Vibration test bench system

Abstract

The invention discloses a vibration test bench system which comprises a base, and a first vibration sliding table is arranged on the base in a sliding mode in the X direction. A vibration exciter is arranged on the base in the X direction, is connected with the first vibration sliding table and generates exciting force for vibration; the first vibration sliding table is provided with a mounting frame, and an auxiliary mounting assembly is arranged on the side, in the X direction, in the mounting frame and used for being connected with the aero-engine. A first main mounting assembly is arranged on one side, in the Y direction, in the mounting frame, the first main mounting assembly comprises three first main mounting bases which are arranged at intervals in the Y direction, each first main mounting base is universally hinged to a first main pull rod, and the ends, facing the center, of the three first main pull rods are universally hinged to a first main mounting section; the first main mounting section is used for connecting an aero-engine. The connecting state of the aero-engine in service is dynamically simulated, and the requirement for thermal expansion of the aero-engine in the working state is met.

Description

Technical Field

[0001] The invention relates to the technical field of aero-engine testing, and in particular to a vibration test bench system. Background Art

[0002] Aircraft engine vibration is one of the important issues that need to be considered during the development and use of the entire aircraft engine. Designing and building an aircraft engine vibration simulation test bench is one of the important means to study aircraft engine vibration failures; according to the provisions of the National Military Standard (GJB150.16A), the test state of the test piece in the aircraft engine whole machine vibration test is required to be consistent with that in working use; during the test, the test piece needs to be fixed on the test fixture installation part, and provide mechanical, electrical, hydraulic, pneumatic or other connections that the aircraft engine test piece needs to use during operation.

[0003] Traditional vibration test equipment usually uses main and auxiliary mounting sections fixed to the test bench to directly fix the engine, but the above connection method is not easy to dynamically simulate the connection state of the aircraft engine when it is in 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 in the prior art that the vibration test equipment is not easy to dynamically simulate the connection state of the aircraft engine when in service, resulting in unsatisfactory vibration simulation test results, thereby providing a vibration test bench system.

[0005] A vibration test bench system provided by the present invention is applied to perform vibration test on an aircraft engine. The vibration test bench system comprises:

[0006] Pedestal;

[0007] A first vibrating slide table is slidably disposed on the base along the X direction;

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

[0009] A mounting frame is arranged on the vibration slide table, a through hole is arranged on one side of the mounting frame along the X direction, and an auxiliary mounting assembly is arranged on the other side, the auxiliary mounting assembly includes two auxiliary mounting seats arranged at intervals along the Y direction, the two auxiliary mounting seats are universally hinged with an auxiliary pull rod, and one end of the two auxiliary pull rods close to each other along the Y direction is universally hinged to an auxiliary mounting section, and the auxiliary mounting section is used to connect the aircraft engine;

[0010] A first main mounting assembly is arranged on one side along the Y direction in the mounting frame, and the first main mounting group includes three first main mounting seats arranged at intervals around the Y direction, each of the first main mounting seats is universally hinged with a first main pull rod, and one end of the three first main pull rods facing the center is universally hinged to the first main mounting section, and the first main mounting section is used to connect the aircraft engine.

[0011] A vibration test bench system according to the present invention has at least the following technical effects:

[0012] The mounting frame adopts a cage structure similar to that of the aircraft engine installed on the aircraft, and the auxiliary mounting section and the first main mounting section are respectively connected to the corresponding bolt holes of the aircraft engine by bolts to achieve support and fixation of the aircraft engine, and the first main mounting section is universally hinged to the first main mounting seat by the first main tie rod, and the auxiliary mounting section is universally hinged to the auxiliary mounting seat by the auxiliary tie rod; during the vibration test of the aircraft engine, a small range of adaptive movement can be generated through the first main mounting section and the auxiliary mounting section, thereby achieving dynamic simulation of the connection state of the aircraft engine when in service and improving the accuracy of the vibration simulation test results.

[0013] In an optional embodiment, a second main mounting assembly is further provided in the mounting frame, and the second main mounting assembly and the first main mounting assembly are arranged relative to each other along the Y direction; the second main mounting assembly includes two second main mounting seats spaced apart along the X direction, and each of the two second main mounting seats is universally hinged with a second main pull rod, and one end of the two second main pull rods close to each other along the X direction is universally hinged to a second main mounting section, and the second main mounting section is used to connect the aircraft engine.

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

[0015] In an optional embodiment, it further comprises an air bleed system, wherein the air bleed system is detachably provided with a telescopic hose, wherein the telescopic hose passes through the through hole and is used to connect to the air bleed outlet of the aircraft engine.

[0016] In an optional embodiment, the mounting frame is detachably connected to the first vibrating slide, and the mounting frame has a first state and a second state of being assembled with the first vibrating slide, and when the mounting frame is in the first state, the first main mounting component and the second main mounting component are arranged relative to each other along the Y direction; when the mounting frame is in the second state, the first main mounting component and the second main mounting component are arranged relative to each other along the X direction.

[0017] In an optional embodiment, a support plate is respectively provided on both sides of the exciter along the Y direction, the exciter is connected between the two support plates by rotating around the Y direction, and the exciter has a third state of being arranged parallel to the X direction, and a fourth state of being arranged parallel to the Z direction; the first vibration slide is detachably connected to the exciter in the third state; the upper end between the two support plates is slidably connected to a second vibration slide along the Z direction, the mounting frame is detachably connected to the second vibration slide, and the second vibration slide is detachably connected to the exciter in the fourth state.

[0018] In an optional embodiment, it also includes a first exhaust chimney, which is located on one side of the mounting frame along the X direction; the first exhaust chimney is driven by a two-axis moving assembly to move along the X direction and the Z direction; the first exhaust chimney is used to correspond 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.

[0019] In an optional embodiment, a connecting plate is respectively provided at the four corners of the lower end of the mounting frame, and a connecting hole is penetrated through the connecting plate along the Z direction, and the connecting hole is used for the rod of the first fastening bolt to pass through, and a first threaded hole is provided at a position of the first vibration slide corresponding to the connecting hole, and the first threaded hole matches the first fastening bolt;

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

[0021] In an optional embodiment, a second exhaust chimney is provided on one side of the base along the Y direction, and the mounting frame is in a second state. The second exhaust chimney 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 an optional embodiment, an opening is provided through the upper end of the mounting frame along the Z direction, and the opening is used for allowing the aircraft engine to pass through.

[0023] Additional aspects and advantages of the present invention will be given in part in the following description and in part will be obvious from the following description, or will be learned through practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] In order to more clearly illustrate the specific implementation methods of the present invention or the technical solutions in the prior art, the drawings required for use in the specific implementation methods or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are some implementation methods of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0025] Figure 1 This is a schematic diagram of the three-dimensional structure of a vibration test bench system of this embodiment after the second vibration slide table is removed;

[0026] Figure 2 It is a schematic diagram of the three-dimensional structure of a mounting frame in a vibration test bench system of this embodiment;

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

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

[0029] Figure 5 Schematic diagram of the structure of a first main pull rod in a vibration test bench system of this embodiment.

[0030] Description of reference numerals:

[0031] 100 - base;

[0032] 200-first vibration slide;

[0033] 300-vibrator, 310-support plate, 320-connecting column, 330-installation frame, 331-guide seat;

[0034] 400-mounting frame, 410-through hole, 420-auxiliary mounting seat, 430-auxiliary pull rod, 440-auxiliary mounting section, 450-connecting plate, 451-connecting hole, 460-opening;

[0035] 510 - first main mounting seat, 520 - first main pull rod, 521 - connecting portion, 522 - threaded rod portion, 523 - nut, 530 - first main mounting section;

[0036] 610 - second main mounting seat, 620 - second main pull rod, 630 - second main mounting section;

[0037] 700-air bleed system, 710-flexible hose, 720-first exhaust pipe, 730-second exhaust pipe;

[0038] 800 - second vibration slide, 810 - guide slide. DETAILED DESCRIPTION

[0039] In order to make the purpose, technical solution and advantages of the embodiments of the present invention clearer, the technical solution in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative work 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", "outer", etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing this embodiment and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting this embodiment. In addition, the terms "first", "second", and "third" are used for descriptive purposes only and cannot be understood as indicating or implying relative importance.

[0041] In the description of this embodiment, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in this embodiment can be understood according to specific circumstances.

[0042] Combine the following Figures 1 to 5 , describing an embodiment of the present invention.

[0043] A vibration test bench system provided according to an embodiment of the present invention is applied to a vibration test of an aircraft engine. The vibration test bench system comprises a base 100, on which a first vibration slide table 200 is slidably arranged along the X direction; an exciter 300 is arranged along the X direction on the base 100, the exciter 300 is connected to the first vibration slide table 200, and generates an excitation force for vibration; the first vibration slide table 200 is provided with a mounting frame 400, a through hole 410 is provided on one side of the mounting frame 400 along the X direction, and an auxiliary mounting assembly is provided on the other side, the auxiliary mounting assembly comprises two auxiliary mounting seats 420 arranged at intervals along the Y direction, The two auxiliary mounting seats 420 are universally hinged with an auxiliary tie rod 430, and the ends of the two auxiliary tie rods 430 close to each other along the Y direction are universally hinged to the auxiliary mounting joint 440, and the auxiliary mounting joint 440 is used to connect the aircraft engine; a first main mounting assembly is arranged on one side along the Y direction in the mounting frame 400, and the first main mounting assembly includes three first main mounting seats 510 arranged circumferentially around the Y direction. Each of the first main mounting seats 510 is universally hinged with a first main tie rod 520, and the ends of the three first main tie rods 520 facing the center are universally hinged to the first main mounting joint 530, and the first main mounting joint 530 is used to connect the aircraft engine. It can be understood that the X direction, Y direction and Z direction mentioned in the text refer to Figure 1 In the X-direction, Y-direction and Z-direction, the X-direction, Y-direction and Z-direction are perpendicular to each other; the X-direction and the Y-direction are in the same horizontal plane.

[0044] The mounting frame 400 of the vibration test bench system of the present embodiment adopts a cage structure similar to that of the aircraft engine installed on the aircraft, and the auxiliary mounting section 440 and the first main mounting section 530 are respectively connected to the corresponding bolt holes of the aircraft engine by bolts to realize the support and fixation of the aircraft engine; and the first main mounting section 530 is universally hinged to the first main mounting seat 510 through the first main tie rod 520, and the auxiliary mounting section 440 is universally hinged to the auxiliary mounting seat 420 through the auxiliary tie rod 430, so that during the vibration test of the aircraft engine, a small range of adaptive movement can be generated through the first main mounting section 530 and the auxiliary mounting section 440, so as to realize dynamic simulation of the connection state of the aircraft engine when in service, meet the requirements of thermal expansion of the aircraft engine when in working state, and improve the accuracy of the vibration simulation test results.

[0045] It should be noted that, since the weight of the aircraft engine is mainly borne by the first main mounting section 530, the first main mounting section 530 is connected to the mounting frame 400 by three first main tie rods 520 arranged in a triangle shape, which can improve the stability of the aircraft engine during the test.

[0046] Considering that only the first main mounting assembly is used to connect and support one side of the aircraft engine along the Y direction (i.e., a single-sided suspended arrangement), it is easy to lead to insufficient connection reliability. In order to solve the above technical problems, in some embodiments, a second main mounting assembly is further provided in the mounting frame 400, and the second main mounting assembly and the first main mounting assembly are arranged relatively 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, and the two second main mounting seats 610 are both universally hinged with a second main pull rod 620, and the ends of the two second main pull rods 620 close to each other along the X direction are universally hinged to the second main mounting section 630, and the second main mounting section 630 is used to connect the aircraft engine. On the one hand, the second main mounting section 630 is connected to the corresponding bolt hole of the aircraft engine by bolts, and the other side of the aircraft engine away from the first main mounting section 530 along the Y direction is connected and supported, so that the aircraft engine is supported in a structural manner similar to "double-sided support", which is beneficial to improving the stability of the aircraft engine during the test; on the other hand, the second main mounting section 630 is universally hinged to the second main mounting seat 610 through the second main pull rod 620, so that during the vibration test of the aircraft engine, the second main mounting section 630 can produce a small range of adaptive movement, so as to better dynamically simulate the connection state of the aircraft engine when it is in 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 all provided with four through holes spaced circumferentially around their own axes corresponding to the positions of the bolt holes of the aircraft engine. The through holes facilitate the passage of bolts to the corresponding bolt holes of the aircraft engine, thereby improving the connection reliability.

[0048] Specifically, the first main mounting seat 510 is provided with a first lug through a first joint bearing, and the first lug is hinged to the first main pull rod 520 , so as to facilitate rotation adjustment of the first main pull rod 520 relative to the first main mounting seat 510 .

[0049] Specifically, the second main mounting seat 610 is provided with a second lug through a second joint bearing, and the second lug is hinged to the second main pull rod 620 , so as to facilitate rotation adjustment of the second main pull rod 620 relative to the second main mounting seat 610 .

[0050] Specifically, the auxiliary mounting seat 420 is provided with a third lug through a third joint bearing, and the third lug is hinged to the auxiliary pull rod 430 , so as to facilitate rotation adjustment of the auxiliary pull rod 430 relative to the auxiliary mounting seat 420 .

[0051] like Figure 5As shown, specifically, the auxiliary rod 430, the first main rod 520 and the second main rod 620 are configured with the same structure; the first main rod 520 includes a hollow connecting portion 521, and a threaded rod 522 is slidably provided at both ends of the connecting portion 521, and the threaded rod 522 is locked by a nut 523. With this configuration, the threaded rod 522 can be flexibly adjusted to move to different positions relative to the connecting portion 521, and the lengths of the auxiliary rod 430, the first main rod 520 and the second main rod 620 can be adjusted, which can not only compensate for the errors caused by manufacturing precision and realize the rapid installation and disassembly of the aircraft engine; but also can be applied to the installation of aircraft engines with different external sizes, further expanding the scope of application of the vibration test bench system of this embodiment.

[0052] It can be understood that external threaded portions are provided on the outer side walls at both ends of the connecting portion 521 along the length direction of the connecting portion 521, and the external threaded portions match the nut 523; when the threaded rod 522 is extended or retracted to the desired position relative to the connecting portion 521, the nut 523 is rotated on the threaded rod 522 until the thread is matched 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 seat 420, the angle of the first main tie rod 520 relative to the first main mounting seat 510 and the angle of the second main tie rod 620 relative to the second main mounting seat 610, the aircraft engine can be quickly installed and disassembled, eliminating the impact of manufacturing precision errors, which is beneficial to reducing the cost of the vibration test bench system of this embodiment.

[0054] like Figure 2 As shown, specifically, an opening 460 is provided through the upper end of the mounting frame 400 along the Z direction, and the opening 460 is used for the aircraft engine to pass through. With this arrangement, before the test, the aircraft engine can be put into the mounting frame 400 from top to bottom through the opening 460 by a crane and installed, and the entire installation and removal process saves manpower, which is conducive to reducing the test cost.

[0055] In some embodiments, a first waist-shaped through hole is formed on the auxiliary mounting seat 420 along the X direction, and the first waist-shaped through hole is used for the rod of the first bolt to pass through. The mounting frame 400 is provided with a third threaded hole at a position corresponding to the first waist-shaped through hole, and the third threaded hole matches the first bolt. The auxiliary mounting seat 420 is detachably connected to the mounting frame 400 by matching the first bolt with the third threaded hole, which can ensure the connection strength and facilitate disassembly for inspection and maintenance. At the same time, the first waist-shaped through hole can be used to compensate for the error caused by insufficient processing accuracy of the third threaded hole, which is conducive to reducing the cost of the vibration test bench system of this embodiment.

[0056] Specifically, a second waist-shaped through hole is formed on the first main mounting seat 510 along the Y direction, and the second waist-shaped through hole is used for the rod of the second bolt to pass through. The mounting frame 400 is provided with a fourth threaded hole at a position corresponding to the second waist-shaped through hole, and the fourth threaded hole matches the second bolt. The first main mounting seat 510 is detachably connected to the mounting frame 400 by matching the second bolt with the fourth threaded hole, which can ensure the connection strength and facilitate disassembly for inspection and maintenance. At the same time, the second waist-shaped through hole can compensate for the error caused by insufficient processing accuracy of the fourth threaded hole, which is conducive to reducing the cost of the vibration test bench system of this embodiment.

[0057] Specifically, a third waist-shaped through hole is formed on the second main mounting seat 610 along the Y direction, and the third waist-shaped through hole is used for the rod of the third bolt to pass through. The mounting frame 400 is provided with a fifth threaded hole at a position corresponding to the third waist-shaped through hole, and the fifth threaded hole matches the third bolt. The second main mounting seat 610 is detachably connected to the mounting frame 400 by matching the third bolt with the fifth threaded hole, which can ensure the connection strength and facilitate disassembly for inspection and maintenance. At the same time, the third waist-shaped through hole can compensate for the error caused by insufficient processing accuracy of the fifth threaded hole, which is conducive to reducing the cost of the vibration test bench system of this embodiment.

[0058] like Figure 1 As shown, in some embodiments, the vibration test bench system also includes an air bleed system 700, and the air bleed system 700 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 aircraft engine. The air bleed outlet of the aircraft engine is connected to the air bleed system 700 through the telescopic hose 710 to meet the air bleed requirements, which is conducive to keeping the test state of the aircraft engine consistent with the state during working use; and the telescopic hose 710 can also deform accordingly to absorb the displacement generated during the vibration test of the aircraft engine, thereby ensuring the quality of the air bleed.

[0059] In some embodiments, the mounting frame 400 is detachably connected to the first vibration slide 200, and the mounting frame 400 has a first state and a second state assembled with the first vibration slide 200. When the mounting frame 400 is in the first state, the first main mounting assembly and the second main mounting assembly are arranged relative to each other along the Y direction (such as 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 relatively along the X direction; so 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 with the first vibration slide 200, the mounting frame 400 can be switched to the second state, so that the aircraft engine installed in the mounting frame 400 is rotated 90° around the Z direction relative to the first vibration slide 200, so that the aircraft engine installed in the mounting frame 400 in the first state is arranged parallel to the X direction, and the aircraft engine installed in the mounting frame 400 in the second state is arranged parallel to the Y direction, so that the aircraft engine is installed in the vibration test bench system of this embodiment at a single time, and only one exciter 300 is required to realize the effect of performing vibration tests in the X direction and vibration tests in the Y direction respectively, which has a wide range of applications and low cost.

[0060] like Figure 1 Shown and Figure 4 Specifically, the exciter 300 is provided with a support plate 310 on both sides along the Y direction, and the exciter 300 is connected between the two support plates 310 by rotating around the Y direction. The exciter 300 has a third state (such as 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; the upper end between the two support plates 310 is slidably connected with a second vibration slide 800 along the Z direction, the mounting frame 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 such arrangement, when it is necessary to conduct a vibration test on the aircraft engine in the X direction, it is only necessary to assemble the mounting frame 400 with the first vibration slide 200 in the first state. At this time, the aircraft engine assembled on the mounting frame 400 is arranged parallel to the X direction, and vibrates with the first vibration slide 200 under the excitation force of the exciter 300 arranged along the X direction, thereby realizing the vibration test in the X direction; when it is necessary to conduct a vibration test on the aircraft engine in the Y direction, it is only necessary to assemble the mounting frame 400 with the first vibration slide 200 in the second state. At this time, the aircraft engine assembled on the mounting frame 400 is arranged parallel to the Y direction, and vibrates with the first vibration slide 200 under the excitation force of the exciter 300 arranged along the X direction, thereby realizing the vibration test in the Y direction; when it is necessary to conduct a vibration test on the aircraft engine in the Z direction, first assemble the exciter 300 with the first vibration slide 200 The slides 200 are separated from each other, and then the exciter 300 is rotated 90° in the Y direction, so that the exciter 300 switches from the third state to the fourth state, and then the second vibration slide 800 is connected to the exciter 300 in the fourth state as a whole, and finally the mounting frame 400 equipped with the aircraft engine is connected to the second vibration slide 800, so that the aircraft engine mounted on the mounting frame 400 vibrates with the second vibration slide 800 under the excitation force of the exciter 300 arranged along the Z direction, thereby realizing a vibration test in the Z direction; on the basis of installing the aircraft engine once on the vibration test bench system of this embodiment, only one exciter 300 is needed to realize the effect of performing vibration tests in the X direction, the Y direction and the Z direction respectively, and realizing a three-axis vibration test on the same vibration test bench system.

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

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

[0063] Here, the detachable connection structure between the mounting frame 400 and the first vibration slide table 200 is described in detail. Figure 1 and Figure 2As shown, in some embodiments, a connecting plate 450 is respectively provided at the four corners of the lower end of the mounting frame 400, and a connecting hole 451 is penetrated along the Z direction on the connecting plate 450, and the connecting hole 451 is used for the rod of the first fastening bolt to pass through, and a first threaded hole is provided at the position of the first vibration slide 200 corresponding to the connecting hole 451, and the first threaded hole matches the first fastening bolt; when it is necessary to connect the mounting frame 400 and the first vibration slide 200 into one, it is only necessary to pass the first fastening bolt through the connecting hole 451 and tighten it in the first threaded hole; when it is necessary to disassemble the mounting frame 400 and the first vibration slide 200, it is only necessary to unscrew the first fastening bolt from the first threaded hole and take it out from the connecting hole 451, and the whole disassembly and assembly process is easy to operate. In another replaceable embodiment, the connecting hole 451 is set to penetrate the first vibration slide 200 along the Z direction, and the first threaded hole is set on the connecting plate 450.

[0064] It should be noted that, no matter the mounting frame 400 is in the first state or the second state, a first threaded hole is provided at a position corresponding to the connecting hole 451 on the first vibration slide table 200 .

[0065] Here, the detachable connection structure between the mounting frame 400 and the second vibration slide table 800 is described in detail. Figure 2 and Figure 4 As shown, in some embodiments, the mounting frame 400 is connected to the second vibration slide 800 in a first state, that is, the aircraft engine assembled in the mounting frame 400 is arranged parallel to the X direction; a connecting plate 450 is respectively provided at the four corners of the lower end of the mounting frame 400, and a connecting hole 451 is penetrated along the Z direction on the connecting plate 450, and the connecting hole 451 is used for the rod of the second fastening bolt to pass through, and the second vibration slide 800 is provided with a second threaded hole at the position corresponding to the connecting hole 451, and the second threaded hole matches the second fastening bolt; when it is necessary to connect the mounting frame 400 in the first state and the second vibration slide 800 into one, it is only necessary to pass the second fastening bolt through the connecting hole 451 and tighten it to the second threaded hole; when it is necessary to disassemble the mounting frame 400 and the second vibration slide 800, it is only necessary to unscrew the second fastening bolt from the second threaded hole and take it out from the connecting hole 451, and the whole disassembly and assembly process is convenient to operate. In another alternative embodiment, the connecting hole 451 is provided through the second vibration slide table 800 along the Z direction, and the second threaded hole is provided on 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 through the connecting column 320, and the four inner walls of the mounting frame 330 are respectively provided with a guide seat 331, and the second vibration slide table 800 is provided with a guide slider 810 corresponding to the position of each guide seat 331, and the guide slider 810 is 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 also includes a first exhaust chimney 720, which is located on the side of the mounting frame 400 in the first state away from the exciter 300 along the X direction; the first exhaust chimney 720 is driven by a two-axis moving assembly to move along the X direction and the Z direction; when the mounting frame 400 equipped with an aircraft engine is connected to the first vibration slide 200 in the first state for an X-direction vibration test, the aircraft engine is arranged parallel to the X direction, that is, the first exhaust chimney 720 corresponds to the tail nozzle of the aircraft engine, so that the first exhaust chimney 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 working use. When the mounting frame 400 equipped with the aircraft engine is connected to the second vibration slide 800 in the first state for a vibration test in the Z direction, the aircraft engine is arranged parallel to the X direction, and the first exhaust pipe 720 and the tail nozzle of the aircraft engine are relatively spaced apart in the X direction and the Z direction. The first exhaust pipe 720 is adjusted by the two-axis moving assembly to move correspondingly to the tail nozzle of the aircraft engine, so that the first exhaust pipe 720 can discharge the high-temperature exhaust gas generated during the vibration test in the Z direction into the atmosphere, which is conducive to keeping the test state of the aircraft engine consistent with the state during working use. It can be understood that the two-axis moving assembly here adopts a mature two-axis moving device in the relevant technology, and it only needs to realize the function of driving the first exhaust pipe 720 to move along the X direction and the Z direction.

[0068] Specifically, the base 100 is provided with a second exhaust chimney 730 on one side along the Y direction. When the mounting frame 400 equipped with the aircraft engine is connected to the first vibration slide 200 in the second state for a Y-direction vibration test, the aircraft engine is arranged parallel to the Y direction, that is, the second exhaust chimney 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 is beneficial to keep the test state of the aircraft engine consistent with the state during working use.

[0069] Obviously, the above embodiments are merely examples for the purpose of clear explanation, and are not intended to limit the implementation methods. For those skilled in the art, other different forms of changes or modifications can be made based on the above description. It is not necessary and impossible to list all the implementation methods here. The obvious changes or modifications derived therefrom are still within the scope of protection of the invention.

Claims

1. A vibration test bench system, used for vibration testing of aircraft engines, characterized in that: The vibration test bench system includes: Base (100); A first vibrating slide table (200) is slidably disposed on the base (100) along the X direction; An exciter (300) is arranged on the base (100) along the X direction, is connected to the first vibration slide table (200), and generates an excitation force for vibration; A mounting frame (400) is arranged on the first vibration slide table (200), a through hole (410) is arranged on one side along the X direction in the mounting frame (400), and an auxiliary mounting assembly is arranged on the other side, the auxiliary mounting assembly comprises two auxiliary mounting seats (420) arranged at intervals along the Y direction, the two auxiliary mounting seats (420) are universally hinged to an auxiliary pull rod (430), one end of the two auxiliary pull rods (430) close to each other along the Y direction is universally hinged to an auxiliary mounting joint (440), and the auxiliary mounting joint (440) is used to connect the aircraft engine; A first main mounting assembly is arranged on one side along the Y direction in the mounting frame (400), and the first main mounting assembly includes three first main mounting seats (510) arranged at intervals around the Y direction, each of the first main mounting seats (510) is universally hinged with a first main pull rod (520), and one end of the three first main pull rods (520) facing the center is universally hinged to a first main mounting section (530), and the first main mounting section (530) is used to connect to an aircraft engine.

2. A vibration test bench system according to claim 1, characterized in that: A second main mounting assembly is also provided in the mounting frame (400), and the second main mounting assembly and the first main mounting assembly are arranged relative 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, and the two second main mounting seats (610) are each universally hinged with a second main pull rod (620), and one end of the two second main pull rods (620) close to each other along the X direction is universally hinged to a second main mounting section (630), and the second main mounting section (630) is used to connect to an aircraft engine.

3. A 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 arranged to have the same structure; the first main pull rod (520) includes a hollow connecting portion (521), and a threaded rod portion (522) is slidably arranged at both ends of the connecting portion (521), and the threaded rod portion (522) is locked by a nut (523).

4. A vibration test bench system according to claim 2, characterized in that: The invention also comprises an air bleed system (700), wherein the air bleed system (700) is detachably provided with a telescopic hose (710), wherein the telescopic hose (710) 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 frame (400) is detachably connected to the first vibration slide (200), and the mounting frame (400) has a first state and a second state of being assembled with the first vibration slide (200). When the mounting frame (400) is in the first state, the first main mounting component and the second main mounting component are arranged relative to each other along the Y direction; when the mounting frame (400) is in the second state, the first main mounting component and the second main mounting component are arranged relative to each other along the X direction.

6. A vibration test bench system according to claim 5, characterized in that: A support plate (310) is respectively provided on both sides of the exciter (300) along the Y direction; the exciter (300) is connected between the two support plates (310) by rotating around the Y direction; the exciter (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 exciter (300) in the third state; a second vibration slide (800) is slidably connected to the upper end between the two support plates (310) along the Z direction; the mounting frame (400) is detachably connected to the second vibration slide (800); the second vibration slide (800) is detachably connected to the exciter (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 frame (400) along the X direction; the first exhaust pipe (720) is driven by a two-axis moving assembly to move along the X direction and the Z direction; 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 respectively arranged at the four corners of the lower end of the mounting frame (400), and a connecting hole (451) is penetrated through the connecting plate (450) along the Z direction, and the connecting hole (451) is used for the rod of the first fastening bolt to pass through, and a first threaded hole is arranged at a position of the first vibration slide table (200) corresponding to the connecting hole (451), and the first threaded hole matches the first fastening bolt; And / or, a connecting plate (450) is respectively provided at the four corners of the lower end of the mounting frame (400), and a connecting hole (451) is penetrated through the connecting plate (450) along the Z direction, and the connecting hole (451) is used for the rod of the second fastening bolt to pass through, and the second vibration slide (800) is provided with a second threaded hole at a position corresponding to the connecting hole (451), and the second threaded hole matches the second fastening bolt.

9. A vibration test bench system according to claim 5, characterized in that: A second exhaust pipe (730) is provided on one side of the base (100) along the Y direction. The mounting frame (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 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: An opening (460) is provided through the upper end of the mounting frame (400) along the Z direction, and the opening (460) is used for allowing the aircraft engine to pass through.

Images