A new type of rotatable aero-engine disassembly platform

Abstract

This invention belongs to the field of aviation equipment technology, specifically relating to a novel rotatable aircraft engine disassembly platform. The platform includes an engine casing comprising an upper casing and a lower casing, with a transition plate fixed to the top of the upper casing. The disassembly mechanism includes a connecting flange and a magnetic heater. The connecting flange is connected to the top flange of the transition plate, and the top of the connecting flange is rotatably connected to a threaded push rod. The interior of the threaded push rod is rotatably connected to a swing arm rotation shaft, and the interior of the connecting flange is slidably connected to a connecting cylinder. The bottom of the connecting cylinder is fixedly connected to a thrust transition cylinder, and the bottom of the thrust transition cylinder is fixedly connected to the magnetic heater. The interior of the thrust transition cylinder is rotatably connected to multiple push rods, which are arranged in an array along the center of the thrust transition cylinder. This invention can simultaneously apply disassembly force to both the upper and lower casings of the engine, ensuring that the casing is not damaged during disassembly, improving disassembly efficiency, and reducing safety hazards.

Description

Technical Field

[0001] This utility model belongs to the field of aviation equipment technology, specifically relating to a novel rotatable aircraft engine disassembly platform. Background Technology

[0002] An aero engine is a highly complex and precise thermodynamic machine. As the heart of an aircraft, it not only powers flight but also serves as a vital driving force for the development of the aviation industry. After more than a century of development, aero engines have become highly reliable and mature products. Due to the special operating conditions of aero engines, the manufacturing process often requires interference fits, which makes disassembly during future maintenance difficult. At the same time, aero engines are expensive, and the disassembly process must ensure that they are not damaged.

[0003] Existing disassembly devices use conventional mechanical pulling methods, which are difficult and time-consuming to disassemble. During the disassembly process, they are also prone to damaging the internal parts and surfaces of the parts. This not only renders the disassembled parts unusable but also wastes resources, reduces maintenance efficiency, increases costs and maintenance workload, and lengthens the disassembly and maintenance cycle. Utility Model Content

[0004] The purpose of this invention is to provide a novel rotatable aircraft engine disassembly platform. By heating the engine connection, the material yield strength is reduced, frictional resistance is decreased, and disassembly efficiency is improved. Furthermore, the pull-down and push-up mechanisms can simultaneously separate the upper and lower outer shells, reducing stress concentration caused by traditional prying and ensuring that the outer shell is not damaged during disassembly, thus reducing safety hazards.

[0005] The specific technical solution adopted by this utility model is as follows: A novel rotatable aircraft engine dismantling platform includes an engine housing, which comprises an upper housing and a lower housing, with an interference fit between the upper housing and the lower housing, and a transition plate fixed to the top of the upper housing. The disassembly mechanism includes a connecting flange and a magnetic heater. The connecting flange is connected to the top flange of the transition plate. The top of the connecting flange is fixedly connected to a tension / compression sensor. The interior of the tension / compression sensor is rotatably connected to a threaded push rod. The interior of the threaded push rod is rotatably connected to a swing arm rotation shaft. The interior of the connecting flange is slidably connected to a connecting cylinder. The bottom of the connecting cylinder is fixedly connected to a thrust transition cylinder. The bottom of the thrust transition cylinder is fixedly connected to the magnetic heater. The interior of the thrust transition cylinder is rotatably connected to multiple push rods, which are arranged in an array along the center of the thrust transition cylinder.

[0006] Furthermore, the upper end of the threaded push rod is provided with a threaded section, which is threadedly connected to the tension / compression sensor, and a thrust bearing is assembled between the lower end of the threaded push rod and the thrust transition cylinder.

[0007] Furthermore, the magnetic heater is electrically connected to the temperature measuring pendulum, the temperature measuring pendulum is rotatably connected to the outer side of the thrust transition cylinder, and the temperature measuring pendulum is fixedly connected to the temperature sensor.

[0008] Furthermore, a sliding groove is provided on the outer side of the connecting flange, and the interior of the sliding groove is slidably connected to the temperature measuring swing rod.

[0009] Furthermore, a limit bearing is fitted between the lower end of the swing arm rotating shaft and the thrust transition cylinder, and the bottom of the swing arm rotating shaft is fixedly connected to the drive gear.

[0010] Furthermore, the bottom of each push rod is fixedly connected to the driven teeth, and the driven teeth are respectively engaged with the driving teeth.

[0011] The technical effects achieved by this utility model are as follows: This utility model discloses a novel rotatable aircraft engine disassembly platform. By heating the connection points of the engine casing, the yield strength of the material is reduced, effectively decreasing the frictional resistance at the connection points and significantly improving disassembly efficiency. Simultaneously, through the cooperation of a threaded push rod and a connecting flange, a thrust transition cylinder and a push rod are used to apply thrust to the lower casing while simultaneously applying tension to the upper casing. This upward and downward pushing action allows for the simultaneous separation of the upper and lower casings, reducing stress concentration caused by traditional prying methods and avoiding damage to the casing caused by traditional prying methods. This reduces safety hazards and maximizes the protection of engine components, facilitating subsequent maintenance and reuse. Attached Figure Description

[0012] Figure 1 This is a schematic diagram of the overall structure of this practical application; Figure 2 This is a partial sectional view of the overall structure of this utility model; Figure 3 This is a practical book Figure 2 Enlarged view of point A in the middle; Figure 4 This is a practical book Figure 2 Enlarged view of point B in the middle; Figure 5 This is a schematic diagram of the disassembly and separation of the casing of this utility model.

[0013] The attached diagram lists the components represented by each number as follows: 10. Engine housing; 11. Upper housing; 12. Lower housing; 13. Transition plate; 20. Disassembly mechanism; 21. Connecting flange; 211. Tension / compression sensor; 212. Connecting cylinder; 213. Thrust transition cylinder; 22. Magnetic heater; 221. Temperature measuring swing arm; 23. Threaded push rod; 231. Threaded section; 24. Swing arm rotation shaft; 241. Drive gear; 25. Push rod; 251. Driven gear. Detailed Implementation

[0014] To make the objectives and advantages of this utility model clearer, the following detailed description is provided in conjunction with embodiments. It should be understood that the following text is merely used to describe one or more specific implementations of this utility model and does not strictly limit the scope of protection specifically claimed by this utility model.

[0015] like Figures 1 to 5 As shown, a novel rotatable aircraft engine dismantling platform includes an engine housing 10, which includes an upper housing 11 and a lower housing 12. The upper housing 11 and the lower housing 12 are interference-fitted together, and a transition plate 13 is fixed to the top of the upper housing 11. The disassembly mechanism 20 includes a connecting flange 21 and a magnetic heater 22. The connecting flange 21 is connected to the top flange of the transition plate 13. The top of the connecting flange 21 is fixedly connected to a tension / compression sensor 211. The interior of the tension / compression sensor 211 is rotatably connected to a threaded push rod 23. The interior of the threaded push rod 23 is rotatably connected to a swing arm rotation shaft 24. The interior of the connecting flange 21 is slidably connected to a connecting cylinder 212. The bottom of the connecting cylinder 212 is fixedly connected to a thrust transition cylinder 213. The bottom of the thrust transition cylinder 213 is fixedly connected to the magnetic heater 22. The outer side of the thrust transition cylinder 213 is rotatably connected to multiple push rods 25. The multiple push rods 25 are arranged in an array along the center of the thrust transition cylinder 213.

[0016] In this embodiment, it should be noted that all operations after the disassembly mechanism 20 enters the engine housing 10 require visual assistance from a micro probe (not shown in the figure). The magnetic heater 22 is an electromagnetic heater that converts electrical energy into electromagnetic energy, and then back into electrical energy. This electrical energy is then converted into heat energy within the metal, thereby heating the connection points of the engine housing 10. This is a conventional technique and will not be elaborated upon further. When the connection points of the engine housing 10 are heated to the disassembly temperature, the rocker arm rotating shaft 24 drives the push rod 25 to... The internal structure unfolds, allowing the bottom of the push rod 25 to effectively contact the top of the lower housing 12. Simultaneously, by rotating the threaded push rod 23 in conjunction with the tension / compression sensor 211, power is generated by the connecting flange 21 and the tension / compression sensor 211. This power is then transmitted to the thrust transition cylinder 213 through the bottom of the threaded push rod 23. The thrust transition cylinder 213 then drives the push rod 25 to press down on the lower housing 12, while simultaneously generating a reaction force that pulls the upper housing 11 upward. This completes the separation of the upper housing 11 from the lower housing 12, effectively improving disassembly efficiency and reducing safety hazards.

[0017] like Figure 2 , Figure 3 As shown, the upper end of the threaded push rod 23 has a threaded section 231, and the threaded section 231 is threadedly connected to the tension and pressure sensor 211. When the threaded push rod 23 is rotated, the threaded section 231 and the tension and pressure sensor 211 are engaged in threaded action, thereby generating power. Since the lower end of the threaded push rod 23 is equipped with a thrust bearing between it and the thrust transition cylinder 213, the power is applied to the thrust transition cylinder 213, which in turn drives the bottom push rod 25 to act on the lower housing 12.

[0018] like Figure 1 , Figure 5 As shown, the magnetic heater 22 is electrically connected to the temperature measuring swing rod 221, the temperature measuring swing rod 221 is rotatably connected to the outer side of the thrust transition cylinder 213, and the temperature measuring swing rod 221 is fixedly connected to the temperature sensor.

[0019] Preferably, a sliding groove is provided on the outer side of the connecting flange 21, and the inside of the sliding groove is slidably connected to the temperature measuring swing rod 221.

[0020] In this embodiment, when the magnetic heater 22 is located inside the engine housing 10, the temperature measuring lever 221 is rotated in the sliding groove by moving the lever 221, which in turn drives the temperature sensor at the bottom to rotate, bringing the temperature sensor closer to the magnetic heater 22 and controlling the magnetic heater 22 to start conducting electricity. This allows the magnetic heater 22 to begin heating the interference fit of the engine housing 10. The temperature sensor monitors the heating temperature. When the specified disassembly temperature is reached, the temperature measuring lever 221 is moved to reset, and the threaded push rod 23 is rotated through the connecting cylinder 212 and the thrust transition cylinder 213 to drive the temperature measuring lever 221 to slide vertically in the sliding groove.

[0021] like Figure 2 , Figure 4 As shown, a limit bearing is installed between the lower end of the swing arm rotating shaft 24 and the thrust transition cylinder 213, and the bottom of the swing arm rotating shaft 24 is fixedly connected to the drive gear 241; the limit bearing ensures that the swing arm rotating shaft 24 can be stably driven to move when the thrust transition cylinder 213 moves.

[0022] Preferably, the bottom of each push rod 25 is fixedly connected to the driven tooth 251, and the driven tooth 251 is respectively engaged with the drive tooth 241. Specifically, when the push rod 25 needs to be unfolded, the drive tooth 241 at the bottom is driven by rotating the swing arm rotation shaft 24, so that the drive tooth 241 and the driven tooth 251 engage, driving the driven tooth 251 and the push rod 25 to rotate, so that multiple push rods 25 unfold at the same time, thereby ensuring that the thrust can be evenly applied to the lower housing 12.

[0023] The working principle of this utility model is as follows: The disassembly mechanism 20 is placed inside the engine housing 10, and the connecting flange 21 is connected to the transition plate 13 on the top of the upper housing 11. Then, the magnetic heater 22 is controlled by moving the temperature-sensing lever 221 to heat the housing connection, while the heating temperature is monitored by a temperature sensor. When the temperature at the housing connection reaches the disassembly temperature, the temperature-sensing lever 221 is retracted, and the swing arm rotation shaft 24 is rotated, causing the drive gear 241 to mesh with the driven gear 251 at the bottom of the push rod 25, simultaneously driving multiple push rods 25 to unfold, ensuring a uniform thrust is applied to the lower housing 12; this completes the disassembly process. After the rod 25 is unfolded, the threaded push rod 23 is rotated to engage with the tension and pressure sensor 211 on the top of the connecting flange 21, thereby generating power to drive the connecting cylinder 212 and the thrust transition cylinder 213 to descend. This also stably drives the internal push rod 25 to act on the lower housing 12, thereby applying a reaction force through the connecting flange 21 and the tension and pressure sensor 211, pulling the transition plate 13 and the upper housing 11. The thrust transition cylinder 213 and the push rod 25 at the bottom push the lower housing 12, so that the force is applied synchronously to the interference fit, ensuring effective disassembly of the engine housing 10, reducing the probability of damage, and improving disassembly efficiency.

[0024] The above description is merely a preferred embodiment of this utility model. It should be noted that those skilled in the art can make various improvements and modifications without departing from the principles of this utility model, and these improvements and modifications should also be considered within the scope of protection of this utility model. Structures, devices, and operating methods not specifically described or explained in this utility model, unless otherwise specified or limited, shall be implemented using conventional methods in the field.

Claims

1. A new and novel rotatable aircraft engine teardown platform, characterized by: Includes an engine housing (10), which includes an upper housing (11) and a lower housing (12), the upper housing (11) and the lower housing (12) being interference-fitted together, and a transition plate (13) being fixed to the top of the upper housing (11). The disassembly mechanism (20) includes a connecting flange (21) and a magnetic heater (22). The connecting flange (21) is connected to the top flange of the transition plate (13). The top of the connecting flange (21) is fixedly connected to a tension / compression sensor (211). The inside of the tension / compression sensor (211) is rotatably connected to a threaded push rod (23). The inside of the threaded push rod (23) is rotatably connected to a swing arm rotation shaft (24). The inside of the connecting flange (21) is slidably connected to a connecting cylinder (212). The bottom of the connecting cylinder (212) is fixedly connected to a thrust transition cylinder (213). The bottom of the thrust transition cylinder (213) is fixedly connected to the magnetic heater (22). The outside of the thrust transition cylinder (213) is rotatably connected to multiple push rods (25). The multiple push rods (25) are arranged in an array along the center of the thrust transition cylinder (213).

2. A rotatable novel aero-engine disassembly platform according to claim 1, characterized in that: The upper end of the threaded push rod (23) is provided with a threaded section (231), the threaded section (231) is threadedly connected to the tension and compression sensor (211), and a thrust bearing is assembled between the lower end of the threaded push rod (23) and the thrust transition cylinder (213).

3. A rotatable novel aero-engine disassembly platform according to claim 1, characterized in that: The magnetic heater (22) is electrically connected to the temperature measuring rod (221), the temperature measuring rod (221) is rotatably connected to the outside of the thrust transition cylinder (213), and the temperature measuring rod (221) is fixedly connected to the temperature sensor.

4. The novel rotatable aero-engine dismantling platform according to claim 3, characterized in that: The outer side of the connecting flange (21) is provided with a sliding groove, and the inside of the sliding groove is slidably connected to the temperature measuring swing rod (221).

5. A rotatable novel aero-engine disassembly platform according to claim 1, characterized in that: A limit bearing is fitted between the lower end of the swing arm rotating shaft (24) and the thrust transition cylinder (213), and the bottom of the swing arm rotating shaft (24) is fixedly connected to the drive gear (241).

6. A novel rotatable aero-engine dismantling platform according to claim 5, characterized in that: The bottom of each push rod (25) is fixedly connected to the driven tooth (251), and the driven tooth (251) is engaged with the drive tooth (241) respectively.

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