Aero-engine hoisting device and aero-engine test run system

Abstract

The invention discloses an aero-engine hoisting device and an aero-engine test run system.The aero-engine hoisting device comprises a crane, two parallel rails used for being installed on a roof of an assembly workshop and parallel to each other, and a transfer rail arranged between the two parallel rails in a striding mode; the pre-assembling track and the transportation track are arranged on the side, away from the other parallel-assembling track, of the parallel-assembling track, the pre-assembling track is used for being arranged above a pre-assembling station, and the transportation track is used for extending to a roof of a test workshop; a moving mechanism is arranged on the transfer rail and used for driving the transfer rail to move in the length direction of the parallel mounting rail to the state of being in butt joint with the preassembling rail or the conveying rail, and the crane is used for hoisting the aero-engine and moving along the preassembling rail, the transfer rail and the conveying rail. According to the aero-engine hoisting device provided by the invention, the aero-engine can be quickly transferred to the test station from any preassembling station, so that quick reloading and transportation are realized, and batch tests are facilitated.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft engine test running, in particular to an aircraft engine hoisting device and an aircraft engine test running system using the aircraft engine hoisting device. Background Art

[0002] At present, for ground tests of aircraft engines, the engine is usually transferred from the assembly workshop to a location near the test bench in the test workshop by a transfer vehicle, and then the engine on the transfer vehicle is lifted to a preset position by a crane, and then the operator installs and fixes the engine to the test bench system mounting frame on the operating platform. However, due to the large size and weight of aircraft engines, it is necessary to adjust the center and deflection angle multiple times before lifting the engine from the transfer vehicle to the appropriate position, and the engine needs to be transferred and transported between the transfer vehicle and the crane, and manual adjustment and positioning are required each time, resulting in extremely low transfer efficiency. When multiple aircraft engines need to be tested in large quantities, the next process can only be carried out after the previous process is completed, and parallel work cannot be achieved. Summary of the invention

[0003] The present invention primarily provides an aircraft engine hoisting device to solve the technical problem of low transportation efficiency of existing aircraft engines during test operations.

[0004] The present invention also provides an aero-engine test system, which adopts the aero-engine hoisting device.

[0005] According to one aspect of the present invention, there is provided an aircraft engine hoisting device, comprising a crane, two parallel mounting rails for mounting on the roof of an assembly workshop, a transfer rail spanning between the two mounting rails, and a pre-mounting rail and a transport rail disposed on a side of the mounting rail away from the other mounting rail, wherein the pre-mounting rail is disposed above a pre-mounting station, and the transport rail is extended to the roof of a test workshop; A moving mechanism is provided on the transfer rail, and the moving mechanism is used to drive the transfer rail to move along the length direction of the assembling rail to a state of docking with the pre-installation rail or docking with the transport rail. The crane is used to lift the aircraft engine on the pre-installation station and drive the aircraft engine to move along the pre-installation rail, the transfer rail and the transport rail.

[0006] Preferably, the transport track is provided with a gap at the position of the silencer door between the assembly workshop and the test workshop, and the aircraft engine lifting device also includes a turning track rotatably arranged at the gap, the turning track is used to rotate to a state aligned with the transport track to fill the gap, and the turning track is also used to rotate to a state offset from the transport track to form an escape space at the gap for closing the silencer door.

[0007] Preferably, the transportation tracks are provided on both of the two parallel tracks, and the transportation tracks on the two parallel tracks are used to extend to different test workshops.

[0008] Preferably, the transportation tracks on the two parallel tracks are arranged opposite to each other, and both ends of the transfer track are used to dock with the transportation tracks on the two parallel tracks simultaneously.

[0009] Preferably, a plurality of pre-installation tracks are arranged at intervals along the length direction on both of the two parallel tracks, and the plurality of pre-installation tracks are used to be correspondingly arranged above a plurality of pre-installation stations one by one.

[0010] Preferably, the pre-installation tracks on the two parallel tracks are arranged in one-to-one correspondence, and both ends of the transfer track are used to dock with the pre-installation tracks on the two parallel tracks simultaneously.

[0011] Preferably, a rail locking mechanism is provided at the end of the transfer track, and the rail locking mechanism is used to lock and fix the transfer track relative to the pre-installation track or to lock and fix the transfer track relative to the transportation track.

[0012] Preferably, the crane includes two lifting assemblies arranged side by side. The lifting assembly includes a drum, a steel wire rope, a pulley and a hook connected in sequence. There are two steel wire ropes, and the two steel wire ropes are arranged at intervals along the axial direction of the pulley and are both wound around the outer periphery of the pulley. The drum is connected to the steel wire rope and is used to drive the steel wire rope to wind or unwind, so as to drive the pulley and the hook to move up and down.

[0013] Preferably, the cross sections of the pre-installation track, the transfer track and the transportation track are all set to an "I"-shaped structure, and a double-hook driving assembly is provided on the crane. The double-hook driving assembly is used to clamp the opposite sides of the "I"-shaped structure and is used to move along the pre-installation track, the transfer track and the transportation track.

[0014] As a second aspect, the present invention also provides an aero-engine test system, including an assembly workshop, a test workshop, and the above-mentioned aero-engine hoisting device. The aero-engine hoisting device is installed on the roof of the assembly workshop and extends to the roof of the test workshop through the transportation track.

[0015] The present invention has the following beneficial effects: The aircraft engine hoisting device provided by the present invention installs a transfer track by spanning two parallel tracks, and a pre-installed track and a transport track are provided on the outer side of the parallel track, so that the transfer track can be stably installed, and the transfer track can be moved along the parallel track with high precision to a state of docking with any pre-installed track or docking with the transport track, so that the crane can move from different pre-installed tracks to the transfer track and move along the transfer track to the transport track, which is convenient for the crane to directly lift the aircraft engines on different pre-installed stations in the assembly workshop to the test station in the test workshop, reduce the use of transfer vehicles, thereby reducing the clamping and positioning processes between the transfer vehicle and the pre-installed station and between the transfer vehicle and the crane, and can be directly transferred from the pre-installed station to the test station through only one lifting operation, so as to realize rapid replacement and transportation. Secondly, multiple pre-installed stations can be operated in parallel by setting multiple pre-installed tracks on the outer side of the parallel track, and multiple aircraft engines can be assembled and prepared for lifting at the same time, effectively improving transportation efficiency and facilitating batch testing of multiple aircraft engines.

[0016] In addition to the above-described purposes, features and advantages, the present invention has other purposes, features and advantages. The present invention will be further described in detail with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] The drawings constituting a part of this application are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the drawings: Figure 1 A schematic diagram of the structure of an aircraft engine hoisting device provided by an embodiment of the present invention; Figure 2 for Figure 1 The reference diagram of the aircraft engine hoisting device in use is shown, showing the state where the change-of-direction track is staggered from the transport track; Figure 3 for Figure 2 The diagram of the changing state of the aircraft engine hoisting device shown shows the state where the direction-changing track is aligned with the transport track; Figure 4 for Figure 3 The diagram of the changing state of the aircraft engine hoisting device shown shows the state of the transfer track docking with the transport track; Figure 5 for Figure 1 A schematic diagram of the structure of a crane in an aircraft engine hoisting device shown; Figure 6 A schematic diagram of the structure of an aircraft engine test system provided by an embodiment of the present invention; Figure 7 for Figure 6 The aircraft engine test system is shown in a side view along the test workshop; Figure 8 The Figure 6 top view of the first - layer auxiliary workshop in the aero - engine test - run system shown; Figure 9 The Figure 6 top view of the second - layer auxiliary workshop in the aero - engine test - run system shown; Figure 10 The Figure 8 structural schematic diagram of the pipeline installation module in the aero - engine test - run system shown; Figure 11 The Figure 9 structural schematic diagram of the wire - threading module in the aero - engine test - run system shown; Figure 12 structural schematic diagram of the sound - proof door in the aero - engine test - run system provided by the embodiment of the present invention; Figure 13 The Figure 12 sectional structure diagram of the sound - proof door at the door - opening position shown; Figure 14 The Figure 13 partial enlarged view of area A in the sound - proof door shown; Figure 15 The Figure 14 structural schematic diagram of the first sealing mechanism in the sound - proof door shown; Figure 16 The Figure 13 partial enlarged view of area B in the sound - proof door shown; Figure 17 The Figure 12 assembly structure diagram of the sound - proof door leaf and the hanging rail in the sound - proof door shown.

[0018] Legend: 1000, aero - engine test - run system; 1, sound - proof door; 11, wall; 111, door - opening; 112, sealing flange; 113, sound - proof cavity; 12, hanging rail; 121, limiting wheel; 13, sound - proof door leaf; 131, door - leaf main body; 132, sealing strip; 14, first sealing mechanism; 141, first sound - proof air cushion; 142, return spring; 143, electromagnet; 144, mounting seat; 145, limiting component; 1451, limiting block; 1452, transmission rod; 15, second sealing mechanism; 151, second sound - proof air cushion; 152, lifting component; 1521, motor; 1522, first crank; 1523, second crank; 1524, screw; 1525, universal joint; 1526, lifting transmission part; 1527, mounting bracket; 16, pressure detection component; 161, safety airbag; 2. Aircraft engine hoisting device; 21. Crane; 211. Hoisting assembly; 2111. Drum; 2112. Steel wire rope; 2113. Pulley; 2114. Hook; 22. Parallel track; 23. Transfer track; 24. Prefabricated track; 25. Transportation track; 251. Notch; 26. Direction-changing track; 3. Assembly workshop; 4. Test workshop; 5. Intake silencing tower; 6. Combustion gas exhaust silencing tower; 7. Propeller flow exhaust silencing room; 8. Auxiliary workshop; 81. Lubricating oil storage room; 82. Electrical equipment room; 821. Process equipment room; 822. Electrical room; 823. Loading cabinet room; 824. Accessory storage room; 825. Air compressor room; 83. Fuel oil room; 84. Dressing and soundproofing room; 841. Dressing room; 842. Soundproofing room; 85. Control room; 851. Instrument and meter room; 852. Operation room; 86. Data analysis room; 87. Washroom; 91. Pipeline installation module; 911. Fixed plate; 912. Pipeline channel; 913. Sound-absorbing material; 92. Wire threading module; 921. Sealing plate; 922. Wire threading hole. Detailed implementation manners

[0019] The following describes the embodiments of the present invention in detail with reference to the accompanying drawings. However, the present invention can be implemented in many different ways defined and covered by the following. Examples of the embodiments are shown in the accompanying drawings, where the same or similar reference numerals represent the same or similar elements or elements with the same or similar functions from beginning to end. The embodiments described below by referring to the accompanying drawings are exemplary and are only used to explain the present invention, and cannot be construed as a limitation to the present invention.

[0020] Those skilled in the art of the present technology can understand that unless specifically stated, the term "including" used in the specification of the present invention means the presence of the described features, integers, steps, operations, components and / or assemblies, but does not exclude the presence or addition of one or more other features, integers, steps, operations, components, assemblies and / or their combinations. It should be understood that when we say that a component is "connected" to another component, it can be directly connected to other components or connected through intermediate components. The term "and / or" used here includes all or any unit and all combinations of one or more related listed items. The terms "first" and "second" etc. in the specification and claims of the present invention are used to distinguish different objects, rather than to describe a specific order.

[0021] Figures 1 to 5The invention collectively shows an aircraft engine lifting device provided in an embodiment of the present invention, which is used to realize the rapid transfer of aircraft engines between a pre-installation station and a test station, and can realize the parallel operation of multiple pre-installation stations, effectively improving the transfer efficiency and test efficiency of aircraft engines, reducing manual operations, and improving safety.

[0022] Please combine Figure 1 and Figure 2 The aircraft engine hoisting device 2 includes a crane 21, two parallel parallel rails 22 for installation on the roof of the assembly workshop 3, a transfer rail 23 spanning between the two parallel rails 22, and a pre-installation rail 24 and a transportation rail 25 arranged on the side of the parallel rail 22 away from the other parallel rail 22. The pre-installation rail 24 is used to be arranged above the pre-installation station, and the transportation rail 25 is used to extend to the roof of the test workshop 4. A moving mechanism (not shown in the figure, the same below) is provided on the transfer rail 23, and the moving mechanism is used to drive the transfer rail 23 to move along the length direction of the parallel rail 22 to a state of docking with the pre-installation rail 24 or docking with the transportation rail 25. The crane 21 is used to hoist the aircraft engine on the pre-installation station and drive the aircraft engine to move along the pre-installation rail 24, the transfer rail 23 and the transportation rail 25.

[0023] Specifically, the aircraft engine hoisting device 2 installs the transfer rail 23 by spanning two parallel rails 22, and a pre-installed rail 24 and a transport rail 25 are provided on the outer side of the parallel rail 22 (the side away from the transfer rail 23), so that the transfer rail 23 can be stably installed while being able to move along the parallel rail 22 to a state of docking with any pre-installed rail 24 or docking with the transport rail 25 with high precision, so that the crane 21 can move into different pre-installed rails 24 to hoist the corresponding The aircraft engines on the pre-installation stations can also be moved from different pre-installation rails 24 to the transfer rails 23 and moved along the transfer rails 23 to the transport rails 25, so that the crane 21 can directly lift the aircraft engines on different pre-installation stations in the assembly workshop 3 to the test stations in the test workshop 4, reducing the use of transfer vehicles, thereby reducing the clamping and positioning processes between the transfer vehicle and the pre-installation station and between the transfer vehicle and the crane. Only one lifting operation is required to directly transfer from the pre-installation station to the test station, realizing rapid replacement and transportation. Secondly, multiple pre-installation rails 24 can be set on the outside of the parallel installation rails 22 to realize parallel operation of multiple pre-installation stations, and multiple aircraft engines can be assembled and prepared for lifting at the same time, effectively improving transportation efficiency and facilitating batch testing of multiple aircraft engines.

[0024] Furthermore, the moving mechanism includes a first roller arranged on both ends of the transfer rail 23, a first moving motor connected to the first roller and used to drive the first roller to roll, the first roller is embedded in a first roller groove preset in the assembling rail 22, and the first moving motor drives the first roller to roll along the first roller groove, thereby driving the transfer rail 23 to move along the assembling rail 22.

[0025] Please combine Figure 2 and Figure 3 The transport track 25 is provided with a gap 251 at the position of the muffler door 1 between the assembly workshop 3 and the test workshop 4. The aircraft engine hoisting device 2 also includes a turning track 26 rotatably arranged at the gap 251. The turning track 26 is used to rotate to a state aligned with the transport track 25 to fill the gap 251 (at Figure 3 ), the direction-changing track 26 is also used to rotate to a state where it is staggered from the transport track 25 to form an escape space at the gap 251 for the silencing door 1 to close (in Figure 2 ).

[0026] Specifically, the changing track 26 is arranged to rotate along a horizontal plane, and a changing motor (not shown in the figure, the same below) for driving the changing track 26 to rotate is provided on the changing track 26. When the changing motor drives the changing track 26 to rotate to a state aligned with the transport track 25, the gap 251 can be filled, so that the crane 21 can move between the assembly workshop 3 and the test workshop 4 along the transport track 25; and when the test workshop 4 is conducting a test, the changing motor can drive the changing track 26 to rotate to a state offset from the transport track 25, so that an escape space for the silencing door 1 to close can be formed at the gap 251, so that the silencing door 1 can be smoothly closed and seal the test workshop 4, which is conducive to achieving the silencing and noise reduction effect of the test workshop 4.

[0027] Preferably, the transport rails 25 are provided on both of the two parallel installation rails 22, and the transport rails 25 on the two parallel installation rails 22 are used to extend to different test workshops 4. That is, the aircraft engine hoisting device 2 can flexibly transport aircraft engines on multiple pre-installation stations to different test workshops 4, respectively, to achieve parallel operation of at least two test workshops 4, and further improve the test efficiency.

[0028] like Figure 4As shown, the transport tracks 25 on the two parallel tracks 22 are arranged opposite to each other, and both ends of the transfer track 23 are used to dock with the transport tracks 25 on the two parallel tracks 22 simultaneously. Since the transport tracks 25 on the two parallel tracks 22 are arranged opposite to each other, only one positioning position needs to be set to enable the transfer track 23 to dock with the two transport tracks 25 simultaneously, thereby reducing the docking and positioning structures on the transfer track 23, simplifying the aero-engine hoisting device 2, and making the overall structure simpler and more efficient.

[0029] Preferably, a plurality of pre-installation tracks 24 are arranged at intervals along the length direction on both of the two parallel tracks 22, and the plurality of pre-installation tracks 24 are used to be respectively arranged above a plurality of pre-installation workstations one by one. By arranging a plurality of pre-installation tracks 24 on the two parallel tracks 22 respectively, it is convenient to arrange more pre-installation workstations to meet the transfer requirements of more pre-installation workstations. It should be understood that each pre-installation workstation can be used for separately assembling an aero-engine, or different assembly processes of the aero-engine can be carried out through a plurality of pre-installation workstations respectively. The hoisting device 2 of the aero-engine can enable the crane 21 to move flexibly between a plurality of pre-installation workstations to meet different usage requirements, and has strong applicability.

[0030] As Figure 2 shown, the pre-installation tracks 24 on the two parallel tracks 22 are arranged in one-to-one correspondence, and both ends of the transfer track 23 are used to dock with the pre-installation tracks 24 on the two parallel tracks 22 simultaneously. Similarly, since the pre-installation tracks 24 on the two parallel tracks 22 are arranged opposite to each other, only one positioning position needs to be set to enable the transfer track 23 to dock with the two pre-installation tracks 24 simultaneously, thereby reducing the docking and positioning structures on the transfer track 23, simplifying the aero-engine hoisting device 2, and making the overall structure simpler and more efficient.

[0031] Preferably, a track locking mechanism (not shown in the figure, the same below) is provided at the end of the transfer track 23, and the track locking mechanism is used to lock and fix the transfer track 23 relative to the pre-installation track 24 or to lock and fix the transfer track 23 relative to the transport track 25. The positioning and fixing of the transfer track 23 are realized through the track locking mechanism to ensure that the transfer track 23 stably docks with the pre-installation track 24 or the transport track 25, so that the crane 21 can move smoothly between the transfer track 23 and the pre-installation track 24 or between the transfer track 23 and the transport track 25.

[0032] Further, the track locking mechanism includes a telescopic assembly and a track locking pin connected to the telescopic assembly. The telescopic assembly can specifically adopt a pneumatic rod and a hydraulic rod, or include a motor and a linear transmission component connected to the output shaft of the motor. The telescopic assembly is connected to the track locking pin and is used to drive the track locking pin to telescopically move, so that the track locking pin extends and inserts into a positioning hole preset on the pre-installed track 24 or the transportation track 25, realizing the locking and fixing of the transfer track 23.

[0033] As Figure 5 shown, the crane 21 includes two lifting assemblies 211 arranged side by side. The lifting assembly 211 includes a drum 2111, a steel wire rope 2112, a pulley 2113, and a hook 2114 connected in sequence. There are two steel wire ropes 2112, and the two steel wire ropes 2112 are arranged at intervals along the axial direction of the pulley 2113 and are both wound around the outer periphery of the pulley 2113. The drum 2111 is connected to the steel wire rope 2112 and is used to drive the steel wire rope 2112 to wind or unwind, thereby driving the pulley 2113 and the hook 2114 to move up and down.

[0034] Since the lifting assembly 211 includes two steel wire ropes 2112 arranged at intervals along the axial direction of the pulley 2113, and the steel wire rope 2112 is wound around the outer periphery of the pulley 2113, so that the two ends of the steel wire rope 2112 are respectively arranged on opposite sides of the pulley 2113, thereby enabling the two steel wire ropes 2112 to jointly form four pulling points, and the steel wire rope 2112 is arranged around the hook 2114, effectively ensuring the stability of the hook 2114 in the three-dimensional direction, capable of preventing the hook 2114 from tilting in any direction, and compared with the conventional hook structure, it can effectively ensure the stable transportation of the lifted object and prevent swinging during the lifting process. Secondly, since the crane 21 includes two lifting assemblies 211 arranged side by side, the opposite sides of the aeroengine are respectively lifted by the hooks 2114 on the two lifting assemblies 211, so that the position of the aeroengine can be flexibly adjusted by independently controlling the lifting height of any one of the hooks 2114, ensuring that the aeroengine is in a horizontal state during lifting and further improving the lifting stability.

[0035] Preferably, the cross-sections of the pre-installed track 24, the transfer track 23, and the transportation track 25 are all set to an "I"-shaped structure. The drum 2111 is provided with a double-hook driving assembly, and the double-hook driving assembly is used to clamp the opposite sides of the "I"-shaped structure and is used to move along the pre-installed track 24, the transfer track 23, and the transportation track 25.

[0036] Specifically, the pre-installed rail 24, the transfer rail 23 and the transport rail 25 are all made of I-beams, with a simple and efficient structure. The double-hook drive assembly includes two relatively arranged inverted "L"-shaped hooks, which are respectively engaged with the limited two sides of the I-beam by the two inverted "L"-shaped hooks, thereby realizing multi-directional limiting of the crane 21 and improving stability.

[0037] Furthermore, a second roller and a second movable motor connected to the second roller are provided at the bottom of the inverted "L"-shaped hook, and the second roller abuts against the upper surface of the flange of the I-beam. The second movable motor drives the second roller to roll along the I-beam, thereby driving the crane 21 to move along the pre-installed rail 24, the transfer rail 23 and the transport rail 25.

[0038] like Figure 6 As shown, as a second aspect, the present invention further provides an aircraft engine test system 1000, comprising an assembly workshop 3 and a test workshop 4, and the above-mentioned aircraft engine hoisting device 2, wherein the aircraft engine hoisting device 2 is installed on the roof of the assembly workshop 3 and extends to the roof of the test workshop 4 through the transport track 25. The engine transfer operation between the assembly workshop 3 and the test workshop 4 is realized by the aircraft engine hoisting device 2, and the aircraft engines on different pre-installation stations of the assembly workshop 3 can be directly hoisted to the test station in the test workshop 4, reducing the use of transfer vehicles, and can be directly transferred from the pre-installation station to the test station through only one hoisting operation, realizing rapid replacement and transportation, and can also realize parallel operation of multiple pre-installation stations, and can simultaneously carry out assembly and hoisting preparation work of multiple aircraft engines, effectively improving transportation efficiency, and facilitating batch testing.

[0039] Please combine Figure 6 and Figure 7 The aircraft engine test system 1000 also includes an air intake silencer 5, a gas exhaust silencer 6 and a paddle flow exhaust silencer room 7. The test workshop 4 is used to test the aircraft engine. The air intake silencer 5 is arranged at the front end of the test workshop 4 along the air flow direction of the aircraft engine. The gas exhaust silencer 6 and the paddle flow exhaust silencer room 7 are arranged at the rear end of the test workshop 4 in sequence along the air flow direction of the aircraft engine.

[0040] Furthermore, the intake silencing tower 5 extends vertically upward and its intake end is arranged vertically downward. The gas exhaust silencing tower 6 is arranged between the test workshop 4 and the propeller flow exhaust silencing chamber 7. The gas exhaust silencing tower 6 extends vertically upward and its exhaust end is arranged vertically upward. The exhaust end of the propeller flow exhaust silencing chamber 7 extends horizontally along the length direction of the test workshop 4. The intake silencing tower 5 is used to introduce air into the test workshop 4. The gas exhaust silencing tower 6 is used to exhaust the gas generated by the aero-engine in the test workshop 4. The propeller flow exhaust silencing chamber 7 is used to exhaust the propeller flow exhaust gas generated by the aero-engine in the test workshop 4. Multi-stage sound absorption structures and rectifying structures are provided in the intake silencing tower 5, the gas exhaust silencing tower 6 and the propeller flow exhaust silencing chamber 7.

[0041] In the aero-engine test run system 1000, the intake end of the intake silencing tower 5 intakes air vertically downward, the exhaust end of the gas exhaust silencing tower 6 exhausts gas vertically upward, and the exhaust end of the propeller flow exhaust silencing chamber 7 exhausts gas horizontally, realizing a structural layout of vertical intake and horizontal exhaust. While meeting the intake requirements and exhaust requirements of the aero-engine, the overall layout is more reasonable and compact, occupies less space, can adapt to different sites, has stronger applicability. And because the gas exhaust silencing tower 6 and the propeller flow exhaust silencing chamber 7 are independently arranged, the gas can be better exhausted, effectively avoiding the problem of gas backflow during the test, and improving the test safety and test effect. Secondly, since multi-stage sound absorption structures and rectifying structures are provided in the intake silencing tower 5, the gas exhaust silencing tower 6 and the propeller flow exhaust silencing chamber 7, hierarchical sound absorption and rectification can be realized, the exhaust effect is better, and the test noise can be prevented from spreading outward, ensuring the test safety.

[0042] As Figure 6 shown, the aero-engine test run system 1000 further includes an auxiliary workshop 8. The assembly workshop 3 and the auxiliary workshop 8 are arranged in a straight line and are located on one side of the test workshop 4. The assembly workshop 3 is used for assembling aero-engines. The assembly workshop 3 is located at the intake end of the test workshop 4. The auxiliary workshop 8 is located at the exhaust end of the test workshop 4. The auxiliary workshop 8 has two floors in the height direction. The first-floor auxiliary workshop includes a lubricating oil storage room 81, an electrical equipment room 82 and a fuel room 83 arranged in sequence along the direction away from the assembly workshop 3. The second-floor auxiliary workshop includes a dressing and sound insulation room 84, a control room 85 and a data analysis room 86 arranged in sequence along the direction away from the assembly workshop 3. The control room 85 is located directly above the electrical equipment room 82 and is used to control the electrical equipment in the electrical equipment room 82.

[0043] Specifically, the lubricating oil storage room 81 is used for storing lubricating oil, and the fuel oil room 83 is used for storing fuel oil. Arranging the lubricating oil storage room 81 near the engine installation position of the test workshop 4 is beneficial for subsequent lubricating oil filling, preparation of various test equipment, and connection of pipelines. Placing the fuel oil room 83 at a position far from the engine installation position of the test workshop 4 can improve safety and avoid direct contact between fuel oil and high temperature. Secondly, since the auxiliary workshop 8 has two floors in the height direction, the dressing and sound insulation room 84, control room 85, and data analysis room 86 that do not require large equipment are sequentially arranged on the second floor. This can not only efficiently utilize the longitudinal space, making the overall layout more reasonable and compact, but also facilitate the pipeline connection and installation between the control room 85 and the electrical equipment room 82, enabling the control room 85 to quickly control the electrical equipment in the electrical equipment room 82. Moreover, the dressing and sound insulation room 84 is used to insulate and reduce noise for the control room 85 and data analysis room 86. While facilitating entry and exit for dressing in the control room 85 and data analysis room 86, it can effectively reduce the noise impact of the test process in the test workshop 4 on the control room 85 and data analysis room 86.

[0044] Preferably, the electrical equipment room 82 includes a process equipment room 821, an electrical room 822, and a loading cabinet room 823 arranged in sequence along the direction away from the assembly workshop 3. The process equipment room 821 is used for arranging an oil supply station, an air system, and a circulating cooling water system. The oil station specifically includes a lifting platform oil station, a hydraulic loading oil station, an oil seal oil station, etc. Since the process equipment room 821 is relatively close to the test workshop 4, it is convenient for the oil station, air system, and circulating cooling water system to be connected to the test workshop 4. Secondly, the electrical room 822 is used for arranging electrical control cabinets and power cabinets, and the loading cabinet room 823 is used for arranging electrical loading cabinets. The loading cabinets are independently arranged to reduce the impact of their heat dissipation operations on other electrical equipment. The adjacent arrangement of the electrical room 822 and the loading cabinet room 823 facilitates unified management.

[0045] Furthermore, the electrical equipment room 82 further includes an accessory storage room 824 and an air compressor room 825 arranged in sequence at the rear end of the loading cabinet room 823 along the direction away from the assembly workshop 3. The accessory storage room 824 is used for storing accessories, and the air compressor room 825 is used for installing air compressors. Different equipment is separated by multiple workshops to avoid mutual influence.

[0046] Furthermore, the dressing and sound insulation room 84 includes a dressing room 841 and a sound insulation room 842 arranged in sequence along the direction away from the assembly workshop 3, achieving double sound insulation for the control room 85 through the dressing room 841 and the sound insulation room 842.

[0047] Further, the control room 85 includes an instrument room 851 and an operation room 852 arranged in sequence along the direction away from the assembly workshop 3. The instrument room 851 is used for arranging instruments and meters, and the operation room 852 is used for operating the instruments and meters. Separating the instrument room 851 and the operation room 852 can avoid the operation room 852 from being too messy, and at the same time, further sound insulation can be achieved for the operation room 852 through the instrument room 851.

[0048] Further, a washroom 87 is also provided on one side of the data analysis room 86 away from the control room 85 to facilitate the testers in the control room 85 and the data analysis room 86.

[0049] Please refer to Figure 8 and Figure 10 , on the wall between the electrical equipment room 82 and the test workshop 4, there is a pipeline installation module 91. The pipeline installation module 91 includes two fixing plates 911 for fitting the opposite sides of the wall, a plurality of pipeline channels 912 arranged between the two fixing plates 911, and sound insulation materials 913 filled around the pipeline channels 912. The pipeline channels 912 are provided with connection ports on the fixing plates 911 for docking equipment pipelines. Among them, at least part of the pipeline channels 912 have different diameters to meet different pipeline installations. By docking the equipment pipelines through the pipeline channels 912, while facilitating the transportation of substances such as lubricating oil, fuel oil, hydraulic oil, and coolant, a good sound insulation and noise reduction effect can also be achieved, avoiding the noise in the test workshop 4 from spreading outward along the pipeline installation position.

[0050] Please refer to Figure 9 and Figure 11 , on the wall between the control room 85 and the test workshop 4, there is a wire threading module 92. The wire threading module 92 includes a plugging board 921 embedded in the wall, a plurality of wire threading holes 922 arranged on the plugging board 921, and a sealing plug for detachably plugging the wire threading holes 922. At least part of the wire threading holes 922 have different diameters. Wiring personnel can remove the sealing plugs at the corresponding positions according to requirements, and then pass the cables in the test workshop 4 through the corresponding wire threading holes 922 to the control room 85. This structure not only ensures the sealing of the test workshop 4, but also reduces the physical vibration of the cables during transmission, ensures the constant temperature and humidity environment of the control room 85, thereby increasing the accuracy and precision of data transmission.

[0051] Preferably, a constant temperature and humidity system (not shown in the figure, the same below) for adjusting temperature and humidity is provided in both the control room 85 and the data analysis room 86. The temperature and humidity of the control room 85 and the data analysis room 86 are adjusted through the constant temperature and humidity system to ensure that relevant instruments and meters are maintained in a suitable working environment and avoid being affected by the high temperature in the test workshop 4.

[0052] Please refer to Figures 12 to 17 , the aero-engine test system 1000 further includes a soundproof door 1. The soundproof door 1 is provided between the test workshop 4 and the assembly workshop 3. Through structural optimization, it can achieve a larger opening and closing area and has a good soundproof effect, meeting the requirements for the entry and exit of large equipment and test sound insulation. It can be applied to the aero-engine test system to achieve sound insulation and noise reduction between the assembly workshop 3 and the test workshop 4.

[0053] Please refer to Figure 12 and Figure 13 , the soundproof door 1 includes a wall body 11, a hanging rail 12, a soundproof door leaf 13 and a translation mechanism (not shown in the figure, the same below). A door opening 111 adapted to the soundproof door leaf 13 is provided on the wall body 11. The hanging rail 12 is installed on the wall body 11. The hanging rail 12 is located above the door opening 111 and extends horizontally to one side of the door opening 111. The soundproof door leaf 13 is slidably installed on the hanging rail 12. The translation mechanism is connected to the soundproof door leaf 13 and is used to drive the soundproof door leaf 13 to slide open and close along the hanging rail 12. Further, the translation mechanism may specifically include a translation motor provided on the wall body 11 and a driving wheel connected to the output shaft of the translation motor. The driving wheel abuts against the soundproof door leaf 13 to drive the rolling motion of the driving wheel through the translation motor to drive the soundproof door leaf 13 to translate. In other embodiments, the driving wheel may also be set as a gear, and a rack meshing with the gear is provided on the soundproof door leaf 13. The gear is driven by the translation motor to rotate to drive the rack to translate, which can achieve a higher-precision translation driving action.

[0054] As Figure 14As shown, on the side of the wall 11 facing the soundproof door leaf 13, there is a sealing flange 112. The sealing flange 112 is arranged above the door opening 111 and extends in the direction towards the soundproof door leaf 13. On the top surface of the sealing flange 112, there is a first sealing mechanism 14. The soundproof door leaf 13 includes a door leaf main body 131 and a sealing strip 132. The first end of the sealing strip 132 is fixedly connected to the door leaf main body 131 in the horizontal direction. The second end of the sealing strip 132 is inserted vertically into the first sealing mechanism 14. The middle position of the sealing strip 132 is set as an arc structure or a right-angle structure so that its first end and second end are arranged in different directions. The first sealing mechanism 14 is used to clamp the sealing strip 132 after the soundproof door leaf 13 is closed, thereby sealing the gap between the soundproof door leaf 13 and the wall 11. The first sealing mechanism 14 is also used to release the sealing strip 132 when the soundproof door leaf 13 moves, so as not to affect the opening and closing movement of the soundproof door leaf 13.

[0055] Specifically, the soundproof door 1 adopts a sliding door structure and is driven to open and close by the translation mechanism, avoiding the situation that the soundproof door is too large in volume and too heavy to be manually opened and closed, so as to meet the sealing requirements of large-sized door openings and adapt to the scenario of large-sized equipment entering and exiting. And it adopts a hanging rail design, which can avoid the problems that the ground is uneven and there are protrusions, which are not conducive to the entry and exit of large-sized equipment compared with the ground rail structure. More importantly, there is a first sealing mechanism 14 on the wall 11, which can clamp the sealing strip 132 on the soundproof door leaf 13 after the soundproof door leaf 13 is closed, thereby sealing the gap between the soundproof door leaf 13 and the wall 11, effectively solving the problem of poor sealing effect of conventional sliding doors, increasing the area of the door opening 111 while ensuring the sound insulation and noise reduction effect, and being able to meet the transfer requirements and noise reduction requirements of large-scale aero-engine tests at the same time.

[0056] Please combine Figure 15 As shown, the first sealing mechanism 14 includes two first soundproof air cushions 141, a return spring 142 elastically pressed between the two first soundproof air cushions 141, and an electromagnet 143 arranged on the first soundproof air cushion 141. Specifically, the two first soundproof air cushions 141 are respectively arranged on the opposite sides of the second end of the sealing strip 132, that is, the second end of the sealing strip 132 is inserted vertically between the two first soundproof air cushions 141. The return spring 142 is used to spring the two first soundproof air cushions 141 to a preset spacing state to release the sealing strip 132. The electromagnet 143 is used to attract the two first soundproof air cushions 141 in the energized state to drive the two first soundproof air cushions 141 to clamp the sealing strip 132.

[0057] The working principle of the first sealing mechanism 14 is as follows: when the electromagnet 143 is in a power-off state, it has no magnetic force. At this time, the two first sound-absorbing air cushions 141 can be bounced open to a preset spacing state by the elastic force of the return spring 142, so that the first sound-absorbing air cushions 141 are separated from the sealing strip 132, enabling the sound-absorbing door leaf 13 to open and close smoothly; when the electromagnet 143 is in a powered-on state, the magnetic force generated by the electromagnet 143 can overcome the elastic force of the return spring 142 and suck the two first sound-absorbing air cushions 141 together, so as to clamp the sealing strip 132 through the two first sound-absorbing air cushions 141, achieving efficient sealing of the gap between the sound-absorbing door leaf 13 and the wall 11. The sealing structure is simple and efficient, and the air cushion structure is used for sealing, which can ensure that the first sound-absorbing air cushion 141 closely fits the sealing strip 132, and the air cavity in the first sound-absorbing air cushion 141 can be used for sound absorption, effectively improving the sound absorption effect.

[0058] Preferably, the first sealing mechanism 14 further includes a mounting seat 144 disposed between the two first sound-absorbing air cushions 141, and two limiting components 145 respectively disposed at both ends of the mounting seat 144. The limiting component 145 includes a limiting block 1451 and a transmission rod 1452 connected to the limiting block 1451. The end of the transmission rod 1452 away from the limiting block 1451 passes through a preset limiting hole on the mounting seat 144 and is connected to the first sound-absorbing air cushion 141, and the transmission rods 1452 of the two limiting components 145 are connected to the two first sound-absorbing air cushions 141 in a one-to-one correspondence. The return spring 142 abuts against the side of the limiting block 1451 away from the transmission rod 1452. The limiting block 1451 is used to move to a state of abutting against the inner wall of the mounting seat 144 under the elastic force of the return spring 142 and limit the maximum moving stroke of the first sound-absorbing air cushion 141.

[0059] The limiting component 145 limits the maximum moving stroke of the first sound-absorbing air cushion 141 through the cooperation of the limiting block 1451 and the mounting seat 144, preventing the first sound-absorbing air cushion 141 from loosening. It can also guide the moving direction of the first sound-absorbing air cushion 141 through the cooperation of the limiting block 1451 and the preset limiting hole on the mounting seat 144, effectively improving the stability of the first sound-absorbing air cushion 141 and preventing the first sound-absorbing air cushion 141 from deflecting and affecting the clamping and sealing effect.

[0060] Preferably, the first sound-absorbing air cushion 141 is provided with the electromagnets 143 on both the upper and lower sides of the return spring 142, so as to simultaneously attract the first sound-absorbing air cushion 141 through the electromagnets 143 on both sides, ensuring that the first sound-absorbing air cushion 141 is evenly stressed and capable of achieving a stable translational movement. In this embodiment, the electromagnets 143 are provided at corresponding positions on the two first sound-absorbing air cushions 141 to enhance the magnetic attraction effect and ensure the sealing strength; in other embodiments, the electromagnet 143 may also be provided only on one of the first sound-absorbing air cushions 141, and a metal part for the electromagnet 143 to magnetically attract is provided on the other first sound-absorbing air cushion 141, and the two first sound-absorbing air cushions 141 can also be controlled to be attracted by the electromagnet 143.

[0061] As Figure 16 shown, the sound-insulating door 1 further includes a second sealing mechanism 15 provided at the bottom of the sound-insulating door leaf 13. The second sealing mechanism 15 includes a second sound-absorbing air cushion 151 and a lifting assembly 152. The second sound-absorbing air cushion 151 is slidably connected to the bottom of the sound-insulating door leaf 13 in the vertical direction. The lifting assembly 152 is connected to the second sound-absorbing air cushion 151 and is used to drive the second sound-absorbing air cushion 151 to lift and move, so as to control the second sound-absorbing air cushion 151 to lift and move to a state of abutting against the ground or separating from the ground.

[0062] Specifically, after the sound-insulating door leaf 13 is closed, the lifting assembly 152 can be used to drive the second sound-absorbing air cushion 151 to descend and move to a state of tightly pressing against the ground, so as to seal the bottom gap of the sound-insulating door leaf 13. Sealing through the air cushion structure can ensure that the second sound-absorbing air cushion 151 closely adheres to the ground, and the air cavity in the second sound-absorbing air cushion 151 can also be used for sound absorption, effectively improving the sound absorption effect at the bottom position, thereby further enhancing the sound insulation and noise reduction effect of the sound-insulating door 1.

[0063] Preferably, the lifting assembly 152 includes a motor 1521 provided on the wall 11, a first crank 1522 connected to the output shaft of the motor 1521, a second crank 1523 rotatably provided on the sound-insulating door leaf 13 in the horizontal direction, a screw rod 1524 rotatably installed in the sound-insulating door leaf 13 in the vertical direction, a universal joint 1525 provided between the second crank 1523 and the screw rod 1524 and used to transmit the rotational power of the second crank 1523 to the screw rod 1524, and a lifting transmission member 1526 connected to the second sound-absorbing air cushion 151. The lifting transmission member 1526 is provided with a threaded hole threadedly connected to the screw rod 1524. The first crank 1522 is used to abut against the second crank 1523 after the sound-insulating door leaf 13 is closed and transmit the rotational power of the motor 1521 to the second crank 1523.

[0064] Specifically, the first crank 1522 and the second crank 1523 are both provided with lapping portions at a preset included angle. When the soundproof door leaf 13 is in the open state, the second crank 1523 moves with the soundproof door leaf 13 to a state of disengaging from the first crank 1522; when the soundproof door leaf 13 is in the closed state, the second crank 1523 moves with the soundproof door leaf 13 to the working position of the first crank 1522. At this time, by driving the first crank 1522 to rotate through the motor 1521, the lapping portion on the first crank 1522 can be rotated to a state of lapping the second crank 1523 and drive the second crank 1523 to rotate. Thus, through the cooperation of the second crank 1523 and the universal joint 1525, reverse transmission is achieved and the screw 1524 is driven to rotate. Furthermore, through thread cooperation, the lifting transmission member 1526 is driven to move up and down, and the second soundproof air cushion 151 is driven to move up and down by the lifting transmission member 1526. Since the motor 1521 is arranged separately from the soundproof door leaf 13, the load of the soundproof door leaf 13 can be reduced, the opening installation structure on the soundproof door leaf 13 can be reduced, and the smooth movement and soundproof effect of the soundproof door leaf 13 can be ensured.

[0065] Further, there are two second soundproof air cushions 151, and the two second soundproof air cushions 151 are respectively arranged on the opposite sides of the soundproof door leaf 13. The two ends of the lifting transmission member 1526 respectively penetrate through the opposite sides of the soundproof door leaf 13 and are correspondingly connected to the two second soundproof air cushions 151 one by one. And the second soundproof air cushion 151 extends upward to cover the through-hole positions of the lifting transmission member 1526 on the soundproof door leaf 13. By synchronously driving the two second soundproof air cushions 151 to move up and down through the lifting transmission member 1526, the two second soundproof air cushions 151 can jointly clamp the soundproof door leaf 13 to achieve a double-layer sealing effect, and the openings on the soundproof door leaf 13 can also be covered by the second soundproof air cushions 151 to ensure the soundproof effect.

[0066] Further, the lifting assembly 152 further includes a mounting bracket 1527 arranged in the inner cavity of the soundproof door leaf 13. The mounting bracket 1527 is arranged above the screw 1524, and the screw 1524 is rotatably mounted on the mounting bracket 1527. By installing and limiting the screw 1524 through the mounting bracket 1527, the stability of the screw 1524 is improved.

[0067] Please combine Figure 12 and Figure 17, there are two walls 11. The two walls 11 are arranged at intervals and enclose to form a sound insulation cavity 113. The door openings 111 and the hanging rails 12 are provided on both walls 11. There are two sound insulation door leaves 13. The two sound insulation door leaves 13 are respectively arranged on the hanging rails 12 of the two walls 11. The two sound insulation door leaves 13 are used to simultaneously block the door openings 111 on the two walls 11 and seal the sound insulation cavity when closed. The sound insulation door 1 forms a cavity structure through two walls 11 arranged at intervals. After the two sound insulation door leaves 13 are closed simultaneously, the sound insulation cavity 113 can be in a completely sealed state, effectively improving the sound insulation effect. It has been detected that the 160dB noise generated in the test workshop of the aero-engine test system can be reduced to 70dB.

[0068] Preferably, the door leaf body 131 sequentially includes a first sound insulation board, a damping layer, a steel frame, sound insulation cotton, a composite sound insulation module, and a second sound insulation board from the outside to the inside. By sequentially arranging multiple layers of sound insulation structures, the noise can be greatly reduced, and the multiple layers of sound insulation structures are supported by the steel frame, which can ensure the structural strength of the door leaf body 131 and prevent deformation from affecting the sealing effect.

[0069] Preferably, an infrared detection component (not shown in the figure, the same below) and / or a pressure detection component 16 are provided on the sound insulation door leaf 13. The infrared detection component includes an infrared sensor, and the infrared sensor is used to detect whether there are obstacles in the closing direction of the sound insulation door leaf 13 through infrared signals. The pressure detection component 16 includes a safety airbag 161 and a pressure sensor arranged in the safety airbag 161. The safety airbag 161 is arranged on the side wall of the sound insulation door leaf 13, and the pressure sensor is used to detect the air pressure change of the safety airbag 161 to judge whether the safety airbag 161 touches an obstacle.

[0070] In this embodiment, both the infrared detection component and the pressure detection component 16 are provided on the sound insulation door leaf 13. By double anti-collision detection, it is judged whether there are obstacles in the closing direction of the sound insulation door leaf 13, effectively improving the safety.

[0071] Furthermore, a limiting wheel 121 is provided on the hanging rail 12. The limiting wheel 121 is used to abut against the sound insulation door leaf 13 and limit the opening and closing movement stroke of the sound insulation door leaf 13 to ensure the high-precision opening and closing of the sound insulation door leaf 13.

[0072] The above are only the preferred embodiments of the present invention and are not used to limit the present invention. For those skilled in the art, the present invention can have various changes and modifications. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. An aircraft engine hoisting device, characterized in that, The invention comprises a crane (21), two parallel mounting rails (22) for mounting on the roof of an assembly workshop (3), a transfer rail (23) spanning between the two mounting rails (22), and a pre-mounting rail (24) and a transport rail (25) disposed on a side of the mounting rail (22) away from the other mounting rail (22), wherein the pre-mounting rail (24) is disposed above a pre-mounting station, and the transport rail (25) is extended to the roof of a test workshop (4); The transfer track (23) is provided with a moving mechanism, the moving mechanism is used to drive the transfer track (23) to move along the length direction of the assembling track (22) to a state where it is docked with the pre-assembly track (24) or docked with the transport track (25), and the crane (21) is used to lift the aircraft engine on the pre-assembly station and drive the aircraft engine to move along the pre-assembly track (24), the transfer track (23) and the transport track (25).

2. The aviation engine hoisting device according to claim 1, characterized in that, The transport track (25) is provided with a notch (251) at the position of the silencer door between the assembly workshop (3) and the test workshop (4); the aircraft engine hoisting device further comprises a direction-changing track (26) rotatably arranged at the notch (251); the direction-changing track (26) is used to rotate to a state aligned with the transport track (25) to fill the notch (251); the direction-changing track (26) is also used to rotate to a state offset from the transport track (25) to form an escape space at the notch (251) for closing the silencer door.

3. The aeroengine hoisting device according to claim 1 or 2, characterized in that The transport track (25) is provided on both of the two parallel installation tracks (22), and the transport tracks (25) on the two parallel installation tracks (22) are used to extend to different test workshops (4).

4. The aero-engine hoisting device according to claim 3, characterized in that, The transport rails (25) on the two parallel installation rails (22) are arranged opposite to each other, and the two ends of the transfer rail (23) are used to simultaneously connect with the transport rails (25) on the two parallel installation rails (22).

5. The aeroengine hoisting device according to claim 1, characterized in that, A plurality of pre-installation rails (24) are arranged at intervals along the length direction on both parallel installation rails (22), and the plurality of pre-installation rails (24) are arranged above a plurality of pre-installation stations in a one-to-one correspondence.

6. The aeroengine hoisting device according to claim 5, wherein The pre-installed rails (24) on the two parallel installation rails (22) are arranged in a one-to-one correspondence, and the two ends of the transfer rail (23) are used to simultaneously connect with the pre-installed rails (24) on the two parallel installation rails (22).

7. The aero-engine hoisting device according to claim 1, characterized in that A rail locking mechanism is provided at the end of the transfer track (23), and the rail locking mechanism is used to lock and fix the transfer track (23) relative to the pre-installed track (24) or to lock and fix the transfer track (23) relative to the transport track (25).

8. The aero-engine hoisting device according to claim 1, wherein The crane (21) comprises two hoisting assemblies (211) arranged side by side. The hoisting assemblies (211) comprise a drum (2111), a steel wire rope (2112), a pulley (2113) and a hook (2114) connected in sequence. Two steel wire ropes (2112) are provided. The two steel wire ropes (2112) are arranged at intervals along the axial direction of the pulley (2113) and are both wound around the outer circumference of the pulley (2113). The drum (2111) is connected to the steel wire rope (2112) and is used to drive the steel wire rope (2112) to be wound or unwound, thereby driving the pulley (2113) and the hook (2114) to move up and down.

9. The aero-engine hoisting device according to claim 1, characterized in that, The cross-sections of the pre-installed track (24), the transfer track (23) and the transport track (25) are all arranged in an "I"-shaped structure. The crane (21) is provided with a double-hook drive assembly, which is used to engage opposite sides of the "I"-shaped structure and to move along the pre-installed track (24), the transfer track (23) and the transport track (25).

10. An aero-engine test run system, comprising an assembly workshop (3) and a test workshop (4), characterized in that, The aircraft engine test system further comprises an aircraft engine hoisting device as claimed in any one of claims 1 to 9, wherein the aircraft engine hoisting device is installed on the roof of the assembly workshop (3) and extends to the roof of the test workshop (4) through the transport track (25).

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