An aircraft engine auxiliary assembly and handling device

Abstract

The utility model discloses an airplane engine auxiliary assembly and carrying device, including base mounting panel, shaft sleeve and driving gear, the base mounting panel is connected with the adapter plate through bolt, the shaft sleeve is cooperated with the small gap of cylindrical roller bearing inner race, the cylindrical roller bearing outer ring is prevented from the shift of cylindrical roller bearing outer ring by the press of check ring, the check ring is connected with bearing seat through bolt, the bearing seat is connected through bolt between the connecting seat, this airplane engine auxiliary assembly and carrying device in preparation stage, firm connection each part, ensure that the assembly basis is stable, avoid the assembly error of loose, accurate fit engine parts when positioning, improve assembly accuracy, reduce the positioning deviation, the manual rotation installation of part assembly process is convenient and efficient, satisfy the high accuracy requirement, when moving and turning, motor drive is nimble, and turning is stable, and the transportation efficiency is improved, and the real -time guardianship of regional sensor prevents the safety accidents such as knock.

Description

Technical Field

[0001] This utility model relates to the field of high-precision engine assembly and engine material conveying production technology, specifically an auxiliary assembly and handling device for aircraft engines. Background Technology

[0002] An aircraft engine is an engine that provides the power needed for an aircraft to fly. There are three main types: piston-engine aircraft engines... Engines include gas turbine engines and ramjet engines. Piston aircraft engines were the earliest type of aircraft engine used in airplanes and helicopters to drive propellers or rotors. Large piston aircraft engines could reach power outputs of 2500 kilowatts. They were later replaced by high-power, high-speed gas turbine engines. However, lower-power piston aircraft engines are still widely used in light aircraft, helicopters, and ultralight aircraft. Gas turbine engines are the most widely used type of engine. They include turbojet engines, turbofan engines, turboprop engines, and turboshaft engines, all of which have a compressor, combustion chamber, and gas turbine. In real-world aircraft engine assembly scenarios, the efficiency of material handling and assembly processes is a significant issue. Engine assembly involves numerous precision components, and currently, materials are mostly moved between different workstations using transfer devices. This transfer process is not only time-consuming but also prone to problems such as material collisions and positioning deviations due to factors like device precision and space limitations. After the materials are in place, various auxiliary equipment, such as specialized fixtures and positioning tooling, are needed to complete the assembly. The poor coordination between these devices and the complexity of the operation further extend the assembly cycle. Therefore, we propose an auxiliary assembly and handling device for aircraft engines to address the aforementioned problems. Utility Model Content

[0003] The purpose of this utility model is to provide an auxiliary assembly and handling device for aircraft engines, so as to solve the problems of poor connection and complicated operation between various equipment of aircraft engines mentioned in the background art.

[0004] To achieve the purpose of this utility model, the utility model is implemented through the following technical solution: an auxiliary assembly and handling device for an aircraft engine, including a base mounting plate, a bushing, and a drive gear; The base mounting plate is connected to the adapter plate by bolts. The bushing is fitted with the inner ring of the cylindrical roller bearing with a small clearance. The outer ring of the cylindrical roller bearing is pressed by a limiting ring to prevent the outer ring of the cylindrical roller bearing from moving. The limiting ring is connected to the bearing housing by bolts. The bearing housing and the connecting seat are connected by bolts. An adjusting shim is provided between the bearing housing and the connecting seat. The connecting seat is connected to the base mounting plate by bolts. The connecting seat is connected to the assembly seat by bolts to form an integral tooling component. The drive gear is bolted together with an external gear motor and a reducer. The drive gear drives the driven gear to rotate through the rotation of the external gear motor and the reducer. The driven gear is connected to the bottom caster to form a set of components. The driven gear assembly is bolted to the bottom mounting plate. The omnidirectional caster is bolted to the middle mounting plate. Multiple sets of area sensors are bolted to the bottom mounting plate.

[0005] A further improvement is that the bushing is connected to the inner ring of the cylindrical roller bearing to form a single component, and the end face of the bushing is in close contact with the engine rotor and can be adjusted to the corresponding working position by manual rotation.

[0006] A further improvement is made by placing an adjusting shim between the bearing housing and the connecting seat. The adjusting shim is made of alloy structural steel and undergoes secondary processing to achieve the final installation accuracy requirements.

[0007] A further improvement is that a drive motor is provided on the side of the bottom caster to control the movement of the entire trolley. The external gear motor and reducer drive the drive gear, thereby causing the driven gear to rotate, while the bottom caster performs steering movement.

[0008] A further improvement is that multiple sets of the area sensors are respectively installed at the four corners of the bottom mounting plate, and the area sensors are electrically connected to the external control system.

[0009] A further improvement is that the outer ring of the cylindrical roller bearing is interference-fitted with the bearing housing, and the bushing and the cylindrical roller bearing form an assembly.

[0010] Compared with the prior art, the beneficial effects of this utility model are as follows: During the preparation stage, the aircraft engine auxiliary assembly and handling device firmly connects the various components to ensure the stability of the assembly foundation and avoid assembly errors caused by loosening. During positioning, it accurately fits the engine components, improves the assembly accuracy, and reduces positioning deviation. The manual rotation installation during the parts assembly process is convenient and efficient, meeting high precision requirements. When moving and turning, the motor drive is flexible and the steering is smooth, improving the transfer efficiency. At the same time, the area sensors provide real-time protection to prevent safety accidents such as collisions. Attached Figure Description

[0011] Figure 1 This is a half-sectional view of the present invention.

[0012] In the diagram: 1. Mounting plate; 2. Adapter plate; 3. Bushing; 4. Cylindrical roller bearing; 5. Limit ring; 6. Bearing housing; 7. Adjusting shim; 8. Connecting seat; 9. Assembly seat; 10. Drive gear; 11. Reducer; 12. Area sensor; 13. Driven gear; 14. Bottom caster; 15. Bottom mounting plate; 16. Universal caster; 17. Middle mounting plate. Detailed Implementation

[0013] The technical solutions of the present utility model will be clearly and completely described below with reference to the accompanying drawings of the embodiments. Obviously, the described embodiments are only some embodiments of the present utility model, and not all embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the protection scope of the present utility model.

[0014] Please see Figure 1 This utility model provides a technical solution: an auxiliary assembly and handling device for an aircraft engine, comprising a base mounting plate 1, a bushing 3, and a drive gear 10; The base mounting plate 1 is connected to the adapter plate 2 by bolts. The bushing 3 is fitted with the inner ring of the cylindrical roller bearing 4 with a small clearance. The outer ring of the cylindrical roller bearing 4 is pressed by the limiting ring 5 to prevent the outer ring of the cylindrical roller bearing 4 from moving. The limiting ring 5 is connected to the bearing housing 6 by bolts. The bearing housing 6 and the connecting seat 8 are connected by bolts. An adjusting shim 7 is provided between the bearing housing 6 and the connecting seat 8. The connecting seat 8 is connected to the base mounting plate 1 by bolts. The connecting seat 8 is connected to the assembly seat 9 by bolts to form an integral tooling component. The bushing 3 is connected to the inner ring of the cylindrical roller bearing 4 to form a component. The end face of the bushing 3 is in close contact with the engine rotor and can be adjusted to the corresponding working position by manual rotation. An adjusting shim 7 is placed between the bearing housing 6 and the connecting seat 8. The adjusting shim 7 is made of alloy structural steel and is processed by secondary machining to obtain the final installation accuracy requirements. The outer ring of the cylindrical roller bearing 4 is interference-fitted with the bearing housing 6. The bushing 3 and the cylindrical roller bearing 4 form an assembly. During use, the base mounting plate 1 is securely connected to the adapter plate 2 with bolts to ensure that the bushing 3 and the inner ring of the cylindrical roller bearing 4 have a small clearance fit. After the outer ring of the bearing is pressed by the limit ring 5, the outer cylindrical surface of the adapter plate 2 is used to position and install the bearing with the stator housing of the aero-engine. The end face of the bushing 3 is tightly attached to the engine rotor. The bearing is adjusted to the working position by manual rotation, so that the corresponding position can be manually rotated to install other parts inside the aero-engine in sequence, meeting the high-precision assembly requirements. The drive gear 10 is bolted together with the external gear motor and the reducer 11. The drive gear 10 drives the driven gear 13 to rotate through the rotation of the external gear motor and the reducer 11. The driven gear 13 is connected to the bottom caster 14 to form a set of components. The driven gear 13 assembly is bolted to the bottom mounting plate 15. The swivel caster 16 is bolted to the middle mounting plate 17. Multiple sets of area sensors 12 are bolted to the bottom mounting plate 15. The bottom caster 14 has a drive motor on its side to control the movement of the entire trolley. The external gear motor and the reducer 11 drive the drive gear 10 to rotate the driven gear 13. At the same time, the bottom caster 14 performs steering movement. Multiple sets of area sensors 12 are installed at the four corners of the bottom mounting plate 15. The area sensors 12 are electrically connected to the external control system. Meanwhile, during use, the overall movement is controlled by the drive motor of the bottom caster 14. The external gear motor and reducer 11 drive the drive gear 10 to drive the driven gear 13 and the bottom caster 14 to turn. At the same time, during the movement, multiple sets of area sensors 12 monitor the position of the four corners of the bottom mounting plate 15 in real time to ensure the safety of the device during movement and assembly.

[0015] Working Principle: When using the aircraft engine auxiliary assembly and handling device, the base mounting plate 1 is securely connected to the adapter plate 2 with bolts to ensure a small clearance fit between the bushing 3 and the inner ring of the cylindrical roller bearing 4. After the bearing outer ring is pressed by the limit ring 5, the outer cylindrical surface of the adapter plate 2 is used to position and install the device against the stator housing of the aircraft engine. The end face of the bushing 3 is tightly attached to the engine rotor. The device is manually rotated to the working position, allowing manual rotation of the corresponding position to install other parts inside the aircraft engine in sequence, meeting the high-precision assembly requirements. During use, the overall movement is controlled by the drive motor of the bottom casters 14. The external gear motor and reducer 11 drive the drive gear 10 to drive the driven gear 13 and the bottom casters 14 to rotate. At the same time, multiple sets of area sensors 12 monitor the position of the four corners of the bottom mounting plate 15 in real time during the movement, ensuring the safety of the device during movement and assembly, thereby completing a series of tasks. The contents not described in detail in this specification are existing technologies known to those skilled in the art.

[0016] It will be apparent to those skilled in the art that this invention is not limited to the details of the exemplary embodiments described above, and that it can be implemented in other specific forms without departing from the spirit or essential characteristics of this invention. Therefore, the embodiments should be considered illustrative and non-limiting in all respects, and the scope of this invention is defined by the appended claims rather than the foregoing description. Thus, it is intended that all variations falling within the meaning and scope of equivalents of the claims be included within this invention. No reference numerals in the claims should be construed as limiting the scope of the claims.

Claims

1. An auxiliary assembly and handling device for an aircraft engine, comprising a base mounting plate (1), a bushing (3), and a drive gear (10). Its features are: The base mounting plate (1) is connected to the adapter plate (2) by bolts. The bushing (3) is fitted with the inner ring of the cylindrical roller bearing (4) with a small clearance. The outer ring of the cylindrical roller bearing (4) is pressed by the limiting ring (5) to prevent the outer ring of the cylindrical roller bearing (4) from moving. The limiting ring (5) is connected to the bearing seat (6) by bolts. The bearing seat (6) and the connecting seat (8) are connected by bolts. An adjusting shim (7) is provided between the bearing seat (6) and the connecting seat (8). The connecting seat (8) is connected to the base mounting plate (1) by bolts. The connecting seat (8) is connected to the assembly seat (9) by bolts to form an integral tooling component. The drive gear (10) is bolted together with an external gear motor and a reducer (11). The drive gear (10) drives the driven gear (13) to rotate by the rotation of the external gear motor and the reducer (11). The driven gear (13) is connected to the bottom caster (14) to form a set of components. The driven gear (13) assembly is bolted to the bottom mounting plate (15). The omnidirectional caster (16) is bolted to the middle mounting plate (17). Multiple sets of area sensors (12) are bolted to the bottom mounting plate (15).

2. The aircraft engine auxiliary assembly and handling device according to claim 1, characterized in that, The bushing (3) is connected to the inner ring of the cylindrical roller bearing (4) to form a component. The end face of the bushing (3) is in close contact with the engine rotor and can be adjusted to the corresponding working position by manual rotation.

3. The aircraft engine auxiliary assembly and handling device according to claim 1, characterized in that, An adjusting shim (7) is placed between the bearing housing (6) and the connecting seat (8). The adjusting shim (7) is made of alloy structural steel and is processed through secondary processing to achieve the final installation accuracy requirements.

4. The aircraft engine auxiliary assembly and handling device according to claim 1, characterized in that, The bottom caster (14) is equipped with a drive motor on its side to control the movement of the whole trolley. The external gear motor and reducer (11) drive the drive gear (10) to drive the driven gear (13) to rotate, while the bottom caster (14) performs a steering movement.

5. The aircraft engine auxiliary assembly and handling device according to claim 1, characterized in that, Multiple sets of the area sensors (12) are respectively installed at the four corners of the bottom mounting plate (15), and the area sensors (12) are electrically connected to the external control system.

6. The aircraft engine auxiliary assembly and handling device according to claim 1, characterized in that, The outer ring of the cylindrical roller bearing (4) is interference-fitted with the bearing housing (6), and the bushing (3) and the cylindrical roller bearing (4) form an assembly.

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