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WO2021000691A1 - Auxiliary tool for disassembling nozzle of aircraft engine - Google Patents

Auxiliary tool for disassembling nozzle of aircraft engine Download PDF

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Publication number
WO2021000691A1
WO2021000691A1 PCT/CN2020/094252 CN2020094252W WO2021000691A1 WO 2021000691 A1 WO2021000691 A1 WO 2021000691A1 CN 2020094252 W CN2020094252 W CN 2020094252W WO 2021000691 A1 WO2021000691 A1 WO 2021000691A1
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WO
WIPO (PCT)
Prior art keywords
actuating rod
nozzle
tail
hole
swivel
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/CN2020/094252
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French (fr)
Chinese (zh)
Inventor
顾辉
张伟光
郭怀超
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Shandong Taikoo Aircraft Engineering Co Ltd
Original Assignee
Shandong Taikoo Aircraft Engineering Co Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Shandong Taikoo Aircraft Engineering Co Ltd filed Critical Shandong Taikoo Aircraft Engineering Co Ltd
Publication of WO2021000691A1 publication Critical patent/WO2021000691A1/en
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
    • B25B—TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING OR HOLDING
    • B25B27/00—Hand tools, specially adapted for fitting together or separating parts or objects whether or not involving some deformation, not otherwise provided for
    • B25B27/14—Hand tools, specially adapted for fitting together or separating parts or objects whether or not involving some deformation, not otherwise provided for for assembling objects other than by press fit or detaching same

Definitions

  • the invention relates to the technical field of aircraft maintenance, in particular to an auxiliary tooling for removing the jet engine tail spray of an aircraft.
  • Aircraft engine maintenance is the top priority for aircraft safety. For the convenience of aircraft maintenance, it is often necessary to remove the engine tail spray for internal inspection or replace related parts.
  • Most of the Boeing 737 series aircraft engine tail nozzles are configured The tail nozzle is fixed to the tail nozzle by bolts. Because the tail nozzle and tail nozzle are in the high and low temperature fusion, high-frequency oscillation and multiple liquid contact areas at the tail of the engine, the bolts are connected to the tail nozzle and tail nozzle. Stress changes, which will result in "seizure" when removing the connecting bolts. Under the existing removal method, it is likely to cause damage to the fasteners and further result in failure to remove smoothly. There are 24 fastening screws, evenly distributed.
  • the present invention provides an auxiliary tool for removing the jet engine tail spray with convenient operation and safe use.
  • An auxiliary tooling for removing jet engine tail spray including:
  • Hydraulic lifting platform with brackets installed on the lifting platform;
  • the guide rail is installed horizontally on the front end of the bracket.
  • the centering column is slidingly sleeved on the guide rail.
  • the centering column is on the same axis as the guide rail.
  • the outer diameter of the centering column matches the diameter of the inner hole at the front end of the tail nozzle. In the inner hole at the front end of the tail nozzle;
  • the rotating guide mechanism is installed at the rear end of the bracket.
  • the ring-shaped rotating ring is rotatingly installed in the rotating guide mechanism.
  • the rotating ring and the centering column are on the same axis.
  • the tail nozzle is located in the inner hole of the rotating ring, and the upper and lower ends of the rotating ring Actuating rods are respectively arranged vertically, the inner end of the actuating rod is provided with a cutter head slot, and the cutter head is inserted into the cutter head slot;
  • the positioning mechanism is arranged on the support ring body. When the rotating ring rotates until the two cutter heads are respectively facing the two symmetrical fixing screws on the tail nozzle, the positioning mechanism locks and fixes the rotating ring;
  • the actuating rod drive mechanism drives the actuating rod to move inward to the screw hole of the fixing screw where the cutter head is inserted into the tail nozzle and driving the actuating rod to rotate to loosen the fixing screw.
  • the above-mentioned steering guide mechanism includes two annular support ring bodies, the support ring body is provided with an annular track concentric with the support ring body, the swivel ring is located between the two support ring bodies and the swivel ring The inner hole is inserted into the track, and the two supporting ring bodies are locked and fixed by a number of bolts.
  • the above-mentioned positioning mechanism includes N positioning holes I arranged on the support ring body at even intervals along the circumferential direction and N positioning holes II arranged on the rotating ring at even intervals along the circumferential direction.
  • the value of N and the tail The number of fixing screws on the nozzle is the same.
  • the above-mentioned actuating rod drive mechanism includes a screw hole provided on the swivel, a hollow screw screwed in the screw hole in the vertical direction, a hexagon head provided at the head end of the hollow screw, and a handle, the inner end of the handle is provided
  • a sleeve the inner end of the sleeve is provided with a hexagonal hole matching the hexagonal head
  • the actuating rod is inserted into the hollow screw
  • the size of the cutter head slot is larger than the inner diameter of the hollow screw
  • the upper end of the actuating rod is provided
  • a socket I and a socket II is provided on the sleeve.
  • rollers are respectively installed at the four corners of the lower end of the hydraulic lifting platform.
  • a handle is installed on one side of the hydraulic lifting platform.
  • a number of jacks are installed on the outer side of the hydraulic lifting platform.
  • the beneficial effect of the present invention is that when the fixing screw on the tail nozzle needs to be removed, the lifting table driving bracket of the hydraulic lifting table moves up and down to the same axis as the centering column and the tail nozzle, and then the centering column is moved inward along the guide rail to make it Insert it into the inner hole at the front end of the tail nozzle.
  • the tail end of the tail nozzle is in the transition.
  • the swivel is rotated to the proper position by the steering guide mechanism and locked by the positioning mechanism, and then the actuator rod is driven inward by the actuator rod drive mechanism. Move, insert the bit on the inner end of the actuating rod into the corresponding fixing screw, and rotate the actuating rod to loosen the fixing screw.
  • Figure 1 is a schematic diagram of the three-dimensional structure of the present invention.
  • Figure 2 is a three-dimensional exploded structure diagram of the swivel part of the present invention.
  • An auxiliary tooling for removing the jet engine tail spray of an aircraft comprising: a hydraulic lifting platform 1 on which a bracket 5 is installed on the lifting platform 4; a guide rail 10, which is horizontally installed on the front end of the bracket 5, and a centering column 6 is slidably fitted on the guide rail 10 ,
  • the centering column 6 is on the same axis as the guide rail 10, the outer diameter of the centering column 6 matches the diameter of the inner hole at the front end of the tail nozzle 7, and the centering column 6 is inserted into the inner hole at the front end of the tail nozzle 7;
  • the rotating guide mechanism Installed at the rear end of the bracket 5, the ring-shaped swivel 16 is rotatably installed in the rotation guide mechanism, the swivel 16 is on the same axis as the centering column 6, and the tail nozzle 7 is located in the inner hole of the swivel 16, and
  • the upper and lower ends are respectively vertically provided with an actuating rod 23, the inner end of the actuating
  • the lifting table 4 of the hydraulic lifting platform 1 drives the bracket 5 to move up and down to the same axis as the centering column 6 and the tail nozzle 7, and then move the centering column 6 to the inside along the guide rail 10 to make It is inserted into the inner hole at the front end of the tail nozzle 7.
  • the tail end of the tail nozzle 7 is located in the conversion 16.
  • the swivel 16 is rotated to a suitable position by the steering guide mechanism and locked by the positioning mechanism, and then driven by the actuating rod drive mechanism
  • the actuating rod 23 moves inwardly, the bit 25 at the inner end of the actuating rod 23 is inserted into the corresponding fixing screw, and the fixing screw can be loosened by rotating the actuating rod 23. Since there are two sets of symmetrical actuating rods 23, simultaneous removal actions in the up and down directions can be realized, so that the tail nozzle 7 is evenly stressed.
  • the fixing screws on the tail nozzle 7 are removed by turning the swivel 16 continuously. The whole process is simple to operate, and will not damage aircraft components, nor will it cause harm to operators.
  • the steering guide mechanism may have the following structure, which includes two circular support ring bodies 12, the support ring body 12 is provided with a circular ring-shaped track 13 concentric with it, and the swivel ring 16 is located on the two support ring bodies 12 The inner hole of the swivel 16 is inserted into the rail 13 and the two supporting ring bodies 12 are locked and fixed by a number of bolts 15. The two supporting ring bodies 12 sandwich the rotating ring 16, and the rotating ring 16 rotates in the track 13.
  • the positioning mechanism may be of the following structure, which includes N positioning holes I14 arranged on the support ring body 12 at even intervals along the circumferential direction and N positioning holes II17, N arranged at even intervals along the circumferential direction correspondingly arranged on the rotating ring 16.
  • the value of is consistent with the number of fixing screws on the tail nozzle 7.
  • positioning holes I14 and positioning holes II17 are the same as the number of fixing screws, it is ensured that when the actuating rod 23 rotates to the position of each corresponding fixing screw, it can be inserted into the positioning hole I14 of the same shaft through the pin.
  • the positioning hole II17 locks and fixes the position of the rotating ring 16.
  • the actuating rod drive mechanism may have the following structure, which includes a screw hole 18 provided on the swivel 16, a hollow screw 19 screwed in the screw hole 18 in the vertical direction, a hexagon head 20 provided at the head end of the hollow screw 19, and
  • the handle 8 the inner end of the handle 8 is provided with a sleeve 22, the inner end of the sleeve 22 is provided with a hexagonal hole 21 matching the hexagonal head 20, the actuating rod 23 is inserted into the hollow screw 19, the size of the cutter head slot 24 Larger than the inner diameter of the hollow screw 19, the upper end of the actuating rod 23 is provided with an insertion hole I, and the sleeve 22 is provided with an insertion hole II, as the head end of the moving rod 23 is inserted into the inner hole of the sleeve 22 and the insertion hole I When it coincides with the jack II, the plug board 9 is inserted into the jack I and the jack II.
  • rollers 2 are respectively installed at the four corners of the lower end of the hydraulic lifting platform 1.
  • the roller 2 can be arranged to easily move the hydraulic lifting platform 1 to the tail nozzle 7 of the aircraft.
  • a handle 3 is installed on one side of the hydraulic lifting platform 1. The handle 3 can facilitate the operator to drive the hydraulic lifting platform 1 to move, which further improves the convenience of operation.
  • each jack 27 moves to prop up the hydraulic lifting platform 1 off the ground to prevent it from moving.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Perforating, Stamping-Out Or Severing By Means Other Than Cutting (AREA)
  • Drilling And Boring (AREA)

Abstract

An auxiliary tool for disassembling a nozzle of an aircraft engine comprises a center-fixing column (6) capable of sliding inward along a guide rail (10) and entering an inner hole at a front end of the nozzle (7). A tail end of the nozzle is located in the rotating ring (16), and the rotating ring is rotated to a suitable position by a rotation direction guide mechanism and locked in place by a positioning mechanism. Next, an actuating rod (23) is driven by an actuating rod drive mechanism to move inward, a tool bit (25) at an inner end of the actuating rod is inserted into a corresponding fastening screw, and the actuating rod is rotated to loosen the fastening screw. Since the actuating rod is provided as a pair arranged symmetrically, a disassembling operation can be performed simultaneously at upper and lower sides, thereby applying balanced forces to the nozzle. The rotating ring is continuously rotated to loosen all fastening screws on the nozzle. The entire process involves simple operations, and does not cause damage to aircraft components or cause risks for operators.

Description

飞机发动机尾喷拆除辅助工装Auxiliary tooling for removing jet engine tail spray 技术领域Technical field

本发明涉及飞机维修技术领域，具体涉及一种飞机发动机尾喷拆除辅助工装。The invention relates to the technical field of aircraft maintenance, in particular to an auxiliary tooling for removing the jet engine tail spray of an aircraft.

背景技术Background technique

飞机发动机的维护工作对于飞机的安全性是重中之中，为了飞机维护的便利性，经常要拆除发动机尾喷进行内部检查或者更换相关部件等工作，波音737系列飞机发动机尾喷嘴大部分构型是通过螺栓将尾喷嘴固定与尾喷管之上，由于尾喷管及尾喷嘴处于发动机尾部高低温聚变，高频震荡及多种液体接触区域，因此螺栓与尾喷管及尾喷嘴的连接发生应力变化，这将导致在拆除连接螺栓时出现“咬死”状况，在现有拆除方法下，很有可能会造成紧固件损伤，进一步导致无法顺利拆除，紧固螺钉共有24颗，均匀分布在尾喷嘴一端，在拆除24颗螺栓时，需要对出现“咬死”情况的紧固件施加较大压力，因此在拆除时也会因为工作人员发力过猛早上身体损伤。常规的损伤紧固件拆除方面如拆钉器拆除、钻孔拆除等方法结不适用，现有拆钉器不适合发动机尾喷嘴构型，强制使用易造成工具及部件损伤，钻孔拆除对于发动机核心部件易造成损伤，如果发生损伤情况，尾喷嘴的拆除工作将十分困难。Aircraft engine maintenance is the top priority for aircraft safety. For the convenience of aircraft maintenance, it is often necessary to remove the engine tail spray for internal inspection or replace related parts. Most of the Boeing 737 series aircraft engine tail nozzles are configured The tail nozzle is fixed to the tail nozzle by bolts. Because the tail nozzle and tail nozzle are in the high and low temperature fusion, high-frequency oscillation and multiple liquid contact areas at the tail of the engine, the bolts are connected to the tail nozzle and tail nozzle. Stress changes, which will result in "seizure" when removing the connecting bolts. Under the existing removal method, it is likely to cause damage to the fasteners and further result in failure to remove smoothly. There are 24 fastening screws, evenly distributed. At the end of the tail nozzle, when removing the 24 bolts, it is necessary to apply greater pressure to the fasteners that have "seized". Therefore, the staff will also be injured in the morning due to excessive force during the removal. Conventional damage fastener removal methods such as nail remover removal and drilling removal are not applicable. The existing nail remover is not suitable for the configuration of the engine tail nozzle. Forced use can easily cause damage to tools and components. Drilling removal is for the engine The core components are easy to cause damage. If damage occurs, the removal of the tail nozzle will be very difficult.

发明内容Summary of the invention

本发明为了克服以上技术的不足，提供了一种操作方便、使用安全的飞机发动机尾喷拆除辅助工装。In order to overcome the shortcomings of the above technologies, the present invention provides an auxiliary tool for removing the jet engine tail spray with convenient operation and safe use.

本发明克服其技术问题所采用的技术方案是：The technical solutions adopted by the present invention to overcome its technical problems are:

一种飞机发动机尾喷拆除辅助工装，包括：An auxiliary tooling for removing jet engine tail spray, including:

液压升降台，其升降台面上安装有支架；Hydraulic lifting platform, with brackets installed on the lifting platform;

导轨，水平安装于支架的前侧端，定中柱滑动套装于导轨上，定中柱与导轨相同轴，定中柱的外径与尾喷嘴前端的内孔直径相匹配，定中柱插装于尾喷嘴前端的内孔中；The guide rail is installed horizontally on the front end of the bracket. The centering column is slidingly sleeved on the guide rail. The centering column is on the same axis as the guide rail. The outer diameter of the centering column matches the diameter of the inner hole at the front end of the tail nozzle. In the inner hole at the front end of the tail nozzle;

转动导向机构，安装于支架的后端，圆环形的转环转动安装于转动导向机构中，转环与定中柱相同轴，尾喷嘴位于转环的内孔中，转环的上下两端分别竖直设置有作动杆，所述作动杆的内侧端设置有刀头插槽，刀头插装于刀头插槽中；The rotating guide mechanism is installed at the rear end of the bracket. The ring-shaped rotating ring is rotatingly installed in the rotating guide mechanism. The rotating ring and the centering column are on the same axis. The tail nozzle is located in the inner hole of the rotating ring, and the upper and lower ends of the rotating ring Actuating rods are respectively arranged vertically, the inner end of the actuating rod is provided with a cutter head slot, and the cutter head is inserted into the cutter head slot;

定位机构，设置于支撑环体上，当转环旋转至两个刀头分别正对尾喷嘴上的两个相互对称的固定螺钉时，定位机构将转环锁死固定；以及The positioning mechanism is arranged on the support ring body. When the rotating ring rotates until the two cutter heads are respectively facing the two symmetrical fixing screws on the tail nozzle, the positioning mechanism locks and fixes the rotating ring; and

作动杆驱动机构，驱动作动杆向内侧移动至刀头插入尾喷嘴的固定螺钉的螺钉孔中并驱动作 动杆转动将固定螺钉松开。The actuating rod drive mechanism drives the actuating rod to move inward to the screw hole of the fixing screw where the cutter head is inserted into the tail nozzle and driving the actuating rod to rotate to loosen the fixing screw.

为了方便操作，还包括水平固定于定中柱前侧端的操作杆。In order to facilitate the operation, it also includes an operating rod fixed horizontally on the front end of the centering column.

进一步的，上述转向导向机构包括两个圆环形的支撑环体，所述支撑环体的内部设置有与其相同心的圆环形的轨道，转环位于两个支撑环体之间且转环的内孔插装于轨道上，两个支撑环体之间通过若干螺栓锁紧固定。Further, the above-mentioned steering guide mechanism includes two annular support ring bodies, the support ring body is provided with an annular track concentric with the support ring body, the swivel ring is located between the two support ring bodies and the swivel ring The inner hole is inserted into the track, and the two supporting ring bodies are locked and fixed by a number of bolts.

进一步的，上述定位机构包括沿圆周方向均匀间隔设置于支撑环体上的N个定位孔Ⅰ以及沿圆周方向均匀间隔设置于对应设置于转环上的N个定位孔Ⅱ，N的数值与尾喷嘴上的固定螺钉的个数相一致，当转环旋转至两个刀头分别正对尾喷嘴上的两个相互对称的固定螺钉时，销轴插入相同轴的两个定位孔Ⅰ与定位孔Ⅱ中。Further, the above-mentioned positioning mechanism includes N positioning holes I arranged on the support ring body at even intervals along the circumferential direction and N positioning holes II arranged on the rotating ring at even intervals along the circumferential direction. The value of N and the tail The number of fixing screws on the nozzle is the same. When the rotating ring rotates until the two cutter heads are respectively facing the two symmetrical fixing screws on the tail nozzle, the pin shaft is inserted into the two positioning holes I and positioning holes on the same axis. In Ⅱ.

进一步的，上述作动杆驱动机构包括设置于转环上的螺孔、沿竖直方向旋合于螺孔中的空心螺杆、设置于空心螺杆头端的六角头以及手柄，所述手柄内侧端设置有套管，套管内侧端设置有与六角头相匹配的六角孔，作动杆插装于空心螺杆中，刀头插槽的尺寸大于空心螺杆的内孔内径，所述作动杆上端设置有插孔Ⅰ，套管上设置有插孔Ⅱ，当作动杆的头端插入套管的内孔中且插孔Ⅰ与插孔Ⅱ相重合时，插板插入插孔Ⅰ与插孔Ⅱ中。Further, the above-mentioned actuating rod drive mechanism includes a screw hole provided on the swivel, a hollow screw screwed in the screw hole in the vertical direction, a hexagon head provided at the head end of the hollow screw, and a handle, the inner end of the handle is provided There is a sleeve, the inner end of the sleeve is provided with a hexagonal hole matching the hexagonal head, the actuating rod is inserted into the hollow screw, the size of the cutter head slot is larger than the inner diameter of the hollow screw, and the upper end of the actuating rod is provided There is a socket I and a socket Ⅱ is provided on the sleeve. When the head end of the moving rod is inserted into the inner hole of the sleeve and the socket I and the socket Ⅱ are overlapped, the plug-in board is inserted into the socket I and the socket II. in.

为了方便移动，上述液压升降台的下端四个边角处分别安装有滚轮。In order to facilitate the movement, rollers are respectively installed at the four corners of the lower end of the hydraulic lifting platform.

为了方便驱动液压升降台移动，上述液压升降台的一侧安装有拉手。In order to facilitate the movement of the hydraulic lifting platform, a handle is installed on one side of the hydraulic lifting platform.

为了防止液压升降台移动，上述液压升降台的外侧安装有若干千斤顶。In order to prevent the hydraulic lifting platform from moving, a number of jacks are installed on the outer side of the hydraulic lifting platform.

本发明的有益效果是：需要拆除尾喷嘴上的固定螺钉时，液压升降台的升降台面驱动支架上下移动至定中柱与尾喷嘴相同轴，之后将定中柱沿导轨向内侧移动，使其插入尾喷嘴前端的内孔中，尾喷嘴的尾端位于转换中，通过转向导向机构使转环转动到合适的位置并通过定位机构锁止，之后通过作动杆驱动机构驱动作动杆向内侧移动，作动杆内侧端的刀头插入对应的固定螺钉中，旋转作动杆即可将固定螺钉松开。由于有两组对称的作动杆，因此可以实现上下方向同时拆除动作，使尾喷嘴受力均匀。通过不断转动转环使其将尾喷嘴上的各个固定螺钉进行拆除。整个过程操作简单，且不会损伤飞机部件，也不会对操作人员造成伤害。The beneficial effect of the present invention is that when the fixing screw on the tail nozzle needs to be removed, the lifting table driving bracket of the hydraulic lifting table moves up and down to the same axis as the centering column and the tail nozzle, and then the centering column is moved inward along the guide rail to make it Insert it into the inner hole at the front end of the tail nozzle. The tail end of the tail nozzle is in the transition. The swivel is rotated to the proper position by the steering guide mechanism and locked by the positioning mechanism, and then the actuator rod is driven inward by the actuator rod drive mechanism. Move, insert the bit on the inner end of the actuating rod into the corresponding fixing screw, and rotate the actuating rod to loosen the fixing screw. Since there are two sets of symmetrical actuating rods, simultaneous removal actions can be realized in the up and down direction, so that the tail nozzle is evenly stressed. Remove the fixing screws on the tail nozzle by turning the swivel continuously. The whole process is simple to operate, and will not damage aircraft components, nor will it cause harm to operators.

附图说明Description of the drawings

图1为本发明的立体结构示意图；Figure 1 is a schematic diagram of the three-dimensional structure of the present invention;

图2为本发明的转环部位的立体爆炸结构图；Figure 2 is a three-dimensional exploded structure diagram of the swivel part of the present invention;

图中，1.液压升降台 2.滚轮 3.拉手 4.升降台面 5.支架 6.定中柱 7.尾喷嘴 8.手柄 9.插板 10.导轨 11.操作杆 12.支撑环体 13.轨道 14.定位孔Ⅰ 15.螺栓 16.转环 17.定位孔Ⅱ 18.螺 孔 19.空心螺杆 20.六角头 21.六角孔 22.套管 23.作动杆 24.刀头插槽 25.刀头 26.销轴 27.千斤顶。In the figure, 1. Hydraulic lifting table 2. Roller 3. Handle 4. Lifting table 5. Bracket 6. Centering column 7. Tail nozzle 8. Handle 9. Insert plate 10. Guide rail 11. Operation lever 12. Support ring 13 .Track 14. Positioning hole I 15. Bolt 16. Swivel 17. Positioning hole II 18. Screw hole 19. Hollow screw 20. Hexagon head 21. Hexagon hole 22. Sleeve 23. Actuating rod 24. Knife socket 25. Knife head 26. Pin shaft 27. Jack.

具体实施方式Detailed ways

下面结合附图1、附图2对本发明做进一步说明。The present invention will be further described below in conjunction with Figure 1 and Figure 2.

一种飞机发动机尾喷拆除辅助工装，包括：液压升降台1，其升降台面4上安装有支架5；导轨10，水平安装于支架5的前侧端，定中柱6滑动套装于导轨10上，定中柱6与导轨10相同轴，定中柱6的外径与尾喷嘴7前端的内孔直径相匹配，定中柱6插装于尾喷嘴7前端的内孔中；转动导向机构，安装于支架5的后端，圆环形的转环16转动安装于转动导向机构中，转环16与定中柱6相同轴，尾喷嘴7位于转环16的内孔中，转环16的上下两端分别竖直设置有作动杆23，作动杆23的内侧端设置有刀头插槽24，刀头25插装于刀头插槽24中；定位机构，设置于支撑环体12上，当转环16旋转至两个刀头25分别正对尾喷嘴7上的两个相互对称的固定螺钉时，定位机构将转环16锁死固定；以及作动杆驱动机构，驱动作动杆23向内侧移动至刀头25插入尾喷嘴7的固定螺钉的螺钉孔中并驱动作动杆23转动将固定螺钉松开。需要拆除尾喷嘴7上的固定螺钉时，液压升降台1的升降台面4驱动支架5上下移动至定中柱6与尾喷嘴7相同轴，之后将定中柱6沿导轨10向内侧移动，使其插入尾喷嘴7前端的内孔中，尾喷嘴7的尾端位于转换16中，通过转向导向机构使转环16转动到合适的位置并通过定位机构锁止，之后通过作动杆驱动机构驱动作动杆23向内侧移动，作动杆23内侧端的刀头25插入对应的固定螺钉中，旋转作动杆23即可将固定螺钉松开。由于有两组对称的作动杆23，因此可以实现上下方向同时拆除动作，使尾喷嘴7受力均匀。通过不断转动转环16使其将尾喷嘴7上的各个固定螺钉进行拆除。整个过程操作简单，且不会损伤飞机部件，也不会对操作人员造成伤害。An auxiliary tooling for removing the jet engine tail spray of an aircraft, comprising: a hydraulic lifting platform 1 on which a bracket 5 is installed on the lifting platform 4; a guide rail 10, which is horizontally installed on the front end of the bracket 5, and a centering column 6 is slidably fitted on the guide rail 10 , The centering column 6 is on the same axis as the guide rail 10, the outer diameter of the centering column 6 matches the diameter of the inner hole at the front end of the tail nozzle 7, and the centering column 6 is inserted into the inner hole at the front end of the tail nozzle 7; the rotating guide mechanism, Installed at the rear end of the bracket 5, the ring-shaped swivel 16 is rotatably installed in the rotation guide mechanism, the swivel 16 is on the same axis as the centering column 6, and the tail nozzle 7 is located in the inner hole of the swivel 16, and The upper and lower ends are respectively vertically provided with an actuating rod 23, the inner end of the actuating rod 23 is provided with a cutter head slot 24, the cutter head 25 is inserted into the cutter head socket 24; the positioning mechanism is arranged on the support ring body 12 Above, when the rotating ring 16 is rotated until the two cutter heads 25 are respectively facing the two mutually symmetrical fixing screws on the tail nozzle 7, the positioning mechanism locks and fixes the rotating ring 16; and the actuating rod driving mechanism drives the actuation The rod 23 moves inward to the screw hole where the cutter head 25 is inserted into the fixing screw of the tail nozzle 7 and drives the actuating rod 23 to rotate to loosen the fixing screw. When the fixing screw on the tail nozzle 7 needs to be removed, the lifting table 4 of the hydraulic lifting platform 1 drives the bracket 5 to move up and down to the same axis as the centering column 6 and the tail nozzle 7, and then move the centering column 6 to the inside along the guide rail 10 to make It is inserted into the inner hole at the front end of the tail nozzle 7. The tail end of the tail nozzle 7 is located in the conversion 16. The swivel 16 is rotated to a suitable position by the steering guide mechanism and locked by the positioning mechanism, and then driven by the actuating rod drive mechanism The actuating rod 23 moves inwardly, the bit 25 at the inner end of the actuating rod 23 is inserted into the corresponding fixing screw, and the fixing screw can be loosened by rotating the actuating rod 23. Since there are two sets of symmetrical actuating rods 23, simultaneous removal actions in the up and down directions can be realized, so that the tail nozzle 7 is evenly stressed. The fixing screws on the tail nozzle 7 are removed by turning the swivel 16 continuously. The whole process is simple to operate, and will not damage aircraft components, nor will it cause harm to operators.

转向导向机构可以为如下结构，其包括两个圆环形的支撑环体12，支撑环体12的内部设置有与其相同心的圆环形的轨道13，转环16位于两个支撑环体12之间且转环16的内孔插装于轨道13上，两个支撑环体12之间通过若干螺栓15锁紧固定。两个支撑环体12将转环16夹在中间，转环16在轨道13中转动。The steering guide mechanism may have the following structure, which includes two circular support ring bodies 12, the support ring body 12 is provided with a circular ring-shaped track 13 concentric with it, and the swivel ring 16 is located on the two support ring bodies 12 The inner hole of the swivel 16 is inserted into the rail 13 and the two supporting ring bodies 12 are locked and fixed by a number of bolts 15. The two supporting ring bodies 12 sandwich the rotating ring 16, and the rotating ring 16 rotates in the track 13.

定位机构可以为如下结构，其包括沿圆周方向均匀间隔设置于支撑环体12上的N个定位孔Ⅰ14以及沿圆周方向均匀间隔设置于对应设置于转环16上的N个定位孔Ⅱ17，N的数值与尾喷嘴7上的固定螺钉的个数相一致，当转环16旋转至两个刀头25分别正对尾喷嘴7上的两个相互对称的固定螺钉时，销轴26插入相同轴的两个定位孔Ⅰ14与定位孔Ⅱ17中。由于定位孔Ⅰ14以及定位孔Ⅱ17的个数与固定螺钉的个数相一致，因此确保作动 杆23转动到每个对应的固定螺钉的位置时，可以通过销轴插入相同轴的定位孔Ⅰ14与定位孔Ⅱ17将转环16的位置锁紧固定。The positioning mechanism may be of the following structure, which includes N positioning holes I14 arranged on the support ring body 12 at even intervals along the circumferential direction and N positioning holes II17, N arranged at even intervals along the circumferential direction correspondingly arranged on the rotating ring 16. The value of is consistent with the number of fixing screws on the tail nozzle 7. When the rotating ring 16 rotates until the two cutter heads 25 are respectively facing the two symmetrical fixing screws on the tail nozzle 7, the pin shaft 26 is inserted into the same shaft The two positioning holes Ⅰ14 and Ⅱ17 of the positioning hole. Since the number of positioning holes I14 and positioning holes II17 is the same as the number of fixing screws, it is ensured that when the actuating rod 23 rotates to the position of each corresponding fixing screw, it can be inserted into the positioning hole I14 of the same shaft through the pin. The positioning hole Ⅱ17 locks and fixes the position of the rotating ring 16.

作动杆驱动机构可以为如下结构，其包括设置于转环16上的螺孔18、沿竖直方向旋合于螺孔18中的空心螺杆19、设置于空心螺杆19头端的六角头20以及手柄8，手柄8内侧端设置有套管22，套管22内侧端设置有与六角头20相匹配的六角孔21，作动杆23插装于空心螺杆19中，刀头插槽24的尺寸大于空心螺杆19的内孔内径，作动杆23上端设置有插孔Ⅰ，套管22上设置有插孔Ⅱ，当作动杆23的头端插入套管22的内孔中且插孔Ⅰ与插孔Ⅱ相重合时，插板9插入插孔Ⅰ与插孔Ⅱ中。当将尾喷嘴7置于转环16中并将转环16转动到位后，先将手柄8下端的六角孔21插入到空心螺杆19的六角头20上，通过转动手柄8驱动空心螺杆19向内侧移动，由于刀头插槽24的尺寸大于空心螺杆19的内径，因此可以驱动作动杆23向内侧移动，直至刀头25插入对应的固定螺钉中。随着空心螺杆19的转动，作动杆23的头端伸出，之后将套管22插入到伸出的作动杆23中，插入插拔9将作动杆23与套管22连接于一体，之后转动手柄8即可驱动作动杆23转动，将固定螺钉松开。The actuating rod drive mechanism may have the following structure, which includes a screw hole 18 provided on the swivel 16, a hollow screw 19 screwed in the screw hole 18 in the vertical direction, a hexagon head 20 provided at the head end of the hollow screw 19, and The handle 8, the inner end of the handle 8 is provided with a sleeve 22, the inner end of the sleeve 22 is provided with a hexagonal hole 21 matching the hexagonal head 20, the actuating rod 23 is inserted into the hollow screw 19, the size of the cutter head slot 24 Larger than the inner diameter of the hollow screw 19, the upper end of the actuating rod 23 is provided with an insertion hole I, and the sleeve 22 is provided with an insertion hole II, as the head end of the moving rod 23 is inserted into the inner hole of the sleeve 22 and the insertion hole I When it coincides with the jack Ⅱ, the plug board 9 is inserted into the jack I and the jack II. When the tail nozzle 7 is placed in the swivel 16 and the swivel 16 is rotated in place, first insert the hexagonal hole 21 at the lower end of the handle 8 into the hexagonal head 20 of the hollow screw 19, and drive the hollow screw 19 to the inside by rotating the handle 8 Moving, since the size of the bit slot 24 is larger than the inner diameter of the hollow screw 19, the actuating rod 23 can be driven to move inward until the bit 25 is inserted into the corresponding fixing screw. With the rotation of the hollow screw 19, the head end of the actuating rod 23 extends, and then the sleeve 22 is inserted into the protruding actuating rod 23, and the plug 9 is inserted to connect the actuating rod 23 and the sleeve 22 together. , Then turn the handle 8 to drive the actuating rod 23 to rotate and loosen the fixing screw.

优选的，还包括水平固定于定中柱6前侧端的操作杆11。通过操作杆11可以方便方便定中柱6沿导轨10滑动，提高操作的便利性。液压升降台1的下端四个边角处分别安装有滚轮2。通过设置滚轮2可以方便将液压升降台1移动至飞机的尾喷嘴7处。液压升降台1的一侧安装有拉手3。通过拉手3可以方便操作人员驱动液压升降台1移动，进一步提高操作的便利性。Preferably, it also includes an operating rod 11 horizontally fixed to the front end of the centering column 6. The operation lever 11 can facilitate the centering column 6 to slide along the guide rail 10, which improves the convenience of operation. Rollers 2 are respectively installed at the four corners of the lower end of the hydraulic lifting platform 1. The roller 2 can be arranged to easily move the hydraulic lifting platform 1 to the tail nozzle 7 of the aircraft. A handle 3 is installed on one side of the hydraulic lifting platform 1. The handle 3 can facilitate the operator to drive the hydraulic lifting platform 1 to move, which further improves the convenience of operation.

优选的，液压升降台1的外侧安装有若干千斤顶27。在操作时，各个千斤顶27动作，将液压升降台1撑离地面，防止其移动。Preferably, a number of jacks 27 are installed on the outside of the hydraulic lifting platform 1. During operation, each jack 27 moves to prop up the hydraulic lifting platform 1 off the ground to prevent it from moving.

Claims (8)

一种飞机发动机尾喷拆除辅助工装，其特征在于，包括：An auxiliary tooling for removing jet engine tail spray, which is characterized in that it comprises: 液压升降台(1)，其升降台面(4)上安装有支架(5)；Hydraulic lifting platform (1), with a bracket (5) installed on the lifting platform (4); 导轨(10)，水平安装于支架(5)的前侧端，定中柱(6)滑动套装于导轨(10)上，定中柱(6)与导轨(10)相同轴，定中柱(6)的外径与尾喷嘴(7)前端的内孔直径相匹配，定中柱(6)插装于尾喷嘴(7)前端的内孔中；The guide rail (10) is installed horizontally on the front end of the bracket (5), the centering column (6) is slidably fitted on the guide rail (10), the centering column (6) is on the same axis as the guide rail (10), and the centering column ( 6) The outer diameter matches the inner hole diameter at the front end of the tail nozzle (7), and the centering post (6) is inserted into the inner hole at the front end of the tail nozzle (7); 转动导向机构，安装于支架(5)的后端，圆环形的转环(16)转动安装于转动导向机构中，转环(16)与定中柱(6)相同轴，尾喷嘴(7)位于转环(16)的内孔中，转环(16)的上下两端分别竖直设置有作动杆(23)，所述作动杆(23)的内侧端设置有刀头插槽(24)，刀头(25)插装于刀头插槽(24)中；The rotating guide mechanism is installed at the rear end of the bracket (5). The ring-shaped rotating ring (16) is rotatingly installed in the rotating guide mechanism. The rotating ring (16) is on the same axis as the centering column (6). The tail nozzle (7) ) Is located in the inner hole of the swivel (16), the upper and lower ends of the swivel (16) are respectively vertically provided with actuating rods (23), and the inner end of the actuating rod (23) is provided with a cutter head slot (24), the cutter head (25) is inserted into the cutter head slot (24); 定位机构，设置于支撑环体(12)上，当转环(16)旋转至两个刀头(25)分别正对尾喷嘴(7)上的两个相互对称的固定螺钉时，定位机构将转环(16)锁死固定；以及The positioning mechanism is arranged on the supporting ring body (12). When the rotating ring (16) rotates until the two cutter heads (25) are respectively facing the two symmetrical fixing screws on the tail nozzle (7), the positioning mechanism will The swivel (16) is locked and fixed; and 作动杆驱动机构，驱动作动杆(23)向内侧移动至刀头(25)插入尾喷嘴(7)的固定螺钉的螺钉孔中并驱动作动杆(23)转动将固定螺钉松开。The actuating rod driving mechanism drives the actuating rod (23) to move inward to the screw hole where the cutter head (25) is inserted into the fixing screw of the tail nozzle (7) and driving the actuating rod (23) to rotate to loosen the fixing screw. 根据权利要求1所述的飞机发动机尾喷拆除辅助工装，其特征在于：还包括水平固定于定中柱(6)前侧端的操作杆(11)。The auxiliary tool for removing the jet engine tail spray of an aircraft according to claim 1, characterized in that it further comprises an operating rod (11) fixed horizontally on the front end of the centering column (6). 根据权利要求1所述的飞机发动机尾喷拆除辅助工装，其特征在于：所述转向导向机构包括两个圆环形的支撑环体(12)，所述支撑环体(12)的内部设置有与其相同心的圆环形的轨道(13)，转环(16)位于两个支撑环体(12)之间且转环(16)的内孔插装于轨道(13)上，两个支撑环体(12)之间通过若干螺栓(15)锁紧固定。The aircraft engine tail jet removal auxiliary tooling according to claim 1, characterized in that: the steering guide mechanism includes two circular support ring bodies (12), and the support ring body (12) is provided with Concentric with the circular rail (13), the swivel (16) is located between the two supporting ring bodies (12) and the inner hole of the swivel (16) is inserted on the rail (13), and the two supports The ring bodies (12) are locked and fixed by a plurality of bolts (15). 根据权利要求3所述的飞机发动机尾喷拆除辅助工装，其特征在于：所述定位机构包括沿圆周方向均匀间隔设置于支撑环体(12)上的N个定位孔Ⅰ(14)以及沿圆周方向均匀间隔设置于对应设置于转环(16)上的N个定位孔Ⅱ(17)，N的数值与尾喷嘴(7)上的固定螺钉的个数相一致，当转环(16)旋转至两个刀头(25)分别正对尾喷嘴(7)上的两个相互对称的固定螺钉时，销轴(26)插入相同轴的两个定位孔Ⅰ(14)与定位孔Ⅱ(17)中。The aircraft engine tail jet removal auxiliary tooling according to claim 3, characterized in that: the positioning mechanism includes N positioning holes I (14) arranged on the support ring body (12) at even intervals along the circumferential direction and The direction is evenly spaced to correspond to the N positioning holes Ⅱ (17) provided on the rotating ring (16), the value of N is consistent with the number of fixing screws on the tail nozzle (7), when the rotating ring (16) rotates When the two cutter heads (25) are respectively facing the two symmetrical fixing screws on the tail nozzle (7), the pin shaft (26) is inserted into the two positioning holes I (14) and positioning holes II (17) of the same shaft. )in. 根据权利要求1所述的飞机发动机尾喷拆除辅助工装，其特征在于：所述作动杆驱动机构包括设置于转环(16)上的螺孔(18)、沿竖直方向旋合于螺孔(18)中的空心螺杆(19)、设置于空心螺杆(19)头端的六角头(20)以及手柄(8)，所述手柄(8)内侧端设置有套管(22)，套管(22)内侧端设置有与六角头(20)相匹配的六角孔(21)，作动杆(23)插装于空心螺杆(19)中，刀头插槽(24)的尺寸大于空心螺杆(19)的内孔内径， 所述作动杆(23)上端设置有插孔Ⅰ，套管(22)上设置有插孔Ⅱ，当作动杆(23)的头端插入套管(22)的内孔中且插孔Ⅰ与插孔Ⅱ相重合时，插板(9)插入插孔Ⅰ与插孔Ⅱ中。The aircraft engine tail jet removal auxiliary tooling according to claim 1, characterized in that: the actuating rod drive mechanism includes a screw hole (18) arranged on the swivel (16), which is screwed on the screw in the vertical direction. The hollow screw (19) in the hole (18), the hexagon head (20) and the handle (8) arranged at the head end of the hollow screw (19), the inner end of the handle (8) is provided with a sleeve (22), the sleeve (22) The inner side is provided with a hexagonal hole (21) matching the hexagonal head (20), the actuating rod (23) is inserted into the hollow screw (19), and the size of the cutter head slot (24) is larger than the hollow screw The inner diameter of the inner hole of (19), the upper end of the actuating rod (23) is provided with an insertion hole I, and the sleeve (22) is provided with an insertion hole II, as the head end of the moving rod (23) is inserted into the sleeve (22) When the socket I and the socket Ⅱ are overlapped in the inner hole of ), the plug-in board (9) is inserted into the socket I and the socket II. 根据权利要求1至5中任意一项所述的飞机发动机尾喷拆除辅助工装，其特征在于：所述液压升降台(1)的下端四个边角处分别安装有滚轮(2)。The auxiliary tooling for removing the jet engine tail spray of any one of claims 1 to 5, characterized in that: the four corners of the lower end of the hydraulic lifting platform (1) are respectively installed with rollers (2). 根据权利要求6所述的飞机发动机尾喷拆除辅助工装，其特征在于：所述液压升降台(1)的一侧安装有拉手(3)。The auxiliary tool for removing the jet engine tail spray of an aircraft according to claim 6, characterized in that: a handle (3) is installed on one side of the hydraulic lifting platform (1). 根据权利要求6所述的飞机发动机尾喷拆除辅助工装，其特征在于：所述液压升降台(1)的外侧安装有若干千斤顶(27)。The auxiliary tool for removing the jet engine tail spray of an aircraft according to claim 6, characterized in that: a plurality of jacks (27) are installed on the outer side of the hydraulic lifting platform (1).
PCT/CN2020/094252 2019-07-04 2020-06-04 Auxiliary tool for disassembling nozzle of aircraft engine Ceased WO2021000691A1 (en)

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