Device and method for replacing hoisting point lining of aircraft generator

Abstract

The embodiment of the invention discloses an aircraft generator lifting point lining replacement device and method.The lifting point lining replacement device comprises a generator body, a lifting point lining and a dismounting device, the lifting point lining is arranged on the side surface of the generator body, and the dismounting device is arranged on the side surface of the generator body; when the static test tool tests that leakage occurs at the lifting point bushing of the generator body, the lifting point bushing can be dismounted and replaced through the dismounting device so as to complete the fault elimination work of leakage of the generator body. According to the structural characteristics of the lifting point bushing, the dismounting device is designed according to the technical scheme, firstly, a spring pin with an internal thread is dismounted, a spring pin hole is exposed, the threaded end of a center screw is screwed into a screw hole in the center of the lifting point bushing, a second pin is inserted into the spring pin hole, and therefore the lifting point bushing is further fixed; and finally, further rotating the central screw rod to finish the dismounting of the hoisting point bushing.

Description

TECHNICAL FIELD

[0001] The embodiment of the present application relates to the technical field of aircraft generator maintenance, in particular to a device and method for replacing a hanger point bushing of an aircraft generator. BACKGROUND

[0002] At present, the mainstream aircraft fleet A320S aircraft power supply system comprises an integral drive generator, a generator at an auxiliary power device, a storage battery and a ram turbine. When the integral drive generator fails, the generator at the auxiliary power device can replace the integral drive generator to supply power to the aircraft. The generator at the auxiliary power device is a 2-pole brushless independent generator, which provides 115V, 400HZ three-phase alternating current for the aircraft at a working speed of 24000rpm (revolutions per minute), and the rated power is 90kVA, which provides an important guarantee for the flight safety of the aircraft. In normal maintenance, according to the manufacturer's data, the performance of the generator can be tested by using a K938 test bench, but since the generator does not have a separate oil pump system, the oil flow is relied on the oil pump of the test bench, so that the inside of the generator is in a negative pressure state during the work of the test bench. This is different from the positive pressure condition of the generator on the aircraft. In normal operation, the generator is installed on the auxiliary power device and is an integral sealed component, which is not allowed to have any leakage. In view of the leakage, it needs to be immediately disassembled and replaced for repair.

[0003] In the patent No. ZL201920841942.0 (a sealing test tool for repairing an aircraft generator), a special generator static test tool is produced for the judgment of leakage. The special static test tool can judge the leakage of the generator, and the sealing ring at the plug can be normally disassembled, replaced and the leakage troubleshooting work is completed. However, for the leakage at the hanger point, the manufacturer's data does not give any troubleshooting instructions. There is no suitable disassembly and replacement device, and there is no effective disassembly and assembly steps. It brings great trouble to the normal maintenance work. When the generator hanger point bolt leaks, there is no effective measure to complete the maintenance work. According to the manufacturer's process, the generator shell can only be sent back to the original factory for repair, which is relatively high in price. SUMMARY

[0004] The present application aims to at least solve one of the problems in the prior art or related art.

[0005] To this end, a first aspect of the present application provides a device for replacing a hanger point bushing of an aircraft generator.

[0006] A second aspect of the present application provides a method for replacing a hanger point bushing of an aircraft generator.

[0007] Therefore, according to the first aspect of the embodiment of the present application, a device for replacing a hanger point bushing of an aircraft generator is provided, which comprises: a generator body;

[0008] A lifting point bushing is located on the side surface of the generator body, the center of the top end of the lifting point bushing has a threaded hole, the top end of the lifting point bushing has a spring pin hole, a spring pin is arranged in the spring pin hole, and the spring pin has an internal thread;

[0009] A dismounting device is used to dismount the lifting point bushing.

[0010] The dismounting device comprises a center screw and a second pin, one end of the center screw is used to be screwed to the threaded hole in the center of the lifting point bushing, and the other end of the center screw is a screw cap.

[0011] In an available embodiment, further comprising:

[0012] A fixing shell is used to fix the generator body, and the upper surface of the bottom of the fixing shell has four first pins.

[0013] The bottom of the generator body has four pin holes, and the positions of the four pin holes correspond to the four first pins.

[0014] In an available embodiment, the dismounting device further comprises:

[0015] A mounting disc is provided with a circular hole in the center, and the center screw passes through the mounting disc through the circular hole.

[0016] The second pin is arranged on the mounting disc.

[0017] In an available embodiment, the second pin comprises:

[0018] A threaded pin is provided with a thread on the outer surface, the size of the threaded pin corresponds to the spring pin, and the threaded pin is rotatably connected to the mounting disc.

[0019] A cross slot is arranged on the side of the mounting disc where the threaded pin is not arranged, and the cross slot is connected to the threaded pin.

[0020] In an available embodiment, the second pin further comprises:

[0021] A sleeve is provided with an internal thread on the upper end.

[0022] A connecting sleeve is annular and arranged on the circumferential side of the threaded pin, the connecting sleeve is provided with an external thread, and the connecting sleeve is connected to the sleeve through the external thread.

[0023] In an available embodiment, the dismounting device further comprises:

[0024] A fastening nut is threadedly connected to the center screw, and the fastening nut is arranged on the side of the center screw where the second pin is not arranged.

[0025] In an embodiment, the dismounting device further comprises:

[0026] A driving nut is threadedly connected to the center screw, and the driving nut is arranged between the fastening nut and the nut of the center screw.

[0027] In an embodiment, the dismounting device further comprises:

[0028] A fixing support is connected to the fixing shell at one end, and the fixing support has a first movable arm, a second movable arm, and a clamping device.

[0029] One end of the first movable arm is fixedly connected to the fixing shell, and the other end of the first movable arm is rotatably connected to one end of the second movable arm, and the clamping device is rotatably connected to the other end of the second movable arm.

[0030] A heating gun is fixed to the fixing support by the clamping device.

[0031] A temperature measuring assembly is arranged at the temperature measuring end of the temperature measuring assembly.

[0032] According to a second aspect of the embodiment of the present application, a method for replacing an aircraft generator lifting point bushing is provided, which is applied to the aircraft generator lifting point bushing replacement device in any of the above embodiments, and comprises the following steps:

[0033] The spring pin in the spring pin hole is removed;

[0034] One end of the center screw is screwed into the threaded hole of the lifting point bushing;

[0035] The second pin is deeply inserted into the spring pin hole;

[0036] The lifting point bushing is taken out by rotating the center screw.

[0037] In an embodiment, the method further comprises:

[0038] The generator body is fixed by a fixing device that is matched with the shape of the outer shell of the generator body;

[0039] The side of the generator body where the lifting point bushing is arranged is heated to above 260℃ and below 280℃ by the heating device.

[0040] Compared with the prior art, the lifting point bushing replacement device provided by the embodiment of the application comprises a generator body, a lifting point bushing and a dismounting device, the lifting point bushing is arranged on the side surface of the generator body, when leakage occurs at the lifting point bushing of the generator body is tested by a static test tool, the dismounting device can be used to dismount and replace the lifting point bushing, so as to complete troubleshooting of the leakage of the generator body.

[0041] The lifting point bushing comprises a top portion and a bottom portion, the top portion of the lifting point bushing is provided with a threaded hole which is recessed towards the inside of the generator body, the top portion of the lifting point bushing is provided with a spring pin hole, a spring pin is arranged in the spring pin hole, and the inner side wall of the spring pin is also provided with threads.

[0042] According to the structural characteristics of the lifting point bushing, the dismounting device is designed, the spring pin with internal threads is first dismounted to expose the spring pin hole, the threaded end of the central screw rod is screwed into the threaded hole at the center of the lifting point bushing, and the second pin is inserted into the spring pin hole, so as to further fix the lifting point bushing, and finally the central screw rod is further rotated, so that the dismounting of the lifting point bushing is completed.

[0043] The technical scheme provides a process scheme for replacing the generator lifting point bolt, leakage at the generator lifting point bolt can be repaired, the leakage problem at the lifting point of the generator is solved at a low cost, and economic benefits are improved on the premise of ensuring reliability. BRIEF DESCRIPTION OF DRAWINGS

[0044] Various other advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The accompanying drawings are included to provide a description of the preferred embodiments and are not intended to limit the scope of the application. Moreover, the same reference numerals are used throughout the same figures. In the drawings:

[0045] Figure 1 The dismounting assembly structure diagram of an embodiment provided by the application;

[0046] Figure 2 The structural block diagram of the generator body of an embodiment provided by the application;

[0047] Figure 3 The structural block diagram of the fixed shell of an embodiment provided by the application;

[0048] Figure 4 The structural block diagram of the fixed support of an embodiment provided by the application;

[0049] Figure 5 The step diagram of the aircraft generator lifting point bushing replacement method of an embodiment provided by the application.

[0050] wherein, Figures 1-4 The correspondence between the reference signs and the component names is as follows:

[0051] 100, generator body; 200, lifting point bushing; 300, spring pin; 400, dismounting device; 500, fixed shell; 600, first pin; 700, fixed support; 800, heating gun;

[0052] 410, center screw; 420, second pin; 430, mounting disc; 440, fastening nut; 450, driving nut. DETAILED DESCRIPTION

[0053] In order to better understand the above technical solutions, the technical solutions of the embodiments of the present application will be described in detail below through the drawings and specific embodiments. It should be understood that the specific features in the embodiments of the present application and the specific embodiments are detailed descriptions of the technical solutions of the embodiments of the present application, and are not limitations of the technical solutions of the present application. In the case of no conflict, the technical features in the embodiments of the present application and the specific embodiments can be combined with each other.

[0054] As Figures 1-4 shown, according to the first aspect of the embodiments of the present application, an aircraft generator lifting point bushing 200 replacement device is provided, comprising: a generator body 100; a lifting point bushing 200 located on the side surface of the generator body 100, the center of the top end of the lifting point bushing 200 has a threaded hole, the top end of the lifting point bushing 200 has a spring pin 300 hole, the spring pin 300 hole is provided with a spring pin 300, and the spring pin 300 has an internal thread; a dismounting device 400 for dismounting the lifting point bushing 200; the dismounting device 400 comprises a center screw 410 and a second pin 420, one end of the center screw 410 is used for threaded connection with the threaded hole in the center of the lifting point bushing 200, and the other end of the center screw 410 is a nut.

[0055] The lifting point bushing 200 replacement device provided by the embodiments of the present application comprises a generator body 100, a lifting point bushing 200 and a dismounting device 400. The lifting point bushing 200 is arranged on the side surface of the generator body 100. When it is tested by a static test tool that leakage occurs at the lifting point bushing 200 of the generator body 100, the lifting point bushing 200 can be dismounted and replaced by the dismounting device 400, so as to complete the troubleshooting of the leakage of the generator body 100.

[0056] The structure of the lifting point bushing 200 is that the center of the top of the lifting point bushing 200 has a threaded hole recessed into the interior of the generator body 100, the top of the lifting point has a spring pin 300 hole, the spring pin 300 hole is provided with a spring pin 300 inside, and the inner side wall of the spring pin 300 also has a thread.

[0057] According to the structural features of the lifting point bushing 200, the technical scheme designs a dismounting device 400, first, the spring pin 300 with internal thread is dismounted to expose the spring pin 300 hole, the threaded end of the central screw 410 is screwed into the screw hole at the center of the lifting point bushing 200, and the second pin 420 is inserted into the spring pin 300 hole, so as to further fix the lifting point bushing 200, and finally, the central screw 410 is further rotated, so that the dismounting of the lifting point bushing 200 is completed.

[0058] The technical scheme provides a process scheme for replacing the generator lifting point bolt, and the leakage at the generator lifting point bolt can be repaired, the leakage problem at the generator lifting point is solved at a low cost, and economic benefits are improved under the premise of ensuring reliability.

[0059] As shown in Figures 1-4 , further comprising: a fixed shell 500, the fixed shell 500 is used for fixing the generator body 100, and the upper surface of the bottom of the fixed shell 500 has four first pins 600; the bottom of the generator body 100 has four pin holes, and the positions of the four pin holes correspond to the four first pins 600.

[0060] In the technical scheme, the replacement device further comprises a fixed shell 500, and the fixed shell 500 is used for fixing the generator body 100, so as to facilitate the dismounting of the lifting point bushing 200.

[0061] The upper surface of the bottom of the fixed shell 500 has four first pins 600, and the bottom of the generator body 100 has four pin holes, and the positions of the first pins 600 correspond to the positions of the pin holes.

[0062] When the lifting point bushing 200 is dismounted, the generator body 100 can be placed in the fixed shell 500, and the four first pins 600 are inserted into the pin holes to further fix the generator body 100.

[0063] As shown in Figures 1-4 , the dismounting device 400 further comprises: a mounting disc 430, a circular hole is formed at the center of the mounting disc 430, and the central screw 410 passes through the mounting disc 430 through the circular hole; and the second pin 420 is arranged on the mounting disc 430.

[0064] In the technical scheme, the dismounting device 400 further comprises a mounting disc 430, and the mounting disc 430 is used for providing a mounting basis for the second pin 420. The mounting disc 430 is annular, the central screw 410 passes through the mounting disc 430 through the circular hole of the mounting disc 430, and when the central screw 410 is connected to the lifting point bushing 200, the second screw arranged on the mounting disc 430 can extend into the spring pin 300 hole.

[0065] As shown in Figures 1-4 , the second pin 420 comprises: a threaded pin, the outer surface of the threaded pin has threads, the threaded pin corresponds in size to the spring pin 300, the threaded pin is rotatably connected to the mounting disc 430; a cross slot, the cross slot is arranged on the side of the mounting disc 430 where the threaded pin is not arranged, and the cross slot is connected to the threaded pin.

[0066] In this technical solution, the second pin 420 has a threaded pin and a cross slot.

[0067] The threaded pin corresponds to the internal threads of the spring pin 300, and when the spring pin 300 is removed, the threaded pin can be aligned with the spring pin 300, and the cross slot is rotated to make the threaded pin screw into the spring pin 300, thereby achieving the fixing and removal of the spring pin 300.

[0068] In this technical solution, the second pin 420 can be used to remove the spring pin 300, without the need for additional tools to remove the spring pin 300, further improving the ease of use of the present technical solution.

[0069] As shown in Figures 1-4 , the second pin 420 further comprises: a sleeve, the upper end of the sleeve has internal threads; a connecting sleeve, the connecting sleeve is annular and arranged on the side of the threaded pin, the connecting sleeve has external threads, and the connecting sleeve is connected to the sleeve through the external threads.

[0070] In this technical solution, the second pin 420 further comprises a sleeve and a connecting sleeve, after the spring pin 300 is removed by the threaded pin, although the threaded pin can directly drive the spring pin 300 hole to rotate, the threaded pin is relatively fragile and has a smaller diameter than the spring pin 300 hole, therefore, the sleeve and the connecting sleeve are added, both of which are arranged on the side of the threaded pin and are detachably connected through threads, when the spring pin 300 needs to be removed, the sleeve is removed, and when the lifting point bushing 200 needs to be removed, the sleeve is connected to the connecting sleeve, and the sleeve is inserted into the spring pin 300 hole to achieve rotation.

[0071] As shown in Figures 1-4 , the dismounting device 400 further comprises: a fastening nut 440, the fastening nut 440 is threadedly connected to the center screw 410, and the fastening nut 440 is arranged on the side of the center screw 410 where the second pin 420 is not arranged.

[0072] In the technical scheme, the dismounting device 400 further comprises a fastening nut 440, the fastening nut 440 is used for fixing the mounting disc 430 so as to fix the second pin 420, and the fastening nut 440 is screwed to the center screw 410, the fastening nut 440 is arranged between the screw cap and the mounting disc 430, and the fastening nut 440 is tightly attached to the mounting disc 430 during the dismounting process.

[0073] As shown in Figures 1-4 the dismounting device 400 further comprises a driving nut 450, the driving nut 450 is screwed to the center screw 410, and the driving nut 450 is arranged between the fastening nut 440 and the screw cap of the center screw 410.

[0074] In the technical scheme, the dismounting device 400 further comprises the driving nut 450, the driving nut 450 is arranged between the fastening nut 440 and the screw cap of the center screw 410, the fastening nut 440 has a reverse screw structure, and the fastening nut 440 is used for connecting an external manual wrench or an electric wrench; because the fastening nut 440 has a large volume, the wrench is convenient to fix, and thus the stability of the technical scheme is improved.

[0075] As shown in Figures 1-4 the dismounting device 400 further comprises a fixing support 700, one end of the fixing support 700 is connected to the fixing shell 500, the fixing support 700 has a first movable arm, a second movable arm and a clamping device; one end of the first movable arm is fixedly connected to the fixing shell 500, the other end of the first movable arm is rotatably connected to one end of the second movable arm, and the clamping device is rotatably connected to the other end of the second movable arm; a heating gun 800 is fixed to the fixing support 700 through the clamping device; and a temperature measuring assembly has a temperature measuring end arranged on the side of the generator body 100 provided with the lifting point bushing 200.

[0076] In the technical scheme, the replacing device further has the fixing support 700, the heating gun 800 and the temperature measuring assembly.

[0077] Because the lifting point bushing 200 is made of steel and has an expansion coefficient of 0.000012 / ℃, the generator body 100 is made of aluminum alloy and has an expansion coefficient of 0.000023 / ℃, the expansion coefficient of the lifting point bushing 200 is much smaller than that of the generator body 100, and the Loctite glue for reinforcing the lifting point bushing 200 will lose the bonding effect at high temperature, therefore, the local heating treatment of the generator body 100 can reduce the difficulty of dismounting the lifting point bushing 200, and thus the fixing support 700 and the heating gun 800 are additionally arranged.

[0078] The normal working temperature of the generator body 100 is 150 DEG C, and the limit temperature that can be tolerated is 300 DEG C, so the temperature measuring assembly is additionally arranged, and when the temperature of the heated part of the generator body 100 exceeds the threshold value, the heating can be stopped.

[0079] Meanwhile, the heating gun 800 is locally heated, and the distance is inversely proportional to the temperature, and is affected by the working environment, and in the actual experimental test on the site, when the heating gun 800 and the heated part are kept at 10 cm, the heating temperature reaches the most suitable temperature for disassembling the bushing.

[0080] As shown in Figures 1-5 The second aspect of the application provides a method for replacing the aircraft generator lifting point bushing 200, which is applied to any of the aircraft generator lifting point bushing 200 replacement devices described above, and comprises the following steps:

[0081] Step 101: remove the spring pin 300 in the hole of the spring pin 300;

[0082] Step 102: rotate one end of the center screw 410 into the threaded hole of the lifting point bushing 200;

[0083] Step 103: insert the second pin 420 into the spring pin 300 hole;

[0084] Step 104: take out the lifting point bushing 200 by rotating the center screw 410.

[0085] When the lifting point bushing 200 is removed, the spring pin 300 is first removed from the spring hole, and in this embodiment, the spring pin 300 is removed by a threaded pin, then the threaded end of the center screw 410 is rotated into the threaded hole in the center of the lifting point bushing 200, and the second pin 420 is inserted into the spring pin 300 hole, thereby realizing the connection with the lifting point bushing 200, then rotating the center screw 410, and separating the lifting point bushing 200 from the generator body 100.

[0086] Further comprising: fixing the generator body 100 through a fixing device matched with the shape of the shell of the generator body 100; heating the side of the generator body provided with the lifting point bushing 200 to above 260 DEG C and below 280 DEG C through the heating device.

[0087] In the embodiment, the fixing device for the generator body 100 is the fixing shell 500, and the heating device for heating the generator body 100 is the heating gun 800. In the technical scheme, the step of "fixing the generator body 100 through the fixing device matched with the shape of the shell of the generator body 100" is before the step of "removing the spring pin 300 in the hole of the spring pin 300", and the step of "heating the peripheral side of the generator body provided with the lifting point bushing 200 to above 260 DEG C and below 280 DEG C through the heating device" is before the step of "taking out the lifting point bushing 200 through the rotating central screw 410".

[0088] In the present application, the terms "first", "second", "third" are only for the purpose of description, and cannot be understood as indicating or implying relative importance; the term "multiple" refers to two or more, unless otherwise explicitly limited. The terms "mounting", "connecting", "connecting", "fixing" and the like should be broadly understood, for example, "connecting" can be fixed connection, or detachable connection, or integrally connected; "connected" can be directly connected, or indirectly connected through an intermediate medium. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0089] In the description of the present application, it should be understood that the terms "upper", "lower", "left", "right", "front", "back" and the like indicate the orientation or positional relationship shown in the drawings, and are only for the purpose of facilitating the description of the present application and simplifying the description, and do not indicate or imply that the devices or units referred to must have a particular direction, be constructed and operated in a particular orientation, therefore, cannot be understood as a limitation on the present application.

[0090] In the description of the present application, the terms "one embodiment", "some embodiments", "a specific embodiment" and the like mean that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present application. In the present application, the illustrative description of the above terms does not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner.

[0091] The above is only the preferred embodiment of the present application, and is not used to limit the present application. For those skilled in the art, the present application can have various modifications and changes. Any modification, equivalent replacement, improvement, etc. made within the spirit and principles of the present application shall be included in the protection scope of the present application.

Claims

1. An aircraft generator hanger bushing replacement device, characterized by, It comprises: A generator body; A lifting point bushing located on the side surface of the generator body, the center of the top end of the lifting point bushing has a threaded hole, the top end of the lifting point bushing has a spring pin hole, a spring pin is arranged in the spring pin hole, and the spring pin has an internal thread; A dismounting device for dismounting the lifting point bushing; The dismounting device comprises a center screw and a second pin, one end of the center screw is screwed into the threaded hole at the center of the lifting point bushing, and the other end of the center screw is a nut.

2. The aircraft generator hanger bushing replacement device of Claim 1, wherein, It also comprises: A fixed shell for fixing the generator body, the upper surface of the bottom of the fixed shell has four first pins; The bottom of the generator body has four pin holes, and the positions of the four pin holes correspond to the four first pins.

3. The aircraft generator hanger bushing replacement device of Claim 1, wherein, The dismounting device further comprises: A mounting disc, a circular hole is formed at the center of the mounting disc, and the center screw passes through the mounting disc through the circular hole; The second pin is arranged on the mounting disc.

4. An aircraft generator hanger bushing replacement device according to claim 3, wherein, The second pin comprises: A threaded pin, the outer surface of the threaded pin has a thread, the size of the threaded pin corresponds to the spring pin, and the threaded pin is rotatably connected to the mounting disc; A cross slot is arranged on the side of the mounting disc where the threaded pin is not arranged, and the cross slot is connected to the threaded pin.

5. The aircraft generator hanger bushing replacement device of Claim 3, wherein, The second pin further comprises: A sleeve, the upper end of the sleeve has an internal thread; A connecting sleeve, which is annular and arranged on the side of the threaded pin, has an external thread, and is connected to the sleeve through the external thread.

6. The aircraft generator hanger bushing replacement device of Claim 3, wherein, The dismounting device further comprises: A fastening nut, which is screwed into the center screw, is arranged on the side of the center screw where the second pin is not arranged.

7. An aircraft generator hanger bushing replacement device according to claim 6, wherein, The dismounting device further comprises: A drive nut, which is screwed into the center screw, is arranged between the fastening nut and the nut of the center screw.

8. The aircraft generator hanger bushing replacement device of Claim 2, wherein, It also comprises: A fixed support, one end of which is connected to the fixed shell, the fixed support has a first movable arm, a second movable arm, and a clamping device; One end of the first movable arm is fixedly connected to the fixed shell, the other end of the first movable arm is rotatably connected to one end of the second movable arm, and the clamping device is rotatably connected to the other end of the second movable arm; A heating gun is fixed to the fixed support through the clamping device; A temperature measuring assembly, the temperature measuring end of which is arranged on the side of the generator body where the lifting point bushing is arranged.

9. An aircraft generator hanger bushing replacement method, characterized by, It is applied to the aircraft generator lifting point bushing replacement device of any one of claims 1-8, comprising: Removing the spring pin in the spring pin hole; Rotating one end of the center screw into the threaded hole of the lifting point bushing; Deepening the second pin into the spring pin hole; Bringing out the lifting point bushing by rotating the center screw.

10. The aircraft generator hanger bushing replacement method of claim 9, wherein, It also comprises: Fixing the generator body through the fixing device matched with the shape of the generator body shell; Heating the side of the generator body where the lifting point bushing is arranged to above 260°C and below 280°C through the heating device.

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