CN115388248B - Hydraulic pipe connector for aircraft engine - Google Patents
Hydraulic pipe connector for aircraft engine Download PDFInfo
- Publication number
- CN115388248B CN115388248B CN202211330902.2A CN202211330902A CN115388248B CN 115388248 B CN115388248 B CN 115388248B CN 202211330902 A CN202211330902 A CN 202211330902A CN 115388248 B CN115388248 B CN 115388248B
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- CN
- China
- Prior art keywords
- main body
- radian
- plates
- hydraulic pipe
- aircraft engine
- 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.)
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Links
- 239000011111 cardboard Substances 0.000 claims description 5
- 230000005540 biological transmission Effects 0.000 claims description 3
- 238000007789 sealing Methods 0.000 claims description 3
- 238000012423 maintenance Methods 0.000 abstract description 2
- 239000003921 oil Substances 0.000 description 14
- 239000012535 impurity Substances 0.000 description 8
- 239000002184 metal Substances 0.000 description 7
- 238000001125 extrusion Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 239000012530 fluid Substances 0.000 description 2
- 230000001360 synchronised effect Effects 0.000 description 2
- 241000209128 Bambusa Species 0.000 description 1
- 235000017166 Bambusa arundinacea Nutrition 0.000 description 1
- 235000017491 Bambusa tulda Nutrition 0.000 description 1
- 235000015334 Phyllostachys viridis Nutrition 0.000 description 1
- 230000003139 buffering effect Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 239000010720 hydraulic oil Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000003014 reinforcing effect Effects 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
- F16L21/00—Joints with sleeve or socket
- F16L21/08—Joints with sleeve or socket with additional locking means
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B08—CLEANING
- B08B—CLEANING IN GENERAL; PREVENTION OF FOULING IN GENERAL
- B08B1/00—Cleaning by methods involving the use of tools
- B08B1/10—Cleaning by methods involving the use of tools characterised by the type of cleaning tool
- B08B1/12—Brushes
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Quick-Acting Or Multi-Walled Pipe Joints (AREA)
Abstract
The invention belongs to the technical field of hydraulic pipe interfaces, in particular to a hydraulic pipe interface for an aeroengine, which aims at the problem that a connecting pipe is inconvenient to disassemble because a connecting pipe is generally connected with a connecting pipe or a connector through a plurality of screws. The invention has simple structure, is convenient to disassemble the connecting pipe during maintenance and is convenient for people to use.
Description
Technical Field
The invention relates to the technical field of hydraulic pipe interfaces, in particular to a hydraulic pipe interface for an aeroengine.
Background
An aircraft engine is a highly complex and precise thermal machine, which serves as the heart of an aircraft, not only as the power for the flight of the aircraft, but also as an important driving force for the development of aviation industry, and an engine-driven pump is the main energy supply pump of an aircraft hydraulic system, and transmits pressure oil to various hydraulic users of the aircraft through hydraulic pipelines. In the sealing hydraulic system, a hydraulic pipe interface is a part for connecting an engine and a hydraulic pipe, and impulse action can be generated on the hydraulic pipe interface due to the fact that hydraulic oil is not steady-state pressure oil but is instantaneously pulsating high-pressure oil. In the invention patent application document with publication number CN114776655A, a hydraulic pipe joint for an aircraft engine is disclosed, a first convex ring, a second convex ring, a third convex ring and a fourth convex ring are arranged on the outer side surface of a joint main body; the reinforcing ring is clamped on the interface main body; the arc electromagnet covers the interface main body; the first magnetic ring is positioned above the fourth convex ring; the second magnetic ring is sleeved on the extension pipe and clamped between the sliding block and the locking piece; the two side surfaces of the magnetic block are symmetrically provided with belleville springs; a slider; the two ends of the electric magnetic strip penetrate out of the interface main body and are connected with the arc-shaped electromagnet; and the filter plate is arranged in the interface main body below the electromagnetic strip. According to the hydraulic pipe joint for the aircraft engine, the arc-shaped electromagnet is used for generating a magnetic field to restrain the movement of the sliding block, the repulsion force between the second magnetic ring and the magnetic block is used, the locking block is used for extruding the butterfly spring to deform, and the triple buffering effect is achieved.
Above-mentioned patent application, interface main part need be connected through a plurality of screws and connection pad with connecting pipe or connector, is not convenient for dismantle the connecting pipe.
Disclosure of Invention
The invention aims to solve the defect that a connector main body and a connecting pipe or a connector are connected through a plurality of screws and connecting discs, and the connecting pipe is inconvenient to disassemble, and provides a hydraulic pipe connector for an aircraft engine.
The invention adopts the following technical scheme:
the utility model provides a hydraulic pressure pipe interface that aeroengine used, including the interface main part, the below of interface main part is equipped with the connecting pipe, be equipped with same fixing base between interface main part and the connecting pipe, and be equipped with same sealed pad between interface main part and the connecting pipe, the fixing base internal rotation is connected with first drive screw and second drive screw, fixedly connected with first synchronizing wheel and second synchronizing wheel on first drive screw and the second drive screw, the transmission is connected with same hold-in range between first synchronizing wheel and the second synchronizing wheel, fixed mounting has two supplementary slide bars in the fixing base, be equipped with disassembly body in the fixing base, sliding connection has the oil pushing plate in the interface main part, one side fixedly connected with connecting rod of oil pushing plate, the right side of interface main part is equipped with the rubber buffer.
Preferably, a component force seat is fixedly mounted in the connector main body, a movable plate is fixedly connected to one end of the connecting rod, two component force rods are movably connected to the right side of the movable plate, a fixed round rod is fixedly mounted in the component force seat, two extrusion plates are slidably connected to the fixed round rod, the two extrusion plates are movably connected to one ends of the two component force rods, two reset springs are sleeved on the fixed round rod, and the two reset springs are connected with the two extrusion plates.
Preferably, the disassembly mechanism comprises two thread cylinders, two dragging plates, two clamping plates, two radian telescopic rods and two radian springs, the two thread cylinders are in threaded connection with a first driving screw and a second driving screw, the two dragging plates are fixedly connected with the two thread cylinders, the two dragging plates are in sliding connection with two auxiliary sliding rods, the two clamping plates are connected with the fixed seat in a rotating mode, and the two clamping plates are attached to the connecting pipe.
Preferably, two radian telescopic links all with fixing base fixed connection, and the one end and two cardboards of two radian telescopic links are connected, two radian spring housing locate on two radian telescopic links.
Preferably, be equipped with two magnetic paths in the interface main part, push away one side fixedly connected with extension rod of oiled-plate, the one end fixedly connected with brush of extension rod is equipped with the deflector in the interface main part, is equipped with fluid filter mesh hole on the deflector, and the both sides of interface main part all are equipped with the collecting box, and the design of deflector upper surface has the slope to correspond the collecting box.
Compared with the prior art, the invention has the advantages that:
(1) This scheme is owing to set up the extension rod and drive the brush and remove to metal impurity on two magnetic paths clears up, and metal impurity after the clearance falls on the deflector, and in sliding into two collecting boxes, has realized carrying out the purpose of collecting to metal impurity.
(2) This scheme is owing to set up two screw thread section of thick bamboos and drive two dragging plates and remove, and two dragging plates drive two cardboards and keep away from the connecting pipe, and two cardboards drive two radian telescopic links and contract to two radian springs of compression can accomplish the dismantlement, have realized convenient to detach's purpose.
The invention has simple structure, is convenient to disassemble the connecting pipe during maintenance and is convenient for people to use.
Drawings
FIG. 1 is a schematic view of a hydraulic tube interface for an aircraft engine according to the present invention;
FIG. 2 is a schematic perspective view of a threaded barrel of a hydraulic pipe joint for an aircraft engine according to the present invention;
FIG. 3 is a schematic structural diagram of part A of a hydraulic pipe joint for an aircraft engine according to the present invention;
FIG. 4 is a schematic structural view of part B of a hydraulic pipe joint for an aircraft engine according to the present invention;
fig. 5 is a schematic structural diagram of a part C of a hydraulic pipe joint for an aircraft engine according to the present invention.
In the figure: 1. an interface body; 2. a connecting pipe; 3. a fixed seat; 4. a gasket; 5. a first drive screw; 6. a second drive screw; 7. a first synchronization wheel; 8. a second synchronizing wheel; 9. a synchronous belt; 10. an auxiliary slide bar; 11. an oil pushing plate; 12. a connecting rod; 13. a rubber plug; 14. a component force seat; 15. moving the plate; 16. a force-dividing rod; 17. fixing the round rod; 18. a pressing plate; 19. a return spring; 20. a threaded barrel; 21. dragging a plate; 22. clamping a plate; 23. a radian telescopic rod; 24. a radian spring; 25. a magnetic block; 26. an extension pole; 27. a brush; 28. a guide plate; 29. and a collecting box.
Detailed Description
The technical solution in this embodiment will be clearly and completely described below with reference to the drawings in this embodiment.
Example one
Referring to fig. 1-5, a hydraulic pipe joint for an aircraft engine includes a joint main body 1, a connecting pipe 2 is arranged below the joint main body 1, a same fixing seat 3 is arranged between the joint main body 1 and the connecting pipe 2, a same sealing gasket 4 is arranged between the joint main body 1 and the connecting pipe 2, a first driving screw 5 and a second driving screw 6 are rotatably connected in the fixing seat 3, a first synchronizing wheel 7 and a second synchronizing wheel 8 are fixedly connected on the first driving screw 5 and the second driving screw 6, a same synchronizing belt 9 is connected between the first synchronizing wheel 7 and the second synchronizing wheel 8 in a transmission manner, two auxiliary sliding rods 10 are fixedly installed in the fixing seat 3, a dismounting mechanism is arranged in the fixing seat 3, an oil pushing plate 11 is slidably connected in the joint main body 1, a connecting rod 12 is fixedly connected on one side of the oil pushing plate 11, and a rubber plug 13 is arranged on the right side of the joint main body 1.
In this embodiment, a force component seat 14 is fixedly installed in the interface main body 1, one end of the connecting rod 12 is fixedly connected with a moving plate 15, the right side of the moving plate 15 is movably connected with two force component rods 16, a fixed round rod 17 is fixedly installed in the force component seat 14, two squeezing plates 18 are slidably connected on the fixed round rod 17, the two squeezing plates 18 are movably connected with one ends of the two force component rods 16, two return springs 19 are sleeved on the fixed round rod 17, and the two return springs 19 are connected with the two squeezing plates 18.
In this embodiment, the detaching mechanism includes two threaded cylinders 20, two dragging plates 21, two clamping plates 22, two radian telescopic links 23 and two radian springs 24, the two threaded cylinders 20 are in threaded connection with the first driving screw 5 and the second driving screw 6, the two dragging plates 21 are fixedly connected with the two threaded cylinders 20, the two dragging plates 21 are in sliding connection with the two auxiliary sliding rods 10, the two clamping plates 22 are both rotatably connected with the fixed base 3, and the two clamping plates 22 are attached to the connecting pipe 2.
In this embodiment, two radian telescopic links 23 all with fixing base 3 fixed connection, and the one end and two cardboard 22 of two radian telescopic links 23 are connected, two radian spring 24 covers are located on two radian telescopic links 23.
In this embodiment, be equipped with two magnetic blocks 25 in the interface main part 1, push away one side fixedly connected with extension rod 26 of oiled plate 11, the one end fixedly connected with brush 27 of extension rod 26, the clean dynamics of designing brush 27 as required is greater than magnetic field 25 to metallic impurity's attraction magnetic force, be equipped with deflector 28 in the interface main part 1, be equipped with fluid filter mesh hole on the deflector 28, the both sides of interface main part 1 all are equipped with collecting box 29, the surface design has the slope to correspond collecting box 29 on the deflector 28.
In this embodiment, when oil enters the interface main body 1, the oil pushes the oil pushing plate 11 to move, the oil pushing plate 11 drives the connecting rod 12 to move, the connecting rod 12 drives the moving plate 15 to move, the moving plate 15 drives one end of the two force dividing rods 16 to be away from each other, the two force dividing rods 16 drive the two extruding plates 18 to slide on the fixed round rods 17, and compress the two return springs 19, metal impurities in the oil fall through the guide plate 28, meanwhile, the two magnetic blocks 25 adsorb the metal impurities, the oil pushing plate 11 drives the extension rod 26 to move, the extension rod 26 drives the brush 27 to move, and cleans the metal impurities on the two magnetic blocks 25, the slope surface on the upper surface of the guide plate 28 corresponds to the collection box 29, cleaned metal impurities fall on the guide plate 28 and slide into the two collection boxes 29, the first driving screw 5 is screwed to rotate, the first driving screw 5 drives the first synchronizing wheel 7 to rotate, the first synchronizing wheel 7 drives the second synchronizing wheel 8 to rotate through the synchronous belt 9, the second synchronizing wheel 8 drives the second driving screw 6 to rotate, the first driving screw 5 and the second driving screw 5 drives the two telescopic rods 21 to retract, and the two telescopic rod 21 to retract the two dragging tubes 22 to move, and two telescopic tubes 22 to complete the disassembly of the two dragging tubes 22.
Example two
In this embodiment, one end of the first driving screw 5 is fixedly connected with a turntable, and a handle is arranged on the turntable.
The difference between this embodiment and the first embodiment is: drive the carousel through the handle and rotate, the carousel drives first drive screw 5 and rotates, the drive of being convenient for, all structures in this application all can carry out the selection of material and length according to the in-service use condition, and the drawing is the schematic structure picture, and suitable adjustment can be made to concrete actual dimensions.
Claims (5)
1. The hydraulic pipe connector for the aircraft engine comprises a connector main body (1), a connecting pipe (2) is arranged below the connector main body (1), the same fixing seat (3) is arranged between the connector main body (1) and the connecting pipe (2), the same sealing gasket (4) is arranged between the connector main body (1) and the connecting pipe (2), the hydraulic pipe connector is characterized in that a first driving screw (5) and a second driving screw (6) are connected in the fixing seat (3) in a rotating mode, a first synchronizing wheel (7) and a second synchronizing wheel (8) are fixedly connected to the first driving screw (5) and the second driving screw (6), the same synchronizing belt (9) is connected between the first synchronizing wheel (7) and the second synchronizing wheel (8) in a transmission mode, two auxiliary sliding rods (10) are fixedly installed in the fixing seat (3), a dismounting mechanism is arranged in the fixing seat (3), an oil pushing plate (11) is connected in the connector main body (1) in a sliding mode, a connecting rod (12) is fixedly connected to one side of the oil pushing plate (11), and a rubber plug (13) is arranged on the right side of the connector main body (1);
the disassembling mechanism comprises two threaded cylinders (20), two dragging plates (21), two clamping plates (22), two radian telescopic rods (23) and two radian springs (24), and the two threaded cylinders (20) are in threaded connection with a first driving screw (5) and a second driving screw (6);
the two dragging plates (21) are fixedly connected with the two threaded cylinders (20), the two dragging plates (21) are slidably connected with the two auxiliary sliding rods (10), the two clamping plates (22) are rotatably connected with the fixed seat (3), and the two clamping plates (22) are attached to the connecting pipe (2);
two radian telescopic links (23) all with fixing base (3) fixed connection, and the one end and two cardboard (22) of two radian telescopic links (23) are connected, two radian springs (24) cover are located on two radian telescopic links (23).
2. The hydraulic pipe joint for the aircraft engine according to claim 1, wherein a force-dividing seat (14) is fixedly installed in the joint main body (1), a moving plate (15) is fixedly connected to one end of the connecting rod (12), and two force-dividing rods (16) are movably connected to the right side of the moving plate (15).
3. A hydraulic pipe joint for an aircraft engine according to claim 2, wherein a fixed round rod (17) is fixedly installed in the force component seat (14), and two pressing plates (18) are slidably connected to the fixed round rod (17).
4. A hydraulic pipe joint for an aircraft engine according to claim 3, wherein the two pressure plates (18) are movably connected with one ends of the two force-dividing rods (16), the fixed round rod (17) is sleeved with two return springs (19), and the two return springs (19) are connected with the two pressure plates (18).
5. The hydraulic pipe joint for the aircraft engine according to claim 1, wherein two magnetic blocks (25) are arranged in the joint main body (1), one side of the oil pushing plate (11) is fixedly connected with an extension rod (26), one end of the extension rod (26) is fixedly connected with a brush (27), a guide plate (28) is arranged in the joint main body (1), oil filter meshes are arranged on the guide plate (28), collecting boxes (29) are arranged on both sides of the joint main body (1), and a slope surface corresponding to the collecting boxes (29) is designed on the upper surface of the guide plate (28).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211330902.2A CN115388248B (en) | 2022-10-28 | 2022-10-28 | Hydraulic pipe connector for aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211330902.2A CN115388248B (en) | 2022-10-28 | 2022-10-28 | Hydraulic pipe connector for aircraft engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115388248A CN115388248A (en) | 2022-11-25 |
| CN115388248B true CN115388248B (en) | 2023-01-31 |
Family
ID=84115239
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211330902.2A Active CN115388248B (en) | 2022-10-28 | 2022-10-28 | Hydraulic pipe connector for aircraft engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115388248B (en) |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA2408413A1 (en) * | 2001-10-16 | 2003-04-16 | Duane J. Duncan | Tubular member coupling device |
| CN203245570U (en) * | 2013-05-14 | 2013-10-23 | 上海大众汽车有限公司 | Tool for demounting shaft |
| CN205070290U (en) * | 2015-11-06 | 2016-03-02 | 国家电网公司 | Cable pillar assembly and disassembly tools |
| CN206416106U (en) * | 2016-12-08 | 2017-08-18 | 江西新裕隆汽车零部件有限公司 | A kind of hub bearing provision for disengagement |
| CN208487309U (en) * | 2018-05-09 | 2019-02-12 | 中国商用飞机有限责任公司 | Lapping device for aircraft hydraulic pipeline and fuel tank |
| CN210071175U (en) * | 2019-07-17 | 2020-02-14 | 宜昌宜控科技有限公司 | Temperature sensor capable of resisting interference |
| CN211888450U (en) * | 2020-03-30 | 2020-11-10 | 浙江德瑞不锈钢有限公司 | Dismounting device of nonrust steel pipe drawing head |
| CN213870232U (en) * | 2020-12-22 | 2021-08-03 | 南通油顺液压机械有限公司 | High-stability industrial hydraulic pump |
| CN216666780U (en) * | 2022-01-28 | 2022-06-03 | 禧阅航空技术(上海)有限公司 | Aviation fluid pipeline joint |
| CN114776655A (en) * | 2022-04-02 | 2022-07-22 | 李冉 | Hydraulic pipe connector for aircraft engine |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| NL6604466A (en) * | 1966-04-04 | 1967-10-05 | ||
| CN211289090U (en) * | 2019-12-30 | 2020-08-18 | 简阳市中原低温设备配套有限公司 | Cavity-separated pressure reducing valve convenient to disassemble |
-
2022
- 2022-10-28 CN CN202211330902.2A patent/CN115388248B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA2408413A1 (en) * | 2001-10-16 | 2003-04-16 | Duane J. Duncan | Tubular member coupling device |
| CN203245570U (en) * | 2013-05-14 | 2013-10-23 | 上海大众汽车有限公司 | Tool for demounting shaft |
| CN205070290U (en) * | 2015-11-06 | 2016-03-02 | 国家电网公司 | Cable pillar assembly and disassembly tools |
| CN206416106U (en) * | 2016-12-08 | 2017-08-18 | 江西新裕隆汽车零部件有限公司 | A kind of hub bearing provision for disengagement |
| CN208487309U (en) * | 2018-05-09 | 2019-02-12 | 中国商用飞机有限责任公司 | Lapping device for aircraft hydraulic pipeline and fuel tank |
| CN210071175U (en) * | 2019-07-17 | 2020-02-14 | 宜昌宜控科技有限公司 | Temperature sensor capable of resisting interference |
| CN211888450U (en) * | 2020-03-30 | 2020-11-10 | 浙江德瑞不锈钢有限公司 | Dismounting device of nonrust steel pipe drawing head |
| CN213870232U (en) * | 2020-12-22 | 2021-08-03 | 南通油顺液压机械有限公司 | High-stability industrial hydraulic pump |
| CN216666780U (en) * | 2022-01-28 | 2022-06-03 | 禧阅航空技术(上海)有限公司 | Aviation fluid pipeline joint |
| CN114776655A (en) * | 2022-04-02 | 2022-07-22 | 李冉 | Hydraulic pipe connector for aircraft engine |
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| Publication number | Publication date |
|---|---|
| CN115388248A (en) | 2022-11-25 |
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Denomination of invention: A hydraulic pipe interface for aircraft engines Effective date of registration: 20230621 Granted publication date: 20230131 Pledgee: Shandong Longkou Rural Commercial Bank Co.,Ltd. Fushan sub branch Pledgor: YANTAI ZHONGYU AEROHYDRAULIC Co.,Ltd. Registration number: Y2023980045396 |