Aero-engine test system

Abstract

The application discloses an aero-engine hoisting device and an aero-engine test system, wherein the aero-engine hoisting device comprises a crane, two parallel installation tracks for being installed on the roof of an assembly workshop, a transfer track arranged between the two installation tracks, a pre-installation track arranged on one side of the installation track away from the other installation track and a transportation track, the pre-installation track is arranged above a pre-installation station, and the transportation track is arranged to extend to the roof of a test workshop; the transfer track is provided with a moving mechanism, the moving mechanism is used for driving the transfer track to move along the length direction of the installation track to a state of being connected with the pre-installation track or the transportation track, and the crane is used for hoisting the aero-engine and moving along the pre-installation track, the transfer track and the transportation track. The aero-engine hoisting device provided by the application can quickly transfer the aero-engine from any pre-installation station to a test station, realize quick replacement transportation, and facilitate batch testing.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of aero-engine test running, in particular to an aero-engine hoisting device and an aero-engine test running system adopting the aero-engine hoisting device. BACKGROUND

[0002] Currently, for the ground test of an aero-engine, the aero-engine is usually transferred from an assembly workshop to a position close to a test bench in a test workshop by a transfer vehicle, then hoisted to a preset position on the transfer vehicle by a crane, and then installed and fixed to a bench system mounting rack on the test bench by an operator on an operation platform. However, due to the large size and weight of the aero-engine, the aero-engine needs to be adjusted multiple times in center and angle to be hoisted to a suitable position from the transfer vehicle, and the aero-engine needs to be transported between the transfer vehicle and the crane, and each time needs to be manually adjusted and positioned, so the transfer efficiency is extremely low, and when a large number of aero-engines need to be tested, the next process cannot be performed until the previous process is completed, and parallel work cannot be realized. SUMMARY

[0003] The present application primarily provides an aero-engine hoisting device to solve the technical problem of low transfer efficiency of the existing aero-engine during test operation.

[0004] The present application also provides an aero-engine test running system adopting the aero-engine hoisting device.

[0005] According to one aspect of the present application, an aero-engine hoisting device is provided, comprising a crane, two parallel installation tracks for being installed on the roof of an assembly workshop, a transfer track crossing between the two installation tracks, and a pre-installation track and a transportation track provided on the side of the installation track away from the other installation track, the pre-installation track is used to be arranged above a pre-installation station, and the transportation track is used to extend to the roof of a test workshop;

[0006] A moving mechanism is arranged on the transfer track, the moving mechanism is used to drive the transfer track to move along the length direction of the installation track to a state of being connected to the pre-installation track or the transportation track, and the crane is used to hoist the aero-engine on the pre-installation station and drive the aero-engine to move along the pre-installation track, the transfer track and the transportation track.

[0007] Preferably, the transport track has a gap at the position of the muffler door between the assembly workshop and the test workshop. The aircraft engine hoisting device also includes a reversible track rotatably disposed at the gap. The reversible track is used to rotate to align with the transport track to fill the gap. The reversible track is also used to rotate to offset the transport track to form a clearance space at the gap for the muffler door to close.

[0008] Preferably, both parallel tracks are equipped with transport tracks, and the transport tracks on the two parallel tracks are used to extend to different test workshops.

[0009] Preferably, the transport tracks on the two parallel tracks are arranged opposite each other, and the two ends of the transfer track are used to simultaneously connect to the transport tracks on the two parallel tracks.

[0010] Preferably, multiple pre-installed tracks are provided at intervals along the length of each of the two parallel tracks, and the multiple pre-installed tracks are used to be installed above multiple pre-installation stations in a one-to-one correspondence.

[0011] Preferably, the pre-installed rails on the two parallel tracks are arranged in a one-to-one correspondence, and the two ends of the transfer rail are used to simultaneously connect to the pre-installed rails on the two parallel tracks.

[0012] Preferably, the end of the transfer track is provided with a locking mechanism, which is used to lock the transfer track relative to the pre-installed track or to lock the transfer track relative to the transport track.

[0013] Preferably, the crane includes two lifting assemblies arranged side by side. Each lifting assembly includes a drum, a wire rope, a pulley, and a hook connected in sequence. There are two wire ropes, which are spaced apart along the axial direction of the pulley and are both wound around the outer circumference of the pulley. The drum is connected to the wire rope and is used to drive the wire rope to wind up or unwind, thereby driving the pulley and the hook to move up and down.

[0014] Preferably, the cross-sections of the pre-installed track, the transfer track, and the transport track are all designed as an "I" shape, and the crane is equipped with a double hook drive assembly. The double hook drive assembly is used to engage the opposite sides of the "I" shape and to move along the pre-installed track, the transfer track, and the transport track.

[0015] As a second aspect, the present invention also provides an aircraft engine test system, including an assembly workshop and a test workshop, and the aforementioned aircraft engine hoisting device, wherein the aircraft engine hoisting device is installed on the roof of the assembly workshop and extends to the roof of the test workshop via the transport track.

[0016] The present invention has the following beneficial effects:

[0017] The aero-engine hoisting device provided by this invention uses two parallel tracks with a connecting track installed across them. Pre-installation tracks and transport tracks are provided on the outer side of the parallel tracks. This ensures stable installation of the connecting track while allowing it to move with high precision along the parallel tracks to mate with any pre-installation track or transport track. This enables the crane to move from different pre-installation tracks to the connecting track and then along the connecting track to the transport track. This facilitates the direct hoisting of aero-engines from different pre-installation stations in the assembly workshop to the test station in the test workshop, reducing the use of transfer vehicles and thus reducing the clamping and positioning processes between the transfer vehicle and the pre-installation station, as well as between the transfer vehicle and the crane. Only one hoisting operation is needed to directly transfer the aero-engine from the pre-installation station to the test station, achieving rapid transfer and transportation. Furthermore, by setting multiple pre-installation tracks on the outer side of the parallel tracks, multiple pre-installation stations can operate in parallel, allowing for the simultaneous assembly and hoisting preparation of multiple aero-engines, effectively improving transportation efficiency and facilitating batch testing of multiple aero-engines.

[0018] In addition to the objectives, features, and advantages described above, the present invention has other objectives, features, and advantages. The invention will now be described in further detail with reference to the figures. Attached Figure Description

[0019] The accompanying drawings, which form part of this application, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings:

[0020] Figure 1 This is a schematic diagram of the structure of the aircraft engine hoisting device provided in an embodiment of the present invention;

[0021] Figure 2 for Figure 1 The diagram shown illustrates the operational status of the aircraft engine hoisting device, showing the state where the reversing track is offset from the transport track.

[0022] Figure 3 for Figure 2 The diagram shown illustrates the changing states of the aircraft engine hoisting device, showing the alignment of the reversing track with the transport track.

[0023] Figure 4 for Figure 3 The diagram shown illustrates the changing states of the aircraft engine hoisting device, showing the connection status of the transfer track with the transport track.

[0024] Figure 5 for Figure 1 A schematic diagram of the crane in the aircraft engine hoisting device shown;

[0025] Figure 6 A structural schematic diagram of an aero-engine test running system provided by an embodiment of the present application is shown in the figure;

[0026] Figure 7 A structural schematic diagram of an aero-engine test running system provided by an embodiment of the present application is shown in the figure; Figure 6 A side view of the aero-engine test running system along a test running workshop is shown in the figure;

[0027] Figure 8 A top view of a first layer auxiliary workshop in the aero-engine test running system is shown in the figure; Figure 6 A top view of a second layer auxiliary workshop in the aero-engine test running system is shown in the figure;

[0028] Figure 9 A structural schematic diagram of a pipeline installation module in the aero-engine test running system is shown in the figure; Figure 6 A structural schematic diagram of a threading module in the aero-engine test running system is shown in the figure;

[0029] Figure 10 A structural schematic diagram of a soundproof door in the aero-engine test running system is shown in the figure; Figure 8 A sectional structure diagram of the soundproof door at a door hole position is shown in the figure;

[0030] Figure 11 A partial enlarged view of an A area in the soundproof door is shown in the figure; Figure 9 A structural schematic diagram of a first sealing mechanism in the soundproof door is shown in the figure;

[0031] Figure 12 A partial enlarged view of a B area in the soundproof door is shown in the figure;

[0032] Figure 13 An assembly structure diagram of a soundproof door leaf and a suspension rail in the soundproof door is shown in the figure. Figure 12

[0033] Figure 14 Figure 13

[0034] Figure 15 Figure 14

[0035] Figure 16 Figure 13

[0036] Figure 17 Figure 12

[0037] Legend:

[0038] 1000, an aero-engine test running system;

[0039] ​​​​​​​​​1, soundproof door; 11, wall; 111, door hole; 112, sealing flange; 113, soundproof cavity; 12, overhead rail; 121, limit wheel; 13, soundproof door leaf; 131, door leaf body; 132, sealing strip; 14, first sealing mechanism; 141, first soundproof air cushion; 142, return spring; 143, electromagnet; 144, mounting seat; 145, limiting assembly; 1451, limiting block; 1452, transmission rod; 15, second sealing mechanism; 151, second soundproof air cushion; 152, lifting assembly; 1521, motor; 1522, first crank; 1523, second crank; 1524, screw rod; 1525, universal joint; 1526, lifting transmission member; 1527, mounting bracket; 16, pressure detection assembly; 161, safety air bag;

[0040] 2, aircraft engine hoisting device; 21, crane; 211, hoisting assembly; 2111, winding drum; 2112, steel wire rope; 2113, pulley; 2114, lifting hook; 22, parallel loading track; 23, transfer track; 24, preloading track; 25, transportation track; 251, notch; 26, direction-changing track;

[0041] 3, assembly workshop; 4, test workshop; 5, air inlet silencing tower; 6, gas exhaust silencing tower; 7, paddle flow exhaust silencing room;

[0042] 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 room; 84, changing soundproof room; 841, changing room; 842, soundproof room; 85, control room; 851, instrument room; 852, operating room; 86, data analysis room; 87, hand washing room;

[0043] 91, pipeline installation module; 911, fixing plate; 912, pipeline channel; 913, soundproof material; 92, threading module; 921, plugging plate; 922, threading hole. DETAILED DESCRIPTION

[0044] The embodiments of the present application will be described in detail below with reference to the accompanying drawings, but the present application can be implemented in various different ways as defined and covered below. Examples of the embodiments are shown in the drawings, wherein the same or similar reference signs represent the same or similar elements or elements having the same or similar functions throughout. The embodiments described below by reference to the drawings are exemplary and are only used to explain the present application, and cannot be interpreted as a limitation on the present application.

[0045] It is to be understood that the phraseology or terminology such as "comprising," "including," "containing," "consisting of," "consisting essentially of," "having," "including," "characterized by," "characterized by any of," and the like used in the specification, including the claims, can be used in the sense of "including but not limited to," except when the context of the specification, including the claims, expressly suggests or requires otherwise. It will be understood by those within the art that, in general, terms used herein, and especially to the right of the "=" in a "consisting of" or "consisting essentially of" claim have their normal dictionary meanings. As used herein, the following terms have the following meanings.

[0046] Figures 1 to 5 The present application provides an aero-engine hoisting device, which is used for realizing the rapid transfer of an aero-engine between a pre-assembly station and a test station, and can realize the parallel operation of multiple pre-assembly stations, effectively improving the transfer efficiency and test efficiency of the aero-engine, reducing manual operation, and improving safety.

[0047] Please refer to Figure 1 and Figure 2 , the aero-engine hoisting device 2 comprises a crane 21, two parallel pre-assembly tracks 22 for being installed on the roof of an assembly workshop 3, a transfer track 23 arranged between the two pre-assembly tracks 22, a pre-assembly track 24 arranged on the side of the pre-assembly track 22 away from the other pre-assembly track 22, and a transportation track 25 arranged on the roof of the pre-assembly track 24 and extending to the roof of a test workshop 4. The transfer track 23 is provided with a moving mechanism (not shown in the figure, the same below), which is used for driving the transfer track 23 to move along the length direction of the pre-assembly track 22 to the state of being connected to the pre-assembly track 24 or the transportation track 25. The crane 21 is used for hoisting the aero-engine on the pre-assembly station and driving the aero-engine to move along the pre-assembly track 24, the transfer track 23 and the transportation track 25.

[0048] Specifically, the aero-engine hoisting device 2 is installed with the transfer track 23 through two parallel tracks 22, and is provided with a pre-installation track 24 and a transportation track 25 outside the parallel tracks 22 (away from the transfer track 23), so that the transfer track 23 can be stably installed and moved along the parallel tracks 22 to the state of being connected to any pre-installation track 24 or the transportation track 25, thereby enabling the crane 21 to be moved into different pre-installation tracks 24 to hoist the aero-engine on the corresponding pre-installation station, and to be moved from the different pre-installation tracks 24 to the transfer track 23 and then to the transportation track 25 along the transfer track 23, so as to facilitate the crane 21 to directly hoist and transport the aero-engine on the different pre-installation stations of the assembly workshop 3 to the test station in the test workshop 4, reduce the use of transfer vehicles, and thus reduce the clamping and positioning procedures between the transfer vehicles and the pre-installation stations and between the transfer vehicles and the crane, so that the aero-engine can be directly transferred from the pre-installation station to the test station through only one hoisting operation, and rapid replacement and transportation are realized. Secondly, a plurality of pre-installation tracks 24 can be arranged outside the parallel tracks 22 to realize parallel operation of multiple pre-installation stations, so that the assembly and hoisting preparation of multiple aero-engines can be simultaneously performed, the transportation efficiency is effectively improved, and batch testing of multiple aero-engines is facilitated.

[0049] Further, the moving mechanism includes a first roller arranged at both ends of the transfer track 23, a first moving motor connected with the first roller and used for driving the first roller to roll, and the first roller is embedded in a first roller groove prearranged in the parallel track 22, and the first roller is driven by the first moving motor to roll along the first roller groove, so as to drive the transfer track 23 to move along the parallel track 22.

[0050] Please refer to Figure 2 and Figure 3 , the transportation track 25 is provided with a gap 251 at the position of the soundproof door 1 between the assembly workshop 3 and the test workshop 4, and the aero-engine hoisting device 2 further includes a turning track 26 rotatably arranged at the gap 251, the turning track 26 is used to be turned to the state of being aligned with the transportation track 25 to fill the gap 251 (shown in Figure 3 ), and the turning track 26 is also used to be turned to the state of being staggered with the transportation track 25 to form an avoidance space for the soundproof door 1 to be closed at the gap 251 (shown in Figure 2 ).

[0051] Specifically, the variable direction track 26 is arranged to rotate along a horizontal plane, and a variable direction motor (not shown in the figure, the same below) is arranged on the variable direction track 26 to drive the variable direction track 26 to rotate. When the variable direction track 26 is driven by the variable direction motor to rotate to a state of aligning with the transportation track 25, the gap 251 can be filled, so that the crane 21 can move along the transportation track 25 between the assembly workshop 3 and the test workshop 4. When the test is performed in the test workshop 4, the variable direction track 26 can be driven by the variable direction motor to rotate to a state of being staggered with the transportation track 25, so that an avoidance space for closing the soundproof door 1 can be formed at the gap 251, thereby enabling the soundproof door 1 to be smoothly closed and seal the test workshop 4, which is conducive to achieving the soundproofing and noise reduction effect of the test workshop 4.

[0052] Preferably, the transportation track 25 is arranged on each of the two parallel tracks 22, and the transportation tracks 25 on the two parallel tracks 22 are used to extend to different test workshops 4. That is, the aero-engine hoisting device 2 can flexibly transfer the aero-engines on the multiple pre-assembly stations to different test workshops 4 respectively, realize parallel operation of at least two test workshops 4, and further improve the test efficiency.

[0053] As shown in Figure 4 The two transportation tracks 25 on the two parallel tracks 22 are arranged opposite to each other, and the two ends of the transfer track 23 are used to simultaneously dock the transportation tracks 25 on the two parallel tracks 22. Since the two transportation tracks 25 on the two parallel tracks 22 are arranged opposite to each other, only one positioning position is needed to enable the transfer track 23 to simultaneously dock the two transportation tracks 25, thereby reducing the docking positioning structure on the transfer track 23, simplifying the aero-engine hoisting device 2, and making the overall structure more simple and efficient.

[0054] Preferably, a plurality of pre-assembly tracks 24 are arranged on each of the two parallel tracks 22 along the length direction, and the plurality of pre-assembly tracks 24 are arranged above the multiple pre-assembly stations one by one. By arranging a plurality of pre-assembly tracks 24 on the two parallel tracks 22 respectively, more pre-assembly stations can be conveniently arranged to meet the transfer requirements of more pre-assembly stations. It should be understood that each pre-assembly station can be used for assembling an aero-engine alone, or different assembly processes of an aero-engine can be performed through multiple pre-assembly stations. The aero-engine hoisting device 2 can realize flexible movement of the crane 21 between the multiple pre-assembly stations to meet different use requirements, and has strong applicability.

[0055] As shown in Figure 2As shown, the two pre-installed tracks 24 on the two parallel tracks 22 are arranged in one-to-one correspondence, and the two ends of the adapter track 23 are used to simultaneously dock the pre-installed tracks 24 on the two parallel tracks 22. Similarly, since the pre-installed tracks 24 on the two parallel tracks 22 are arranged opposite to each other, only one positioning position is needed to simultaneously dock the two pre-installed tracks 24 by the adapter track 23, thereby reducing the docking positioning structure on the adapter track 23, simplifying the aero-engine hoisting device 2, and making the overall structure more simple and efficient.

[0056] Preferably, the end of the adapter track 23 is provided with a track locking mechanism (not shown), which is used to lock and fix the adapter track 23 relative to the pre-installed track 24 or to lock and fix the adapter track 23 relative to the transport track 25. The positioning and fixing of the adapter track 23 are realized by the track locking mechanism, which ensures that the adapter track 23 is stably docked with the pre-installed track 24 or the transport track 25, so that the crane 21 can move smoothly between the adapter track 23 and the pre-installed track 24 or between the adapter track 23 and the transport track 25.

[0057] Further, the track locking mechanism includes a telescopic assembly and a locking pin connected with the telescopic assembly. The telescopic assembly can specifically adopt a gas rod and a hydraulic rod, or include a motor and a linear transmission component connected with the output shaft of the motor. The telescopic assembly is connected with the locking pin and is used to drive the locking pin to move telescopically, so that the locking pin is inserted into the pre-positioning hole on the pre-installed track 24 or the transport track 25, realizing the locking and fixing of the adapter track 23.

[0058] As shown, Figure 5 The crane 21 includes two hoisting assemblies 211 arranged side by side. The hoisting assembly 211 includes a winding drum 2111, a steel wire rope 2112, a pulley 2113 and a lifting hook 2114 connected in sequence. The steel wire rope 2112 is provided with two steel wire ropes 2112 arranged along the axial direction of the pulley 2113 and wound around the outer periphery of the pulley 2113. The winding drum 2111 is connected with 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 lifting hook 2114 to move up and down.

[0059] Since the lifting assembly 211 includes two steel wire ropes 2112 spaced apart along the axial direction of the pulley 2113, and the steel wire ropes 2112 are wound around the outer circumference of the pulley 2113, so that the two ends of the steel wire ropes 2112 are respectively located on opposite sides of the pulley 2113, the two steel wire ropes 2112 together form four traction points. The steel wire ropes 2112 are arranged around the hook 2114, which effectively ensures the stability of the hook 2114 in three dimensions and can prevent the hook 2114 from tilting in any direction. Compared with conventional hook structures, it can effectively ensure the stable transportation of the lifted items and prevent swaying during the lifting process. Secondly, since the crane 21 includes two lifting components 211 arranged side by side, the aircraft engine is lifted on opposite sides by hooks 2114 on the two lifting components 211 respectively. Thus, the position of the aircraft engine can be flexibly adjusted by individually controlling the lifting height of any one hook 2114, ensuring that the aircraft engine is in a horizontal state during lifting, and further improving the lifting stability.

[0060] Preferably, the cross-sections of the pre-installed track 24, the transfer track 23, and the transport track 25 are all designed as "I"-shaped structures. The drum 2111 is provided with a double hook drive assembly, which is used to engage the 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.

[0061] Specifically, the pre-installed track 24, the transfer track 23, and the transport track 25 are all made of I-beams, which have a simple and efficient structure. The double hook drive assembly includes two oppositely arranged inverted "L" shaped hooks. By engaging the two inverted "L" shaped hooks with the limiting sides of the I-beams respectively, the crane 21 can be multi-directionally limited, thus improving stability.

[0062] Furthermore, the bottom of the inverted "L"-shaped hook is provided with a second roller and a second moving motor connected to the second roller. The second roller abuts against the upper surface of the flange of the I-beam. By driving the second roller to roll along the I-beam through the second moving motor, the crane 21 can be moved along the pre-installed track 24, the transfer track 23 and the transport track 25.

[0063] like Figure 6As shown, as a second aspect, the application also provides an aero-engine test system 1000, comprising an assembly workshop 3 and a test workshop 4, and the aero-engine hoisting device 2 described above, which 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 aero-engine hoisting device 2, which can directly hoist the aero-engine on different pre-assembly stations in the assembly workshop 3 to the test station in the test workshop 4, reduces the use of transfer vehicles, and only needs to be transferred from the pre-assembly station to the test station through one hoisting operation, realizes rapid replacement transportation, and can also realize parallel operation of multiple pre-assembly stations, which can simultaneously assemble and hoist multiple aero-engines, effectively improve the transportation efficiency, and facilitate batch testing.

[0064] Please refer to Figure 6 and Figure 7 , the aero-engine test system 1000 further comprises an air intake silencing tower 5, a gas exhaust silencing tower 6 and a propeller flow exhaust silencing room 7, the test workshop 4 is used for testing the aero-engine, the air intake silencing tower 5 is arranged at the front end of the test workshop 4 along the airflow direction of the aero-engine, and the gas exhaust silencing tower 6 and the propeller flow exhaust silencing room 7 are arranged at the rear end of the test workshop 4 along the airflow direction of the aero-engine.

[0065] Further, the air intake silencing tower 5 extends upward along the vertical direction and its air intake end is arranged downward along the vertical direction, the gas exhaust silencing tower 6 is arranged between the test workshop 4 and the propeller flow exhaust silencing room 7, the gas exhaust silencing tower 6 extends upward along the vertical direction and its exhaust end is arranged upward along the vertical direction, and the exhaust end of the propeller flow exhaust silencing room 7 is arranged horizontally along the length direction of the test workshop 4. The air intake silencing tower 5 is used for introducing air into the test workshop 4, the gas exhaust silencing tower 6 is used for exhausting the gas generated by the aero-engine in the test workshop 4, and the propeller flow exhaust silencing room 7 is used for exhausting the propeller flow exhaust gas generated by the aero-engine in the test workshop 4. The air intake silencing tower 5, the gas exhaust silencing tower 6 and the propeller flow exhaust silencing room 7 are all provided with multi-stage silencing structures and flow regulating structures.

[0066] In the aero-engine test system 1000, the air intake end of the air intake silencer tower 5 is vertically downward, the exhaust end of the gas exhaust silencer tower 6 is vertically upward, and the exhaust end of the paddle flow exhaust silencer room 7 is horizontally exhaust, realizing the structural layout of vertical air intake and horizontal exhaust, meeting the air intake and exhaust requirements of the aero-engine, and the overall layout is more reasonable and compact, occupying less space, which can adapt to different sites, has stronger applicability, and because the gas exhaust silencer tower 6 and the paddle flow exhaust silencer room 7 are independently arranged, the gas can be better discharged, the problem of gas backflow during the test process can be effectively avoided, and the test safety and test effect are improved. Secondly, because the air intake silencer tower 5, the gas exhaust silencer tower 6 and the paddle flow exhaust silencer room 7 are all provided with multi-stage silencing structure and flow regulating structure, hierarchical silencing and flow regulation can be realized, the exhaust effect is better, and the test noise can be prevented from diffusing outward, thereby ensuring the test safety.

[0067] As shown in Figure 6 The aero-engine test system 1000 further includes an auxiliary workshop 8, the assembly workshop 3 and the auxiliary workshop 8 are arranged along a straight line and 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 air 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 is provided with two layers along the height direction, the first layer auxiliary workshop includes a lubricating oil storage room 81, an electrical equipment room 82 and a fuel room 83 which are sequentially arranged away from the assembly workshop 3, the second layer auxiliary workshop includes a changing soundproof room 84, a control room 85 and a data analysis room 86 which are sequentially arranged away from the assembly workshop 3, and the control room 85 is located directly above the electrical equipment room 82 and is used for controlling the electrical equipment in the electrical equipment room 82.

[0068] Specifically, the oil storage room 81 is used for storing oil, and the fuel room 83 is used for storing fuel, the oil storage room 81 is arranged close to the engine mounting position of the test vehicle room 4, which is conducive to subsequent oil filling and preparation of each test equipment and connection of pipelines; the fuel room 83 is arranged away from the engine mounting position of the test vehicle room 4, which can improve safety and avoid direct contact of fuel with high temperature. Secondly, since the auxiliary room 8 is provided with two layers in the height direction, the changing soundproof room 84, the control room 85 and the data analysis room 86 which do not need to be provided with large equipment are sequentially arranged on the second layer, which not only can efficiently utilize the longitudinal space and make the overall layout more reasonable and compact, but also can facilitate the pipeline connection and installation between the control room 85 and the electrical equipment room 82, facilitate the control of the electrical equipment in the electrical equipment room 82 by the control room 85, and utilize the changing soundproof room 84 to soundproof and reduce noise of the control room 85 and the data analysis room 86, facilitate changing in and out of the control room 85 and the data analysis room 86, and effectively reduce the noise influence of the test process of the test vehicle room 4 on the control room 85 and the data analysis room 86.

[0069] Preferably, the electrical equipment room 82 comprises a process equipment room 821, an electrical room 822 and a loading cabinet room 823 which are sequentially arranged away from the assembly room 3, the process equipment room 821 is used for arranging oil stations, air systems and circulating cooling water systems, and the oil stations specifically comprise lifting platform oil stations, hydraulic loading oil stations, oil seal oil stations and the like, since the process equipment room 821 is relatively close to the test vehicle room 4, the oil stations, the air systems and the circulating cooling water systems are convenient for docking with the test vehicle room 4. Secondly, the electrical room 822 is used for arranging electrical control cabinets and power supply cabinets, and the loading cabinet room 823 is used for arranging electrical loading cabinets, the loading cabinets are independently arranged to reduce the influence of heat dissipation operation of the loading cabinets on other electrical equipment, and the electrical room 822 and the loading cabinet room 823 are adjacently arranged to facilitate unified management.

[0070] Further, the electrical equipment room 82 further comprises an accessory storage room 824 and an air compressor room 825 which are sequentially arranged at the rear end of the loading cabinet room 823 away from the assembly room 3, the accessory storage room 824 is used for storing accessories, and the air compressor room 825 is used for arranging air compressors, different equipment is separated by multiple rooms to avoid mutual influence.

[0071] Further, the changing soundproof room 84 comprises a changing room 841 and a soundproof room 842 which are sequentially arranged away from the assembly room 3, and the changing room 841 and the soundproof room 842 realize double soundproofing of the control room 85.

[0072] Further, the control room 85 comprises an instrument room 851 and a manipulation room 852 arranged in sequence in a direction away from the assembly workshop 3, the instrument room 851 is used for arranging instruments, and the manipulation room 852 is used for manipulating the instruments, the instrument room 851 and the manipulation room 852 are separated, which can avoid the manipulation room 852 being too messy, and further soundproof the manipulation room 852 through the instrument room 851.

[0073] Further, the data analysis room 86 is provided with a washroom 87 away from one side of the control room 85, so as to facilitate the test personnel in the control room 85 and the data analysis room 86.

[0074] Please refer to Figure 8 and Figure 10 , the wall surface between the electrical equipment room 82 and the test workshop 4 is provided with a pipeline installation module 91, the pipeline installation module 91 comprises two fixed plates 911 used for fitting opposite sides of the wall surface, a plurality of pipeline channels 912 arranged between the two fixed plates 911, and soundproofing material 913 filled in the outer periphery of the pipeline channels 912, and the pipeline channels 912 are provided with connecting ports used for connecting equipment pipelines on the fixed plates 911. Among them, at least part of the pipeline channels 912 have different diameters to meet different pipeline installations, and the equipment pipelines are connected through the pipeline channels 912, which can conveniently transport substances such as lubricating oil, fuel oil, hydraulic oil and cooling liquid, and also can achieve good soundproofing effect, so as to avoid the noise in the test workshop 4 from being transmitted outward along the pipeline installation position.

[0075] Please refer to Figure 9 and Figure 11 , the wall surface between the control room 85 and the test workshop 4 is provided with a threading module 92, the threading module 92 comprises a blocking plate 921 embedded in the wall surface, a plurality of threading holes 922 arranged on the blocking plate 921, and a sealing plug detachably blocking the threading holes 922. At least part of the threading holes 922 have different diameters, and the wiring personnel can take out the sealing plug at the corresponding position according to the needs, so that the cable in the test workshop 4 can be threaded to the control room 85 through the corresponding threading hole 922. This structure can ensure the sealing of the test workshop 4, reduce the physical vibration of the cable in the transmission process, ensure the constant temperature and humidity environment of the control room 85, and thus increase the accuracy and precision of data transmission.

[0076] Preferably, a constant temperature and humidity system (not shown in the figure, the same below) for adjusting temperature and humidity is arranged in the control room 85 and the data analysis room 86, and the temperature and humidity of the control room 85 and the data analysis room 86 are adjusted by the constant temperature and humidity system, so as to ensure that the related instruments and meters are kept in a suitable working environment and are not affected by the high temperature of the test workshop 4.

[0077] Please refer to Figures 12 to 17 , the aero-engine test system 1000 further comprises a soundproof door 1 arranged between the test workshop 4 and the assembly workshop 3, which can realize a larger opening and closing area and has a better soundproof effect through structure optimization, meets the requirements of large equipment access and test soundproofing, and can be applied to the aero-engine test system to realize sound insulation and noise reduction between the assembly workshop 3 and the test workshop 4.

[0078] Please refer to Figure 12 and Figure 13 , the soundproof door 1 comprises 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), the wall body 11 is provided with a door hole 111 matched with the soundproof door leaf 13, the hanging rail 12 is installed on the wall body 11, the hanging rail 12 is located above the door hole 111 and extends to one side of the door hole 111 in the horizontal direction, the soundproof door leaf 13 is slidably installed on the hanging rail 12, and the translation mechanism is connected with the soundproof door leaf 13 and used for driving the soundproof door leaf 13 to slide along the hanging rail 12. Further, the translation mechanism can specifically comprise a translation motor arranged on the wall body 11 and a driving wheel connected with the output shaft of the translation motor, the driving wheel abuts against the soundproof door leaf 13, so as to drive the soundproof door leaf 13 to translate through the rolling action of the driving wheel driven by the translation motor. In other embodiments, the driving wheel can be provided as a gear, and a rack engaged with the gear is arranged on the soundproof door leaf 13, and the rack is driven to translate through the rotation of the gear driven by the translation motor, so as to realize a higher-precision translation driving action.

[0079] As Figure 14As shown, one side of the wall body 11 facing the soundproof door leaf 13 is provided with a sealing flange 112, which is arranged above the door opening 111 and extends towards the soundproof door leaf 13, and the top surface of the sealing flange 112 is provided with a first sealing mechanism 14. The soundproof door leaf 13 comprises a door leaf body 131 and a sealing batten 132, the first end of the sealing batten 132 is fixedly connected with the door leaf body 131 in the horizontal direction, and the second end of the sealing batten 132 is inserted into the first sealing mechanism 14 in the vertical direction. The middle segment of the sealing batten 132 is provided with an arc surface structure or a right angle structure so that the first end and the second end of the sealing batten 132 are arranged in different directions. The first sealing mechanism 14 is used to clamp the sealing batten 132 after the soundproof door leaf 13 is closed, so as to seal the gap between the soundproof door leaf 13 and the wall body 11. The first sealing mechanism 14 is also used to release the sealing batten 132 when the soundproof door leaf 13 moves, so as to avoid affecting the opening and closing action of the soundproof door leaf 13.

[0080] Specifically, the soundproof door 1 adopts a sliding door structure and is driven to open and close by the translation mechanism, so as to avoid the situation that the soundproof door is too large in size and too heavy in weight to be manually opened and closed, thereby being able to meet the sealing requirements of a large-size door opening, adapt to the entry and exit of large-volume equipment, and adopt a suspended rail design, which can avoid the problem that the uneven ground surface and the existence of protrusions are not conducive to the entry and exit of large equipment compared with a ground rail structure. More importantly, the first sealing mechanism 14 provided on the wall body 11 can clamp the sealing batten 132 on the soundproof door leaf 13 after the soundproof door leaf 13 is closed, so as to seal the gap between the soundproof door leaf 13 and the wall body 11, effectively solve the problem of poor sealing effect of conventional sliding doors, increase the area of the door opening 111 while ensuring the sound insulation and noise reduction effect, and be able to meet the transfer requirements and noise reduction requirements of large aero-engine tests at the same time.

[0081] Please refer to Figure 15 The first sealing mechanism 14 comprises 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 arranged on opposite sides of the second end of the sealing batten 132, i.e. the second end of the sealing batten 132 is inserted into the two first soundproof air cushions 141 in the vertical direction. The return spring 142 is used to elastically open the two first soundproof air cushions 141 to a preset spacing state to release the sealing batten 132, and 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 batten 132.

[0082] The working principle of the first sealing mechanism 14 is that when the electromagnet 143 is in a power-off state, it has no magnetic force, at which time the two first sound-absorbing air cushions 141 can be popped open to a preset spacing state by the elastic force of the reset spring 142, so that the first sound-absorbing air cushions 141 are separated from the sealing clamping strip 132, and the sound-absorbing door leaf 13 can be smoothly opened and closed; when the electromagnet 143 is in a power-on state, the magnetic force generated by the electromagnet 143 can overcome the elastic force of the reset spring 142 and attract the two first sound-absorbing air cushions 141, so that the sealing clamping strip 132 is clamped by the two first sound-absorbing air cushions 141, realizing efficient sealing of the gap between the sound-absorbing door leaf 13 and the wall body 11. The sealing structure is simple and efficient, and the sealing is carried out through the air cushion structure, which can ensure that the first sound-absorbing air cushions 141 are tightly attached to the sealing clamping strip 132, and the sound-absorbing air cavity in the first sound-absorbing air cushions 141 can also be used for sound absorption, effectively improving the sound-absorbing effect.

[0083] Preferably, the first sealing mechanism 14 further comprises a mounting seat 144 arranged between the two first sound-absorbing air cushions 141, and two limiting assemblies 145 arranged on both ends of the mounting seat 144, the limiting assembly 145 comprising a limiting block 1451 and a transmission rod 1452 connected with the limiting block 1451, one end of the transmission rod 1452 away from the limiting block 1451 penetrates through a limiting hole prearranged on the mounting seat 144 and is connected with the first sound-absorbing air cushion 141, and the transmission rods 1452 of the two limiting assemblies 145 are connected with the two first sound-absorbing air cushions 141 one by one, the reset spring 142 abuts against one side of the limiting block 1451 away from the transmission rod 1452, and the limiting block 1451 is used to move to the state of abutting against the inner wall of the mounting seat 144 under the elastic force of the reset spring 142 and limit the maximum moving stroke of the first sound-absorbing air cushion 141.

[0084] The limiting assembly 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, avoids the loosening of the first sound-absorbing air cushion 141, and also guides the moving direction of the first sound-absorbing air cushion 141 through the cooperation of the limiting block 1451 and the limiting hole prearranged on the mounting seat 144, effectively improving the stability of the first sound-absorbing air cushion 141 and avoiding the deflection of the first sound-absorbing air cushion 141 affecting the clamping sealing effect.

[0085] Preferably, the first sound insulation air cushion 141 is provided with the electromagnet 143 on both upper and lower sides of the return spring 142, so that the electromagnet 143 on both upper and lower sides can attract the first sound insulation air cushion 141 at the same time, ensuring that the first sound insulation air cushion 141 is uniformly stressed and can realize stable and smooth movement. In the embodiment, the corresponding positions on the two first sound insulation air cushions 141 are provided with the electromagnet 143, so as to improve the magnetic attraction effect and ensure the sealing strength; in other embodiments, the electromagnet 143 can be provided on only one of the first sound insulation air cushions 141, and a metal part for magnetic attraction of the electromagnet 143 can be provided on the other first sound insulation air cushion 141, and the electromagnet 143 can also control the attraction of the two first sound insulation air cushions 141.

[0086] As shown in Figure 16 The sound insulation door 1 further comprises a second sealing mechanism 15 provided on the bottom of the sound insulation door leaf 13, the second sealing mechanism 15 comprising a second sound insulation air cushion 151 and a lifting assembly 152, the second sound insulation air cushion 151 being in sliding connection with the bottom of the sound insulation door leaf 13 in the vertical direction, and the lifting assembly 152 being connected with the second sound insulation air cushion 151 and being used to drive the second sound insulation air cushion 151 to move up and down, so as to control the second sound insulation air cushion 151 to move up and down to abut against the ground or to be separated from the ground.

[0087] Specifically, after the sound insulation door leaf 13 is closed, the second sound insulation air cushion 151 can be driven by the lifting assembly 152 to move downward to abut against the ground, so as to seal the gap at the bottom of the sound insulation door leaf 13. The sealing is realized by the air cushion structure, which can ensure that the second sound insulation air cushion 151 closely abuts against the ground and can also utilize the air cavity in the second sound insulation air cushion 151 to realize sound insulation, effectively improving the sound insulation effect at the bottom position, so as to further improve the sound insulation and noise reduction effect of the sound insulation door 1.

[0088] Preferably, the lifting assembly 152 comprises a motor 1521 provided on the wall 11, a first crank 1522 connected with the output shaft of the motor 1521, a second crank 1523 rotatably provided on the sound insulation door leaf 13 in the horizontal direction, a screw rod 1524 rotatably mounted in the sound insulation 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 rotary power of the second crank 1523 to the screw rod 1524, and a lifting transmission member 1526 connected with the second sound insulation air cushion 151, the lifting transmission member 1526 being provided with a threaded hole in threaded connection with the screw rod 1524, and the first crank 1522 being used to abut against the second crank 1523 after the sound insulation door leaf 13 is closed and to transmit the rotary power of the motor 1521 to the second crank 1523.

[0089] Specifically, the first crank 1522 and the second crank 1523 are provided with overlapping portions at a preset included angle, when the soundproof door leaf 13 is in an open state, the second crank 1523 moves with the soundproof door leaf 13 to a state of being separated from the first crank 1522; when the soundproof door leaf 13 is in a 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, the first crank 1522 is driven to rotate by the motor 1521, so that the overlapping portion on the first crank 1522 is rotated to the state of overlapping the second crank 1523 and drives the second crank 1523 to rotate, thereby realizing reverse transmission through the cooperation of the second crank 1523 and the universal joint 1525 and driving the screw rod 1524 to rotate, and then driving the lifting transmission member 1526 to move up and down through the threaded cooperation, and driving the second soundproof air cushion 151 to move up and down by the lifting transmission member 1526. Since the motor 1521 is arranged away from the soundproof door leaf 13, the load of the soundproof door leaf 13 can be reduced, the opening mounting structure on the soundproof door leaf 13 can be reduced, and the smoothness of movement and the soundproof effect of the soundproof door leaf 13 can be ensured.

[0090] Further, the second soundproof air cushion 151 is provided with two, two second soundproof air cushions 151 are arranged on opposite sides of the soundproof door leaf 13, the two ends of the lifting transmission member 1526 respectively penetrate the opposite sides of the soundproof door leaf 13 and are connected with two second soundproof air cushions 151 one by one, and the second soundproof air cushion 151 extends upward to cover the penetrating hole position of the lifting transmission member 1526 on the soundproof door leaf 13, and the two second soundproof air cushions 151 are driven to move up and down synchronously by the lifting transmission member 1526, so that the two second soundproof air cushions 151 can jointly clamp the soundproof door leaf 13 to realize a double-layer sealing effect, and the second soundproof air cushion 151 can also cover the opening on the soundproof door leaf 13 to ensure the soundproof effect.

[0091] Further, the lifting assembly 152 further comprises a mounting bracket 1527 arranged in the inner cavity of the soundproof door leaf 13, the mounting bracket 1527 is arranged above the screw rod 1524, and the screw rod 1524 is rotatably mounted on the mounting bracket 1527. The mounting bracket 1527 is used for mounting and limiting the screw rod 1524, thereby improving the stability of the screw rod 1524.

[0092] Please refer to Figure 12 and Figure 17The wall body 11 is provided with two walls 11 which are spaced apart and form a sound insulation cavity 113, the door opening 111 and the overhead rail 12 are arranged on the two walls 11, and the sound insulation door leaf 13 is provided with two sound insulation door leaves 13 which are arranged on the overhead rails 12 of the two walls 11 in a one-to-one correspondence, and the two sound insulation door leaves 13 are used to close the door openings 111 on the two walls 11 and seal the sound insulation cavity at the same time. The sound insulation door 1 forms a cavity structure through the two spaced-apart walls 11, and after the two sound insulation door leaves 13 are closed at the same time, the sound insulation cavity 113 can be in a completely closed state, effectively improving the sound insulation effect, and the noise of 160 dB generated in the test workshop of the aero-engine test system can be reduced to 70 dB.

[0093] Preferably, the door leaf body 131 includes, in sequence from the outside to the inside, a first sound insulation plate, a damping layer, a steel frame, sound insulation cotton, a composite sound insulation module and a second sound insulation plate, and through the arrangement of the multiple sound insulation structures in sequence, the noise can be greatly reduced, and through the support of the steel frame on the multiple sound insulation structures, the structural strength of the door leaf body 131 can be ensured, and deformation is avoided to affect the sealing effect.

[0094] Preferably, the sound insulation door leaf 13 is provided with an infrared detection assembly (not shown, the same below) and / or a pressure detection assembly 16, the infrared detection assembly includes an infrared sensor, the infrared sensor is used to detect whether there is an obstacle in the closing direction of the sound insulation door leaf 13 through an infrared signal, and the pressure detection assembly 16 includes a safety air bag 161 and a pressure sensor arranged in the safety air bag 161, the safety air bag 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 air bag 161 to determine whether the safety air bag 161 touches an obstacle.

[0095] In the embodiment, the sound insulation door leaf 13 is provided with the infrared detection assembly and the pressure detection assembly 16 at the same time, whether there is an obstacle in the closing direction of the sound insulation door leaf 13 is determined through double anti-collision detection, and the safety is effectively improved.

[0096] Further, the overhead rail 12 is provided with a limiting wheel 121, 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, and the high-precision opening and closing of the sound insulation door leaf 13 is ensured.

[0097] The above only describes the preferred embodiments of the present application and is not used to limit the present application. For those skilled in the art, the present application can have various modifications and changes. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. An aircraft engine test system, comprising an assembly workshop (3) and a test workshop (4), and an aircraft engine hoisting device; The aircraft engine hoisting device includes a crane (21), two parallel mounting tracks (22) installed on the roof of the assembly workshop (3) and parallel to each other, a transfer track (23) spanning between the two parallel mounting tracks (22), and a pre-assembly track (24) and a transport track (25) located on the side of the parallel mounting track (22) away from the other parallel mounting track (22), the pre-assembly track (24) being used to be set above the pre-assembly station, and the transport track (25) extending to the roof of the test workshop (4); The transfer track (23) is provided with a moving mechanism, which is used to drive the transfer track (23) to move along the length direction of the parallel track (22) to the state of docking with the pre-installed track (24) or docking with the transport track (25). The crane (21) is used to lift the aircraft engine on the pre-installation station and drive the aircraft engine to move along the pre-installed track (24), the transfer track (23) and the transport track (25). The aircraft engine test system also includes a soundproof door (1) located between the assembly workshop (3) and the test workshop (4). The soundproof door (1) includes a wall (11) with a door opening (111), a hanging rail (12) located above the door opening (111), a soundproof door leaf (13) installed on the hanging rail (12), and a translation mechanism connected to the soundproof door leaf (13). The translation mechanism is used to drive the soundproof door leaf (13) to slide open and close along the hanging rail (12). The wall (11) has a sealing flange (112) on the side facing the soundproof door (13). The sealing flange (112) is located above the door opening (111). The top surface of the sealing flange (112) is provided with a first sealing mechanism (14). The soundproof door (13) includes a door body (131) and a sealing strip (132). The first end of the sealing strip (132) is fixedly connected to the door body (131). The second end of the sealing strip (132) is inserted vertically into the first sealing mechanism (14). The first sealing mechanism (14) is used to clamp the sealing strip (132) after the soundproof door (13) is closed, thereby sealing the gap between the soundproof door (13) and the wall (11). The first sealing mechanism (14) is also used to release the sealing strip (132) when the soundproof door (13) moves. The first sealing mechanism (14) includes two first noise-absorbing air cushions (141), a return spring (142) pressed between the two first noise-absorbing air cushions (141), and an electromagnet (143) disposed on the first noise-absorbing air cushions (141); The second end of the sealing strip (132) is inserted vertically between the two first noise-absorbing air pads (141). The reset spring (142) is used to spring the two first noise-absorbing air pads (141) to a preset distance to release the sealing strip (132). The electromagnet (143) is used to attract the two first noise-absorbing air pads (141) in the energized state to drive the two first noise-absorbing air pads (141) to clamp the sealing strip (132). The first sealing mechanism (14) further includes a mounting base (144) disposed between two first noise-absorbing air cushions (141), and two limiting components (145) disposed at both ends of the mounting base (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 base (144) and then connects with the limiting block (1451). The first noise-absorbing air cushion (141) is connected, and the transmission rods (1452) of the two limiting components (145) are connected to the two first noise-absorbing air cushions (141) one by one. 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 the state of abutting against the inner wall of the mounting base (144) under the elastic force of the return spring (142) and limit the maximum movement stroke of the first noise-absorbing air cushion (141). The soundproof door (1) also includes a second sealing mechanism (15) disposed on the bottom of the soundproof door leaf (13). The second sealing mechanism (15) includes a second soundproof air cushion (151) that is slidably connected to the soundproof door leaf (13) in the vertical direction, and a lifting assembly (152) that is connected to the second soundproof air cushion (151) and used to drive the second soundproof air cushion (151) to move up and down. The lifting assembly (152) includes a motor (1521) mounted on the wall (11), a first crank (1522) connected to the output shaft of the motor (1521), a second crank (1523) rotatably mounted on the soundproof door leaf (13) in the horizontal direction, a screw (1524) rotatably mounted in the soundproof door leaf (13) in the vertical direction, and a screw (1524) disposed between the second crank (1523) and the screw (1524) for adjusting the second crank (1523). The rotational power is transmitted to the universal joint (1525) on the screw (1524) and the lifting transmission component (1526) connected to the second noise-absorbing air cushion (151). The lifting transmission component (1526) is provided with a threaded hole that is threadedly connected to the screw (1524). The first crank (1522) is used to abut against the second crank (1523) after the noise-absorbing door (13) is closed and transmit the rotational power of the motor (1521) to the second crank (1523).

2. The aircraft engine test system according to claim 1, characterized in that, The transport track (25) has a gap (251) at the position of the muffler door between the assembly workshop (3) and the test workshop (4). The aircraft engine hoisting device also includes a deflector track (26) rotatably disposed at the gap (251). The deflector track (26) is used to rotate to align with the transport track (25) to fill the gap (251). The deflector track (26) is also used to rotate to offset the transport track (25) to form a clearance space at the gap (251) for the muffler door to close.

3. The aircraft engine test system according to claim 1 or 2, characterized in that, The two parallel tracks (22) are each equipped with the transport track (25), and the transport track (25) on the two parallel tracks (22) is used to extend to different test workshops (4).

4. The aircraft engine test system according to claim 3, characterized in that, The transport tracks (25) on the two parallel tracks (22) are arranged opposite each other, and the two ends of the transfer track (23) are used to simultaneously connect to the transport tracks (25) on the two parallel tracks (22).

5. The aircraft engine test system according to claim 1, characterized in that, Multiple pre-installed tracks (24) are provided at intervals along the length of each of the two parallel tracks (22). The multiple pre-installed tracks (24) are used to be set above multiple pre-installation stations in a one-to-one correspondence.

6. The aircraft engine test system according to claim 5, characterized in that, The pre-installed tracks (24) on the two parallel tracks (22) are set one-to-one, and the two ends of the transfer track (23) are used to simultaneously connect to the pre-installed tracks (24) on the two parallel tracks (22).

7. The aircraft engine test system according to claim 1, characterized in that, The end of the transfer track (23) is provided with a locking mechanism, which is used to lock the transfer track (23) relative to the pre-installed track (24) or to lock the transfer track (23) relative to the transport track (25).

8. The aircraft engine test system according to claim 1, characterized in that, The crane (21) includes two lifting assemblies (211) arranged side by side. Each lifting assembly (211) includes a drum (2111), a wire rope (2112), a pulley (2113), and a hook (2114) connected in sequence. There are two wire ropes (2112), which are spaced apart 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 wire rope (2112) and is used to drive the wire rope (2112) to wind up or unwind, thereby driving the pulley (2113) and the hook (2114) to move up and down.

9. The aircraft engine test system 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 designed as "I"-shaped structures. The crane (21) is equipped with a double hook drive assembly, which is used to engage the 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).

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