A vibration test bench system

Abstract

This invention discloses a vibration test bench system, comprising a base, a first vibration slide slidably disposed on the base along the X-axis, an exciter arranged on the base along the X-axis and connected to the first vibration slide to generate an excitation force for vibration, a mounting frame for the first vibration slide, an auxiliary mounting assembly disposed on one side of the mounting frame along the X-axis for connecting an aero-engine, and a first main mounting assembly disposed on one side of the mounting frame along the Y-axis, the first main mounting assembly comprising three first main mounting seats spaced apart around the Y-axis, each first main mounting seat being universally hinged to a first main tie rod, the three first main tie rods having their center-facing ends universally hinged to a first main mounting section for connecting the aero-engine. This invention achieves dynamic simulation of the connection state of an aero-engine during service and meets the thermal expansion requirements of the aero-engine during operation.

Description

Technical Field

[0001] This invention relates to the field of aero-engine testing technology, and more specifically to a vibration test bench system. Background Technology

[0002] Vibration of aero-engines is one of the important issues that need to be considered in the entire process of aero-engine development and use. Designing and building a vibration simulation test bench for aero-engines is one of the important means to study vibration faults in aero-engines. According to the national military standard (GJB150.16A), the test state of the test piece in the whole-engine vibration test should be consistent with that during operation. During the test, the test piece should be fixed on the mounting position of the test fixture, and the mechanical, electrical, hydraulic, pneumatic or other connections used by the aero-engine test piece during operation should be provided.

[0003] Traditional vibration testing equipment typically uses main and auxiliary mounting sections fixed to the test bench to directly fix the engine. However, this connection method is not easy to dynamically simulate the connection state of an aero-engine during service, resulting in unsatisfactory vibration simulation test results. Summary of the Invention

[0004] Therefore, the technical problem to be solved by the present invention is to overcome the defect that the vibration test equipment in the prior art is not easy to dynamically simulate the connection state of the aircraft engine during service, resulting in unsatisfactory vibration simulation test results, and thus provide a vibration test bench system.

[0005] According to the present invention, a vibration test bench system is used for vibration testing of aero engines. The vibration test bench system includes:

[0006] Base;

[0007] The first vibration slide is slidably disposed on the base along the X direction;

[0008] The exciter is arranged along the X direction on the base and connected to the first vibration slide, and generates an excitation force for vibration;

[0009] A mounting bracket is provided on the vibration slide. A through hole is provided on one side of the mounting bracket along the X direction, and an auxiliary mounting assembly is provided on the other side. The auxiliary mounting assembly includes two auxiliary mounting seats arranged at intervals along the Y direction. Each of the two auxiliary mounting seats is universally hinged to an auxiliary tie rod. The ends of the two auxiliary tie rods that are close to each other along the Y direction are universally hinged to an auxiliary mounting section. The auxiliary mounting section is used to connect the aero-engine.

[0010] A first main mounting assembly is provided on one side of the mounting frame along the Y direction. The first main mounting assembly includes three first main mounting seats arranged at intervals around the Y direction. Each first main mounting seat is universally hinged to a first main tie rod. The three first main tie rods are universally hinged to a first main mounting section at one end facing the center. The first main mounting section is used to connect the aero-engine.

[0011] According to the vibration test bench system of the present invention, at least the following technical effects are achieved:

[0012] The mounting bracket adopts a cage-like structure similar to that used for mounting aircraft engines. The auxiliary mounting section and the first main mounting section are bolted to the corresponding bolt holes of the aircraft engine to support and fix the aircraft engine. The first main mounting section is universally hinged to the first main mounting base via the first main tie rod, and the auxiliary mounting section is universally hinged to the auxiliary mounting base via the auxiliary tie rod. This allows the aircraft engine to undergo small-range adaptation movements through the first main mounting section and the auxiliary mounting section during vibration testing, dynamically simulating the connection state of the aircraft engine during service and improving the accuracy of vibration simulation test results.

[0013] In one optional embodiment, the mounting frame further includes a second main mounting assembly, which is arranged opposite to the first main mounting assembly along the Y direction. The second main mounting assembly includes two second main mounting seats spaced apart along the X direction. Each of the two second main mounting seats is universally hinged to a second main tie rod. The ends of the two second main tie rods that are close to each other along the X direction are universally hinged to a second main mounting section, which is used to connect the aircraft engine.

[0014] In one optional embodiment, the auxiliary pull rod, the first main pull rod, and the second main pull rod are configured with the same structure; the first main pull rod includes a hollow connecting part, and a threaded rod part is slidably provided at both ends of the connecting part, and the threaded rod part is locked by a nut.

[0015] In one alternative embodiment, the system further includes a bleed air system detachably equipped with a telescopic hose that passes through the through-hole and is used to connect to the bleed air outlet of the aircraft engine.

[0016] In one optional embodiment, the mounting bracket is detachably connected to the first vibration slide. The mounting bracket has a first state and a second state in which it is assembled with the first vibration slide. In the first state, the first main mounting assembly and the second main mounting assembly are arranged opposite each other along the Y direction. In the second state, the mounting bracket is arranged opposite each other along the X direction.

[0017] In one optional embodiment, the vibrator is provided with a support plate on each side along the Y direction, and the vibrator is rotatably connected between the two support plates about the Y direction. The vibrator has a third state arranged parallel to the X direction and a fourth state arranged parallel to the Z direction. The first vibration slide is detachably connected to the vibrator in the third state. A second vibration slide is slidably connected at the upper end between the two support plates along the Z direction. The mounting bracket is detachably connected to the second vibration slide, and the second vibration slide is detachably connected to the vibrator in the fourth state.

[0018] In an alternative embodiment, a first exhaust pipe is further included, the first exhaust pipe being located on one side of the mounting bracket along the X direction; the first exhaust pipe is driven to move along the X and Z directions by a two-axis moving assembly; the first exhaust pipe is used to correspond to the tail nozzle of the aircraft engine and to discharge the high-temperature exhaust gas generated during the test into the atmosphere.

[0019] In one optional embodiment, a connecting plate is provided at each of the four corners of the lower end of the mounting bracket. A connecting hole is provided through the connecting plate along the Z direction. The connecting hole is used for the shank of the first fastening bolt to pass through. The first vibration slide is provided with a first threaded hole corresponding to the position of the connecting hole. The first threaded hole matches the first fastening bolt.

[0020] And / or, a connecting plate is provided at each of the four corners of the lower end of the mounting bracket, and a connecting hole is provided through the connecting plate along the Z direction. The connecting hole is used for the rod of the second fastening bolt to pass through. The second vibration slide is provided with a second threaded hole corresponding to the position of the connecting hole, and the second threaded hole matches the second fastening bolt.

[0021] In one alternative embodiment, a second exhaust pipe is provided on one side of the base along the Y direction, the mounting bracket is in a second state, the second exhaust pipe corresponds to the tail nozzle of the aircraft engine, and is used to discharge the high-temperature exhaust gas generated during the test into the atmosphere.

[0022] In one alternative embodiment, the upper end of the mounting bracket is provided with an opening along the Z direction for the aircraft engine to pass through.

[0023] Additional aspects and advantages of the invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. Attached Figure Description

[0024] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0025] Figure 1 This is a three-dimensional structural diagram of a vibration test bench system after the second vibration slide is removed, according to this embodiment.

[0026] Figure 2 This is a three-dimensional structural diagram of the mounting frame in a vibration test bench system according to this embodiment;

[0027] Figure 3 for Figure 2 A schematic diagram of the side view structure;

[0028] Figure 4 This is a schematic diagram of the assembly structure of the second vibration slide and the mounting frame in a vibration test bench system according to this embodiment;

[0029] Figure 5 This is a schematic diagram of the structure of the first main tie rod in a vibration test bench system according to this embodiment.

[0030] Explanation of reference numerals in the attached figures:

[0031] 100-Base;

[0032] 200 - First Vibration Slide;

[0033] 300-Vibrator, 310-Support plate, 320-Connecting column, 330-Mounting frame, 331-Guide seat;

[0034] 400-Mounting bracket, 410-Through hole, 420-Auxiliary mounting base, 430-Auxiliary tie rod, 440-Auxiliary mounting section, 450-Connecting plate, 451-Connecting hole, 460-Opening;

[0035] 510-First main mounting base, 520-First main tie rod, 521-Connecting part, 522-Threaded rod part, 523-Nut, 530-First main mounting section;

[0036] 610 - Second main mounting base, 620 - Second main tie rod, 630 - Second main mounting section;

[0037] 700 - Air intake system; 710 - Telescopic hose; 720 - First exhaust stack; 730 - Second exhaust stack;

[0038] 800 - Second vibration slide, 810 - Guide slider. Detailed Implementation

[0039] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0040] In the description of this embodiment, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this embodiment and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this embodiment. In addition, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0041] In the description of this embodiment, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this embodiment according to the specific circumstances.

[0042] The following is combined with Figures 1 to 5 The following describes embodiments of the present invention.

[0043] A vibration test bench system according to an embodiment of the present invention is used for vibration testing of aero-engines. The vibration test bench system includes a base 100, on which a first vibration slide 200 is slidably disposed along the X-direction; an exciter 300 is arranged along the X-direction on the base 100, the exciter 300 being connected to the first vibration slide 200 and generating an excitation force for vibration; the first vibration slide 200 is provided with a mounting bracket 400, which has a through hole 410 on one side along the X-direction and an auxiliary mounting assembly on the other side, the auxiliary mounting assembly including two auxiliary mounting seats 420 spaced apart along the Y-direction. Each of the two auxiliary mounting seats 420 is universally hinged to an auxiliary tie rod 430. The ends of the two auxiliary tie rods 430, which are close to each other along the Y-direction, are universally hinged to an auxiliary mounting section 440, which is used to connect to the aero-engine. A first main mounting assembly is provided on one side of the mounting frame 400 along the Y-direction. The first main mounting assembly includes three first main mounting seats 510 arranged circumferentially around the Y-direction. Each first main mounting seat 510 is universally hinged to a first main tie rod 520. The ends of the three first main tie rods 520 facing the center are universally hinged to a first main mounting section 530, which is used to connect to the aero-engine. It is understood that the X-direction, Y-direction, and Z-direction mentioned in this text refer to... Figure 1 The X, Y, and Z directions are mutually perpendicular; the X and Y directions are located on the same horizontal plane.

[0044] The mounting frame 400 of the vibration test bench system in this embodiment adopts a cage-like structure similar to that used for mounting aircraft engines. The auxiliary mounting section 440 and the first main mounting section 530 are respectively bolted to the corresponding bolt holes of the aircraft engine to support and fix the aircraft engine. The first main mounting section 530 is universally hinged to the first main mounting base 510 through the first main tie rod 520, and the auxiliary mounting section 440 is universally hinged to the auxiliary mounting base 420 through the auxiliary tie rod 430. This allows the aircraft engine to undergo a small range of adaptive movement through the first main mounting section 530 and the auxiliary mounting section 440 during vibration testing, thereby dynamically simulating the connection state of the aircraft engine during service and meeting the thermal expansion requirements of the aircraft engine during operation, thus improving the accuracy of the vibration simulation test results.

[0045] It should be noted that since the weight of the aero engine is mainly borne by the first main mounting section 530, connecting the first main mounting section 530 to the mounting frame 400 through three first main tie rods 520 arranged in a triangular shape can improve the stability of the aero engine during testing.

[0046] Considering that supporting the aero-engine on only one side along the Y direction using only the first main mounting assembly (i.e., single-sided suspension) can easily lead to insufficient connection reliability, in order to solve the above-mentioned technical problem, in some embodiments, a second main mounting assembly is also provided within the mounting frame 400. The second main mounting assembly and the first main mounting assembly are arranged opposite to each other along the Y direction. The second main mounting assembly includes two second main mounting seats 610 spaced apart along the X direction. Each of the two second main mounting seats 610 is universally hinged to a second main tie rod 620. The ends of the two second main tie rods 620 that are close to each other along the X direction are universally hinged to a second main mounting section 630. The second main mounting section 630 is used to connect the aero-engine. On the one hand, the second main mounting section 630 is bolted to the corresponding bolt holes of the aero-engine, providing connection and support to the aero-engine on the other side away from the first main mounting section 530 along the Y direction. This structure, similar to "double-sided support," supports the aero-engine, which helps improve the stability of the aero-engine during testing. On the other hand, the second main mounting section 630 is universally hinged to the second main mounting base 610 via the second main tie rod 620. This allows the aero-engine to undergo small-range adaptation movements through the second main mounting section 630 during vibration testing, better simulating the connection state of the aero-engine during service.

[0047] It should be noted that the auxiliary mounting section 440, the first main mounting section 530 and the second main mounting section 630 are each provided with four through holes spaced circumferentially around their own axis at the positions of the bolt holes of the aero-engine. The through holes facilitate the passage of bolts to connect to the corresponding bolt holes of the aero-engine, thereby improving the reliability of the connection.

[0048] Specifically, the first main mounting base 510 is provided with a first lug via a first joint bearing. The first lug is hinged to the first main tie rod 520, which facilitates the rotation and adjustment of the first main tie rod 520 relative to the first main mounting base 510.

[0049] Specifically, the second main mounting base 610 is provided with a second lug via a second joint bearing. The second lug is hinged to the second main tie rod 620, which facilitates the rotation adjustment of the second main tie rod 620 relative to the second main mounting base 610.

[0050] Specifically, the auxiliary mounting base 420 is provided with a third lug via a third joint bearing. The third lug is hinged to the auxiliary pull rod 430, which facilitates the rotation and adjustment of the auxiliary pull rod 430 relative to the auxiliary mounting base 420.

[0051] like Figure 5As shown, specifically, the auxiliary tie rod 430, the first main tie rod 520, and the second main tie rod 620 are configured with the same structure; the first main tie rod 520 includes a hollow connecting part 521, and a threaded rod part 522 is slidably provided at both ends of the connecting part 521, and the threaded rod part 522 is locked by a nut 523. This configuration allows for flexible adjustment of the threaded rod part 522 relative to the connecting part 521 to different positions, thereby adjusting the lengths of the auxiliary tie rod 430, the first main tie rod 520, and the second main tie rod 620. This not only compensates for errors caused by manufacturing precision, enabling rapid installation and disassembly of aero engines, but also makes it suitable for installing aero engines of different external dimensions, further expanding the applicability of the vibration test bench system of this embodiment.

[0052] It is understood that the connecting part 521 has external threaded portions on the outer side walls at both ends along the length direction of the connecting part 521, and the external threaded portions match the nut 523; when the threaded rod 522 extends or retracts relative to the connecting part 521 to the required position, the nut 523 is rotated on the threaded rod 522 until the thread engages with the external threaded portion to achieve locking.

[0053] It should be noted that by changing the length of the auxiliary tie rod 430, the length of the first main tie rod 520 and the length of the second main tie rod 620, as well as changing the angle of the auxiliary tie rod 430 relative to the auxiliary mounting base 420, the angle of the first main tie rod 520 relative to the first main mounting base 510 and the angle of the second main tie rod 620 relative to the second main mounting base 610, the aircraft engine can be quickly installed and disassembled, eliminating the impact of manufacturing precision errors and helping to reduce the cost of the vibration test bench system in this embodiment.

[0054] like Figure 2 As shown, specifically, the upper end of the mounting bracket 400 is provided with an opening 460 along the Z direction, which is used for the aircraft engine to pass through. With this configuration, before the test, a crane can be used to pass the aircraft engine from top to bottom through the opening 460 into the mounting bracket 400 for installation. The entire installation and disassembly process saves manpower and helps to reduce test costs.

[0055] In some embodiments, the auxiliary mounting base 420 has a first oblong through hole formed along the X direction, which is used for the shank of the first bolt to pass through. The mounting bracket 400 has a third threaded hole corresponding to the position of the first oblong through hole, and the third threaded hole matches the first bolt. The auxiliary mounting base 420 is detachably connected to the mounting bracket 400 by the engagement of the first bolt and the third threaded hole, which ensures connection strength and facilitates disassembly for inspection and maintenance. At the same time, the use of the first oblong through hole can compensate for the error caused by insufficient machining accuracy of the third threaded hole, which helps to reduce the cost of the vibration test bench system in this embodiment.

[0056] Specifically, a second oblong through hole is formed along the Y direction on the first main mounting base 510. The second oblong through hole is used for the shank of the second bolt to pass through. The mounting bracket 400 is provided with a fourth threaded hole corresponding to the position of the second oblong through hole. The fourth threaded hole matches the second bolt. The first main mounting base 510 is detachably connected to the mounting bracket 400 by the engagement of the second bolt and the fourth threaded hole, which ensures the connection strength and facilitates disassembly for inspection and maintenance. At the same time, the use of the second oblong through hole can compensate for the error caused by insufficient machining accuracy of the fourth threaded hole, which helps to reduce the cost of the vibration test bench system in this embodiment.

[0057] Specifically, a third oblong through hole is formed along the Y direction on the second main mounting base 610. This third oblong through hole allows the shank of the third bolt to pass through. A fifth threaded hole is provided on the mounting bracket 400 corresponding to the position of the third oblong through hole, and this fifth threaded hole matches the third bolt. The second main mounting base 610 is detachably connected to the mounting bracket 400 by the engagement of the third bolt and the fifth threaded hole, ensuring connection strength while facilitating disassembly for inspection and maintenance. Furthermore, the use of the third oblong through hole can compensate for errors caused by insufficient machining precision in the fifth threaded hole, thus reducing the cost of the vibration test bench system in this embodiment.

[0058] like Figure 1 As shown, in some embodiments, the vibration test bench system further includes an air bleed system 700, which is detachably connected to a telescopic hose 710 by bolts. The telescopic hose 710 passes through the through hole 410 and is used to connect to the air bleed outlet of the aero-engine. The air bleed outlet of the aero-engine is connected to the air bleed system 700 through the telescopic hose 710 to meet the air bleed requirements, which helps to keep the test state of the aero-engine consistent with its working state. In addition, the telescopic hose 710 can also deform to absorb the displacement generated during the vibration test of the aero-engine, ensuring the quality of the air bleed.

[0059] In some embodiments, the mounting bracket 400 is detachably connected to the first vibration slide 200. The mounting bracket 400 has a first state and a second state of being assembled with the first vibration slide 200. In the first state, the mounting bracket 400 is arranged opposite to the first main mounting assembly and the second main mounting assembly along the Y direction (e.g., ...). Figure 1 (As shown); the mounting frame 400 is in the second state, and the first main mounting assembly and the second main mounting assembly are arranged opposite each other along the X direction; such that after the mounting frame 400 in the first state is separated from the first vibration slide 200, rotated 90° around the Z direction and reconnected to the first vibration slide 200, the mounting frame 400 can be switched to the second state, thereby rotating the aero-engine installed in the mounting frame 400 90° relative to the first vibration slide 200 around the Z direction, so that the aero-engine installed in the mounting frame 400 in the first state is arranged parallel to the X direction, and the aero-engine installed in the mounting frame 400 in the second state is arranged parallel to the Y direction. This achieves the effect of performing X-direction vibration tests and Y-direction vibration tests separately with only one exciter 300 based on the single installation of the aero-engine in the vibration test bench system of this embodiment, which has a wide range of applications and low cost.

[0060] like Figure 1 As shown and Figure 4 As shown, specifically, the vibrator 300 has a support plate 310 on each side along the Y direction, and the vibrator 300 is rotatably connected between the two support plates 310 around the Y direction. The vibrator 300 has a third state arranged parallel to the X direction (e.g., Figure 1As shown), and a fourth state arranged parallel to the Z direction; the first vibration slide 200 is detachably connected to the exciter 300 in the third state; a second vibration slide 800 is slidably connected at the upper end between the two support plates 310 along the Z direction, the mounting bracket 400 is detachably connected to the second vibration slide 800, and the second vibration slide 800 is detachably connected to the exciter 300 in the fourth state. With this configuration, when an X-axis vibration test of the aero-engine is required, the mounting bracket 400 is simply assembled with the first vibration slide 200 in its first state. At this time, the aero-engine mounted on the mounting bracket 400 is arranged parallel to the X-axis and vibrates under the excitation force of the exciter 300 arranged along the X-axis, thus achieving the X-axis vibration test. When a Y-axis vibration test of the aero-engine is required, the mounting bracket 400 is assembled with the first vibration slide 200 in its second state. At this time, the aero-engine mounted on the mounting bracket 400 is arranged parallel to the Y-axis and vibrates under the excitation force of the exciter 300 arranged along the X-axis, thus achieving the Y-axis vibration test. When a Z-axis vibration test of the aero-engine is required, the exciter 300 is first assembled with the first vibration slide 200... The slides 200 are disassembled, and then the exciter 300 is rotated 90° in the Y direction, switching the exciter 300 from the third state to the fourth state. Then, the second vibration slide 800 is connected to the exciter 300 in the fourth state. Finally, the mounting bracket 400 with the aircraft engine is connected to the second vibration slide 800, so that the aircraft engine mounted on the mounting bracket 400 vibrates under the excitation force of the exciter 300 arranged in the Z direction, realizing the vibration test in the Z direction. This achieves the effect of performing vibration tests in the X direction, Y direction and Z direction separately with only one exciter 300 based on the single installation of the aircraft engine in the vibration test bench system of this embodiment, realizing triaxial vibration test on the same vibration test bench system.

[0061] Specifically, the second vibration slide 800 and the exciter 300 in the fourth state are detachably connected by bolts.

[0062] Specifically, the first vibration slide 200 and the exciter 300 in the third state are detachably connected by bolts.

[0063] The detachable connection structure between the mounting bracket 400 and the first vibrating slide 200 is described in detail here, such as... Figure 1 and Figure 2As shown, in some embodiments, a connecting plate 450 is provided at each of the four corners of the lower end of the mounting bracket 400. A connecting hole 451 extends through the connecting plate 450 along the Z-direction, allowing the shank of the first fastening bolt to pass through. A first threaded hole is provided on the first vibrating slide 200 corresponding to the connecting hole 451, and this threaded hole matches the first fastening bolt. When the mounting bracket 400 and the first vibrating slide 200 need to be connected as a single unit, simply pass the first fastening bolt through the connecting hole 451 and tighten it into the first threaded hole. When the mounting bracket 400 and the first vibrating slide 200 need to be disassembled, simply unscrew the first fastening bolt from the first threaded hole and remove it from the connecting hole 451. The entire assembly and disassembly process is convenient. In another alternative embodiment, the connecting hole 451 extends through the first vibrating slide 200 along the Z-direction, and the first threaded hole is located on the connecting plate 450.

[0064] It should be noted that, regardless of whether the mounting bracket 400 is in the first state or the second state, the first vibration slide 200 is provided with a first threaded hole at the position corresponding to the connection hole 451.

[0065] This section describes in detail the detachable connection structure between the mounting bracket 400 and the second vibration slide 800, such as... Figure 2 and Figure 4 As shown, in some embodiments, the mounting bracket 400 is connected to the second vibration slide 800 in a first state, that is, the aircraft engine assembled in the mounting bracket 400 is arranged parallel to the X-direction; a connecting plate 450 is provided at each of the four corners of the lower end of the mounting bracket 400, and a connecting hole 451 is provided through the connecting plate 450 along the Z-direction. The connecting hole 451 is used for the shank of the second fastening bolt to pass through. The second vibration slide 800 is provided with a second threaded hole corresponding to the position of the connecting hole 451, and the second threaded hole matches the second fastening bolt; when it is necessary to connect the mounting bracket 400 and the second vibration slide 800 in the first state to form a whole, it is only necessary to pass the second fastening bolt through the connecting hole 451 and tighten it into the second threaded hole; when it is necessary to disassemble the mounting bracket 400 and the second vibration slide 800, it is only necessary to unscrew the second fastening bolt from the second threaded hole and remove it from the connecting hole 451. The entire disassembly and assembly process is convenient. In another alternative embodiment, the connecting hole 451 is disposed through the second vibration slide 800 along the Z direction, and the second threaded hole is disposed in the connecting plate 450.

[0066] like Figure 4As shown, specifically, the upper ends of the two support plates 310 are connected to the mounting frame 330 via the connecting column 320. Each of the four inner walls of the mounting frame 330 is provided with a guide seat 331. The second vibration slide 800 is provided with a guide slider 810 corresponding to the position of each guide seat 331. The guide slider 810 is slidably connected to the guide groove of the guide seat 331 along the Z direction.

[0067] like Figure 1 As shown, in some embodiments, the vibration test bench system further includes a first exhaust stack 720, which is located on the side of the mounting frame 400 in the first state that is away from the exciter 300 along the X direction; the first exhaust stack 720 is driven by a two-axis moving assembly to move along the X and Z directions; when the mounting frame 400 equipped with the aircraft engine is connected to the first vibration slide 200 in the first state for vibration testing in the X direction, the aircraft engine is arranged parallel to the X direction, that is, the first exhaust stack 720 corresponds to the tail nozzle of the aircraft engine, so that the first exhaust stack 720 discharges the high-temperature exhaust gas generated during the test into the atmosphere, which is beneficial to keep the test state of the aircraft engine consistent with the state during operation. When the mounting bracket 400, equipped with the aircraft engine, is connected to the second vibration slide 800 in the first state for a Z-axis vibration test, the aircraft engine is arranged parallel to the X-axis, and the first exhaust pipe 720 and the aircraft engine's tail nozzle are significantly spaced in both the X and Z axes. The first exhaust pipe 720 is adjusted using a two-axis moving assembly to align with the aircraft engine's tail nozzle, allowing the first exhaust pipe 720 to discharge the high-temperature exhaust gas generated during the Z-axis vibration test into the atmosphere. This helps maintain consistency between the aircraft engine's test state and its operational state. It can be understood that the two-axis moving assembly here uses a mature two-axis moving device from relevant technologies, only needing to be able to move the first exhaust pipe 720 along both the X and Z axes.

[0068] Specifically, a second exhaust pipe 730 is provided on one side of the base 100 along the Y direction. When the mounting bracket 400 equipped with the aircraft engine is connected to the first vibration slide 200 in the second state for vibration test in the Y direction, the aircraft engine is arranged parallel to the Y direction, that is, the second exhaust pipe 730 corresponds to the tail nozzle of the aircraft engine and is used to discharge the high-temperature exhaust gas generated during the test into the atmosphere, which helps to keep the test state of the aircraft engine consistent with the state during operation.

[0069] Obviously, the above embodiments are merely illustrative examples for clear explanation and are not intended to limit the implementation. Those skilled in the art will recognize that other variations or modifications can be made based on the above description. It is neither necessary nor possible to exhaustively list all possible implementations here. However, obvious variations or modifications derived therefrom are still within the scope of protection of this invention.

Claims

1. A vibration test bench system for conducting vibration tests on aero engines, characterized in that, The vibration test bench system includes: Base (100); A first vibration slide (200) is slidably disposed on the base (100) along the X direction; A vibrator (300) is arranged along the X direction on the base (100) and connected to the first vibration slide (200), and generates an excitation force for vibration; A mounting bracket (400) is disposed on the first vibration slide (200). A through hole (410) is provided on one side along the X direction of the mounting bracket (400), and an auxiliary mounting assembly is provided on the other side. The auxiliary mounting assembly includes two auxiliary mounting seats (420) arranged at intervals along the Y direction. Each of the two auxiliary mounting seats (420) is universally hinged to an auxiliary tie rod (430). The ends of the two auxiliary tie rods (430) that are close to each other along the Y direction are universally hinged to an auxiliary mounting section (440). The auxiliary mounting section (440) is used to connect the aircraft engine. The mounting bracket (400) has a first main mounting assembly on one side along the Y direction. The first main mounting assembly includes three first main mounting seats (510) arranged at intervals around the Y direction. Each first main mounting seat (510) is universally hinged to a first main tie rod (520). The three first main tie rods (520) are universally hinged to the center end of a first main mounting section (530). The first main mounting section (530) is used to connect the aircraft engine.

2. The vibration test bench system according to claim 1, characterized in that, The mounting bracket (400) is also provided with a second main mounting assembly, which is arranged opposite to the first main mounting assembly along the Y direction. The second main mounting assembly includes two second main mounting seats (610) spaced apart along the X direction. Each of the two second main mounting seats (610) is universally hinged to a second main tie rod (620). The ends of the two second main tie rods (620) that are close to each other along the X direction are universally hinged to a second main mounting section (630). The second main mounting section (630) is used to connect the aircraft engine.

3. The vibration test bench system according to claim 2, characterized in that, The auxiliary pull rod (430), the first main pull rod (520) and the second main pull rod (620) are configured with the same structure; the first main pull rod (520) includes a hollow connecting part (521), and a threaded rod part (522) is slidably provided at both ends of the connecting part (521), and the threaded rod part (522) is locked by a nut (523).

4. The vibration test bench system according to claim 2, characterized in that, It also includes an air bleed system (700) which is detachably provided with a telescopic hose (710) that passes through the through hole (410) and is used to connect to the air bleed outlet of the aircraft engine.

5. A vibration test bench system according to any one of claims 2 to 4, characterized in that, The mounting bracket (400) is detachably connected to the first vibration slide (200). The mounting bracket (400) has a first state and a second state in which it is assembled with the first vibration slide (200). In the first state, the first main mounting assembly and the second main mounting assembly are arranged opposite each other along the Y direction. In the second state, the mounting bracket (400) is arranged opposite each other along the X direction.

6. The vibration test bench system according to claim 5, characterized in that, The vibrator (300) has a support plate (310) on each side along the Y direction. The vibrator (300) is rotatably connected between the two support plates (310) around the Y direction. The vibrator (300) has a third state arranged parallel to the X direction and a fourth state arranged parallel to the Z direction. The first vibration slide (200) is detachably connected to the vibrator (300) in the third state. The upper end between the two support plates (310) is slidably connected to a second vibration slide (800) along the Z direction. The mounting bracket (400) is detachably connected to the second vibration slide (800). The second vibration slide (800) is detachably connected to the vibrator (300) in the fourth state.

7. A vibration test bench system according to claim 6, characterized in that, It also includes a first exhaust pipe (720), which is located on one side of the mounting bracket (400) along the X direction; the first exhaust pipe (720) is driven to move along the X and Z directions by a two-axis moving assembly; the first exhaust pipe (720) is used to correspond to the tail nozzle of the aircraft engine and to discharge the high-temperature exhaust gas generated during the test into the atmosphere.

8. A vibration test bench system according to claim 6, characterized in that, A connecting plate (450) is provided at each of the four corners of the lower end of the mounting bracket (400). A connecting hole (451) is provided through the connecting plate (450) along the Z direction. The connecting hole (451) is used for the rod of the first fastening bolt to pass through. The first vibration slide (200) is provided with a first threaded hole corresponding to the position of the connecting hole (451). The first threaded hole matches the first fastening bolt. And / or, a connecting plate (450) is provided at each of the four corners of the lower end of the mounting bracket (400), and a connecting hole (451) is provided through the connecting plate (450) along the Z direction. The connecting hole (451) is used for the rod of the second fastening bolt to pass through. The second vibration slide (800) is provided with a second threaded hole corresponding to the position of the connecting hole (451). The second threaded hole matches the second fastening bolt.

9. A vibration test bench system according to claim 5, characterized in that, The base (100) is provided with a second exhaust pipe (730) on one side along the Y direction. The mounting bracket (400) is in a second state. The second exhaust pipe (730) corresponds to the tail nozzle of the aircraft engine and is used to discharge the high-temperature exhaust gas generated during the test into the atmosphere.

10. A vibration test bench system according to any one of claims 1 to 4, characterized in that, The upper end of the mounting bracket (400) is provided with an opening (460) along the Z direction, the opening (460) being used for the aircraft engine to pass through.

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