CN115673744A - Dismounting device for connecting nut in shaft cavity of aircraft engine - Google Patents
Dismounting device for connecting nut in shaft cavity of aircraft engine Download PDFInfo
- Publication number
- CN115673744A CN115673744A CN202211522195.7A CN202211522195A CN115673744A CN 115673744 A CN115673744 A CN 115673744A CN 202211522195 A CN202211522195 A CN 202211522195A CN 115673744 A CN115673744 A CN 115673744A
- Authority
- CN
- China
- Prior art keywords
- wrench
- lifting
- folding
- electric
- platform
- 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.)
- Granted
Links
- 230000007246 mechanism Effects 0.000 claims abstract description 130
- 230000008878 coupling Effects 0.000 claims abstract description 24
- 238000010168 coupling process Methods 0.000 claims abstract description 24
- 238000005859 coupling reaction Methods 0.000 claims abstract description 24
- 230000005012 migration Effects 0.000 claims abstract description 5
- 238000013508 migration Methods 0.000 claims abstract description 5
- 239000000126 substance Substances 0.000 claims description 2
- 230000009471 action Effects 0.000 description 3
- 238000009434 installation Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000006467 substitution reaction Methods 0.000 description 2
- 230000007717 exclusion Effects 0.000 description 1
- 230000000750 progressive effect Effects 0.000 description 1
Images
Landscapes
- Automatic Assembly (AREA)
Abstract
The utility model belongs to the technical field of aviation engine axle intracavity coupling nut dismouting, concretely relates to aviation engine axle intracavity coupling nut dismouting device, including the automatic subassembly of screwing up, the automatic subassembly of screwing up further includes electronic folding spanner, vertical lift mechanism, horizontal migration mechanism, horizontal rotation mechanism, wherein: the bottom end of the electric folding wrench is used for being connected with the wrench head, and the wrench head can be horizontally folded; the vertical lifting mechanism is used for lifting the electric folding wrench in the vertical direction and comprises a lifting platform, a lifting servo motor, a ball screw and a lifting guide pillar; the horizontal moving mechanism is used for moving the electric folding wrench in the horizontal direction and comprises a moving platform, a moving servo electric cylinder, a guide rail and a sliding block; the horizontal slewing mechanism is used for horizontally rotating the electric folding wrench and comprises a slewing platform, a slewing servo motor and a slewing bearing.
Description
Technical Field
The application belongs to the technical field of aviation engine shaft cavity connecting nut dismounting, and particularly relates to an aviation engine shaft cavity connecting nut dismounting device.
Background
Aviation engine shaft intracavity utilizes coupling nut cooperation connecting screw to carry out the connection between the part, and is current, utilizes the spanner to carry out the dismouting with the manual work to coupling nut in the shaft chamber mostly, and is little at the shaft chamber opening, and is whole long and thin, under the narrow and small situation of inner space, is difficult to carry out effectual twisting to coupling nut and moves, and the operation is inconvenient, and causes the damage of colliding with to shaft intracavity portion easily.
The present application has been made in view of the above-mentioned technical drawbacks.
It should be noted that the above background disclosure is only for the purpose of assisting understanding of the inventive concept and technical solutions of the present invention, and does not necessarily belong to the prior art of the present patent application, and the above background disclosure should not be used for evaluating the novelty and inventive step of the present application without explicit evidence to suggest that the above content is already disclosed at the filing date of the present application.
Disclosure of Invention
The present application aims to provide a device for dismounting a coupling nut in an aircraft engine shaft cavity, which overcomes or alleviates at least one of the technical drawbacks of the known prior art.
The technical scheme of the application is as follows:
the utility model provides an aeroengine axle intracavity coupling nut dismouting device, includes the automatic subassembly of screwing up, the automatic subassembly of screwing up further includes electronic folding spanner, vertical lift mechanism, horizontal migration mechanism, horizontal rotation mechanism, wherein:
the bottom end of the electric folding wrench is used for being connected with the wrench head, and the wrench head can be horizontally folded;
the vertical lifting mechanism is used for lifting the electric folding wrench in the vertical direction and comprises a lifting platform, a lifting servo motor, a ball screw and a lifting guide pillar;
the horizontal moving mechanism is used for moving the electric folding wrench in the horizontal direction and comprises a moving platform, a moving servo electric cylinder, a guide rail and a sliding block;
the horizontal slewing mechanism is used for horizontally rotating the electric folding wrench and comprises a slewing platform, a slewing servo motor and a slewing bearing;
the electric folding wrench is positioned on a lifting platform in the middle of four lifting guide pillars in the vertical lifting mechanism, a lifting servo motor and a ball screw are arranged on one side of each of the four lifting guide pillars, and a lifting platform is connected to the upper surfaces of the four lifting guide pillars in the vertical lifting mechanism;
a moving platform is connected below four lifting guide pillars in the vertical lifting mechanism, four sliding blocks are fixed below the moving platform, and the four sliding blocks are respectively positioned above two guide rails in a group of two;
the movable servo electric cylinder is arranged on the rotary platform, a rotary support is arranged below the rotary platform, a rotary servo motor is arranged on one side of the rotary support, and the rotary support and the rotary servo motor are arranged on the fixed base;
the fixed base is used for centering and fixing the mounting edge of the stator casing of the engine;
can fold into vertical state with electronic folding wrench with the spanner head, and then can send into the lumen of axle along vertical direction with vertical lift mechanism with the spanner head, descend to near coupling nut, fold into horizontal state with electronic folding wrench with the spanner head thereafter, fix a position the spanner head to rotor coupling nut directly over with horizontal migration mechanism, further descend along vertical direction with vertical lift mechanism with the spanner head, thereby cup joint the spanner head on the device coupling nut, load coupling nut, twist coupling nut and carry out the dismouting.
According to at least one embodiment of the application, in the dismounting device for the connecting nut in the shaft cavity of the aircraft engine, D < D;
wherein the content of the first and second substances,
d is the inner diameter of the fixed base;
d is the radial dimension of the lumen opening.
According to at least one embodiment of the application, in the dismounting device for the connecting nut in the shaft cavity of the aircraft engine, the surface of the wrench head is provided with the pressure-sensitive sensor.
According to at least one embodiment of the application, the device for dismounting and mounting the connecting nut in the shaft cavity of the aircraft engine further comprises a fixed platform, a torque calibrator, a roller car bottom and an electric operating cabinet;
the fixed platform is connected to the bottom of the roller vehicle and is used for fixing the automatic tightening assembly;
the torque calibrator is arranged on the automatic tightening assembly and used for calibrating the torque of the automatic tightening assembly;
the electric operation cabinet is connected to the bottom of the roller vehicle, can record programs and is connected with the electric folding wrench, the vertical lifting mechanism, the horizontal moving mechanism and the driving mechanism of the horizontal rotating mechanism, and under the condition that the connecting nuts are uniformly distributed in the shaft cavity, the connecting nuts are screwed one by one according to the recorded programs to finish the dismounting.
According to at least one embodiment of the application, in the device for dismounting and mounting the connecting nut in the shaft cavity of the aircraft engine, the electric folding wrench comprises an electric wrench mechanism, a wrench head folding mechanism, an auxiliary elastic mechanism and a wrench rod positioning mechanism;
the electric wrench mechanism is used for electrically tightening the nut and consists of an electric wrench, a wrench lengthening bar and a wrench head;
the wrench head folding mechanism is used for folding the wrench head and consists of a folding mechanism servo electric cylinder, a guide sleeve, a guide pillar, a folding driving seat, a folding rod, a switching rod and the wrench head;
the wrench rod positioning mechanism is used for positioning and butting the wrench extension rod and the wrench head and consists of a positioning mechanism servo electric cylinder, a positioning mechanism driving seat, a positioning mechanism sliding block, a positioning mechanism guide rail, a positioning mechanism mounting seat and a wrench extension rod.
Drawings
FIG. 1 is a schematic view of a device for dismounting and mounting a coupling nut in a shaft cavity of an aircraft engine provided by an embodiment of the application;
FIG. 2 is a schematic view of an angle of a partial structure of a device for dismounting and mounting a connecting nut in a shaft cavity of an aircraft engine provided by an embodiment of the application;
FIG. 3 is a schematic view of another angle of a part structure of a connecting nut dismounting device in a shaft cavity of an aircraft engine provided by an embodiment of the application;
FIG. 4 is a partial schematic view of an aircraft engine shaft cavity coupling nut dismounting device provided by an embodiment of the present application during operation;
5-7 are schematic views of an electric folding wrench in the operation of the dismounting device for connecting nuts in the shaft cavity of the aircraft engine provided by the embodiment of the application;
wherein:
1-automatic tightening of the assembly; 2-fixing the platform; 3-a torque calibrator; 4-roller car bottom; 5-an electrical operation cabinet; 6-electric folding spanner; 7-a vertical lifting mechanism; 8-a horizontal movement mechanism; 9-a horizontal slewing mechanism; 10-hoisting a platform; 11-a lifting platform; 12-a mobile platform; 13-a rotary servo motor; 14-a stationary base; 15-a slewing bearing; 16-a slide block; 17-a guide rail; 18-a rotating platform; 19-moving the servo electric cylinder; 20-lifting guide columns; 21-a ball screw; 22-a lifting servo motor; 23-an engine stator case; 24-a rotor of the engine; 25-a coupling nut; 26-wrench head; 27-an electric wrench mechanism; 28-wrench head folding mechanism; 30-a wrench rod positioning mechanism; 31-positioning mechanism servo electric cylinder; 32-a positioning mechanism drive seat; 33-a positioning mechanism slide; 34-a positioning mechanism guide rail; 35-positioning mechanism mounting base; 36-wrench extension bar; 37-folding mechanism fixing seat; 38-folding bar; 39-a transfer lever; 40-folding the driving seat; 41-guide column; 42-a guide sleeve; 43-folding mechanism servo electric cylinder; 44-an electric wrench; 45-fixing a guide seat;
for a better understanding of the present embodiments, certain elements of the drawings may be omitted, enlarged or reduced, and do not represent actual product dimensions, and the drawings are for illustrative purposes only and are not to be construed as limiting the present patent.
Detailed Description
In order to make the technical solutions and advantages of the present application clearer, the technical solutions of the present application will be described in detail with reference to the accompanying drawings, and it should be understood that the specific embodiments described herein are only some of the embodiments of the present application, and are used for explaining the present application and not limiting the present application. It should be noted that, for convenience of description, only the parts related to the present application are shown in the drawings, and other related parts may refer to general designs, and in case of conflict, the embodiments and technical features in the embodiments in the present application may be combined with each other to obtain a new embodiment.
In addition, unless otherwise defined, technical or scientific terms used in the description of the present application shall have the ordinary meaning as understood by one of ordinary skill in the art to which the present application belongs. The terms "upper", "lower", "left", "right", "center", "vertical", "horizontal", "inner", "outer", and the like used in the description of the present application, which indicate orientations, are used only to indicate relative directions or positional relationships, and do not imply that the devices or elements must have a specific orientation, be constructed and operated in a specific orientation, and when the absolute position of the object to be described is changed, the relative positional relationships may be changed accordingly, and thus, should not be construed as limiting the present application. The use of "first," "second," "third," and the like in the description of the present application is for descriptive purposes only to distinguish between different components and is not to be construed as indicating or implying relative importance. The use of the terms "a," "an," or "the" and similar referents in the description of the application should not be construed as an absolute limitation of quantity, but rather as the presence of at least one. The word "comprising" or "comprises", and the like, when used in this description, is intended to specify the presence of stated elements or items, but not the exclusion of any other elements or items.
Further, it is noted that, unless expressly stated or limited otherwise, the terms "mounted," "connected," and the like are used in the description of the invention in a generic sense, e.g., connected as either a fixed connection or a removable connection or integrally connected; can be mechanically or electrically connected; they may be directly connected or indirectly connected through an intermediate medium, or they may be connected through the inside of two elements, and those skilled in the art can understand their specific meaning in the present application according to their specific situation.
The present application is described in further detail below with reference to fig. 1 to 7.
As shown in figure 1, the device for dismounting and mounting the connecting nut in the shaft cavity of the aircraft engine consists of an automatic screwing component 1, a fixed platform 2, a torque calibrator 3, a roller car bottom 4 and an electric operating cabinet 5.
Referring to fig. 2 and 3, the automatic tightening assembly 1 is composed of an electric folding wrench 6, a vertical lifting mechanism 7, a horizontal moving mechanism 8, and a horizontal turning mechanism 9.
The vertical lifting mechanism 7 is positioned at the rear side of the electric folding wrench 6, the horizontal moving mechanism 8 is positioned below the electric folding wrench 6, and the horizontal turning mechanism 9 is positioned below the horizontal moving mechanism 8.
The electric folding wrench 6 is used for horizontally folding the wrench head 26 to realize electric rotary loading of the connecting nut 25;
the vertical lifting mechanism 7 realizes the vertical Z-axis lifting of the electric folding wrench 6;
the horizontal moving mechanism 8 is used for moving the electric folding wrench 6 in the horizontal x-axis direction;
the horizontal turning mechanism 9 is used for horizontal θ -direction rotation of the electric folding wrench 6.
As shown in fig. 2 and 3, the vertical lift mechanism 7 is composed of a lift platform 11, a lift servo motor 22, a ball screw 21, a lift guide post 20, and the like.
Referring to fig. 5-7, the electric folding wrench 6 is composed of an electric wrench mechanism 27, a wrench head folding mechanism 28, and a wrench rod positioning mechanism 30.
The electric wrench mechanism 27 is used for electrically tightening nuts, the wrench head folding mechanism 28 is used for folding the wrench head 26, and the wrench rod positioning mechanism 30 is used for positioning and butting the wrench extension rod 36 with the wrench head 26.
The electric wrench mechanism 27 is composed of an electric wrench 44, a wrench extension bar 36 and a wrench head 26.
The wrench head folding mechanism 28 consists of a folding mechanism servo electric cylinder 43, a guide sleeve 42, a guide post 41, a folding driving seat 40, a folding rod 38, an adapter rod 39 and a wrench head 26.
The wrench rod positioning mechanism 30 is composed of a positioning mechanism servo electric cylinder 31, a positioning mechanism driving seat 32, a positioning mechanism sliding block 33, a positioning mechanism guide rail 34, a positioning mechanism mounting seat 35 and a wrench extension bar 36.
The wrench extension bar 36 is connected below the electric wrench 44, and the wrench extension bar 36 is installed on the folding mechanism fixing seat 37 and depends on four fixing guide seats 45 to carry out constraint in the vertical direction.
The electric wrench 44 is installed on the positioning mechanism driving seat 32, meanwhile, the positioning mechanism driving seat 32 is fixed with the electric cylinder head of the positioning mechanism servo electric cylinder 31, the positioning mechanism driving seat 32 is fixed on the positioning mechanism sliding block 33, the positioning mechanism sliding block 33 is installed on the positioning mechanism guide rail 34, the positioning mechanism guide rail 34 is fixed on the positioning mechanism installing seat 35, and therefore the downward movement extension of the wrench extension rod 36 can be achieved by driving the positioning mechanism servo electric cylinder 31.
The positioning mechanism mounting seat 35 is fixed on one side of the lifting platform 11, a folding mechanism fixing seat 37 is fixed below the lifting platform 11, a folding mechanism servo electric cylinder 43 is fixed on one side of the lifting platform 11, two guide sleeves 42 are mounted on the lifting platform 11, two guide pillars 41 are mounted in the guide sleeves 42 and fixed on a folding driving seat 40, the folding driving seat 40 is fixed with an electric cylinder head of the folding mechanism servo electric cylinder 43, the folding driving seat 40 is connected with a folding rod 38 through a pin shaft, the folding rod 38 is vertically constrained through four fixed guide seats 45, the folding rod 38 is connected with an adapter rod 39 through a pin shaft, the adapter rod 39 is connected with the wrench head 26 through a pin shaft, thus, the wrench head 26 is horizontally folded by driving the folding mechanism servo electric cylinder 43, the positioning mechanism servo electric cylinder 31 is driven, the wrench extension rod 36 is operated to move downwards, outer sleeve teeth at the front end of the wrench head are positioned and butted with inner sleeve teeth of the wrench head 26, the wrench head 26 is internally composed of a gear pair, the sleeve teeth are connected with the driving gear pair to transmit the sleeve teeth to a sleeve barrel of the wrench head 15, and loading nut connection is realized.
The horizontal moving mechanism 8 is composed of a moving platform 12, a moving servo electric cylinder 19, a guide rail 17, a slide block 16 and the like.
The horizontal rotation mechanism 9 is composed of a rotation platform 18, a rotation servo motor 13, a rotation support 15 and the like.
As shown in fig. 2 and 3, the electric folding wrench 6 is located on the lifting platform 11 in the middle of the four lifting guide pillars 20 in the vertical lifting mechanism 7, a lifting servo motor 22 and a ball screw 21 are arranged on one side of the four lifting guide pillars 20, a lifting platform 10 is connected to the upper surfaces of the four lifting guide pillars 20 in the vertical lifting mechanism 7, and the lifting platform 10 is used for lifting and transferring the automatic tightening assembly 1. A movable platform 12 is connected below four lifting guide pillars 20 in a vertical lifting mechanism 7, four sliding blocks 16 are fixed below the movable platform 12, the left sliding block 16 and the right sliding block 16 are respectively positioned above a left guide rail 17 and a right guide rail 17, a movable servo electric cylinder 19 is installed on a rotary platform 18, a rotary support 15 is arranged below the rotary platform 18, a rotary servo motor 13 is installed on one side of the rotary support 15, the rotary support 15 and the rotary servo motor 13 are arranged on a fixed base 14, and the fixed base 14 is used for centering and fixing with an installation edge of an engine stator casing 23.
As shown in fig. 4, the automatic tightening assembly 1 is mounted on the mounting edge of the engine stator casing 23 through the fixing base 14, and is centered through the mounting edge spigot of the engine stator casing 23, because the axis of the engine stator casing 23 coincides with the axis of the engine rotor 24, the axis of the electric folding wrench 6 coincides with the axis of the fixing base 14, so that the axis of the electric folding wrench 6 coincides with the axis of the engine rotor 24, and the rotation center of the electric folding wrench 6 is the theoretical position center of the rotor connecting nut 25 reference circle.
Design unable adjustment base 14 internal diameter D is less than 24 front axle journals internal diameter D of engine rotor, and the axostylus axostyle of electronic folding spanner 6 can not take place to bump and grind with 24 shaft cavity inner walls of engine rotor when guaranteeing the operation, and can arrange pressure sensitive sensor on spanner 26 surfaces, and spanner 26 takes place slight collision stress with 24 inner chamber inner walls of engine rotor, will report to the police immediately and indicate, solves the damage problem that the shaft cavity inner wall collides with.
The dismounting device for the connecting nut in the shaft cavity of the aircraft engine is used for dismounting, and can be carried out according to the following steps:
folding the wrench head 26 at the bottom end of the electric folding wrench 6 into a vertical state, and lowering the foldable wrench head 26 to the vicinity of the rotor connecting nut 25 along the vertical Z direction through the vertical lifting mechanism 7;
the wrench head 26 is folded into a horizontal state, if the space in the shaft cavity is insufficient, the wrench head 26 can be moved to a certain eccentric distance through the horizontal moving mechanism 8, and the sleeve on the wrench head 26 is positioned right above the connecting nut 25 through the combined action of the folding function of the wrench head 26, the vertical lifting function of the vertical lifting mechanism 7 and the horizontal moving function of the horizontal moving mechanism 8;
the wrench head 26 is continuously lowered along the vertical Z-axis direction through the vertical lifting mechanism 7, the sleeve on the wrench head is sleeved on the connecting nut 25, and electric rotary loading and screwing are carried out;
if all the connecting nuts 25 are uniformly distributed, a program can be recorded according to the uniformly distributed angles of all the connecting nuts 25, and the dismounting and mounting of all the connecting nuts 25 are completed one by controlling the vertical lifting mechanism 7, the horizontal moving mechanism 8 and the horizontal rotating mechanism 9;
if the connecting nuts 25 are not uniformly distributed, the positions of the connecting nuts 25 can be found one by one through the vertical lifting mechanism 7, the horizontal moving mechanism 8 and the horizontal rotating mechanism 9, and the disassembly and assembly of all the connecting nuts 25 are completed;
after the connection nuts 25 are disassembled, the original path of the electric folding wrench 6 exits from the cavity of the engine rotor 24, the lifting appliance is installed on the lifting platform 10, and the lifting automatic tightening assembly 1 is installed on the fixed platform 2.
After the complete installation action of each connecting nut 25 in the shaft cavity of the aircraft engine is completed for the first time, an automatic operation program can be set through the action and position information track of the whole electric folding wrench 6 which is completely recorded by the servo motors of all mechanisms, and when the connecting nuts 25 in the shaft cavity of the aircraft engine with the same model are dismounted next time, the dismounting can be automatically carried out according to the program.
The embodiments are described in a progressive mode in the specification, the emphasis of each embodiment is on the difference from the other embodiments, and the same and similar parts among the embodiments can be referred to each other.
Having thus described the present application in connection with the preferred embodiments illustrated in the accompanying drawings, it will be understood by those skilled in the art that the scope of the present application is not limited to those specific embodiments, and that equivalent modifications or substitutions of related technical features may be made by those skilled in the art without departing from the principle of the present application, and those modifications or substitutions will fall within the scope of the present application.
Claims (5)
1. The utility model provides an aviation engine shaft intracavity coupling nut dismouting device which characterized in that, including automatic subassembly (1) of screwing up, automatic subassembly (1) of screwing up further includes electronic folding spanner (6), vertical lift mechanism (7), horizontal migration mechanism (8), horizontal rotation mechanism (9), wherein:
the bottom end of the electric folding wrench (6) is connected with a wrench head (26) and can horizontally fold the wrench head (26);
the vertical lifting mechanism (7) is used for lifting the electric folding wrench (6) in the vertical direction and comprises a lifting platform (11), a lifting servo motor (22), a ball screw (21) and a lifting guide post (20);
the horizontal moving mechanism (8) is used for moving the electric folding wrench (6) in the horizontal direction and comprises a moving platform (12), a moving servo electric cylinder (19), a guide rail (17) and a sliding block (16);
the horizontal rotating mechanism (9) is used for horizontally rotating the electric folding wrench (6) and comprises a rotating platform (18), a rotating servo motor (13) and a rotating support (15);
the electric folding wrench (6) is positioned on a lifting platform (11) in the middle of four lifting guide posts (20) in the vertical lifting mechanism (7), a lifting servo motor (22) and a ball screw (21) are arranged on one side of each of the four lifting guide posts (20), and a hoisting platform (10) is connected to the upper surfaces of the four lifting guide posts (20) in the vertical lifting mechanism (7);
the lower surfaces of four lifting guide columns (20) in the vertical lifting mechanism (7) are connected with a movable platform (12), four sliding blocks (16) are fixed below the movable platform (12), and two of the four sliding blocks (16) are respectively positioned above two guide rails (17);
the movable servo electric cylinder (19) is arranged on the rotary platform (18), the rotary support (15) is arranged below the rotary platform (18), the rotary servo motor (13) is arranged on one side of the rotary support (15), and the rotary support (15) and the rotary servo motor (13) are arranged on the fixed base (14);
the fixed base (14) is used for centering and fixing with the mounting edge of the engine stator casing (23);
can fold into vertical state with electronic folding spanner (6) with wrench head (26), and then can send into shaft cavity with vertical lift mechanism (7) along vertical direction wrench head (26), descend near coupling nut (25), later fold into horizontal state with electronic folding spanner (6) with wrench head (26), with horizontal migration mechanism (8) with wrench head (26) location to rotor coupling nut (25) directly over, further descend with vertical lift mechanism (7) with wrench head (26) along vertical direction, thereby on sleeve cup joint device coupling nut (25) on wrench head (26), the sleeve is connected with the insection between electronic folding spanner (6), load coupling nut (25), twist and move coupling nut (25) and carry out the dismouting.
2. The aero-engine shaft cavity coupling nut removal apparatus of claim 1 wherein D < D;
wherein the content of the first and second substances,
d is the inner diameter of the fixed base (14);
d is the radial dimension of the lumen opening.
3. An aircraft engine axial bore coupling nut removal device according to claim 1, wherein the trigger head (26) has a surface with a pressure sensitive sensor.
4. The device for dismounting the connecting nut in the shaft cavity of the aircraft engine according to claim 1, characterized by further comprising a fixed platform (2), a torque calibrator (3), a roller car bottom (4) and an electric operating cabinet (4);
the fixed platform (2) is connected to the roller car bottom (4) and used for fixing the automatic tightening assembly (1);
the torque calibrator (3) is arranged on the automatic tightening assembly (1) and is used for calibrating the torque of the automatic tightening assembly (1);
the electric operation cabinet (4) is connected to the roller car bottom (4), can record programs, is connected with the electric folding wrench (6), the vertical lifting mechanism (7), the horizontal moving mechanism (8) and the driving mechanism of the horizontal rotating mechanism (9), and screws the connecting nuts (25) one by one according to the recorded programs under the condition that the connecting nuts (25) are uniformly distributed in the shaft cavity to complete disassembly and assembly.
5. The aircraft engine axial cavity coupling nut removal device of claim 1,
the electric folding wrench (6) comprises an electric wrench mechanism (27), a wrench head folding mechanism (28) and a wrench rod positioning mechanism (30);
the electric wrench mechanism (27) is used for electrically tightening the nut, the wrench head folding mechanism (28) is used for folding the wrench head (28), and the wrench rod positioning mechanism (30) is used for positioning and butting the wrench extension bar (36) and the wrench head (26).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211522195.7A CN115673744B (en) | 2022-11-30 | 2022-11-30 | Device for dismounting connecting nut in shaft cavity of aeroengine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211522195.7A CN115673744B (en) | 2022-11-30 | 2022-11-30 | Device for dismounting connecting nut in shaft cavity of aeroengine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115673744A true CN115673744A (en) | 2023-02-03 |
| CN115673744B CN115673744B (en) | 2024-01-30 |
Family
ID=85055008
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211522195.7A Active CN115673744B (en) | 2022-11-30 | 2022-11-30 | Device for dismounting connecting nut in shaft cavity of aeroengine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115673744B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116638296A (en) * | 2022-11-30 | 2023-08-25 | 苏州海通机器人系统有限公司 | Device and method for disassembling and assembling connecting nuts in shaft cavity of aero-engine |
Citations (21)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR20010061430A (en) * | 1999-12-28 | 2001-07-07 | 송재인 | Screw tightening apparatus |
| US6279427B1 (en) * | 1999-05-19 | 2001-08-28 | Francis Torq/Lite, Inc. | Crosshead jam nut torque tool |
| JP2003048128A (en) * | 2001-08-07 | 2003-02-18 | Mitsubishi Automob Eng Co Ltd | Automatic fastening machine |
| US20110030513A1 (en) * | 2008-03-13 | 2011-02-10 | Honda Motor Co., Ltd. | Bolt tightening method, bolt tightening device, bolt supplying method, and bolt supplying device |
| CN106315452A (en) * | 2016-10-11 | 2017-01-11 | 江苏理工学院 | Automatic disassembling device of automobile engine |
| CN106392601A (en) * | 2016-06-01 | 2017-02-15 | 重庆延锋江森汽车部件系统有限公司 | Bolt screwing-down device |
| CN107160157A (en) * | 2017-06-05 | 2017-09-15 | 大连理工大学 | A kind of automatic pre-tension method of bolt towards the deep chamber environment of slot |
| CN108000127A (en) * | 2017-12-12 | 2018-05-08 | 大连理工大学 | A kind of aircraft engine high pressure rotor seal pan postposition nut tightening device and method |
| CN108080939A (en) * | 2017-12-12 | 2018-05-29 | 大连理工大学 | A kind of preposition nut tightening device of aircraft engine high pressure rotor seal pan and method |
| CN108081189A (en) * | 2017-12-12 | 2018-05-29 | 大连理工大学 | It is a kind of to be useful in the link-type tightening mechanism tightened in inner-cavity structure and method |
| CN108237393A (en) * | 2016-12-27 | 2018-07-03 | 中国航发商用航空发动机有限责任公司 | Nut tightening device |
| CN110000530A (en) * | 2019-04-02 | 2019-07-12 | 江苏哈工药机科技股份有限公司 | A kind of automatic assembling device and automatic assemble method of railway bracket component |
| CN110497190A (en) * | 2019-09-03 | 2019-11-26 | 大连理工大学 | A kind of aero-engine internal nut cardan drive formula device for screwing up and method |
| CN110561097A (en) * | 2019-09-03 | 2019-12-13 | 大连理工大学 | device and method for tightening alignment nut of aircraft engine link mechanism |
| CN110561098A (en) * | 2019-09-03 | 2019-12-13 | 大连理工大学 | flexible shaft transmission type screwing device and method for nuts inside aircraft engine |
| CN210677669U (en) * | 2019-06-14 | 2020-06-05 | 广东贝迪机器人有限公司 | Screw locking device capable of monitoring pressure |
| CN111660085A (en) * | 2020-06-16 | 2020-09-15 | 中国航发航空科技股份有限公司 | Assembling device for connecting nut in narrow space of high-pressure rotor of engine and operation method |
| CN111673447A (en) * | 2020-07-28 | 2020-09-18 | 杭州研卓智能科技有限公司 | Nut screwing equipment used in assembling process of water pump impeller |
| CN212286614U (en) * | 2020-09-22 | 2021-01-05 | 沈阳航空航天大学 | Device is screwed up to narrow and small long space blind chamber quick big moment |
| CN112589408A (en) * | 2020-12-11 | 2021-04-02 | 北京航空航天大学 | Automatic tightening device and method for blind cavity nut of aero-engine compressor rotor |
| CN113414578A (en) * | 2021-05-25 | 2021-09-21 | 常州工学院 | Multi-degree-of-freedom screwing device |
-
2022
- 2022-11-30 CN CN202211522195.7A patent/CN115673744B/en active Active
Patent Citations (21)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6279427B1 (en) * | 1999-05-19 | 2001-08-28 | Francis Torq/Lite, Inc. | Crosshead jam nut torque tool |
| KR20010061430A (en) * | 1999-12-28 | 2001-07-07 | 송재인 | Screw tightening apparatus |
| JP2003048128A (en) * | 2001-08-07 | 2003-02-18 | Mitsubishi Automob Eng Co Ltd | Automatic fastening machine |
| US20110030513A1 (en) * | 2008-03-13 | 2011-02-10 | Honda Motor Co., Ltd. | Bolt tightening method, bolt tightening device, bolt supplying method, and bolt supplying device |
| CN106392601A (en) * | 2016-06-01 | 2017-02-15 | 重庆延锋江森汽车部件系统有限公司 | Bolt screwing-down device |
| CN106315452A (en) * | 2016-10-11 | 2017-01-11 | 江苏理工学院 | Automatic disassembling device of automobile engine |
| CN108237393A (en) * | 2016-12-27 | 2018-07-03 | 中国航发商用航空发动机有限责任公司 | Nut tightening device |
| CN107160157A (en) * | 2017-06-05 | 2017-09-15 | 大连理工大学 | A kind of automatic pre-tension method of bolt towards the deep chamber environment of slot |
| CN108000127A (en) * | 2017-12-12 | 2018-05-08 | 大连理工大学 | A kind of aircraft engine high pressure rotor seal pan postposition nut tightening device and method |
| CN108080939A (en) * | 2017-12-12 | 2018-05-29 | 大连理工大学 | A kind of preposition nut tightening device of aircraft engine high pressure rotor seal pan and method |
| CN108081189A (en) * | 2017-12-12 | 2018-05-29 | 大连理工大学 | It is a kind of to be useful in the link-type tightening mechanism tightened in inner-cavity structure and method |
| CN110000530A (en) * | 2019-04-02 | 2019-07-12 | 江苏哈工药机科技股份有限公司 | A kind of automatic assembling device and automatic assemble method of railway bracket component |
| CN210677669U (en) * | 2019-06-14 | 2020-06-05 | 广东贝迪机器人有限公司 | Screw locking device capable of monitoring pressure |
| CN110561097A (en) * | 2019-09-03 | 2019-12-13 | 大连理工大学 | device and method for tightening alignment nut of aircraft engine link mechanism |
| CN110561098A (en) * | 2019-09-03 | 2019-12-13 | 大连理工大学 | flexible shaft transmission type screwing device and method for nuts inside aircraft engine |
| CN110497190A (en) * | 2019-09-03 | 2019-11-26 | 大连理工大学 | A kind of aero-engine internal nut cardan drive formula device for screwing up and method |
| CN111660085A (en) * | 2020-06-16 | 2020-09-15 | 中国航发航空科技股份有限公司 | Assembling device for connecting nut in narrow space of high-pressure rotor of engine and operation method |
| CN111673447A (en) * | 2020-07-28 | 2020-09-18 | 杭州研卓智能科技有限公司 | Nut screwing equipment used in assembling process of water pump impeller |
| CN212286614U (en) * | 2020-09-22 | 2021-01-05 | 沈阳航空航天大学 | Device is screwed up to narrow and small long space blind chamber quick big moment |
| CN112589408A (en) * | 2020-12-11 | 2021-04-02 | 北京航空航天大学 | Automatic tightening device and method for blind cavity nut of aero-engine compressor rotor |
| CN113414578A (en) * | 2021-05-25 | 2021-09-21 | 常州工学院 | Multi-degree-of-freedom screwing device |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116638296A (en) * | 2022-11-30 | 2023-08-25 | 苏州海通机器人系统有限公司 | Device and method for disassembling and assembling connecting nuts in shaft cavity of aero-engine |
| CN116638296B (en) * | 2022-11-30 | 2024-03-19 | 苏州海通机器人系统有限公司 | Device and method for disassembling and assembling connecting nuts in shaft cavity of aero-engine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN115673744B (en) | 2024-01-30 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN115673744A (en) | Dismounting device for connecting nut in shaft cavity of aircraft engine | |
| CN204608642U (en) | A kind of hand clutch mechanism | |
| CN201065317Y (en) | Frame type radar antenna lifting device | |
| CN115741070A (en) | Tool and method for disassembling and assembling connecting nut in shaft cavity of aircraft engine | |
| CN110561097B (en) | Device and method for tightening alignment nut of aircraft engine link mechanism | |
| CN102430625A (en) | Electric control edge wrapping unit for automotive opener | |
| CN115890216A (en) | Device and method for dismounting connecting nut in shaft cavity of aircraft engine | |
| CN209425368U (en) | A kind of hand-rail type general automobile spring assembling/disassembling tool | |
| CN214538561U (en) | Steering column test bed | |
| CN201016228Y (en) | Swing-bar device parking apparatus having rotary bench | |
| CN105252199B (en) | Polyhedron rotation welding tool commonly used for multiple vehicle bodies | |
| CN208700483U (en) | A kind of lifting body and unmanned floor truck | |
| CN112720442A (en) | Unit module of reconfigurable mechanical arm | |
| CN213874952U (en) | Test fixture for detecting speed reducing motor | |
| CN105537916A (en) | Torsional spring assembling device for automatic car window lifter | |
| CN113007529A (en) | Image moving and splicing equipment applied to automatic control of computer | |
| CN220205086U (en) | Environment-friendly assembled monitoring equipment for building construction | |
| CN115741558A (en) | Dismounting wrench for connecting nut in shaft cavity of aircraft engine | |
| CN211401539U (en) | Torque wrench detection device | |
| CN209867446U (en) | Drilling equipment for automobile front axle | |
| CN115722909B (en) | Assembling and disassembling wrench for connecting nuts in shaft cavity of aeroengine and assembling and disassembling method for assembling wrench | |
| CN221337477U (en) | Automatic nut tightening equipment in narrow space | |
| CN114104325B (en) | Automatic propeller coiling device | |
| CN220389171U (en) | High-safety vehicle body overturning and positioning device | |
| CN212158507U (en) | Axle semi-axis ring flange hole position comprehensive testing platform |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| TA01 | Transfer of patent application right | ||
| TA01 | Transfer of patent application right |
Effective date of registration: 20230602 Address after: Building 3, Tianlong Science Park, No. 1, Zhufeng Road, Mudu Town, Wuzhong District, Suzhou City, Jiangsu Province, 215101 Applicant after: Suzhou Haitong Robot System Co.,Ltd. Address before: Shenhe District of Shenyang City, 110015 Wan Lin Road No. 1 in Liaoning Province Applicant before: AECC SHENYANG ENGINE Research Institute |
|
| GR01 | Patent grant | ||
| GR01 | Patent grant |