CN112025666A - Vehicle for assembling aviation turbine engine equipment - Google Patents
Vehicle for assembling aviation turbine engine equipment Download PDFInfo
- Publication number
- CN112025666A CN112025666A CN202010999204.6A CN202010999204A CN112025666A CN 112025666 A CN112025666 A CN 112025666A CN 202010999204 A CN202010999204 A CN 202010999204A CN 112025666 A CN112025666 A CN 112025666A
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- Prior art keywords
- turbine engine
- ring
- lifting
- fixed
- shaped movable
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- 230000007246 mechanism Effects 0.000 claims abstract description 37
- 230000007306 turnover Effects 0.000 claims abstract description 13
- 230000006872 improvement Effects 0.000 description 8
- 238000000034 method Methods 0.000 description 5
- 230000008569 process Effects 0.000 description 5
- 230000006978 adaptation Effects 0.000 description 2
- 239000000306 component Substances 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 240000007643 Phytolacca americana Species 0.000 description 1
- 239000008358 core component Substances 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 238000003756 stirring Methods 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25H—WORKSHOP EQUIPMENT, e.g. FOR MARKING-OUT WORK; STORAGE MEANS FOR WORKSHOPS
- B25H5/00—Tool, instrument or work supports or storage means used in association with vehicles; Workers' supports, e.g. mechanics' creepers
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Automatic Assembly (AREA)
Abstract
The invention discloses a vehicle for assembling aviation turbine engine equipment, which comprises a base, a lifting mechanism arranged on the base and a turnover mechanism connected with the lifting mechanism, wherein the lifting mechanism is arranged on the base; the turnover mechanism comprises a C-shaped fixed ring, and a C-shaped movable ring is arranged on the inner ring surface of the C-shaped fixed ring; a plurality of fixing devices for fixing the aviation turbine engine are arranged on the C-shaped movable ring; the C-shaped movable ring can rotate along the inner ring surface of the C-shaped fixed ring and further comprises a driving device for driving the C-shaped movable ring to rotate. The engine is lifted through the lifting mechanism, the engine is fixed through the C-shaped movable ring, and when the C-shaped movable ring rotates, the engine also overturns along with the C-shaped movable ring.
Description
Technical Field
The invention belongs to the field of automatic assembly, and particularly relates to a device for assembling an aircraft turbine engine.
Background
The turbine equipment structure is complicated, the required assembly flow is longer, the assembly precision requirement is high, the assembly process needs to start from the core component of the turbine equipment, gradually from the middle to both sides installation, in the whole assembly process, the turbine equipment needs to overturn and rotate for many times, multiple tests need to be carried out in the process, the assembly process is long in consumed time, the required space during assembly is large, meanwhile, certain parts need to be assembled at specific positions and angles, the installation is difficult, in addition, the assembly process of the turbine engine needs multiple tools, and an unassembled engine needs to be transferred among different tools, the operation is complex, personnel need to move back and forth, and the assembly required time is long.
Disclosure of Invention
In view of this, the invention provides a vehicle for assembling an aircraft turbine engine device, which is fixed and can be turned over when the aircraft turbine engine is assembled, so that the assembly is convenient.
In order to solve the technical problems, the technical scheme of the invention is as follows: the vehicle for assembling the aviation turbine engine equipment comprises a base, a lifting mechanism arranged on the base and a turnover mechanism connected with the lifting mechanism; the turnover mechanism comprises a C-shaped fixed ring, and a C-shaped movable ring is arranged on the inner ring surface of the C-shaped fixed ring; a plurality of fixing devices for fixing the aviation turbine engine are arranged on the C-shaped movable ring; the C-shaped movable ring can rotate along the inner ring surface of the C-shaped fixed ring and further comprises a driving device for driving the C-shaped movable ring to rotate. The engine is lifted through the lifting mechanism, the engine is fixed through the C-shaped movable ring, and when the C-shaped movable ring rotates, the engine also overturns along with the C-shaped movable ring.
As an improvement, an annular groove is formed in the outer ring surface of the C-shaped movable ring, and a plurality of pin shafts are transversely arranged in the annular groove; the driving device comprises a motor and a fluted disc fixed on a main shaft of the motor, and the fluted disc poking pin shaft drives the C-shaped movable ring to rotate. The C-shaped movable ring rotates by stirring the pin shaft through the fluted disc, and the control is more accurate.
As an improvement, a sliding groove is formed in the inner ring surface of the C-shaped fixed ring, and a roller matched with the sliding groove to slide is arranged on the C-shaped movable ring. The motion trail of the C-shaped movable ring is limited, and the derailment of the C-shaped movable ring is avoided.
Preferably, the fixing device comprises a connecting rod base fixed with the C-shaped movable ring, and a connecting rod connected with the connection point of the aircraft turbine engine is fixed on the connecting rod base; and the connecting rod base is also provided with a telescopic clamping plate for clamping the aviation turbine engine. The connecting rod is used for being connected with the engine tie point and fixes, and the splint are used for the centre gripping engine, makes it more firm. The clamping plate can be extended and retracted to deal with engines with different specifications.
As an improvement, a lead screw is arranged on the connecting rod base, and a sliding block is arranged on the lead screw; the clamping plate is fixed on the sliding block. The screw rod and the sliding block are used for driving the clamping plate to stretch, so that clamping is more stable.
As an improvement, the lifting mechanism comprises a vertically arranged screw rod, a lifting trolley in threaded fit with the screw rod is arranged on the screw rod, and a connecting plate is fixed on the lifting trolley; a lifting slide rail and a lifting slide block which is matched with the lifting slide rail to slide are vertically arranged beside the screw rod, and the connecting plate is fixed with the lifting slide block; the connecting plate is provided with a rotary ring, and the rotary ring is connected with a connecting piece on the C-shaped fixing ring. Utilize lead screw and dolly to drive the connecting plate up-and-down motion for whole tilting mechanism's lift control is more accurate.
As an improvement, the revolving ring is in threaded connection with the connecting piece.
As an improvement, a horizontal rail is horizontally arranged on the base, and a horizontal trolley is arranged on the horizontal rail; the lifting mechanism is fixed on the horizontal trolley. So that the lifting mechanism can move horizontally, and the whole engine is driven to move horizontally.
As an improvement, the device also comprises a lifting platform arranged on the base, and a fence is arranged at the edge of the lifting platform; a sliding door is arranged on the fence; the bottom of the lifting platform is provided with a through hole for the aviation turbine engine to pass through. The lifting platform provides a standing space for the assembly work of workers, and devices such as an escalator and the like do not need to be additionally arranged.
As an improvement, a scissor frame is arranged between the lifting platform and the base and is driven by an oil cylinder.
The invention has the advantages that: the vehicle for assembling the aviation turbine engine equipment with the structure lifts the engine through the lifting mechanism and overturns the engine through the overturning mechanism so as to adapt to the assembling work of the engine, greatly reduce the labor intensity of workers and improve the assembling efficiency and quality.
Drawings
FIG. 1 is a schematic structural diagram of the present invention.
Fig. 2 is a schematic structural diagram of the lifting mechanism.
Fig. 3 is a schematic structural view of the turnover mechanism.
Fig. 4 is a schematic structural view of the lifting platform.
The labels in the figure are:
the device comprises a base 1, a lifting structure 2, a turnover mechanism 3, a lifting platform 4 and an aviation turbine engine 5.
101 speed reducing motor, 102 screw rod, 103 connecting plate, 104 revolving ring, 105 lifting slide rail, 106 lifting slide block and 107 shell.
The device comprises a 201C-shaped fixed ring, a 202C-shaped movable ring, a 203 speed reducing motor, a 204 connecting piece, 205 pin shafts, 206 connecting rod bases, 207 connecting rods, 208 clamping plates, 209 lead screws and 210 sliding blocks.
502 fence, 503 sliding door, 504 via hole, 505 scissor rack, 506 oil cylinder, 602 horizontal trolley, 603 horizontal rail.
Detailed Description
In order that those skilled in the art will better understand the technical solutions of the present invention, the present invention will be further described in detail with reference to the following embodiments.
As shown in fig. 1-4, the present invention comprises a base 1, a lifting mechanism 2 disposed on the base 1, and a turnover mechanism 3 connected to the lifting mechanism 2; and a lifting platform 4 for providing a stepping space for a worker.
The turnover mechanism 3 comprises a C-shaped fixed ring 201, and a C-shaped movable ring 202 is arranged on the inner annular surface of the C-shaped fixed ring 301; a plurality of fixing devices for fixing the aircraft turbine engine 5 are arranged on the C-shaped movable ring 202; the C-shaped movable ring 202 can rotate along the inner annular surface of the C-shaped fixed ring 201, and further comprises a driving device for driving the C-shaped movable ring 202 to rotate. Specifically, an annular groove is formed in the outer annular surface of the C-shaped movable ring 202, and a plurality of pin shafts 205 are transversely arranged in the annular groove; the driving device comprises a speed reducing motor 203 and a fluted disc (not shown in the figure) fixed on a main shaft of the speed reducing motor 203, and the fluted disc poke pin shaft 205 drives the C-shaped movable ring 202 to rotate. The inner ring surface of the C-shaped fixed ring 201 is provided with a sliding groove, and the C-shaped movable ring 202 is provided with a roller which is matched with the sliding groove to slide.
The fixing device comprises a connecting rod base 206 fixed with the C-shaped movable ring 202, and a connecting rod 205 connected with a connecting point of the aircraft turbine engine 5 is fixed on the connecting rod base 206; the connecting rod foot 206 is also provided with a retractable clamping plate 208 for clamping the aircraft turbine engine 5. Specifically, a lead screw 209 is arranged on the connecting rod base 206, and a sliding block 210 in threaded fit with the lead screw 209 is arranged on the lead screw 209; the clamping plate 208 is fixed to a slide block 210. The lead screw 209 is driven by a motor. In this embodiment, the number of the fixing devices is two.
The lifting mechanism 2 comprises a vertically arranged screw rod 102 driven by a speed reducing motor 101, a lifting trolley (not shown in the figure) in threaded fit with the screw rod 102 is arranged on the screw rod 102, and a connecting plate 103 is fixed on the lifting trolley; a lifting slide rail 105 and a lifting slide block 106 which is matched with the lifting slide rail 105 to slide are vertically arranged beside the screw rod 102, and the connecting plate 103 is fixed with the lifting slide block 106; the two lifting slide rails 105 are respectively arranged at the left side and the right side of the screw rod 102. A rotary ring 104 is arranged on the connecting plate 103, and the rotary ring 104 is connected with a connecting piece 204 on the C-shaped fixing ring 201. The elevator mechanism 2 further comprises a housing 107 for shielding the above components, so that the lamp is more aesthetically pleasing and also dust-proof. The swivel ring 104 is threadedly coupled to the connector 204.
A horizontal rail 603 is horizontally arranged on the base 1, and a horizontal trolley 602 is arranged on the horizontal rail 603; the lifting mechanism 2 is fixed on the horizontal trolley 602. The horizontal rails 603 are two rails arranged in parallel, which helps to keep the lifting mechanism 2 balanced.
The edge of the lifting platform 4 arranged on the base 1 is provided with a fence 502; a sliding door 503 is arranged on the fence 502; the bottom of the lifting platform 4 is provided with a through hole 504 for the aircraft turbine engine 5 to pass through. A scissor frame 505 is arranged between the lifting platform 4 and the base 1, and the scissor frame 505 is driven by an oil cylinder 506.
In addition, the bottom of the base 1 is provided with support legs, the support is provided with rollers, and the support legs are provided with unfolding mechanisms for controlling the rollers to unfold and fold, so that the whole device is convenient to transfer.
When in use, the aircraft turbine engine 5 is fixed on the C-shaped movable ring 202, namely the connecting rod 207 is fixedly connected with an engine connecting point, and then the clamping plate 208 clamps the engine by rotating the lead screw 209. When the engine needs to be lifted, the speed reduction motor 101 is used for driving the screw rod 102 to rotate, and the rotation of the screw rod 102 drives the lifting trolley to enable the connecting plate 103 to move up and down along with the lifting trolley. The revolving ring 104 on the connecting plate 103 is connected with the connecting piece 204 on the turnover mechanism 3, so that the turnover mechanism 204 can be driven to move up and down, and the engine is driven to lift. When the engine needs to be turned over, the gear disc is driven by the speed reducing motor 203, and the teeth on the gear disc toggle the pin shaft 205 to enable the C-shaped movable ring 202 to rotate along the inner annular surface of the C-shaped fixed ring 201, so that the engine is driven to turn over. An assembler stands on the lifting platform 4 and lifts along with the lifting platform 4, so that components with different heights can be assembled conveniently.
The above is only a preferred embodiment of the present invention, and it should be noted that the above preferred embodiment should not be considered as limiting the present invention, and the protection scope of the present invention should be subject to the scope defined by the claims. It will be apparent to those skilled in the art that various modifications and adaptations can be made without departing from the spirit and scope of the invention, and these modifications and adaptations should be considered within the scope of the invention.
Claims (10)
1. The utility model provides an aviation turbine engine equipment assembly is with car, includes the base, its characterized in that: the lifting mechanism is arranged on the base, and the turnover mechanism is connected with the lifting mechanism; the turnover mechanism comprises a C-shaped fixed ring, and a C-shaped movable ring is arranged on the inner ring surface of the C-shaped fixed ring; a plurality of fixing devices for fixing the aviation turbine engine are arranged on the C-shaped movable ring; the C-shaped movable ring can rotate along the inner ring surface of the C-shaped fixed ring and further comprises a driving device for driving the C-shaped movable ring to rotate.
2. The aircraft turbine engine equipment assembly vehicle of claim 1, wherein: an annular groove is formed in the outer ring surface of the C-shaped movable ring, and a plurality of pin shafts are transversely arranged in the annular groove; the driving device comprises a motor and a fluted disc fixed on a main shaft of the motor, and the fluted disc poking pin shaft drives the C-shaped movable ring to rotate.
3. The aircraft turbine engine equipment assembly vehicle of claim 1, wherein: the inner ring surface of the C-shaped fixed ring is provided with a sliding groove, and the C-shaped movable ring is provided with a roller which is matched with the sliding groove to slide.
4. The aircraft turbine engine equipment assembly vehicle of claim 1, wherein: the fixing device comprises a connecting rod base fixed with the C-shaped movable ring, and a connecting rod connected with the connecting point of the aircraft turbine engine is fixed on the connecting rod base; and the connecting rod base is also provided with a telescopic clamping plate for clamping the aviation turbine engine.
5. An aircraft turbine engine equipment assembly vehicle according to claim 4, characterised in that: a lead screw is arranged on the connecting rod base, and a sliding block is arranged on the lead screw; the clamping plate is fixed on the sliding block.
6. The aircraft turbine engine equipment assembly vehicle of claim 1, wherein: the lifting mechanism comprises a vertically arranged screw rod, a lifting trolley in threaded fit with the screw rod is arranged on the screw rod, and a connecting plate is fixed on the lifting trolley; a lifting slide rail and a lifting slide block which is matched with the lifting slide rail to slide are vertically arranged beside the screw rod, and the connecting plate is fixed with the lifting slide block; the connecting plate is provided with a rotary ring, and the rotary ring is connected with a connecting piece on the C-shaped fixing ring.
7. An aircraft turbine engine equipment assembly vehicle according to claim 6, characterised in that: the rotary ring is in threaded connection with the connecting piece.
8. The aircraft turbine engine equipment assembly vehicle of claim 1, wherein: a horizontal rail is horizontally arranged on the base, and a horizontal trolley is arranged on the horizontal rail; the lifting mechanism is fixed on the horizontal trolley.
9. The aircraft turbine engine equipment assembly vehicle of claim 1, wherein: the lifting platform is arranged on the base, and a fence is arranged at the edge of the lifting platform; a sliding door is arranged on the fence; the bottom of the lifting platform is provided with a through hole for the aviation turbine engine to pass through.
10. An aircraft turbine engine equipment assembly vehicle according to claim 10, characterised in that: a scissor frame is arranged between the lifting platform and the base and is driven by an oil cylinder.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010999204.6A CN112025666A (en) | 2020-09-21 | 2020-09-21 | Vehicle for assembling aviation turbine engine equipment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010999204.6A CN112025666A (en) | 2020-09-21 | 2020-09-21 | Vehicle for assembling aviation turbine engine equipment |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN112025666A true CN112025666A (en) | 2020-12-04 |
Family
ID=73575616
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010999204.6A Pending CN112025666A (en) | 2020-09-21 | 2020-09-21 | Vehicle for assembling aviation turbine engine equipment |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN112025666A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113618688A (en) * | 2021-07-26 | 2021-11-09 | 成都航利装备科技有限公司 | Engine multi-degree-of-freedom assembly operation platform |
| CN114687546A (en) * | 2022-06-01 | 2022-07-01 | 四川万顺达机械制造有限公司 | Aeroengine assembly platform |
| CN115184028A (en) * | 2022-08-25 | 2022-10-14 | 芜湖中科飞机制造有限公司 | Fixing device for detecting aero-engine |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203779096U (en) * | 2014-04-08 | 2014-08-20 | 中国农业机械化科学研究院 | Multi-degree-of-freedom aero-engine assembly platform |
| US20160263715A1 (en) * | 2015-03-12 | 2016-09-15 | Ansaldo Energia Switzerland AG | Turbine part replacing apparatus |
| CN206263513U (en) * | 2016-11-21 | 2017-06-20 | 刘俊宝 | A kind of welding positioner |
| CN107775611A (en) * | 2017-10-10 | 2018-03-09 | 北京卫星环境工程研究所 | Spacecraft posture adjustment cantilevered multi-axis turntable |
| CN109095392A (en) * | 2018-10-16 | 2018-12-28 | 中国航发南方工业有限公司 | Hoistable platform for the assembly of whirlpool paddle type aero-engine |
| CN213439639U (en) * | 2020-09-21 | 2021-06-15 | 成都市珑熙科技有限公司 | Vehicle for assembling aviation turbine engine equipment |
-
2020
- 2020-09-21 CN CN202010999204.6A patent/CN112025666A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203779096U (en) * | 2014-04-08 | 2014-08-20 | 中国农业机械化科学研究院 | Multi-degree-of-freedom aero-engine assembly platform |
| US20160263715A1 (en) * | 2015-03-12 | 2016-09-15 | Ansaldo Energia Switzerland AG | Turbine part replacing apparatus |
| CN206263513U (en) * | 2016-11-21 | 2017-06-20 | 刘俊宝 | A kind of welding positioner |
| CN107775611A (en) * | 2017-10-10 | 2018-03-09 | 北京卫星环境工程研究所 | Spacecraft posture adjustment cantilevered multi-axis turntable |
| CN109095392A (en) * | 2018-10-16 | 2018-12-28 | 中国航发南方工业有限公司 | Hoistable platform for the assembly of whirlpool paddle type aero-engine |
| CN213439639U (en) * | 2020-09-21 | 2021-06-15 | 成都市珑熙科技有限公司 | Vehicle for assembling aviation turbine engine equipment |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113618688A (en) * | 2021-07-26 | 2021-11-09 | 成都航利装备科技有限公司 | Engine multi-degree-of-freedom assembly operation platform |
| CN114687546A (en) * | 2022-06-01 | 2022-07-01 | 四川万顺达机械制造有限公司 | Aeroengine assembly platform |
| CN114687546B (en) * | 2022-06-01 | 2022-08-12 | 四川万顺达机械制造有限公司 | Aeroengine assembly platform |
| CN115184028A (en) * | 2022-08-25 | 2022-10-14 | 芜湖中科飞机制造有限公司 | Fixing device for detecting aero-engine |
| CN115184028B (en) * | 2022-08-25 | 2023-09-01 | 芜湖中科飞机制造有限公司 | Fixing device for aeroengine detection |
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