阅读说明：本技术 航空发动机配重螺钉分装工具及分装方法 (Aero-engine counterweight screw subpackaging tool and method ) 是由 苏新文 方洲 谢东 卢子元 向往 周颖 谭坤 胡磊 于 2021-01-29 设计创作，主要内容包括：本发明公开了一种航空发动机配重螺钉分装工具及分装方法,涉及航空发动机维修领域,解决配重螺钉安装区域空间狭窄,现有技术只能通过分解原台轴承的方式分装配重螺钉的问题,采用的技术方案是：航空发动机配重螺钉分装工具,包括套筒、第一传动杆、第二传动杆和扳手头,套筒呈L形,套筒内设置第一传动杆和第二传动杆,第一传动杆和第二传动杆在套筒的转角处通过传动结构连接,第一传动杆的一端为旋转操作端,第二传动杆的一端连接扳手头,扳手头设置用于与配重螺钉适配的卡槽或沉台。配重螺钉卡于扳手头的卡槽或沉台内,即可实现配重螺钉的装配,避免在动平衡工序反复分装原台轴承。本发明适用于航空发动机压气机转子动平衡工序分装配重螺钉。(The invention discloses a separate loading tool and a separate loading method for a counterweight screw of an aeroengine, relates to the field of maintenance of aeroengines, and solves the problems that the installation area space of the counterweight screw is narrow, and the counterweight screw can only be separately loaded in a mode of decomposing an original platform bearing in the prior art, and the technical scheme is as follows: aeroengine counter weight screw partial shipment instrument, including sleeve, first transfer line, second transfer line and wrench head, the sleeve is L shape, sets up first transfer line and second transfer line in the sleeve, and first transfer line and second transfer line pass through transmission structural connection at telescopic corner, and the one end of first transfer line is rotatory operation end, and the wrench head is connected to the one end of second transfer line, and the wrench head sets up the draw-in groove or heavy platform that is used for with the counter weight screw adaptation. The counterweight screw is clamped in the clamping groove or the sinking platform of the wrench head, so that the assembly of the counterweight screw can be realized, and the repeated split charging of the original platform bearing in the dynamic balance process is avoided. The invention is suitable for subpackaging the counterweight screws in the dynamic balance process of the aero-engine compressor rotor.)

1. Aeroengine counter weight screw partial shipment instrument, its characterized in that: including the sleeve, first transfer line (1), second transfer line (2) and wrench head (3), the sleeve is L shape, set up first transfer line (1) and second transfer line (2) in the sleeve, first transfer line (1) and second transfer line (2) are connected through transmission structure in telescopic corner, the one end of keeping away from transmission structure in first transfer line (1) is the rotation operation end, wrench head (3) is connected to the one end that transmission structure was kept away from in second transfer line (2), wrench head (3) set up the draw-in groove or the heavy platform that are used for with counter weight screw (4) adaptation one side back to second transfer line (2).

2. An aircraft engine counterweight screw split-charging tool as in claim 1, wherein: a magnetic object (5) is arranged in the clamping groove or the sinking platform of the wrench head (3).

3. An aircraft engine counterweight screw split-charging tool as in claim 2, wherein: the magnetic object (5) is a magnet which is stuck and fixed at the bottom of the clamping groove or the sinking platform.

4. An aircraft engine counterweight screw split-charging tool as in claim 2, wherein: the outline of wrench head (3) is the cuboid, and wrench head (3) sets up the draw-in groove, and the draw-in groove runs through wrench head (3), and the both sides of draw-in groove are the dog respectively.

5. An aircraft engine counterweight screw sub-assembly tool as claimed in any one of claims 1 to 4, wherein: the sleeve comprises a first sleeve (6) and a second sleeve (7), the first sleeve (6) and the second sleeve (7) are perpendicular to each other and are connected through two connecting plates (8) in a welding mode, and the connecting plates (8) are L-shaped.

6. An aircraft engine counterweight screw split-charging tool as in claim 5, wherein: and two ends of the first sleeve (6) and the second sleeve (7) are respectively provided with a lining (9).

7. An aircraft engine counterweight screw sub-assembly tool as claimed in any one of claims 1 to 4, wherein: the transmission structure is as follows: one end of the first transmission rod (1) is fixedly provided with an umbrella-shaped gear, one end of the second transmission rod (2) is fixedly provided with an umbrella-shaped gear, and the two umbrella-shaped gears are meshed with each other.

8. An aircraft engine counterweight screw sub-assembly tool as claimed in any one of claims 1 to 4, wherein: the rotary operation end of the first transmission rod (1) is provided with an external thread, and the outer side of the rotary operation end is provided with a knurled nut (10).

9. An aircraft engine counterweight screw split-charging tool as in claim 8, wherein: one side of the knurled nut (10) back to the sleeve is provided with a locking nut (11).

10. The aeroengine counterweight screw split charging method is characterized in that: the aerial engine counterweight screw sub-assembly tool sub-assembly counterweight screw (4) as claimed in any one of claims 1 to 9, comprising the steps of:

s1, placing the counterweight screws (4) to be assembled into the clamping grooves or the sinking platforms of the wrench heads (3);

s2, adjusting the angle of the aeroengine counterweight screw split-charging tool, and inserting the counterweight screw (4) and the wrench head (3) into the space between the compressor rotor (14) and the original platform bearing (13);

and S3, adjusting the aerial engine counterweight screw split-charging tool to enable the counterweight screw (4) to reach the mounting position.

S4, rotating the rotating operation end of the first transmission rod (1) until the balance weight screw (4) is locked in the corresponding bolt hole.

Technical Field

The invention relates to the field of maintenance of aero-engines, in particular to a split charging tool for split charging of a balance weight screw in a dynamic balancing process of an aero-engine compressor rotor and a split charging method implemented by the split charging tool.

Background

The dynamic balancing process of the compressor rotor of a certain type of aeroengine is a key process in repair, if the compressor rotor which is not balanced is used for assembly, the excessive residual unbalance amount causes the vibration of the engine, the abrasion of a bearing is aggravated, and the problems of oil leakage, excessive metal chips and the like can be caused in serious conditions. Because the original bearing of the engine needs to be assembled for dynamic balance, the outer diameter of the original bearing is large and is provided with a flange mounting edge, so that the space of a mounting area of the counterweight screws is very narrow, and the counterweight screws cannot be separately assembled on the premise of not disassembling the original bearing. The original bearing is required to be subpackaged on a special overturning frame, the time is averagely consumed for 50 minutes at one time, and the production efficiency is low.

Disclosure of Invention

The invention firstly provides a separate loading tool for a counterweight screw of an aeroengine, which solves the problems that the installation area space of the counterweight screw is narrow, and the counterweight screw can only be separately loaded in a mode of decomposing an original bearing in the prior art.

The technical scheme adopted by the invention for solving the technical problems is as follows: aeroengine counter weight screw partial shipment instrument, including the sleeve, first transfer line, second transfer line and wrench head, the sleeve is L shape, set up first transfer line and second transfer line in the sleeve, first transfer line and second transfer line pass through transmission structural connection in telescopic corner, the one end that transmission structure was kept away from to first transfer line is rotatory operation end, the one end that transmission structure was kept away from to the second transfer line is connected the wrench head, the one side setting of wrench head back to the second transfer line is used for the draw-in groove or the heavy platform with the counter weight screw adaptation.

Further, the method comprises the following steps: magnetic objects are arranged in the clamping grooves or the sinking platforms of the wrench head.

Specifically, the method comprises the following steps: the magnetic object is a magnet which is adhered and fixed at the bottom of the clamping groove or the sinking platform.

Specifically, the method comprises the following steps: the outline of wrench end is the cuboid, and wrench end sets up the draw-in groove, and the draw-in groove runs through wrench end, and the both sides of draw-in groove are the dog respectively.

Further, the method comprises the following steps: the sleeve comprises a first sleeve and a second sleeve, the first sleeve and the second sleeve are perpendicular to each other and are connected through two connecting plates in a welding mode, and the connecting plates are L-shaped.

Further, the method comprises the following steps: and two ends of the first sleeve and the second sleeve are respectively provided with a bushing.

Specifically, the method comprises the following steps: the transmission structure is as follows: one end of the first transmission rod is fixedly provided with an umbrella-shaped gear, one end of the second transmission rod is fixedly provided with an umbrella-shaped gear, and the two umbrella-shaped gears are meshed with each other.

Specifically, the method comprises the following steps: the rotary operation end of the first transmission rod is provided with an external thread, and the outer side of the rotary operation end is provided with a knurled nut.

Further, the method comprises the following steps: one side of the knurled nut back to the sleeve is provided with a locking nut.

The invention also provides a method for subpackaging the weight screws of the aero-engine, which subpackages the weight screws by using any one aero-engine weight screw subpackaging tool and comprises the following steps:

s1, placing the counterweight screws 4 to be assembled into the clamping grooves or the sinking platforms of the wrench heads 3;

s2, adjusting the angle of the aeroengine counterweight screw split-charging tool, and inserting the counterweight screw 4 and the wrench head 3 into the space between the compressor rotor 14 and the original platform bearing 13;

s3, adjusting the aeroengine counterweight screw split-charging tool to enable the counterweight screws 4 to reach the mounting positions;

and S4, rotating the rotating operation end of the first transmission rod 1 until the counterweight screws 4 are locked in the corresponding bolt holes.

The aeroengine counterweight screw subpackaging tool and the subpackaging method have the beneficial effects that: the counterweight screw is clamped in the clamping groove or the sinking platform of the wrench head, so that the assembly of the counterweight screw can be realized, and the repeated split charging of the original platform bearing in the dynamic balance process is avoided. Because the wrench head is mutually matched through the sleeve, the first transmission rod and the second transmission rod to support, the counterweight screw can be accurately placed in the installation position in a narrow space. When the counterweight screw is used, the fixing sleeve is held, and the rotating operation end is rotated, so that the counterweight screw can be installed or detached, and the operation is convenient.

The aeroengine counterweight screw subpackaging tool and the subpackaging method can be used for assisting in positioning and screwing the counterweight screw in a narrow space on the premise of not repeatedly subpackaging an original bearing, then the unbalance amount of a compressor rotor is adjusted, the time for averagely installing one counterweight screw is shortened from 50 minutes to 2 minutes, the production efficiency is greatly improved, the damage to parts is avoided, the maintenance period of an engine is shortened, and the maintenance cost of the engine is reduced.

The magnetic object is arranged in the clamping groove or the sinking platform of the wrench head, so that the counterweight screw can be prevented from falling from the clamping groove or the sinking platform of the wrench head. The first sleeve and the second sleeve are connected through the connecting plates in a welding mode, and the transmission structure between the first sleeve and the second sleeve is exposed between the two connecting plates, so that the transmission structure can be observed, installed and adjusted conveniently. The rotary operation end is provided with the knurled nut, so that the antiskid effect of the knurled nut is utilized, and the rotary operation end can be conveniently rotated manually or by other auxiliary tools.

Drawings

FIG. 1 is a schematic structural diagram of an aircraft engine counterweight screw split-charging tool of the invention.

FIG. 2 is a schematic view of the matching relationship between the aero-engine counterweight screw split-charging tool and a counterweight screw.

FIG. 3 is a structural diagram of the aero-engine counterweight screw split charging tool in use.

Fig. 4 is a longitudinal sectional view of fig. 3.

Reference numerals: the device comprises a first transmission rod 1, a second transmission rod 2, a wrench head 3, a balance weight screw 4, a magnetic object 5, a first sleeve 6, a second sleeve 7, a connecting plate 8, a bush 9, a knurled nut 10, a locking nut 11, a front journal 12, an original platform bearing 13 and a compressor rotor 14.

Detailed Description

The invention will be further explained with reference to the drawings.

Referring to fig. 1 and 2, the aeroengine counterweight screw split charging tool comprises a sleeve, a first transmission rod 1, a second transmission rod 2 and a wrench head 3. The sleeve is L-shaped and is of a hollow structure, and can be a whole, see figure 1; alternatively, with reference to fig. 2, the sleeve comprises a first sleeve 6 and a second sleeve 7, the first sleeve 6 and the second sleeve 7 being perpendicular to each other and being welded by two connecting plates 8, both connecting plates 8 being L-shaped and being arranged opposite each other. A first transmission rod 1 and a second transmission rod 2 are arranged in the sleeve, the first transmission rod 1 and the second transmission rod 2 are connected at the corner of the sleeve through a transmission structure, the transmission structure refers to a structure that the first transmission rod 1 is rotated, and the second transmission rod 2 can synchronously rotate along with the first transmission rod 1. For example, the transmission structure is a universal joint, or one end of the first transmission rod 1 is fixedly provided with a bevel gear, one end of the second transmission rod 2 is fixedly provided with a bevel gear, and the two bevel gears are meshed with each other. The first transmission rod 1 and the second transmission rod 2 can be directly penetrated into the sleeve, only a small gap is reserved between the first transmission rod 1 and the sleeve and between the second transmission rod 2 and the sleeve, and the first transmission rod 1 and the second transmission rod 2 can rotate relative to the sleeve, as shown in fig. 1. In order to facilitate the installation of the first transmission rod 1 and the second transmission rod 2, referring to fig. 2, a larger gap is reserved between the first transmission rod 1 and the second transmission rod 2 and the sleeve, meanwhile, bushings 9 are respectively arranged at two ends of the first transmission rod 1 and the second transmission rod 2, the first transmission rod 1 and the second transmission rod 2 are respectively inserted into the two bushings 9, and the first transmission rod 1 and the second transmission rod 2 are not directly contacted with the sleeve. The bushings 9 are fixedly connected to both ends of the first and second sleeves 6, 7, for example, the bushings 9 are connected to both ends of the first and second sleeves 6, 7 by threads.

One end of the first transmission rod 1, which is far away from the transmission structure, is a rotation operation end, and the rotation operation end is used for rotating the first transmission rod 1 manually or by matching with other auxiliary tools. In order to rotate the first driving lever 1 more conveniently, the rotating operation end of the first driving lever 1 is provided with an external thread, and the outer side of the rotating operation end is provided with a knurled nut 10. The knurled nut 10 can be fixed on the end of the first transmission rod 1 far away from the transmission structure through threads, or a locking nut 11 is arranged on the side of the knurled nut 10 opposite to the sleeve. One end of the second transmission rod 2, which is far away from the transmission structure, is connected with a wrench head 3, and one side of the wrench head 3, which is back to the second transmission rod 2, is provided with a clamping groove or a sinking platform which is used for being matched with the counterweight screw 4. In order to prevent the counterweight screws 4 from falling off the wrench head 3, a magnetic object 5 is arranged in a clamping groove or a sinking platform of the wrench head 3. For example, the magnetic object 5 is a magnet, and the magnet is fixed to the bottom of the slot or the sinking platform by adhesive. Spanner head 3 is used for blocking counter weight screw 4, and under the condition that satisfies the intensity requirement, its size should be as little as possible, for example, spanner head 3's outline is the cuboid, and spanner head 3 sets up the draw-in groove, and the draw-in groove runs through spanner head 3, and the both sides of draw-in groove are the dog respectively, refer to fig. 2.

The dynamic balancing process of the rotor is carried out by a weight screw assembling tool of the aircraft engine, and the dynamic balancing process is shown in figures 3 and 4. Firstly, putting a counterweight screw 4 to be assembled into a clamping groove or a sinking platform of a spanner head 3, and sucking the counterweight screw 4 by a magnetic object 5; secondly, the angle of the split charging tool is adjusted to enable the plane where the split charging tool is located to be parallel to the rotating plane of the compressor rotor 14, and the balance weight screw 4 and the wrench head 3 are inserted into the space between the compressor rotor 14 and the original platform bearing 13. And thirdly, adjusting the angle of the subpackaging tool to enable the plane where the subpackaging tool is located to be perpendicular to the rotating plane of the compressor rotor 14, and rotating to adjust the rotating operation end of the first transmission rod 1 to enable the counterweight screws 4 to avoid the sealing labyrinth and reach the installation positions of the counterweight screws 4. Finally, the rotating operation end of the first transmission rod 1 is rotated until the balance weight screw 4 is locked in the corresponding bolt hole. Through the actual structural feature of aeroengine counter weight screw partial shipment instrument according to compressor rotor subassembly, guarantee counter weight screw 4 can not fall into the complicated airflow channel of rotor subassembly at the partial shipment in-process, can rotate simultaneously in order to screw up counter weight screw 4.