CN119880314B - Vibration test bench system - Google Patents
Vibration test bench systemInfo
- Publication number
- CN119880314B CN119880314B CN202510091321.5A CN202510091321A CN119880314B CN 119880314 B CN119880314 B CN 119880314B CN 202510091321 A CN202510091321 A CN 202510091321A CN 119880314 B CN119880314 B CN 119880314B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
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- General Physics & Mathematics (AREA)
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Vibration Prevention Devices (AREA)
Abstract
The invention discloses a vibration test bench system which comprises a base, wherein a first vibration sliding table is arranged on the base in a sliding mode along the X direction, a vibration exciter is arranged on the base in the X direction and connected with the first vibration sliding table and used for generating exciting force for vibration, an installation frame is arranged on the first vibration sliding table, an auxiliary installation assembly is arranged on one side of the installation frame along the X direction and used for being connected with an aeroengine, a first main installation assembly is arranged on one side of the installation frame along the Y direction and comprises three first main installation seats which are arranged at intervals around the Y direction, each first main installation seat is hinged with a first main pull rod in a universal mode, one ends of the three first main pull rods, facing the center, are hinged to the first main installation joints in a universal mode, and the first main installation joints are used for being connected with the aeroengine. The invention realizes the dynamic simulation of the connection state of the aero-engine in service and meets the requirement of thermal expansion of the aero-engine in the working state.
Description
Technical Field
The invention relates to the technical field of aero-engine tests, in particular to a vibration test bench system.
Background
Aeroengine vibration is one of the important issues to be considered in the development and use of the whole aeroengine. The design and construction of the aero-engine vibration simulation test bed is one of important means for researching the vibration faults of the aero-engine, the test state of a test piece is required to be consistent with that of the whole machine vibration test of the aero-engine according to the regulations of national army standard (GJB150.16A), the test piece is required to be fixed on the mounting part of a test fixture during the test, and mechanical, electrical, hydraulic, pneumatic or other connection for the test piece of the aero-engine during the operation is provided.
The traditional vibration test equipment generally adopts a main installation joint and an auxiliary installation joint which are fixed on a rack to directly fix the engine, but the connection mode is not easy to dynamically simulate the connection state of the aeroengine during service, so that the vibration simulation test result is not ideal.
Disclosure of Invention
Therefore, the technical problem to be solved by the invention is to overcome the defect that the vibration test equipment in the prior art is difficult to dynamically simulate the connection state of the aeroengine during service, so that the vibration simulation test result is not ideal, thereby providing the vibration test bench system.
According to the invention, the vibration test bench system is applied to vibration test of an aeroengine and comprises:
A base;
The first vibration sliding table is arranged on the base in a sliding manner along the X direction;
the vibration exciter is arranged on the base along the X direction, is connected with the first vibration sliding table and generates excitation force for vibration;
The vibration sliding table comprises a mounting frame, wherein a through hole is formed in one side of the mounting frame along the X direction, an auxiliary mounting assembly is arranged on the other side of the mounting frame, the auxiliary mounting assembly comprises two auxiliary mounting seats which are arranged at intervals along the Y direction, each auxiliary mounting seat is articulated with an auxiliary pull rod in a universal mode, one ends, close to each other, of the two auxiliary pull rods along the Y direction are articulated with auxiliary mounting joints in a universal mode, and the auxiliary mounting joints are used for being connected with an aeroengine;
The novel aircraft engine is characterized in that a first main installation component is arranged on one side of the mounting frame along the Y direction, the first main installation group comprises three first main installation seats which are arranged at intervals around the Y direction, each first main installation seat is all articulated with a first main pull rod in a universal mode, one end of each first main pull rod, which faces the center, is articulated with a first main installation section in a universal mode, and the first main installation section is used for being connected with an aircraft engine.
The vibration test bench system provided by the invention has at least the following technical effects:
The installation frame adopts a cage structure similar to that of the aeroengine installed on the aeroengine, the auxiliary installation section and the first main installation section are respectively connected into corresponding bolt holes of the aeroengine through bolts, the aeroengine is supported and fixed, the first main installation section is universally hinged to the first main installation seat through the first main pull rod, and the auxiliary installation section is universally hinged to the auxiliary installation seat through the auxiliary pull rod, so that the aeroengine can generate small-range adaptive movement through the first main installation section and the auxiliary installation section in the vibration test process, the connection state of the aeroengine in service is dynamically simulated, and the accuracy of the vibration simulation test result is improved.
In an alternative embodiment, a second main installation component is further arranged in the installation frame, the second main installation component and the first main installation component are oppositely arranged along the Y direction, the second main installation component comprises two second main installation seats which are arranged at intervals along the X direction, each of the two second main installation seats is hinged with a second main pull rod in a universal mode, one ends, close to each other, of the two second main pull rods along the X direction are hinged with a second main installation joint in a universal mode, and the second main installation joint is used for being connected with an aeroengine.
In an alternative embodiment, the auxiliary pull rod, the first main pull rod and the second main pull rod are arranged in the same structure, the first main pull rod comprises a hollow connecting part, two ends of the connecting part are respectively provided with a threaded rod part in a sliding mode, and the threaded rod parts are locked through nuts.
In an alternative embodiment, the aircraft engine further comprises a bleed air system, which is detachably provided with a telescopic hose, which passes through the via hole and is used for connecting a bleed air outlet of the aircraft engine.
In an alternative embodiment, the mounting frame is detachably connected to the first vibration sliding table, the mounting frame has a first state and a second state assembled with the first vibration sliding table, the mounting frame is in the first state, the first main mounting component and the second main mounting component are oppositely arranged along the Y direction, and the mounting frame is in the second state, and the first main mounting component and the second main mounting component are oppositely arranged along the X direction.
In an alternative implementation mode, two sides of the vibration exciter along the Y direction are respectively provided with a supporting plate, the vibration exciter is connected between the two supporting plates in a rotating mode around the Y direction, the vibration exciter is in a third state parallel to the X direction and a fourth state parallel to the Z direction, the first vibration sliding table is detachably connected with the vibration exciter in the third state, the upper ends between the two supporting plates are connected with a second vibration sliding table in a sliding mode along the Z direction, the mounting frame is detachably connected with the second vibration sliding table, and the second vibration sliding table is detachably connected with the vibration exciter in the fourth state.
In an alternative embodiment, the device further comprises a first exhaust barrel, wherein the first exhaust barrel is positioned on one side of the mounting frame along the X direction, the first exhaust barrel is driven by the two-axis moving assembly to move along the X direction and the Z direction, and the first exhaust barrel is used for corresponding to a tail pipe of an aeroengine and exhausting high-temperature tail gas generated during testing into the atmosphere.
In an optional embodiment, four corners of the lower end of the mounting frame are respectively provided with a connecting plate, connecting holes are formed in the connecting plates in a penetrating manner along the Z direction, the connecting holes are used for allowing the rod parts of the first fastening bolts to penetrate through, first threaded holes are formed in positions, corresponding to the connecting holes, of the first vibration sliding table, and the first threaded holes are matched with the first fastening bolts;
And/or, four corners of the lower end of the mounting frame are respectively provided with a connecting plate, connecting holes penetrate through the connecting plates along the Z direction, the connecting holes are used for allowing the rod parts of the second fastening bolts to penetrate through, the positions of the second vibration sliding tables corresponding to the connecting holes are provided with second threaded holes, and the second threaded holes are matched with the second fastening bolts.
In an alternative embodiment, a second exhaust pipe is arranged on one side of the base along the Y direction, the mounting frame is in a second state, and the second exhaust pipe corresponds to a tail pipe of the aeroengine and is used for exhausting high-temperature tail gas generated during testing into the atmosphere.
In an alternative embodiment, the upper end of the mounting frame is provided with an opening penetrating in the Z direction, the opening being used for the aero-engine to pass through.
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.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings that are needed in the description of the embodiments or the prior art will be briefly described, and it is obvious that the drawings in the description below are some embodiments of the present invention, and other drawings can be obtained according to the drawings without inventive effort for a person skilled in the art.
Fig. 1 is a schematic perspective view of a vibration test bench system according to the embodiment, with a second vibration table removed;
Fig. 2 is a schematic perspective view of a mounting frame in a vibration test bench system according to the embodiment;
FIG. 3 is a schematic side view of the structure of FIG. 2;
Fig. 4 is a schematic diagram of an assembly structure of a second vibration table and a mounting frame in the vibration test bench system according to the embodiment;
Fig. 5 is a schematic structural view of a first main pull rod in a vibration test bench system according to the embodiment.
Reference numerals illustrate:
100-base;
200-a first vibration slipway;
300-vibration exciter, 310-supporting plate, 320-connecting column, 330-mounting frame and 331-guide seat;
400-mounting frames, 410-through holes, 420-auxiliary mounting seats, 430-auxiliary pull rods, 440-auxiliary mounting joints, 450-connecting plates, 451-connecting holes and 460-open holes;
510-first main mount, 520-first main tie rod, 521-connecting portion, 522-threaded shank, 523-nut, 530-first main mounting section;
610-second main mount, 620-second main tie rod, 630-second main mounting section;
700-bleed air system, 710-telescopic hose, 720-first exhaust stack, 730-second exhaust stack;
800-second vibration slipway, 810-direction slider.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments of the present invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
In the description of the present embodiment, it should be noted that the directions or positional relationships indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the directions or positional relationships shown in the drawings, are merely for convenience of description of the present embodiment and for simplification of the description, and do not indicate or imply that the apparatus or element to be referred to must have a specific direction, be configured and operated in the specific direction, and thus should not be construed as limiting the present embodiment. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present embodiment, unless explicitly specified and limited otherwise, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, integrally connected, mechanically connected, electrically connected, directly connected, indirectly connected through an intermediary, or communicating between two elements. The specific meaning of the above terms in the present embodiment can be understood by those of ordinary skill in the art according to the specific circumstances.
Embodiments of the present invention are described below with reference to fig. 1 to 5.
According to the vibration test bench system provided by the embodiment of the invention, the vibration test bench system is applied to vibration tests of an aeroengine and comprises a base 100, a first vibration sliding table 200 is slidably arranged on the base 100 along the X direction, a vibration exciter 300 is arranged on the base 100 along the X direction, the vibration exciter 300 is connected with the first vibration sliding table 200 and generates excitation force for vibration, a mounting frame 400 is arranged on the first vibration sliding table 200, a through hole 410 is arranged on one side of the mounting frame 400 along the X direction, an auxiliary mounting assembly is arranged on the other side of the mounting frame 400, the auxiliary mounting assembly comprises two auxiliary mounting seats 420 which are arranged at intervals along the Y direction, an auxiliary pull rod 430 is universally hinged to one end of each auxiliary pull rod 430, which is mutually close to the auxiliary mounting seat 440 along the Y direction, a first main mounting assembly is arranged on one side of the mounting frame 400 along the Y direction and comprises three main mounting seats which are circumferentially arranged along the Y direction, each main mounting seat is universally hinged to one main joint 520, and each main joint is universally hinged to one main joint 520, and the main joint is used for connecting the main joint 520. It will be understood that the X direction, Y direction and Z direction refer to the X direction, Y direction and Z direction in fig. 1, and are perpendicular to each other, and the X direction and the Y direction are located on the same horizontal plane.
The mounting frame 400 of the vibration test bench system of the embodiment adopts a cage structure similar to that of an aeroengine mounted on the aeroengine, the auxiliary mounting section 440 and the first main mounting section 530 are respectively connected into corresponding bolt holes of the aeroengine through bolts to support and fix the aeroengine, the first main mounting section 530 is universally hinged to the first main mounting seat 510 through the first main pull rod 520, and the auxiliary mounting section 440 is universally hinged to the auxiliary mounting seat 420 through the auxiliary pull rod 430, so that the small-range adaptive movement of the aeroengine can be generated through the first main mounting section 530 and the auxiliary mounting section 440 in the vibration test process, the connection state of the aeroengine in service can be dynamically simulated, the requirement of thermal expansion of the aeroengine in the working state can be met, and the accuracy of the vibration simulation test result can be improved.
It should be noted that, because the weight of the aero-engine is mainly borne by the first main mounting section 530, the stability of the aero-engine during the test can be improved by connecting the first main mounting section 530 to the mounting frame 400 by the three first main tie rods 520 arranged in a triangular shape.
Considering that only one side of the aero-engine along the Y-direction is supported by the first main mounting component (i.e. one side is suspended), which is prone to cause insufficient connection reliability, in order to solve the above technical problem, in some embodiments, a second main mounting component is further disposed in the mounting frame 400, where the second main mounting component and the first main mounting component are oppositely disposed along the Y-direction, the second main mounting component includes two second main mounting seats 610 disposed at intervals along the X-direction, each of the two second main mounting seats 610 is universally hinged with one second main pull rod 620, and one ends of the two second main pull rods 620, which are close to each other along the X-direction, are universally hinged with a second main mounting joint 630, where the second main mounting joint 630 is used for connecting the aero-engine. On one hand, the second main mounting joint 630 is connected into a corresponding bolt hole of the aeroengine through a bolt, and the aeroengine is connected and supported on the other side, deviating from the first main mounting joint 530 along the Y direction, of the aeroengine, so that the aeroengine is borne in a similar double-sided supporting structural mode, the stability of the aeroengine in the test process is improved, on the other hand, the second main mounting joint 630 is hinged to the second main mounting seat 610 in a universal mode through the second main pull rod 620, and in the vibration test process of the aeroengine, small-range adapting movement can be generated through the second main mounting joint 630, and the connection state of the aeroengine in service can be dynamically simulated better.
It should be noted that, the positions of the auxiliary mounting section 440, the first main mounting section 530 and the second main mounting section 630 corresponding to the bolt holes of the aero-engine are provided with four through holes along the circumferential direction around the axis of the auxiliary mounting section, the first main mounting section and the second main mounting section at intervals, and the through holes are convenient for the bolts to pass through and connect in the corresponding bolt holes of the aero-engine, so that the connection reliability is improved.
Specifically, the first main mount 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 that the first main pull rod 520 can be adjusted in rotation relative to the first main mount 510.
Specifically, the second main mount 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 the rotation adjustment of the second main pull rod 620 relative to the second main mount 610.
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 that the auxiliary pull rod 430 can be conveniently adjusted in a rotating manner relative to the auxiliary mounting seat 420.
As shown in fig. 5, specifically, the auxiliary pull rod 430, the first main pull rod 520 and the second main pull rod 620 are configured in the same structure, the first main pull rod 520 includes a hollow connection portion 521, two ends of the connection portion 521 are slidably provided with a threaded rod portion 522, and the threaded rod portion 522 is locked by a nut 523. By means of the arrangement, the threaded rod 522 can be flexibly adjusted to move to different positions relative to the connecting portion 521, the lengths of the auxiliary pull rod 430, the first main pull rod 520 and the second main pull rod 620 are adjusted, errors caused by manufacturing accuracy can be made up, quick installation and disassembly of the aero-engine can be achieved, the vibration test bench system is applicable to installation of aero-engines with different external dimensions, and the application range of the vibration test bench system of the embodiment is further enlarged.
It can be understood that the outer side walls of the two ends of the connecting portion 521 along the length direction of the connecting portion 521 are provided with external screw thread portions, the external screw thread portions are matched with the nuts 523, and when the threaded rod portion 522 is extended or retracted to a required position relative to the connecting portion 521, the nuts 523 are rotated on the threaded rod portion 522 until the threads are matched with the external screw thread portions, so that the locking can be realized.
It should be noted that, by changing the length of the auxiliary pull rod 430, the length of the first main pull rod 520, and the length of the second main pull rod 620, and changing the angle of the auxiliary pull rod 430 relative to the auxiliary mounting seat 420, the angle of the first main pull rod 520 relative to the first main mounting seat 510, and the angle of the second main pull rod 620 relative to the second main mounting seat 610, the aero-engine can be quickly mounted and dismounted, which eliminates the influence caused by the manufacturing precision error, and is beneficial to reducing the manufacturing cost of the vibration test bench system of the embodiment.
As shown in fig. 2, specifically, an opening 460 is disposed through the upper end of the mounting frame 400 along the Z direction, and the opening 460 is used for the aero-engine to pass through. By means of the arrangement, the aero-engine can penetrate through the opening 460 from top to bottom to enter the mounting frame 400 to be mounted by means of the crane before testing, manpower is saved in the whole mounting and dismounting process, and the testing cost is reduced.
In some embodiments, a first kidney-shaped through hole is formed in the auxiliary mounting seat 420 along the X direction, the first kidney-shaped through hole is used for allowing a shaft portion of a first bolt to pass through, a third threaded hole is formed in a position of the mounting frame 400 corresponding to the first kidney-shaped through hole, and the third threaded hole is matched with the first bolt. The auxiliary mounting seat 420 is detachably connected to the mounting frame 400 through the first bolt and the third threaded hole in a matched mode, so that the connection strength can be ensured, and the dismounting is convenient for overhauling and maintenance. Meanwhile, the first waist-shaped through hole is adopted, so that errors caused by insufficient machining precision of the third threaded hole can be compensated, and the manufacturing cost of the vibration test bench system of the embodiment is reduced.
Specifically, a second kidney-shaped through hole is formed in the first main mounting seat 510 along the Y direction, the second kidney-shaped through hole is used for allowing a rod portion of a second bolt to pass through, a fourth threaded hole is formed in a position of the mounting frame 400 corresponding to the second kidney-shaped through hole, and the fourth threaded hole is matched with the second bolt. The first main mounting seat 510 is detachably connected to the mounting frame 400 through the second bolt and the fourth threaded hole in a matched mode, so that the connection strength can be ensured, and the dismounting is convenient for overhauling and maintenance. Meanwhile, the second waist-shaped through hole is adopted, so that errors caused by insufficient machining precision of the fourth threaded hole can be compensated, and the manufacturing cost of the vibration test bench system of the embodiment is reduced.
Specifically, a third kidney-shaped through hole is formed in the second main mounting seat 610 along the Y direction, the third kidney-shaped through hole is used for allowing a rod portion of a third bolt to pass through, a fifth threaded hole is formed in a position of the mounting frame 400 corresponding to the third kidney-shaped through hole, and the fifth threaded hole is matched with the third bolt. The second main mounting seat 610 is detachably connected to the mounting frame 400 through the mode of matching the third bolt with the fifth threaded hole, so that the connection strength can be ensured, and the dismounting is convenient for overhauling and maintenance. Meanwhile, the third waist-shaped through hole is adopted, so that errors caused by insufficient machining precision of the fifth threaded hole can be compensated, and the manufacturing cost of the vibration test bench system of the embodiment is reduced.
As shown in fig. 1, in some embodiments, the vibration test bench system further includes a bleed air system 700, the bleed air system 700 is detachably connected with a telescopic hose 710 through a bolt, the telescopic hose 710 passes through the through hole 410 and is used for connecting a bleed air outlet of the aeroengine, the telescopic hose 710 communicates the bleed air outlet of the aeroengine with the bleed air system 700 to meet the bleed air requirement, so that the test state of the aeroengine is consistent with the state in use, and the telescopic hose 710 can correspondingly deform to absorb displacement generated in the vibration test of the aeroengine, thereby ensuring the quality of the bleed air.
In some embodiments, the mounting frame 400 is detachably connected to the first vibration sliding table 200, the mounting frame 400 has a first state and a second state assembled with the first vibration sliding table 200, the mounting frame 400 is in the first state, the first main mounting component and the second main mounting component are oppositely arranged along the Y direction (as shown in fig. 1), the mounting frame 400 is in the second state, the first main mounting component and the second main mounting component are oppositely arranged along the X direction, so that after the mounting frame 400 in the first state is detached from the first vibration sliding table 200 and rotated 90 ° around the Z direction and is connected with the first vibration sliding table 200 again, the mounting frame 400 can be switched to the second state, thereby rotating the aeroengine mounted in the mounting frame 400 around the Z direction by 90 ° relative to the first vibration sliding table 200, so that the aeroengine mounted in the mounting frame 400 in the first state is parallel to the X direction, and the aeroengine mounted in the second state is parallel to the Y direction, and the vibration test can be realized on the basis of the single mounting frame 400, and the vibration test system can realize a wide vibration test in the X direction and a wide vibration test range.
As shown in fig. 1 and fig. 4, specifically, two support plates 310 are respectively disposed on two sides of the vibration exciter 300 along the Y direction, the vibration exciter 300 is rotatably connected between the two support plates 310 along the Y direction, the vibration exciter 300 has a third state (as shown in fig. 1) parallel to the X direction and a fourth state parallel to the Z direction, the first vibration slipway 200 is detachably connected with the vibration exciter 300 in the third state, a second vibration slipway 800 is slidably connected at the upper end between the two support plates 310 along the Z direction, the mounting frame 400 is detachably connected with the second vibration slipway 800, and the second vibration slipway 800 is detachably connected with the vibration exciter 300 in the fourth state. The vibration test device is characterized in that when an aeroengine is required to be subjected to an X-direction vibration test, the mounting frame 400 is only required to be assembled with the first vibration slipway 200 in a first state, the aeroengine assembled on the mounting frame 400 is arranged parallel to the X-direction and vibrates along with the first vibration slipway 200 under the action of the excitation force of the vibration exciter 300 arranged along the X-direction, the X-direction vibration test is realized, when the aeroengine is required to be subjected to the Y-direction vibration test, the mounting frame 400 is only required to be assembled with the first vibration slipway 200 in a second state, the aeroengine assembled on the mounting frame 400 is arranged parallel to the Y-direction, and vibrates along with the first vibration slipway 200 under the action of the excitation force of the vibration exciter 300 arranged along the X-direction, when the aeroengine is required to be subjected to the Z-direction vibration test, the vibration exciter 300 is firstly separated from the first vibration slipway 200 with the first vibration slipway by 90 degrees, the second vibration slipway 800 is then connected with the vibration exciter 300 in the fourth state into a whole, and finally the vibration bench is assembled on the mounting frame 400 along with the second vibration slipway under the action of the excitation force of the vibration exciter 300 along the X-direction, and the vibration bench is required to realize the vibration test of the vibration system along the Z-direction, and the vibration test can realize the vibration test along with the vibration system is realized.
Specifically, the second vibration table 800 is detachably connected to the vibration exciter 300 in the fourth state by bolts.
Specifically, the first vibration table 200 is detachably connected to the vibration exciter 300 in the third state by bolts.
In the embodiment, as shown in fig. 1 and 2, four corners of the lower end of the mounting frame 400 are respectively provided with a connecting plate 450, the connecting plate 450 is penetrated with a connecting hole 451 along the Z direction, the connecting hole 451 is used for allowing the rod portion of the first fastening bolt to pass through, the position of the first vibration sliding table 200 corresponding to the connecting hole 451 is provided with a first threaded hole, the first threaded hole is matched with the first fastening bolt, when the mounting frame 400 and the first vibration sliding table 200 are required to be connected into a whole, only the first fastening bolt is required to pass through the connecting hole 451 and be screwed into the first threaded hole, when the mounting frame 400 and the first vibration sliding table 200 are required to be disassembled, only the first fastening bolt is required to be screwed out from the first threaded hole and taken out from the connecting hole 451, and the whole disassembly and assembly process is convenient to operate. In another alternative embodiment, the connection hole 451 is provided through the first vibration table 200 in the Z direction, and the first screw hole is provided in the connection plate 450.
It should be noted that, no matter the mounting frame 400 is in the first state or the second state, the first threaded hole is disposed at the position of the first vibration slipway 200 corresponding to the connection hole 451.
In the embodiment, as shown in fig. 2 and 4, the mounting frame 400 and the second vibration sliding table 800 are connected into a whole in a first state, that is, the aeroengine assembled in the mounting frame 400 is arranged parallel to the X direction, four corners of the lower end of the mounting frame 400 are respectively provided with a connecting plate 450, a connecting hole 451 is formed in the connecting plate 450 in the Z direction, the connecting hole 451 is used for allowing a rod portion of a second fastening bolt to pass through, a second threaded hole is formed in the position, corresponding to the connecting hole 451, of the second vibration sliding table 800, and is matched with the second fastening bolt, when the mounting frame 400 and the second vibration sliding table 800 in the first state are required to be connected into a whole, only the second fastening bolt passes through the connecting hole 451 and is screwed into the second threaded hole, and when the mounting frame 400 and the second vibration sliding table 800 are required to be disassembled, only the second fastening bolt is required to be screwed down from the second threaded hole and taken out from the connecting hole 451, and the disassembly and assembly are convenient. In another alternative embodiment, the connection hole 451 is disposed through the second vibration table 800 along the Z direction, and the second screw hole is disposed in the connection plate 450.
As shown in fig. 4, specifically, the upper ends of the two support plates 310 are connected with a mounting frame 330 through a connecting column 320, four inner walls of the mounting frame 330 are respectively provided with a guide seat 331, the positions of the second vibration sliding table 800 corresponding to each guide seat 331 are respectively provided with a guide slide block 810, and the guide slide blocks 810 are slidably connected to the guide grooves of the guide seats 331 along the Z direction.
As shown in FIG. 1, in some embodiments, the vibration test bench system further comprises a first exhaust pipe 720, wherein the first exhaust pipe 720 is positioned at one side of the mounting frame 400 in the first state, which is away from the vibration exciter 300 in the X direction, the first exhaust pipe 720 is driven to move along the X direction and the Z direction by a two-axis moving assembly, and when the mounting frame 400 provided with the aeroengine is connected to the first vibration sliding table 200 in the first state for performing the X-direction vibration test, the aeroengine is arranged in parallel to the X direction, namely, the first exhaust pipe 720 corresponds to the tail pipe of the aeroengine, so that the first exhaust pipe 720 discharges high-temperature tail gas generated during the test into the atmosphere, thereby being beneficial to keeping the test state of the aeroengine consistent with the state during operation. When the mounting frame 400 provided with the aeroengine is connected to the second vibration sliding table 800 in a first state for Z-direction vibration test, the aeroengine is arranged parallel to the X-direction, the first exhaust barrel 720 and the tail nozzle of the aeroengine are arranged at a larger interval in the X-direction and the Z-direction, and the two-axis moving assembly is used for adjusting the first exhaust barrel 720 to correspondingly move to correspond to the tail nozzle of the aeroengine, so that the first exhaust barrel 720 discharges high-temperature tail gas generated during the Z-direction vibration test into the atmosphere, and the test state of the aeroengine is consistent with the state during working and use. It should be understood that the two-axis moving assembly herein adopts the two-axis moving device mature in the related art, and only needs to implement the function of driving the first exhaust pipe 720 to move along the X-direction and the Z-direction.
Specifically, the second exhaust pipe 730 is disposed at one side of the base 100 along the Y direction, when the mounting frame 400 equipped with the aero-engine is connected to the first vibration sliding table 200 in the second state for performing the Y-direction vibration test, the aero-engine is disposed parallel to the Y direction, that is, the second exhaust pipe 730 corresponds to the tail pipe of the aero-engine, and is used for exhausting the high-temperature tail gas generated during the test into the atmosphere, which is favorable for keeping the test state of the aero-engine consistent with the state during the working and use.
It is apparent that the above examples are given by way of illustration only and are not limiting of the embodiments. Other variations or modifications of the above teachings will be apparent to those of ordinary skill in the art. It is not necessary here nor is it exhaustive of all embodiments. While still being apparent from variations or modifications that may be made by those skilled in the art are within the scope of the invention.
Claims (10)
1. A vibration testing bench system for use in vibration testing an aircraft engine, the vibration testing bench system comprising:
A base (100);
A first vibration slide table (200) slidably disposed on the base (100) along the X-direction;
an exciter (300) which is arranged on the base (100) along the X direction, is connected with the first vibration slipway (200), and generates exciting force for vibration;
The mounting frame (400) is arranged on the first vibration sliding table (200), a through hole (410) is formed in one side of the mounting frame (400) along the X direction, an auxiliary mounting assembly is arranged on the other side of the mounting frame, the auxiliary mounting assembly comprises two auxiliary mounting seats (420) which are arranged at intervals along the Y direction, the two auxiliary mounting seats (420) are all articulated with an auxiliary pull rod (430) in a universal mode, one ends, close to each other, of the two auxiliary pull rods (430) along the Y direction are articulated with an auxiliary mounting joint (440) in a universal mode, and the auxiliary mounting joint (440) is used for being connected with an aeroengine;
One side along Y in mounting bracket (400) is provided with first main installation component, first main installation group includes three around Y to first main mount pad (510) of interval arrangement, every first main mount pad (510) all universal hinge has a first main pull rod (520), and three first main pull rod (520) are towards the one end universal hinge in first main installation festival (530) at center, first main installation festival (530) are used for connecting aeroengine.
2. The vibration test bench system according to claim 1, wherein a second main mounting assembly is further arranged in the mounting frame (400), the second main mounting assembly and the first main mounting assembly are oppositely arranged along the Y direction, the second main mounting assembly comprises two second main mounting seats (610) which are arranged at intervals along the X direction, the two second main mounting seats (610) are all articulated with one second main pull rod (620), one end, close to each other, of each second main pull rod (620) along the X direction is articulated with a second main mounting joint (630) in a universal mode, and the second main mounting joints (630) are used for connecting an aeroengine.
3. The vibration testing bench system according to claim 2, wherein the auxiliary pull rod (430), the first main pull rod (520) and the second main pull rod (620) are arranged in the same structure, the first main pull rod (520) comprises hollow connecting parts (521), two ends of each connecting part (521) are respectively provided with a threaded rod part (522) in a sliding manner, and the threaded rod parts (522) are locked by nuts (523).
4. A vibration testing stand system according to claim 2, further comprising a bleed air system (700), the bleed air system (700) being detachably provided with a telescopic hose (710), the telescopic hose (710) passing through the via (410) and being adapted to be connected to a bleed air outlet of an aeroengine.
5. The vibration testing bench system according to any of claims 2-4, wherein said mounting frame (400) is detachably connected to said first vibration table (200), said mounting frame (400) has a first state and a second state assembled with said first vibration table (200), said mounting frame (400) is in the first state, said first main mounting assembly and said second main mounting assembly are oppositely disposed in the Y-direction, and said mounting frame (400) is in the second state, said first main mounting assembly and said second main mounting assembly are oppositely disposed in the X-direction.
6. The vibration test bench system according to claim 5, wherein two support plates (310) are respectively arranged on two sides of the vibration exciter (300) along the Y direction, the vibration exciter (300) is rotatably connected between the two support plates (310) along the Y direction, the vibration exciter (300) has a third state parallel to the X direction and a fourth state parallel to the Z direction, the first vibration sliding table (200) is detachably connected with the vibration exciter (300) in the third state, a second vibration sliding table (800) is slidably connected to the upper ends between the two support plates (310) along the Z direction, the mounting frame (400) is detachably connected with the second vibration sliding table (800), and the second vibration sliding table (800) is detachably connected with the vibration exciter (300) in the fourth state.
7. The vibration testing bench system according to claim 6, further comprising a first exhaust pipe (720), wherein the first exhaust pipe (720) is located at one side of the mounting frame (400) along the X direction, the first exhaust pipe (720) is driven by the two-axis moving assembly to move along the X direction and the Z direction, and the first exhaust pipe (720) is used for corresponding to a tail pipe of an aeroengine and exhausting high-temperature tail gas generated during testing into the atmosphere.
8. The vibration test bench system according to claim 6, wherein four corners of the lower end of the mounting frame (400) are respectively provided with a connecting plate (450), a connecting hole (451) is formed in the connecting plate (450) in a penetrating manner along the Z direction, the connecting hole (451) is used for a rod portion of a first fastening bolt to penetrate through, a first threaded hole is formed in the position, corresponding to the connecting hole (451), of the first vibration sliding table (200), and the first threaded hole is matched with the first fastening bolt;
And/or, four corners of the lower end of the mounting frame (400) are respectively provided with a connecting plate (450), a connecting hole (451) is formed in the connecting plate (450) in a penetrating mode along the Z direction, the connecting hole (451) is used for allowing the rod part of a second fastening bolt to pass through, a second threaded hole is formed in the position, corresponding to the connecting hole (451), of the second vibration sliding table (800), and the second threaded hole is matched with the second fastening bolt.
9. The vibration testing bench system according to claim 5, wherein a second exhaust pipe (730) is arranged on one side of the base (100) along the Y direction, the mounting frame (400) is in the second state, and the second exhaust pipe (730) corresponds to a tail pipe of an aeroengine and is used for exhausting high-temperature tail gas generated during testing into the atmosphere.
10. A vibration testing bench system according to any of claims 1-4, characterized in that the upper end of the mounting frame (400) is provided with an opening (460) therethrough in the Z-direction, said opening (460) being for the passage of an aeroengine.
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| CN202510091321.5A CN119880314B (en) | 2025-01-20 | 2025-01-20 | Vibration test bench system |
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116046409A (en) * | 2022-12-29 | 2023-05-02 | 彩虹无人机科技有限公司 | An aero-engine test bench with adjustable attitude angle |
| CN219935241U (en) * | 2023-06-25 | 2023-10-31 | 中国航发长江动力有限公司 | Vibration test stand for metal seal ring of aero-engine |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2000356565A (en) * | 1999-06-14 | 2000-12-26 | Ishikawajima Harima Heavy Ind Co Ltd | Vibration test equipment |
| KR100952785B1 (en) * | 2008-06-13 | 2010-04-14 | 현대자동차주식회사 | Engine mount test vibrator and actual simulation device using the same |
| CN108775996B (en) * | 2018-08-01 | 2020-03-27 | 中电科芜湖通用航空产业技术研究院有限公司 | Vibration test method for hybrid power device |
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116046409A (en) * | 2022-12-29 | 2023-05-02 | 彩虹无人机科技有限公司 | An aero-engine test bench with adjustable attitude angle |
| CN219935241U (en) * | 2023-06-25 | 2023-10-31 | 中国航发长江动力有限公司 | Vibration test stand for metal seal ring of aero-engine |
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