Aero-engine part girth welding butt joint tool

Abstract

The utility model discloses an aero-engine part girth welding butt joint tool which comprises a base, the base is a frame of a rectangular structure, a containing groove is formed in the base, a control mechanical arm is arranged on one side of the base, and an indexing control assembly is arranged on one side of the containing groove. The utility model relates to the technical field of aero-engine ring welding tools, in the welding process of an aero-engine, the ring welding butt joint tool for the aero-engine parts limits a rotor shaft through a containing groove in the tool, the end of the rotor shaft is limited through an indexing control assembly at the end of the containing groove, and therefore the rotor shaft is prevented from being damaged. According to the indexing control assembly, an indexing controller rotates to drive a connector to rotate, the connector fixes the two radial ends of a rotor shaft, and by means of the multi-stage speed reduction effect driven by the indexing controller, the indexing rotation precision of the rotating shaft at the output position is improved in the mode that the wheel diameter is increased through speed reduction.

Description

TECHNICAL FIELD

[0001] The utility model relates to aviation ring welding tool technical field, concretely is a kind of aviation engine parts ring welding butt joint tool. BACKGROUND

[0002] The aviation engine is the heart of aviation equipment, and the current aviation engine is mainly of axial flow structure. The blades of the engine need to be arranged around the rotor of the aviation engine. In order to ensure the stable operation of the aviation engine and the operation time of the aviation engine, the blades of the aviation engine need to be welded.

[0003] In the welding work, the welding tool needs to be assisted to ensure that the blades correspond to the shaft of the rotor. The existing ring welding butt joint of the aviation engine mainly uses the tool to weld the blades and the rotor. The rotor is fixed by the butt joint tool. In order to ensure the uniform arrangement of the blades, the rotor needs to be driven to rotate at a fixed angle during welding. The indexing device of the current stage mainly relies on the rotation angle of the control motor. However, this method needs to accurately control the angular velocity of the motor and needs to be matched with an accurate sensor. Therefore, the equipment maintenance and equipment cost are high. In view of this, the present case is generated after in-depth research on the above problems. SUMMARY

[0004] In view of the deficiencies of the prior art, the aviation engine part ring welding butt joint tool is provided to solve the problems of the prior art.

[0005] To achieve the above purpose, the utility model discloses the following technical scheme: an aviation engine part ring welding butt joint tool, comprising a base, the base is a rectangular structure frame, the base is provided with a placing groove, one side of the base is provided with a control mechanical arm, one side of the placing groove is provided with an indexing control assembly;

[0006] The indexing control assembly comprises a control motor, the control motor is arranged on the base, one side of the control motor is provided with a speed reducer indexer, one side of the speed reducer indexer is provided with a connector, one side of the connector is connected with a rotor shaft.

[0007] The speed reducer indexer comprises a mounting shell; the mounting shell is mounted on the base, a driving shaft is arranged on the mounting shell, the driving shaft is connected with the control motor, a driving gear is sleeved on the driving shaft, a driven gear is meshed on one side of the driving gear, a driven shaft is connected at the center of the driven gear, a driving worm is connected at the end of the driven shaft, a driving worm wheel is movably arranged in the mounting shell, the driving worm is meshed with the driving worm wheel, and the center of the driving worm wheel is connected with the connector.

[0008] Preferably, the speed reducer index device further comprises a transmission gear, one side of the mounting shell is provided with a transmission groove, the transmission gear is assembled in the transmission groove, and the transmission gear is meshed with the driven gear.

[0009] Preferably, one side of the central shaft of the transmission gear extends a transmission rod, and the transmission rod is connected with the index angle detector.

[0010] Preferably, the end of the driving worm extends a control rod, and the end of the control rod is sleeved with a brake.

[0011] Preferably, the diameter and the number of teeth of the driving gear are smaller than the diameter and the number of teeth of the driven gear.

[0012] Preferably, the connector comprises a control guide rail, the control guide rail is assembled on the driving worm gear, a pair of clamping wire rods are installed on the driving worm gear, and a pair of clamping blocks in opposite motion are assembled on the pair of clamping wire rods. Beneficial effects

[0013] The utility model provides a kind of aeroengine parts ring welding butt joint tool.There is following beneficial effect: the aeroengine parts ring welding butt joint tool, in the welding process of aeroengine, limiting rotor shaft is positioned using the placing groove on tool, the end of rotor shaft is positioned by the index control assembly at the end of placing groove, index control assembly uses index controller rotation to drive connector rotation, connector is fixed to the radial both ends of rotor shaft, using the multistage reduction effect of index controller drive, by the way of reducing the wheel diameter, improve the output position of shaft index rotation accuracy. ACCURACY

[0014] Fig. 1 It is the first three-dimensional structure schematic view of the aeroengine parts ring welding butt joint tool of the utility model.

[0015] Fig. 2 It is the second three-dimensional structure schematic view of the aeroengine parts ring welding butt joint tool of the utility model.

[0016] Fig. 3 It is the local enlarged structure schematic view of the aeroengine parts ring welding butt joint tool of the utility model.

[0017] In the drawing: 1, base; 2, placing groove; 3, control motor; 4, speed reducer index device; 5, connector; 6, rotor shaft; 7, transmission rod; 8, index angle detector; 9, control rod; 10, brake; 41, mounting shell; 42, driving shaft; 43, driving gear; 44, driven gear; 45, driven shaft; 46, driving worm; 47, driving worm gear; 48, transmission gear; 51, control guide rail; 52, clamping wire rod; 53, clamping block. DETAILED DESCRIPTION

[0018] The technical solutions in the embodiments of the utility model will be apparently and completely described in connection with the drawings in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, rather than all the embodiments. Based on the embodiments in the utility model, all the other embodiments obtained by the ordinary skilled in the art without creative labor belong to the scope of protection of the utility model.

[0019] Please refer to Figs. 1-3 The utility model provides a kind of implementation scheme: in modern aero-engine production process, when aero-engine is welded, modern aero-engine is mainly supported by bearing bush structure when rotor is fixed, and then welding is completed by changing the angle of engine rotor and blade butt joint, but the angle adjustment of present aero-engine welding mainly adopts motor control, and at most sets up one-stage speed reducer, so that not only the angular velocity control of motor needs to be more accurate, but also high-precision angular velocity sensor is needed for detection, so the cost is higher.

[0020] For the above problems, the application discloses an aero-engine part welding butt joint tool, which comprises a base 1, the base 1 is a rectangular frame, the base 1 is the main support of the equipment, a placing groove 2 is arranged on the base 1, the placing groove 2 is used for the rotor of aero-engine, the placing groove 2 is limited by the setting of bearing bush while the aero-engine rotor can be rotated based on the bearing bush, a control arm is arranged on one side of the base 1, the end of the arm is loaded with a welding gun, and then a division control assembly is arranged on one side of the placing groove 2, which rotates and adjusts the aero-engine rotor by the division control assembly;

[0021] According to the description Figs. 1-3 It can be seen that the above-mentioned division control assembly comprises a control motor 3, the control motor 3 is arranged on the base 1, one side of the control motor 3 is provided with a speed reducer 4, one side of the speed reducer 4 is provided with a connector 5, one side of the connector 5 is connected with a rotor shaft 6;

[0022] In the specific implementation process, the control motor 3 is used as power, the control motor 3 drives the speed reducer 4 to rotate, the speed reducer 4 is accurately adjusted in angle by multi-stage speed reduction, and since the end of the rotor shaft 6 is clamped and fixed by the connector 5, the speed reducer 4 can more accurately rotate and adjust the rotor shaft 6;

[0023] According to the description Figs. 1-3It can be known that the above-mentioned speed reducer indexer 4 comprises a mounting shell 41; the mounting shell 41 is mounted on the base 1, and the mounting shell 41 is provided with a driving shaft 42 connected with the control motor 3; the driving shaft 42 is sleeved with a driving gear 43; one side of the driving gear 43 is engaged with a driven gear 44; the center of the driven gear 44 is connected with a driven shaft 45; the end of the driven shaft 45 is connected with a driving worm 46; the driving worm 46 is engaged with a driving worm wheel 47 movably arranged in the mounting shell 41; the center of the driving worm wheel 47 is connected with the connector 5;

[0024] In the specific implementation process, the mounting shell 41 is used as the installation basis of the speed reducer indexer 4; the driving shaft 42 is connected with the control motor 3; when the control motor 3 rotates, the driving shaft 42 drives the driving gear 43 to rotate synchronously; then the driving gear 43 is engaged with the driven gear 44; the driven gear 44 drives the driven shaft 45 to rotate; the engagement of the driving gear 43 and the driven gear 44 transmits the power torque to the driving worm 46 after one-stage speed reduction; then the engagement of the driving worm 46 and the driving worm wheel 47 completes two-stage speed reduction; thus the driving worm wheel 47 is reduced in speed again; in this way, through two-stage speed reduction, the angular velocity ratio of the control motor 3 and the driving worm wheel 47 is reduced; thus the angular velocity of the driving worm wheel 47 can be controlled more accurately.

[0025] As a preferred solution, further, according to the description attached Figs. 1-3 It can be known that the above-mentioned speed reducer indexer 4 further comprises a transmission gear 48; one side of the mounting shell 41 is provided with a transmission groove; the transmission gear 48 is assembled in the transmission groove; the transmission gear 48 is engaged with the driven gear 44; through the engagement of the transmission gear 48 and the driven gear 44, the rotational speed can be transmitted to the transmission gear 48; the output of the transmission gear 48 is used as the port for detecting the change in angle.

[0026] As a preferred solution, further, the middle shaft of the transmission gear 48 extends out a transmission rod 7; the end of the transmission rod 7 is connected with a graduation angle detector 8; the graduation angle detector 8 is connected with the transmission rod 7 through shaft connection; the transmission angle of the transmission gear 48 is detected by the graduation angle detector 8 to realize the detection of the change in angle.

[0027] As a preferred solution, further, the end of the driving worm 46 extends out a control rod 9; the end of the control rod 9 is sleeved with a brake 10; the control rod 9 is controlled by the brake 10 to stop the driving worm 46; in particular, the brake 10 is used to stop the driving worm 46.

[0028] As a preferred solution, further, the diameter and the number of teeth of the driving gear 43 are smaller than the diameter and the number of teeth of the driven gear 44.

[0029] As a preferred solution, further, according to the description attachedFigs. 1-3 It can be known that the connector 5 comprises a control guide rail 51, the control guide rail 51 is assembled on the driving worm gear 47, the driving worm gear is provided with a pair of clamping rods 52, and the pair of clamping rods 52 is assembled with a pair of clamping blocks 53 in relative motion;

[0030] In the specific implementation process, the control guide rail 51 is arranged on the central axis of the driving worm gear 47, the pair of clamping blocks 53 is linearly moved on the pair of clamping rods 52 by rotating the pair of clamping rods 52 on the control guide rail 51 and by the threaded engagement of the pair of clamping rods 52 and the threaded holes of the clamping blocks 53, and then the pair of clamping blocks 53 clamps the opposite sides of the rotor shaft 6, thereby achieving the limiting effect of the rotor shaft 6.

[0031] As can be known from the above, the aviation engine part ring welding butt joint tool limits the rotor shaft 6 by using the placing groove 2 on the tool during the welding process of the aviation engine, limits the end of the rotor shaft 6 by the indexing control assembly at the end of the placing groove 2, rotates the connector 5 by using the indexing controller of the indexing control assembly, fixes the rotor shaft 6 at the radial two ends of the connector 5, and improves the indexing rotation accuracy of the output position of the rotating shaft by the multi-stage reduction effect of the indexing controller and the way of increasing the wheel diameter through reduction.

[0032] Although the embodiments of the utility model have been shown and described, it can be understood by those skilled in the art that various changes, modifications, replacements and variations can be made to these embodiments without departing from the principles and spirits of the utility model, and the scope of the utility model is defined by the appended claims and their equivalents.

Claims

1. An aero-engine part ring welding butt joint tool, comprising a base (1), the base (1) is a rectangular structure frame, a placing groove (2) is arranged on the base (1), and a control mechanical arm is arranged on one side of the base (1), characterized in that, One side of the placing groove (2) is provided with a division control assembly; The division control assembly comprises a control motor (3), the control motor (3) is arranged on the base (1), one side of the control motor (3) is provided with a reduction division device (4), one side of the reduction division device (4) is provided with a connector (5), one side of the connector (5) is connected with a rotor shaft (6). The reduction division device (4) comprises a mounting shell (41); the mounting shell (41) is mounted on the base (1), the mounting shell (41) is provided with a driving shaft (42), the driving shaft (42) is connected with the control motor (3), the driving shaft (42) is sleeved with a driving gear (43), one side of the driving gear (43) is engaged with a driven gear (44), the center of the driven gear (44) is connected with a driven shaft (45), the end of the driven shaft (45) is connected with a driving worm (46), the mounting shell (41) is movably provided with a driving worm wheel (47), the driving worm (46) is engaged with the driving worm wheel (47), the center of the driving worm wheel (47) is connected with the connector (5).

2. The aircraft engine part girth welding butt joint tooling according to claim 1, characterized in that, The reduction division device (4) further comprises a transmission gear (48), one side of the mounting shell (41) is provided with a transmission groove, the transmission groove is fitted with the transmission gear (48), the transmission gear (48) is engaged with the driven gear (44).

3. The aircraft engine part girth welding butt joint tooling according to claim 2, characterized in that, The middle shaft of the transmission gear (48) extends a transmission rod (7), the shaft end of the transmission rod (7) is connected with a division angle detector (8).

4. The aircraft engine part girth welding butt joint tooling according to claim 3, characterized in that, The end of the driving worm (46) extends a control rod (9), the end of the control rod (9) is sleeved with a brake (10).

5. The aircraft engine part girth welding butt joint tooling according to claim 4, characterized in that, The wheel diameter and the number of teeth of the driving gear (43) are smaller than the wheel diameter and the number of teeth of the driven gear (44).

6. The aircraft engine part girth welding butt joint tooling according to claim 5, characterized in that, The connector (5) comprises a control guide rail (51), the control guide rail (51) is fitted on the driving worm wheel (47), the driving worm wheel is provided with a pair of clamping wire rods (52), the pair of clamping wire rods (52) are fitted with a pair of clamping blocks (53) moving oppositely.

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