A bevel gear disassembly device for an aeroengine

Abstract

The application provides an aero-engine bevel gear disassembling device, which comprises a support assembly formed by fixed connection of an upper support plate, a left side support plate, a right side support plate and a support bottom plate, and has a space for accommodating a bevel gear assembly inside; a hydraulic jack is fixed on the upper support plate and used for applying a disassembling force along an axial direction to the bevel gear; a reverse torsion rod is arranged at a lower end of the hydraulic jack, and an outer spline is arranged on an upper side outer surface of the reverse torsion rod and used for cooperating with an inner spline of the bevel gear to prevent the bevel gear from rotating circumferentially during disassembling; the lower end of the reverse torsion rod is a smooth structure and is used for cooperating with a reverse torsion rod adapter to make the bevel gear move along the axial direction during disassembling; a pressing plate is arranged on the reverse torsion rod and has a pressing part and a supporting part, the supporting part is fixedly arranged on a bevel gear support frame, and the pressing part presses a ball bearing inner ring; the reverse torsion rod adapter is fixed on the right side support plate and is provided with a guide groove at a position matched with the reverse torsion rod, and the reverse torsion rod is inserted into the guide groove.

Description

Technical Field

[0001] This invention belongs to the field of aero-engine technology, and specifically relates to an aero-engine bevel gear disassembly device. Background Technology

[0002] The bevel gear structure is a major transmission component of an aero-engine. Bevel gears are typically supported by two or three bearings, such as... Figure 1 and Figure 2 As shown, in the bevel gear assembly 10, the bevel gear 11 is mounted on the support frame 16 via a first rod bearing 12, a ball bearing 13, and a second rod bearing 14. The inner rings 131 of the first rod bearing 12 and the ball bearing 13 are of upper half structure 131A and lower half structure 131B. The inner rings of the second rod bearing 14 and the ball bearing 13 are both interference fit with the bevel gear 1. A spacer ring 15 is installed between the second rod bearing 14 and the ball bearing 13. The spacer ring 15 is fitted onto the bevel gear 11 and is clearance fit with the bevel gear 11. The bearings are locked on the outside of the first rod bearing 12 by a lock nut 17.

[0003] When disassembling the bevel gear assembly 10, the bearing clamping nut 17 needs to be unscrewed first, then the inner ring of the first bearing 12 needs to be separated, then the interference fit between the inner ring 131 of the ball bearing 13 and the bevel gear 11 needs to be overcome, and finally the bevel gear 11 needs to be separated.

[0004] However, due to the precise fit between the components, if the bevel gear 11 is disassembled by hammering, the hammering force will be transmitted to the ball bearing 13. The instability and unevenness of the hammering force may damage the ball bearing 13. Therefore, the disassembly force must be applied stably and evenly during the disassembly process. During disassembly, the bevel gear 11 must not rotate, and its disassembly path must be axial and free from deviation. Since the ball bearing 13 is under pressure during disassembly, if the bevel gear 11 deviates, it will cause localized pressure on the ball bearing 13. If the bevel gear 11 rotates, it will cause sliding friction between the inner ring 131 and the balls of the ball bearing 13, resulting in damage to the ball bearing 13. After the bevel gear 11 is disassembled, the balls of the ball bearing 13 will scatter, easily causing ball damage and rendering the bearing unusable, resulting in significant economic losses. Summary of the Invention

[0005] The purpose of this invention is to provide a disassembly device for bevel gears in aircraft engines, so as to solve or alleviate at least one of the problems in the prior art.

[0006] The technical solution of this invention is: a disassembly device for aero-engine bevel gears, comprising:

[0007] A support assembly is formed by fixing the upper support plate, the left support plate, the right support plate, and the support base plate together. The support assembly has a space inside to accommodate the bevel gear assembly.

[0008] A hydraulic jack, fixed to an upper support plate, is used to apply a decomposed force along the axial direction to the bevel gear.

[0009] An anti-torsion bar is provided at the lower end of the hydraulic jack, and the upper outer surface of the anti-torsion bar is provided with an external spline for engaging with the internal spline of the bevel gear to prevent the bevel gear from rotating circumferentially during disassembly. The lower end of the anti-torsion bar has a smooth structure for engaging with the anti-torsion bar transition section to allow the bevel gear to move axially during disassembly.

[0010] A pressure plate is disposed on an anti-torsion bar and has a pressing part with a diameter adapted to the inner ring of a ball bearing and a support part integrally connected to the pressing part. The support part is fixedly disposed on a bevel gear support frame, and the pressing part presses against the inner ring of the ball bearing.

[0011] The anti-torsion bar adapter section is fixed on the right support plate and has a guide groove at the position of the anti-torsion bar. The anti-torsion bar is inserted into the guide groove to prevent the bevel gear from rotating during the disassembly process, while ensuring that the bevel gear moves axially.

[0012] In at least one embodiment of the present invention, the left and right support plates are respectively provided with boss structures, and the boss structures are positioned with the two end stops of the bevel gear support frame to form a simply supported beam support.

[0013] In at least one embodiment of the present invention, the hydraulic jack is fixed to the upper support plate by a threaded structure.

[0014] In at least one embodiment of the present invention, the hydraulic jack has a digital pressure display function for displaying the pressure value of the hydraulic jack.

[0015] In at least one embodiment of the present invention, the axial length of the extrusion section is not less than the sum of the width of the first rod bearing and half the width of the ball bearing.

[0016] In at least one embodiment of the present invention, the cross-section of the guide groove includes a square or a regular hexagon.

[0017] The aircraft engine bevel gear disassembly device of the present invention has the following advantages:

[0018] 1) A hydraulic jack is used to apply a uniform disintegration force to the bevel gear along the axis of the bevel gear. The stability of the disintegration force during the disintegration process can be monitored in real time by displaying the pressure value of the hydraulic jack.

[0019] 2) By connecting the external spline at one end of the anti-torsion bar with the internal spline of the bevel gear, and connecting the other end with the anti-torsion bar adapter section fixed to the side plate, the rotation of the bevel gear during disassembly can be suppressed.

[0020] 3) The anti-torsion bar and the anti-torsion bar transition section are planar fits. During the disassembly process, the anti-torsion bar also plays a guiding role to prevent the bevel gear from deflecting.

[0021] 4) Design a pressure plate structure and fix it on the support frame. At the same time, apply pressure to the inner ring of the ball bearing to ensure that the inner ring of the ball bearing and the balls are evenly pressed together, so as to prevent the inner ring of the ball bearing and the balls from scattering after disassembly.

[0022] 5) The support frame of the bevel gear adopts a simple beam structure with a two-end stop structure and each support plate as a component to ensure more stable support during disassembly. Attached Figure Description

[0023] To more clearly illustrate the technical solution provided by the present invention, the accompanying drawings will be briefly described below. Obviously, the drawings described below are merely some embodiments of the present invention.

[0024] Figure 1 This is a schematic diagram of a bevel gear assembly in the prior art.

[0025] Figure 2 This is a schematic diagram of the disassembly process of the inner ring of a ball bearing in the prior art.

[0026] Figure 3 This is a front view of the bevel gear disassembly device of the present invention.

[0027] Figure 4 This is a side view of the bevel gear disassembly device of the present invention.

[0028] Figure 5 This is a schematic diagram showing the assembly result of the bevel gear disassembly device of the present invention. Detailed Implementation

[0029] To make the objectives, technical solutions, and advantages of this invention clearer, the technical solutions in the embodiments of this invention will be described in more detail below with reference to the accompanying drawings.

[0030] In order to overcome the problems of unstable disassembly force and easy tilting of bevel gears during disassembly in the prior art, which can lead to damage to ball bearings, the present invention provides a bevel gear disassembly device for aero-engines.

[0031] like Figures 3 to 5As shown, the aircraft engine bevel gear disassembly device 20 provided by the present invention mainly includes an upper support plate 21, a left support plate 22, a right support plate 23, a support base plate 24, a hydraulic jack 25, a pressure plate 26, an anti-torsion bar 27, and an anti-torsion bar adapter section 28.

[0032] The upper support plate 21, left support plate 22, right support plate 23, and support base plate 24 are fixedly connected by connectors to form a support assembly, which has a space to accommodate the bevel gear assembly 10. The left support plate 22 and right support plate 23 each have a boss structure on the opposite side of the space accommodating the bevel gear assembly 10. This boss structure and the bevel gear support frame 16 are positioned at both ends to form a simply supported beam, ensuring the stability of the bevel gear assembly support and also ensuring that the direction of force applied by the hydraulic jack 25 is consistent with the axis of the bevel gear 11.

[0033] The hydraulic jack 25 is fixed to the upper support plate 21 by a threaded structure and is used to apply a decomposed force along the axial direction to the bevel gear 11, so that the bevel gear 11 separates from the second rod gear 14 and the inner ring of the ball bearing 13.

[0034] The anti-torsion bar 27 is located at the lower end of the hydraulic jack 25, and its upper outer surface is provided with an external spline for engaging with the internal spline of the bevel gear 11. The lower end of the anti-torsion bar 27 has a smooth structure for engaging with the anti-torsion bar transition section 28. The anti-torsion bar 27 ensures that the bevel gear 11 moves axially and does not rotate circumferentially during disassembly.

[0035] The pressure plate 26 is fitted onto the anti-torsion bar 27. It has a pressing part 261 with a diameter adapted to the inner ring of the ball bearing 13 and a support part 262 integrally connected to the pressing part 27. The support part 261 is set on the support frame 16 of the bevel gear. The pressing part 261 presses the inner ring of the ball bearing 13 to ensure that the inner ring of the ball bearing 13 and the balls do not fall apart after disassembly. At the same time, the pressure plate 26 can also serve as the inner ring of the first bearing 12, playing a positioning role for the bevel gear 11. In this invention, the axial length of the pressing part 261 is set to be no less than the sum of the width of the first bearing 12 and half the width of the ball bearing 13, so that the pressing part 261 of the pressure plate 26 can separate the upper end of the bevel gear 11 from the lower half ring of the ball bearing 11 along the axis.

[0036] The anti-torsion bar adapter section 28 is fixed to the right support plate 23. A guide groove with a specific cross-section is provided at the position where it adapts to the anti-torsion bar 27. The anti-torsion bar adapter section 28 and the anti-torsion bar 27 work together to ensure that the bevel gear 11 cannot rotate during disassembly, while simultaneously ensuring that the bevel gear 11 moves axially. In some embodiments of the present invention, the cross-section of the guide groove can be square or regular hexagonal, and the cross-section of the lower side of the anti-torsion bar 27 matches the cross-section of the guide groove.

[0037] The process of using the aircraft engine bevel gear disassembly device of the present invention is as follows: First, fix the left support plate 22 on the support base plate 24, then install the bevel gear assembly 10 on the left support plate 22, so that the left support plate 22 is bolted to the stop of the support frame 16; then install the pressure plate 26 on the support frame 16 of the bevel gear assembly 10 and fix it with the bolts, and make it fit with the bevel gear with a small clearance, and ensure that the pressure plate 26 presses the inner ring 131 of the ball bearing 13; install the anti-torsion bar transition section 28 on the right support plate 23, then install the right support plate 23 on the support base plate 24, and make the right support plate 23 fit with the stop of the support frame; insert the anti-torsion bar 27 into Inside the bevel gear 11, align the external spline of the anti-torsion rod 27 with the internal spline of the bevel gear 11, and simultaneously insert the anti-torsion rod 27 into the mating guide groove of the anti-torsion rod transition section 28; install the hydraulic jack 25 onto the upper support plate 21, and then assemble the upper support plate 21 with the left support plate 22 and the right support plate 23 into an integral structure. Check that the installed bevel gear disassembly device is not stuck and rotates and moves flexibly, and then tighten all connecting bolts; through the operating rod of the hydraulic jack 1, extend the top of the hydraulic jack 1 and press it onto the anti-torsion rod 27, thereby driving the pressure plate 26 to move axially and enter the bevel gear disassembly process, while monitoring the pressure value displayed by the hydraulic jack 1 to ensure stable pressure.

[0038] The aircraft engine bevel gear disassembly device of the present invention has the following advantages:

[0039] 1) A hydraulic jack 21 is used to apply a uniform disintegration force to the bevel gear 11 along the axis of the bevel gear 11. The stability of the disintegration force during the disintegration process can be monitored in real time by displaying the pressure value of the hydraulic jack 21.

[0040] 2) The external spline at one end of the anti-torsion bar 27 engages with the internal spline of the bevel gear 11, and the other end engages with the anti-torsion bar transition section 28 fixed on the side plate, which can suppress the rotation of the bevel gear 11 during disassembly.

[0041] 3) The anti-torsion bar 27 and the anti-torsion bar transition section 28 are planar fits. During the disassembly process, the anti-torsion bar 27 also plays a guiding role to prevent the bevel gear 11 from deflecting.

[0042] 4) Design a pressure plate structure and fix it on the support frame 16. At the same time, apply pressure to the inner ring of the ball bearing 13 to ensure that the inner ring of the ball bearing 13 and the balls are evenly pressed together, so as to prevent the inner ring of the ball bearing 13 and the balls from falling apart after disassembly.

[0043] 5) The support frame 16 of the bevel gear 11 adopts a two-end stop structure and is positioned in conjunction with the components composed of each support plate to form a simply supported beam structure, which ensures more stable support during the disassembly process.

[0044] The aero-engine bevel gear disassembly device of the present invention has a simple structure and can be applied to the disassembly process of gears with similar structures in all fields such as aero-engines and gas turbines. It solves the technical problems such as damage to bevel gear ball bearings during the disassembly process and avoids economic losses caused by damage to engine parts.

[0045] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present invention should be included within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. A device for disassembling bevel gears for aircraft engines, characterized in that, include: A support assembly is formed by the fixed connection of the upper support plate (21), the left support plate (22), the right support plate (23), and the support base plate (24), and the support assembly has a space inside to accommodate the bevel gear assembly; A hydraulic jack (25), fixed to the upper support plate (21), is used to apply a decomposed force along the axial direction to the bevel gear (11). Anti-torsion bar (27), the anti-torsion bar (27) is set at the lower end of the hydraulic jack (25), and the upper outer surface of the anti-torsion bar (27) is provided with an external spline, which is used to cooperate with the internal spline of the bevel gear (1) to prevent the bevel gear from rotating circumferentially during disassembly. The lower end of the anti-torsion bar (27) is a smooth structure, which is used to cooperate with the anti-torsion bar transition section (28) to make the bevel gear (11) move axially during disassembly. A pressure plate (26) is mounted on a torsion bar (27) and has a pressing part (261) with a diameter adapted to the inner ring of a ball bearing (13) and a support part (262) integrally connected to the pressing part (27). The support part (261) is fixedly mounted on a bevel gear support frame (17), and the pressing part (261) presses against the inner ring of the ball bearing (13). The anti-torsion bar adapter section (28) is fixed on the right side support plate (23) and has a guide groove at the position of the anti-torsion bar (27). The anti-torsion bar (27) is inserted into the guide groove to prevent the bevel gear (11) from rotating during the disassembly process, while ensuring that the bevel gear (11) moves axially.

2. The aircraft engine bevel gear disassembly device as described in claim 1, characterized in that, The left support plate (22) and the right support plate (23) are respectively provided with boss structures, and the boss structures are positioned with the two ends of the bevel gear support frame to form a simply supported beam support.

3. The aircraft engine bevel gear disassembly device as described in claim 1, characterized in that, The hydraulic jack (25) is fixed to the upper support plate (21) by a threaded structure.

4. The aircraft engine bevel gear disassembly device as described in claim 3, characterized in that, The hydraulic jack (25) has a digital pressure display function, which is used to display the pressure value of the hydraulic jack (25).

5. The aircraft engine bevel gear disassembly device as described in claim 1, characterized in that, The axial length of the extrusion section (261) is not less than the sum of the width of the first rod bearing (12) and half the width of the ball bearing (13).

6. The aircraft engine bevel gear disassembly device as described in claim 1, characterized in that, The cross-section of the guide groove includes square and regular hexagon.

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