two conical protrusion ends (402) are rotatably connected to movable rods (403), and the ends of the two movable rods (403) away from the corresponding conical protrusion ends (402) are respectively rotatably connected to one end of two swing arms (406), and the two swing arms (406) are fixedly connected to the front and rear sides of the swing bracket (407), and the left and right ends of the swing bracket (407) are movably connected to swing leaves (408).

2. The aero-engine rotor system sudden unbalance test device according to claim 1, characterized in that: The lower end of the swing bracket (407) is snap-connected with a rough surface test shaft (8), an aircraft engine body (2) is arranged below the rough surface test shaft (8), and a coupling (7) is key-connected between the lower end of the rough surface test shaft (8) and a rotor of the aircraft engine body (2).

3. The aero-engine rotor system sudden unbalance test device according to claim 1, characterized in that: The balance test mechanism (3) comprises a fixed bracket (301), a motor (302), a rotating arm 1 (303), a rotating arm 2 (304), a rocking arm (305), a connecting arm (306) and an up-and-down moving ring (307), wherein the number of the fixed brackets (301) is set to three, the three fixed brackets (301) are distributed around the upper surface of the balance test frame (1), and the upper surfaces of the three fixed brackets (301) are all fixedly connected to the motor (302).

4. The aero-engine rotor system sudden unbalance test device according to claim 3, characterized in that: The output end of each motor (302) is drivingly connected to a rotating arm 1 (303); one end of the rotating arm 1 (303) away from the output end of the motor (302) is rotationally connected to a rotating arm 2 (304); and one end of the rotating arm 2 (304) away from the rotating arm 1 (303) is rotationally connected to a rocking arm (305).

5. The aero-engine rotor system sudden unbalance test device according to claim 4, characterized in that: The upper end of the rocking rod (305) is rotatably connected to the outer end of the connecting arm (306), and the inner end of the connecting arm (306) is fixedly connected to the outer side of the up-and-down moving ring (307), and the up-and-down moving ring (307) is sleeved on the outer side of the rough surface test shaft (8).

6. The aero-engine rotor system sudden unbalance test device according to claim 1, characterized in that: The outer side of the square protruding end (411) on the right side is rotatably connected to the limiting swing arm 1 (409), the upper end of the limiting swing arm 1 (409) is rotatably connected to the lower end of the limiting swing arm 2 (410), and the end of the limiting swing arm 2 (410) away from the limiting swing arm 1 (409) is rotatably connected to the outer side of the lower end of the swing bracket (407).

7. The aircraft engine rotor system sudden unbalance test device according to claim 2, characterized in that: Four engine mounting rods (6) are arranged on the upper surface of the aircraft engine body (2), and each of the engine mounting rods (6) is threadedly connected to the aircraft engine body (2).

8. The aero-engine rotor system sudden unbalance test device according to claim 7, characterized in that: The upper end of each engine mounting rod (6) passes through the balancing test frame (1), and the upper end of each engine mounting rod (6) is threadedly connected to a mounting nut (5), wherein the mounting nut (5) is arranged on the upper surface of the balancing test frame (1).

9. The aircraft engine rotor system sudden unbalance test device according to claim 1, characterized in that: A fastening nut (404) is provided on the upper surface of the square protruding end (411) on the left side, and the lower end of the fastening nut (404) passes through the square protruding end (411) and is threadedly connected to the square protruding end (411).

10. The aircraft engine rotor system sudden unbalance test device according to claim 5, characterized in that: A connecting rod (308) is fixedly connected to one side of the up-and-down moving ring (307), and one end of the connecting rod (308) away from the up-and-down moving ring (307) is arranged to penetrate the interior of a limiting bracket (309), and a limiting groove (310) is provided inside the limiting bracket (309).

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