Aircraft engine bearing removal tool

Abstract

The utility model discloses an aero-engine bearing dismounting tool, include: the upper ring, a plurality of even distribution and all with the upper ring fixed connection's metal elastic arm and with a plurality of metal elastic arm's inside contact and can drive a plurality of metal elastic arm to move away from the end part of the upper ring and the tension ring of dispersing, the end of each metal elastic arm away from the upper ring all is provided with the arc force part of inclining away from the upper ring axis, and the inner wall of bearing outer ring is protruding and has the protruding part, and this tool is just using the structural characteristics of bearing no.

Description

Technical Field

[0001] This utility model relates to the technical field of aircraft engine bearing disassembly, specifically to an aircraft engine bearing disassembly tool. Background Technology

[0002] The No. 3 bearing on an aero-engine is located in the core section, specifically between the rear end of the high-pressure compressor and the front end of the high-pressure turbine. It supports the tail of the high-pressure rotor. The No. 3 bearing bears the radial loads (gravity, inertial forces, etc.) and axial loads (gas thrust) of the high-pressure rotor, ensuring that the high-pressure turbine and high-pressure compressor maintain precise concentricity and position during high-speed rotation. The No. 3 bearing transfers the loads it bears to the main load-bearing casing of the engine and is a key support point for maintaining the dynamic stability of the high-pressure rotor.

[0003] When repairing an aircraft engine, the No. 3 bearing is located in a special position and there is no leverage point during disassembly. During maintenance, the No. 3 bearing and surrounding components are usually disassembled as a whole. However, during the disassembly process, the No. 3 bearing will be slightly damaged. Such damage is unacceptable. If it is replaced, the cost will be high and the maintenance cycle will be long.

[0004] The No. 3 bearing typically consists of an outer bearing ring, an upper inner bearing ring, a lower inner bearing ring, and several balls mounted on the outer bearing ring. When disassembling, the upper inner bearing ring can be easily removed, but there is no leverage point when disassembling the outer bearing ring, making disassembly difficult. If other common tools, such as screwdrivers, are used for prying, it will not only be inconvenient to use, but will also cause irreversible damage to the outer bearing ring. Therefore, a special disassembly tool for aero-engine bearings is needed. Utility Model Content

[0005] In view of the above-mentioned technical problems, the purpose of this utility model is to overcome the problem of inconvenient disassembly of the outer ring of the No. 3 bearing in the existing technology of aero-engines.

[0006] To achieve the above objectives, this utility model provides an aircraft engine bearing disassembly tool, comprising: an upper ring, several metal spring arms evenly distributed along the circumference of the upper ring and fixedly connected to the upper ring, and a tensioning ring that contacts the inner side of the several metal spring arms and can drive the ends of the several metal spring arms away from the upper ring to disperse when moving away from the upper ring. Each metal spring arm has an arc-shaped force-bearing part that is inclined away from the axis of the upper ring at its end away from the upper ring.

[0007] Preferably, the upper surface of the arc-shaped force-bearing part is fitted with a rubber pad.

[0008] Preferably, the tensioning ring is equipped with at least one first handle, which passes through the space between two adjacent metal spring arms.

[0009] Preferably, at least one second handle is fitted on the upper ring, and the second handle is located on the outside of the upper ring.

[0010] Preferably, the upper end of the metal spring arm is assembled to the upper ring by a number of mounting bolts.

[0011] Preferably, the metal spring arm has a limiting part protruding on the side near the upper ring axis, which is located near the arc-shaped force-bearing part.

[0012] Preferably, the width of the metal spring arm gradually increases from the arc-shaped force-bearing part toward the upper ring.

[0013] Preferably, the cross-section of the metal spring arm is arc-shaped, and the curvature of the metal spring arm gradually increases from the upper ring toward the arc-shaped force-bearing part.

[0014] According to the above technical solution, the beneficial effects of the aircraft engine bearing disassembly tool provided by this utility model in use are as follows: The inner wall of the bearing outer ring has protrusions. This tool utilizes the structural features of the No. 3 bearing to easily remove the bearing outer ring. Manually hold and squeeze several metal spring arms, causing the lower ends of the metal spring arms to converge and deform. This allows the arc-shaped force-bearing part to pass through the space between the bearing outer ring and the lower bearing inner ring and contact the lower surface of the protrusions. Then, push the tension ring downward to keep the metal spring arms open. Pull the upper ring upward, and apply tension to the bearing outer ring through the arc-shaped force-bearing part, thereby pulling the bearing outer ring upward. The operation is simple and convenient and will not damage the bearing outer ring.

[0015] Other features and advantages of this utility model will be described in detail in the following detailed description section; and all parts not covered in this utility model are the same as or can be implemented using existing technology. Attached Figure Description

[0016] The accompanying drawings are provided to further illustrate the present invention and form part of the specification. They are used together with the following detailed description to explain the present invention, but do not constitute a limitation thereof. In the drawings: Figure 1 This is a three-dimensional structural diagram of the aircraft engine bearing disassembly tool provided in this utility model during use; Figure 2 This is a three-dimensional structural diagram of a tool for disassembling aircraft engine bearings provided in this utility model. Figure 1 ; Figure 3 This is a three-dimensional structural diagram of a tool for disassembling aircraft engine bearings provided in this utility model. Figure 2 ; Figure 4This is a partial perspective view of the use of an aircraft engine bearing disassembly tool provided in this utility model.

[0017] Explanation of reference numerals in the attached figures 1. Upper ring; 2. Metal spring arm; 3. Tensioning ring; 4. Arc-shaped force-bearing part; 5. First handle; 6. Second handle; 7. Mounting bolt; 8. Limiting part; 9. Bearing outer ring; 10. Ball; 11. Protrusion; 12. Lower bearing inner ring. Detailed Implementation

[0018] The specific embodiments of this utility model will be described in detail below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are for illustration and explanation only and are not intended to limit the scope of this utility model.

[0019] In this utility model, unless otherwise stated, directional words such as "upper," "lower," "inner," and "outer" included in the terminology only represent the orientation of the term in its conventional use or are common terms understood by those skilled in the art, and should not be regarded as limitations on the term.

[0020] like Figure 1-4 As shown, an aircraft engine bearing disassembly tool includes: an upper ring 1, several metal spring arms 2 evenly distributed along the circumference of the upper ring 1 and fixedly connected to the upper ring 1, and a tensioning ring 3 that contacts the inner side of the several metal spring arms 2 and can drive the ends of the several metal spring arms 2 away from the upper ring 1 to disperse when moving away from the upper ring 1. Each metal spring arm 2 is provided with an arc-shaped force part 4 that is inclined away from the axis of the upper ring 1 at its end away from the upper ring 1.

[0021] In the above technical solution, a protrusion 11 protrudes from the inner wall of the outer ring 9 of the bearing. This tool utilizes the structural features of the No. 3 bearing itself to easily remove the outer ring 9 of the bearing. By manually holding and squeezing several metal spring arms 2, the lower ends of several metal spring arms 2 are gathered and deformed, and several arc-shaped force parts 4 move close to the axis of the upper ring 1, so that several arc-shaped force parts 4 can pass through the space between the outer ring 9 of the bearing and the inner ring 12 of the lower bearing. Then, by releasing several metal spring arms 2, the metal spring arms 2 return to their original shape, and the arc-shaped force parts 4 will move to directly below the protrusion 11 on the inner wall of the outer ring 9 of the bearing. Then push the tension ring 3 downward, and the tension ring 3 will press against the inner wall of several metal spring arms 2. The function of the tension ring 3 is to prevent the lower ends of several metal spring arms 2 from gathering together after being stressed when the upper ring 1 is pulled upward. The tension ring 3 keeps several metal spring arms 2 in a dispersed state. When the upper ring 1 is pulled upward, the arc-shaped force part 4 fits against the lower surface of the protrusion 11, and at the same time, it drives several metal spring arms 2 to move upward. The arc-shaped force part 4 applies a pulling force to the outer ring 9 of the bearing, thereby removing the outer ring 9 of the bearing from the mounting groove. The operation is simple and convenient, and will not damage the outer ring 9 of the bearing. When the metal spring arm is squeezed by a person, the displacement of the arc-shaped force part 4 at the lower end of the metal spring arm is within 1 cm. It is necessary to ensure the strength of the metal spring arm 2 and also to give the metal spring arm 2 a certain deformation capacity. Therefore, the thickness of the metal spring arm 2 is at least 0.5 mm. In actual operation, the force required to pull the outer ring 9 of the bearing upward is about 20 Newtons. Therefore, during the upward pulling process, the arc-shaped force-bearing part 4 will not slip off the protrusion 11 on the outer ring 9 due to the force. At the same time, through the action of the tension ring 3, even if the metal spring arm 2 deforms due to the force during the upward application of force, it will not slip off the protrusion 11. Because the applied pulling force is 20 Newtons, it will not cause the arc-shaped force-bearing part 4 on the lower end of the metal spring arm 2 to slip off and separate from the protrusion 11.

[0022] In a preferred embodiment of this utility model, a rubber pad is fitted on the upper surface of the arc-shaped force-bearing part 4.

[0023] In the above technical solution, the rubber pad can prevent the arc-shaped force part 4 from scratching the protrusion 11. At the same time, the rubber pad can also increase the friction between the two, and reduce the relative sliding distance between the arc-shaped force part and the protrusion 11 when the upper ring 1 is pulled upward.

[0024] In a preferred embodiment of the present invention, at least one first handle 5 is mounted on the tensioning ring 3, and the first handle 5 passes through the space between two adjacent metal spring arms 2.

[0025] In the above technical solution, the first handle 5 can easily apply pressure to the tension ring 3, thereby pushing the tension ring 3 to move downward and open up several metal spring arms 2. The squeezing force between the metal spring arms 2 and the tension ring 3 can also increase the friction force, preventing the tension ring 3 and the metal spring arms 2 from sliding relative to each other during the upward pulling of the upper ring 1, thus improving the ease of use and comfort.

[0026] In a preferred embodiment of the present invention, at least one second handle 6 is fitted on the upper ring 1, and the second handle 6 is located on the outside of the upper ring 1.

[0027] In the above technical solution, the second handle 6 facilitates the application of pulling force to the upper ring 1, thereby improving ease of use and comfort.

[0028] In a preferred embodiment of this utility model, the upper end of the metal spring arm 2 is assembled onto the upper ring 1 by a plurality of mounting bolts 7.

[0029] In the above technical solution, after loosening and removing several mounting bolts 7, the metal spring arm 2 can be replaced, reducing maintenance costs and making the replacement operation simple and convenient.

[0030] In a preferred embodiment of this utility model, the metal spring arm 2 is provided with a limiting part 8 protruding from the side near the axis of the upper ring 1, which is located near the arc-shaped force part 4.

[0031] In the above technical solution, the limiting part 8 can limit the lowest position of the tension ring 3 moving downward. When the tension ring 3 is in contact with the limiting part 8 on several metal spring arms 2, the tension ring 3 is in a horizontal state. The horizontal state of the tension ring 3 can increase the contact area between the tension ring 3 and the inner wall of the metal spring arm 2, and improve the anti-slip performance. At the same time, the limiting part 8 also reduces the difficulty of pushing the tension ring 3 downward. There is no need to control the downward movement position of the tension ring 3. During operation, it is only necessary for the tension ring 3 to contact the limiting part 8 to know that the tension ring 3 has moved to the corresponding position.

[0032] In a preferred embodiment of this utility model, the width of the metal spring arm 2 gradually increases from the arc-shaped force part 4 toward the upper ring 1.

[0033] In the above technical solution, the width of the metal bullet arm 2 is set in a gradually changing manner, which can improve the strength of the metal bullet arm 2.

[0034] In a preferred embodiment of this utility model, the cross-section of the metal spring arm 2 is arc-shaped, and the curvature of the metal spring arm 2 gradually increases from the upper ring 1 toward the arc-shaped force part 4.

[0035] In the above technical solution, during the downward movement of the tension ring 3, the tension ring 3 will expand the inner wall of the metal spring arm 2, which can increase the force between the tension ring 2 and the metal spring arm, and prevent the tension ring 2 from moving during the upward pulling of the upper ring 1.

[0036] The preferred embodiments of the present invention have been described in detail above with reference to the accompanying drawings. However, the present invention is not limited to the specific details of the above embodiments. Within the scope of the technical concept of the present invention, various simple modifications can be made to the technical solution of the present invention, and these simple modifications all fall within the protection scope of the present invention.

[0037] It should also be noted that the various specific technical features described in the above specific embodiments can be combined in any suitable way without contradiction. In order to avoid unnecessary repetition, this utility model will not describe the various possible combinations separately.

[0038] Furthermore, various different embodiments of this utility model can be combined in any way, as long as they do not violate the spirit of this utility model, they should also be regarded as the content disclosed by this utility model.

Claims

1. A tool for disassembling aircraft engine bearings, characterized in that, include: The upper ring (1), several metal spring arms (2) evenly distributed along the circumference of the upper ring (1) and fixedly connected to the upper ring (1), and a tensioning ring (3) that contacts the inner side of the several metal spring arms (2) and can drive the ends of the several metal spring arms (2) away from the upper ring (1) when moving away from the upper ring (1). Each metal spring arm (2) is provided with an arc-shaped force part (4) that is inclined away from the axis of the upper ring (1) at its end away from the upper ring (1).

2. The aircraft engine bearing disassembly tool according to claim 1, characterized in that, The upper surface of the arc-shaped force-bearing part (4) is fitted with a rubber pad.

3. The aircraft engine bearing disassembly tool according to claim 1, characterized in that, At least one first handle (5) is fitted on the tensioning ring (3), and the first handle (5) passes through the space between two adjacent metal spring arms (2).

4. The aircraft engine bearing disassembly tool according to claim 1, characterized in that, At least one second handle (6) is fitted on the upper ring (1), and the second handle (6) is located on the outside of the upper ring (1).

5. The aircraft engine bearing disassembly tool according to claim 1, characterized in that, The upper end of the metal spring arm (2) is assembled onto the upper ring (1) by a number of mounting bolts (7).

6. The aircraft engine bearing disassembly tool according to claim 1, characterized in that, The metal spring arm (2) has a limiting part (8) protruding on one side near the axis of the upper ring (1) and located near the arc-shaped force part (4).

7. The aircraft engine bearing disassembly tool according to claim 1, characterized in that, The width of the metal spring arm (2) gradually increases from the arc-shaped force part (4) toward the upper ring (1).

8. The aircraft engine bearing disassembly tool according to claim 1, characterized in that, The cross-section of the metal spring arm (2) is arc-shaped, and the curvature of the metal spring arm (2) gradually increases from the upper ring (1) toward the arc-shaped force part (4).

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