Dismounting device for aircraft main propeller shaft

Abstract

The utility model relates to the technical field of shaft dismounting, in particular to a dismounting device for a main propeller shaft of an airplane, which comprises a stress application part and a supporting part, the force applying part is used for abutting against the shaft end face to apply axial force to the shaft end face and comprises a force applying rod, a lead screw, a lead screw nut, an outer lining, a reducing sleeve, a positioning pin, an end bearing and a bearing mounting plate. The supporting part is used for clamping the end face of a large bearing at the bottom of the bearing seat and providing support for the axial force applied by the force applying part to the end face of a shaft, and comprises a supporting plate, a pull rod, a clamping device and a protective sleeve; the upper supporting plate is used for connecting the stress application part and the supporting part; the clamping device is matched with the protective sleeve to be arranged on a shaft in a sleeving mode, and the protective sleeve is used for preventing the outer surface of the shaft and a bearing from being damaged in the dismounting process. And the pull rod is used for transmitting the axial force applied to the shaft end surface by the force applying part to the end surface of a large bearing at the bottom of the bearing seat. The utility model has the advantages of simple installation, convenient disassembly, flexible use and low cost.

Description

Technical Field

[0001] The utility model relates to the technical field of shaft disassembly, in particular to a disassembly device for an aircraft main propeller shaft. Background Art

[0002] During the repair and maintenance of the main propeller of a propeller aircraft, the main propeller shaft needs to be disassembled, that is, the main propeller shaft needs to be pulled out from the bearing and the bearing seat. However, the shape and structure of the bearing seat of the main propeller shaft are relatively special, such as Figure 1 , Figure 2 As shown, the outer body is a cone, a large bearing is provided at the bottom of the bearing seat, a small bearing is provided at the upper end, and the large bearing has a larger diameter, so the bearing installation position is far away from the shaft end face; eight bolt holes for installing other components are also provided around the large bearing at the bottom of the bearing seat.

[0003] The above characteristics lead to the problem of insufficient claw length when using the common puller-type bearing removal tool currently on the market to dismantle the main propeller shaft of this type of aircraft. Even if the claw length is sufficient, it cannot pass through the bolt hole at the bottom of the bearing seat and cannot adapt to the conical bearing seat and the larger bearing diameter. In addition, the common puller-type bearing removal tool currently on the market mostly uses two or three claws, with fewer points of force. During the repair process, it is often the case that the claw breaks the outer ring of the bearing, while the inner ring of the bearing is still retained on the shaft. Sometimes, it will also cause damage to the end face and surface of the main propeller shaft, increasing the repair cycle and repair cost. Summary of the invention

[0004] In order to overcome the deficiencies of the prior art, the utility model provides a disassembly device for an aircraft main propeller shaft. The upper and lower ends of a pull rod are designed to be detachable, the pull rod is passed through the bottom of a conical bearing seat, and then installed with the force end and the support end, thereby solving the problem that the conical bearing seat is difficult to dismantle; and the clamping device cooperates with the protective sleeve to ensure that the shaft surface will not be damaged when the main propeller shaft is pulled out from the bearing and the bearing seat.

[0005] The technical solution of the utility model is:

[0006] A disassembly device for an aircraft main propeller shaft comprises a force adding part and a support part; the force adding part is fixedly mounted on the upper end of the support part by bolts;

[0007] The force-applying part is used to press against the end face of the shaft and apply axial force thereto, and comprises a force-applying rod, a screw, a screw nut, an outer bushing, an adapter sleeve, a positioning pin, an end bearing and a bearing mounting plate; a through hole perpendicular to the axial direction is provided at the upper end of the screw, and the force-applying rod passes through the through hole at the upper end of the screw, and is used as an operating handle to drive the screw to rotate; the external thread of the screw matches the screw nut, and the screw nut and the outer bushing are fixedly connected as a whole by welding and sleeved on the screw; the adapter sleeve is fixedly mounted on the lower end of the screw; the end bearing is mounted on the lower end of the adapter sleeve through the bearing mounting plate; when the rotating screw applies axial force to the end face of the shaft, the end bearing can ensure that the bearing mounting plate presses against the end face of the shaft and does not rotate, so as to avoid damage to the end face of the shaft during the force-applying process;

[0008] The support part is used to clamp the end face of the large bearing at the bottom of the bearing seat, and provide support for the axial force applied by the force-applying part to the end face of the shaft, and includes an upper support plate, a pull rod, a clamp, and a protective sleeve; the upper support plate is used to connect the force-applying part and the support part; the clamp is mounted on the shaft together with the protective sleeve, and the protective sleeve is in contact with the outer surface of the main propeller shaft and the end face of the large bearing, and the hardness of the material used for the protective sleeve is lower than that of the shaft, so as to avoid damage to the outer surface of the shaft and the large bearing during disassembly; the pull rod is four straight rods of the same specification; the length of the pull rod is designed according to the axial dimensions of the main propeller shaft and the bearing seat to be disassembled, and the diameter of the pull rod is designed according to the diameter of the bolt through hole at the bottom of the bearing seat; the pull rod is provided with threads at both ends, and is connected to the upper support plate through the upper threaded part, and is connected to the clamp through the lower threaded part; the pull rod is used to transmit the axial force applied by the force-applying part to the end face of the shaft to the end face of the large bearing at the bottom of the bearing seat.

[0009] Furthermore, a circular mounting portion is provided at the lower end of the outer sleeve, and a plurality of mounting holes are provided in its circumference; a circular hole is provided at the upper end of the adapter sleeve, a threaded hole is provided at the lower end, and a limit stop is provided on the middle outer part; the lower end of the screw rod is not threaded, but is pressed into the circular hole at the upper end of the adapter sleeve, and forms an interference fit with the adapter sleeve; the side surface of the lower end of the screw rod and the side surface of the adapter sleeve are both provided with through pin holes, and are fixedly connected with the locating pins; the end bearing sleeve is arranged at the lower end of the adapter sleeve, and abuts against the limit stop in the middle of the adapter sleeve; the bearing mounting plate is mounted on the lower end of the adapter sleeve by screws through the threaded hole at the lower end of the adapter sleeve.

[0010] Furthermore, a circular hole with the same diameter as the inner diameter of the outer bushing of the force-adding part is provided in the middle of the upper support plate; a plurality of threaded holes are provided in the circumferential direction of the outer periphery of the circular hole, and the threaded holes can be aligned with the mounting holes on the circular mounting part at the lower end of the outer bushing, so as to ensure that the force-adding part can be mounted on the upper end of the upper support plate through the threaded holes using bolts; four tie rod upper end mounting holes are provided in the circumferential direction of the outer periphery of the upper support plate at equal angles; the clamp adopts the form of two semicircles, and the joint part of the two semicircles is provided with a first step, and the two semicircles are overlapped together through the first step to form a full circle; four tie rod lower end mounting holes are provided in the circumferential direction of the clamp at equal angles, and two tie rod lower end mounting holes pass through the first step; the inner ring of the clamp is provided with a second step; the protective sleeve also adopts the form of two semicircles; the outer ring of the protective sleeve is provided with a third step matching the second step, so as to ensure that the outer ring of the protective sleeve can be clamped on the second step of the clamp; the inner ring of the protective sleeve is provided with a fourth step, which is used to reduce the contact area between the inner ring of the protective sleeve and the outer surface of the main propeller shaft to be disassembled.

[0011] Furthermore, the threads of the screw rod and the screw rod nut are trapezoidal threads, made of 45 steel, and are quenched and tempered.

[0012] Furthermore, the thread at the lower end of the pull rod is longer than the thread at the upper end, the upper end of the pull rod passes through the upper end mounting hole of the pull rod on the upper support plate and is installed with a nut, and the lower end of the pull rod passes through the lower end mounting hole of the pull rod on the clamp and is installed with a nut.

[0013] Furthermore, the protective cover is made of aluminum alloy material.

[0014] When the main propeller shaft is disassembled using the embodiment of the utility model, the pull rod is passed through the bolt through hole at the bottom of the bearing seat of the main propeller shaft to be disassembled, the clamp is put on the main propeller shaft together with the protective sleeve, the lower end of the pull rod is passed through the lower end mounting hole of the pull rod on the clamp and then installed with a nut, and the length of the pull rod is adjusted to ensure that the bearing mounting plate at the lower end of the force-adding part is in contact with and tight against the end face of the shaft. By operating the force-adding rod to rotate the screw rod, the bearing mounting plate at the lower end of the force-adding part is further pressed to the end face of the shaft, and the force on the end face of the main propeller shaft is transmitted to the end face of the large bearing at the bottom of the bearing seat through the pull rod. The screw rod rotates to continuously add force to the end face of the main propeller shaft to be disassembled, thereby causing displacement between the main propeller shaft and the bearing, gradually ejecting the main propeller shaft, and finally completing the disassembly.

[0015] Beneficial Effects

[0016] The utility model provides a disassembly device for an aircraft main propeller shaft. The length and diameter of the pull rod are designed according to the sizes of the main propeller shaft, bearing and bearing seat to be disassembled, which can solve the problem of incompatibility of the length and size of the pull claws of the traditional puller; by designing the upper and lower ends of the pull rod to be detachable, the pull rod is passed through the bottom of the cone-shaped bearing seat, and then installed with the force-applying end and the supporting end, which can solve the adaptation problem of the cone-shaped bearing seat; and the clamping device cooperates with the protective sleeve to ensure that the bearing will not be damaged and the shaft surface will not be damaged when the main propeller shaft is disassembled; in addition, the utility model is simple to install, convenient to disassemble, flexible to use, and low in cost. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 This is a schematic diagram of the installation of the embodiment of the utility model on the main shaft to be disassembled;

[0018] Figure 2 for Figure 1 Schematic diagram of the MM section;

[0019] Figure 3 for Figure 1 A partial enlarged view of the middle A;

[0020] Figure 4 It is a schematic diagram of the overall structure of an embodiment of the utility model;

[0021] Figure 5 A schematic diagram of a force-adding part of an embodiment of the utility model;

[0022] Figure 6 It is a cross-sectional schematic diagram of the force-applying part of an embodiment of the utility model;

[0023] Figure 7 A schematic diagram of a clamping device according to an embodiment of the utility model;

[0024] Figure 8 This is a schematic diagram of the installation of the clamp and the protective cover of the embodiment of the utility model;

[0025] Fig. 9 A schematic diagram of a pull rod according to an embodiment of the utility model;

[0026] In the figure: 1-force rod; 2-screw rod; 3-screw rod nut; 4-outer bushing; 41-outer bushing mounting part; 5-upper support plate; 6-adapter sleeve; 7-end bearing; 8-bearing mounting plate; 9-pull rod; 91-upper end threaded portion of pull rod; 92-lower end threaded portion of pull rod; 10-clamp; 101-first step; 102-second step; 11-protective sleeve; 111-third step; 112-fourth step; 12-nut; 13-hexagonal bolt; 14-locating pin; 15-main propeller shaft; 151-end face of main propeller shaft; 16-bearing seat; 161-bolt through hole at the bottom of bearing seat; 17-large bearing; 171-end face of large bearing; 18-small bearing. DETAILED DESCRIPTION

[0027] The present invention is further described in detail below in conjunction with the accompanying drawings and specific implementation methods:

[0028] like Figure 1 , Figure 2 , Figure 4 As shown, a disassembly device for an aircraft main propeller shaft comprises a force adding part and a support part; the force adding part is fixedly mounted on the upper end of the support part by bolts;

[0029] like Figure 1 , Figure 2 , Figure 5 and Figure 6 As shown, the force-applying part is used to resist the end face 151 of the shaft 15 to apply axial force thereto, and includes a force-applying rod 1, a screw rod 2, a screw nut 3, an outer bushing 4, an adapter sleeve 6, a positioning pin 14, an end bearing 7 and a bearing mounting plate 8; a through hole vertical to the axial direction is provided at the upper end of the screw rod 2, and the force-applying rod 1 passes through the through hole at the upper end of the screw rod 2 and is used as an operating handle to drive the screw rod 2 to rotate; the external thread of the screw rod 2 matches the screw nut 3, and the screw nut 3 and the outer bushing 4 are fixedly connected as a whole by welding and sleeved on the screw rod 2; the adapter sleeve 6 is fixedly installed at the lower end of the screw rod 2; the end bearing 7 is installed at the lower end of the adapter sleeve 6 through the bearing mounting plate 8; when the rotating screw rod 2 applies axial force to the end face of the shaft 15, the end bearing 7 can ensure that the bearing mounting plate 8 is pressed against the end face 151 of the shaft 15 without rotating, so as to avoid damage to the end face 151 of the shaft 15 during the force-applying process;

[0030] In this embodiment, if Figure 5 and Figure 6 As shown, a circular mounting portion 41 is provided at the lower end of the outer bushing 4, and a plurality of mounting holes are provided in its circumferential direction; a circular hole is provided at the upper end of the adapter sleeve 6, a threaded hole is provided at the lower end, and a limit stop is provided at the middle outer portion; the lower end of the screw rod 2 is not threaded, and is pressed into the circular hole at the upper end of the adapter sleeve 6, and forms an interference fit with the adapter sleeve 6; the side surfaces of the lower end of the screw rod 2 and the side surfaces of the adapter sleeve 6 are provided with through pin holes, and are fixedly connected with the positioning pins 14; the end bearing 7 is sleeved on the lower end of the adapter sleeve 6, and rests on the limit stop in the middle of the adapter sleeve 6; the bearing mounting plate 8 is mounted on the lower end of the adapter sleeve 6 by screws through the threaded holes at the lower end of the adapter sleeve 6.

[0031] The support portion is used to clamp the end face 171 of the large bearing 17 at the bottom of the bearing seat 16, and provide support for the axial force applied by the force-applying portion to the shaft end face 151, including an upper support plate 5, a pull rod 9, a clamp 10, and a protective sleeve 11; Figure 4 and Figure 6As shown, the upper support plate 5 is used to connect the force-applying part and the support part; Figure 3 As shown, the clamp 10 is sleeved on the shaft 15 together with the protective sleeve 11, and the protective sleeve 11 is in contact with the outer surface of the main propeller shaft 15 and the end surface 171 of the large bearing 17, and the hardness of the material used for the protective sleeve 11 is lower than the hardness of the material of the shaft 15, so as to avoid damage to the outer surface of the shaft 15 and the large bearing 17 during the disassembly process; Figure 4 and Fig. 9 As shown, the pull rod 9 is four straight rods of the same specification; the length of the pull rod 9 is designed according to the axial dimensions of the main propeller shaft 15 and the bearing seat 16 to be disassembled, and the diameter of the pull rod 9 is designed according to the diameter of the bolt through hole 161 at the bottom of the bearing seat 16; the pull rod 9 is provided with threads at both the upper and lower ends, and is connected to the upper support plate 5 through the upper threaded portion 91, and is connected to the clamp 10 through the lower threaded portion 92; the pull rod 9 is used to transmit the axial force applied by the force-applying portion to the end face 151 of the shaft 15 to the end face 171 of the bottom large bearing 17 of the bearing seat 16.

[0032] In this embodiment, if Figure 4 and Figure 6 As shown, a circular hole with the same diameter as the inner diameter of the outer bushing 4 of the force-applying part is provided in the middle of the upper support plate 5; a plurality of threaded holes are provided in the circumferential direction of the outer periphery of the circular hole, and the threaded holes can be aligned with the mounting holes on the circular mounting part 41 at the lower end of the outer bushing 4, so as to ensure that the force-applying part can be mounted on the upper end of the upper support plate 5 through the threaded holes using bolts 13; four tie rod upper end mounting holes are provided in the circumferential direction of the outer periphery of the upper support plate 5 at equal angles; Figure 7 As shown, the clamp 10 is in the form of two semicircles, the joint part of the two semicircles is provided with a first step 101, and the two semicircles are overlapped and combined together through the first step 101 to form a full circle; the clamp 10 is provided with four tie rod lower end mounting holes at equal angles in the circumferential direction, two of which penetrate the first step 101; the inner circle of the clamp 10 is provided with a second step 102; Figure 8 As shown, the protective cover 11 also adopts two semicircular forms; the outer ring of the protective cover 11 is provided with a third step 111 matching the second step 102, so as to ensure that the outer ring of the protective cover 11 can be clamped on the second step 102 of the clamp 10; the inner ring of the protective cover 11 is provided with a fourth step 112, which is used to reduce the contact area between the inner ring of the protective cover 11 and the outer surface of the main propeller shaft 15 to be disassembled, as shown in FIG. Figure 3 shown.

[0033] In this embodiment, the threads of the screw rod 2 and the screw rod nut 3 are trapezoidal threads, made of 45 steel, and are quenched and tempered.

[0034] In this embodiment, if Fig. 9As shown, the threaded portion 92 at the lower end of the pull rod 9 is longer than the threaded portion 91 at the upper end. The upper end of the pull rod 9 is passed through the upper end mounting hole of the pull rod on the upper support plate 5 and installed with a nut 12. The lower end of the pull rod 9 is passed through the lower end mounting hole of the pull rod on the clamp 10 and installed with a nut 12.

[0035] In this embodiment, the protective cover 11 is made of aluminum alloy.

[0036] like Figure 1 , Figure 2 As shown, when the main propeller shaft is disassembled using the embodiment of the utility model, the pull rod 9 is passed through the bolt through hole at the bottom of the bearing seat 16 of the main propeller shaft 15 to be disassembled, the clamp 10 is put on the main propeller shaft 15 together with the protective sleeve 11, the lower end of the pull rod 9 is passed through the lower end installation hole of the pull rod on the clamp 10 and then installed with the nut 12, and the length of the pull rod 9 is adjusted to ensure that the bearing mounting plate 8 at the lower end of the force-adding part is in contact with and tightly against the end face 151 of the shaft 15. By operating the force-adding rod 1 to rotate the screw rod 2, the bearing mounting plate 8 at the lower end of the force-adding part is further pressed to the end face 151 of the shaft 15, and the force on the end face 151 of the main propeller shaft is transmitted to the end face 171 of the large bearing 17 at the bottom of the bearing seat 16 through the pull rod 9. The screw rod 2 rotates to continuously add force to the end face 151 of the main propeller shaft 15 to be disassembled, so that displacement occurs between the main propeller shaft 15 and the bearing, and the main propeller shaft 15 is gradually pushed out, and finally the disassembly is completed.

[0037] Although the embodiments of the present invention have been shown and described above, it can be understood that the above embodiments are illustrative and cannot be understood as limitations on the present invention. Ordinary technicians in the field can change, modify, replace and modify the above embodiments within the scope of the present invention without departing from the principles and purpose of the present invention.

Claims

1. A disassembly device for an aircraft main propeller shaft, characterized in that: It comprises a force-applying part and a supporting part; the force-applying part is fixedly mounted on the upper end of the supporting part by bolts; The force-applying part is used to press against the end face of the shaft and apply axial force thereto, and comprises a force-applying rod, a screw, a screw nut, an outer bushing, an adapter sleeve, a positioning pin, an end bearing and a bearing mounting plate; a through hole perpendicular to the axial direction is provided at the upper end of the screw, and the force-applying rod passes through the through hole at the upper end of the screw, and is used as an operating handle to drive the screw to rotate; the external thread of the screw matches the screw nut, and the screw nut and the outer bushing are fixedly connected as a whole by welding and sleeved on the screw; the adapter sleeve is fixedly mounted on the lower end of the screw; the end bearing is mounted on the lower end of the adapter sleeve through the bearing mounting plate; when the rotating screw applies axial force to the end face of the shaft, the end bearing can ensure that the bearing mounting plate presses against the end face of the shaft and does not rotate, so as to avoid damage to the end face of the shaft during the force-applying process; The support part is used to clamp the end face of the large bearing at the bottom of the bearing seat, and provide support for the axial force applied by the force-applying part to the end face of the shaft, and includes an upper support plate, a pull rod, a clamp, and a protective sleeve; the upper support plate is used to connect the force-applying part and the support part; the clamp is mounted on the shaft together with the protective sleeve, and the protective sleeve is in contact with the outer surface of the main propeller shaft and the end face of the large bearing, and the hardness of the material used for the protective sleeve is lower than that of the shaft, so as to avoid damage to the outer surface of the shaft and the large bearing during disassembly; the pull rod is four straight rods of the same specification; the length of the pull rod is designed according to the axial dimensions of the main propeller shaft and the bearing seat to be disassembled, and the diameter of the pull rod is designed according to the diameter of the bolt through hole at the bottom of the bearing seat; the pull rod is provided with threads at both ends, and is connected to the upper support plate through the upper threaded part, and is connected to the clamp through the lower threaded part; the pull rod is used to transmit the axial force applied by the force-applying part to the end face of the shaft to the end face of the large bearing at the bottom of the bearing seat.

2. A disassembly device for an aircraft main propeller shaft according to claim 1, characterized in that: A circular mounting portion is provided at the lower end of the outer bushing, and a plurality of mounting holes are provided in its circumference; a circular hole is provided at the upper end of the adapter sleeve, a threaded hole is provided at the lower end, and a limit stop is provided on the middle outer part; the lower end of the screw rod is not threaded, but is pressed into the circular hole at the upper end of the adapter sleeve, and forms an interference fit with the adapter sleeve; through pin holes are provided on the side surfaces of the lower end of the screw rod and the side surfaces of the adapter sleeve, and are fixedly connected with the locating pins; the end bearing sleeve is provided at the lower end of the adapter sleeve, and abuts against the limit stop in the middle of the adapter sleeve; the bearing mounting plate is mounted on the lower end of the adapter sleeve by screws through the threaded holes at the lower end of the adapter sleeve.

3. A disassembly device for an aircraft main propeller shaft according to claim 1, characterized in that: A circular hole with the same diameter as the inner diameter of the outer bushing of the force-adding part is provided in the middle of the upper support plate; a plurality of threaded holes are provided in the circumferential direction of the outer periphery of the circular hole, and the threaded holes can be aligned with the mounting holes on the circular mounting part at the lower end of the outer bushing, so as to ensure that the force-adding part can be mounted on the upper end of the upper support plate through the threaded holes using bolts; four tie rod upper end mounting holes are provided at equal angles in the circumferential direction of the outer periphery of the upper support plate; the clamp adopts the form of two semicircles, and the joint part of the two semicircles is provided with a first step, and the two semicircles are overlapped together through the first step to form a full circle; four tie rod lower end mounting holes are provided at equal angles in the circumference of the clamp, and two tie rod lower end mounting holes pass through the first step; the inner ring of the clamp is provided with a second step; the protective sleeve also adopts the form of two semicircles; the outer ring of the protective sleeve is provided with a third step matching the second step, so as to ensure that the outer ring of the protective sleeve can be clamped on the second step of the clamp; the inner ring of the protective sleeve is provided with a fourth step, which is used to reduce the contact area between the inner ring of the protective sleeve and the outer surface of the main propeller shaft to be disassembled.

4. The disassembly device for an aircraft main propeller shaft according to claim 1, characterized in that: The threads of the screw rod and the screw rod nut are trapezoidal threads, made of 45# steel, and are quenched and tempered.

5. The disassembly device for an aircraft main propeller shaft according to claim 1, characterized in that: The thread at the lower end of the pull rod is longer than the thread at the upper end. The upper end of the pull rod passes through the upper end mounting hole of the pull rod on the upper support plate and is installed with a nut. The lower end of the pull rod passes through the lower end mounting hole of the pull rod on the clamp and is installed with a nut.

6. The disassembly device for an aircraft main propeller shaft according to claim 1, characterized in that: The protective cover is made of aluminum alloy material.

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