CN114198378B - Rapid assembling and disassembling type mounting structure for aero-engine lubricating oil tank - Google Patents
Rapid assembling and disassembling type mounting structure for aero-engine lubricating oil tank Download PDFInfo
- Publication number
- CN114198378B CN114198378B CN202111457071.0A CN202111457071A CN114198378B CN 114198378 B CN114198378 B CN 114198378B CN 202111457071 A CN202111457071 A CN 202111457071A CN 114198378 B CN114198378 B CN 114198378B
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- China
- Prior art keywords
- oil tank
- lubricating oil
- wedge
- mounting structure
- shaped
- 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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- 239000010687 lubricating oil Substances 0.000 title claims abstract description 46
- 239000006096 absorbing agent Substances 0.000 claims abstract description 17
- 230000035939 shock Effects 0.000 claims abstract description 16
- 239000002184 metal Substances 0.000 claims description 8
- 239000003921 oil Substances 0.000 claims description 5
- 239000002828 fuel tank Substances 0.000 claims 2
- 238000000034 method Methods 0.000 abstract description 14
- 238000011900 installation process Methods 0.000 abstract description 6
- 238000009434 installation Methods 0.000 abstract description 4
- 238000013016 damping Methods 0.000 abstract 1
- 238000012423 maintenance Methods 0.000 description 3
- 238000004873 anchoring Methods 0.000 description 2
- 230000003287 optical effect Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000005284 excitation Effects 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 239000000725 suspension Substances 0.000 description 1
Images
Classifications
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- 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
- F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
- F16B21/00—Means for preventing relative axial movement of a pin, spigot, shaft or the like and a member surrounding it; Stud-and-socket releasable fastenings
- F16B21/02—Releasable fastening devices locking by rotation
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/06—Arrangements of bearings; Lubricating
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- 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
- F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
- F16B5/00—Joining sheets or plates, e.g. panels, to one another or to strips or bars parallel to them
- F16B5/02—Joining sheets or plates, e.g. panels, to one another or to strips or bars parallel to them by means of fastening members using screw-thread
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- 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
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/02—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems
- F16F15/04—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means
- F16F15/08—Suppression of vibrations of non-rotating, e.g. reciprocating systems; Suppression of vibrations of rotating systems by use of members not moving with the rotating systems using elastic means with rubber springs ; with springs made of rubber and metal
Abstract
The invention discloses a quick assembling and disassembling type mounting structure for an aircraft engine lubricating oil tank, and belongs to the technical field of assembly of parts of an aircraft engine external system. The quick assembling and disassembling type mounting structure comprises a supporting plate of a lubricating oil tank, a locking cavity cover, a wedge-shaped locking block, a connecting shaft, a shock absorber, a mounting support and a connecting part buckle cover. The invention adopts a split structure, the centering and fastening of parts are easy to realize in the actual installation process, and the installation process is simple and easy to realize; in the actual disassembly process, the parts are separated conveniently, so that the parts can be taken down smoothly. The invention realizes the fastening of the installation structure part and the lubricating oil tank by utilizing the matching between the locking cavity and the wedge-shaped locking block, and the hollow structure of the locking cavity reduces the mass of the whole device; meanwhile, the adopted vibration damper plays a role in damping a vibration system consisting of the lubricating oil tank, the mounting structure and the engine case, and particularly can avoid damaging each part of the mounting structure.
Description
Technical Field
The invention belongs to the technical field of assembly of parts of an external system of an aero-engine, and relates to a quick assembling and disassembling type mounting structure for an aero-engine lubricating oil tank.
Background
The aero-engine external system is one of engine subsystems and comprises a plurality of parts such as external accessories, engine pipelines, supporting and fixing parts and the like. The external system itself includes numerous components, making the external system extremely complex and requiring frequent assembly and disassembly of the components of the external system during actual use and maintenance of the engine.
The lubricating oil tank is an important component of an external system of the engine, and is fixed outside the engine box through a multipoint anchoring type mounting structure. For the mounting structure of the anchoring part, on one hand, the lubricating oil tank is large in size and inconvenient to move and fix in the actual assembly process, and the existing mounting structure is mostly semi-closed, so that the assembly and disassembly process of the lubricating oil tank is difficult, and the working cost is increased for daily maintenance; on the other hand, the mass of the lubricating oil tank is large after the lubricating oil tank is filled with lubricating oil, vibration and damage are easily caused in the flight process of an airplane due to the characteristics of basic excitation and liquid-solid coupling, the installation structure forms of all anchor points in the system are different, the assembly requirement is high, the system is easily influenced by part machining errors and assembly deviation, and the vibration of the lubricating oil tank and the installation structure of the lubricating oil tank is further uncontrollable.
Therefore, it is highly desirable to optimize the mounting structure of the oil tank component, so that the mounting and dismounting processes of the oil tank can be easily realized, and at the same time, a safe support can be provided for the oil tank.
Disclosure of Invention
The invention designs a quick assembling and disassembling type mounting structure of an aircraft engine lubricating oil tank, which is convenient for daily maintenance of lubricating oil tank components and ensures reliable mounting and fixing of the lubricating oil tank on an engine casing. The invention mainly solves the problem of complex assembling and disassembling process of the actual lubricating oil tank, has the characteristics of light weight and small volume, is slightly influenced by the manufacturing error and the assembling deviation of parts in the actual assembling process, and can reduce the requirement on assembling.
The technical scheme of the invention is as follows:
a quick assembling and disassembling type mounting structure for an aircraft engine lubricating oil tank comprises a lubricating oil tank supporting plate 1, a locking cavity cover 2, a wedge-shaped locking block 3, a connecting shaft 4, a shock absorber 5, a mounting support 6 and a connecting part buckling cover 7.
The lubricating oil tank supporting disk 1 is welded and fixed at the mounting points at the left side and the right side of the lubricating oil tank body, and cannot be detached from the tank body when in use; the surface of the supporting disk 1 of the lubricating oil tank is provided with a cylindrical boss structure, and a pair of inclined planes which are centrosymmetric about the circle center are arranged on the boss. The locking cavity cover 2 is a columnar cavity, and the surface of the locking cavity cover is provided with a fan-shaped special-shaped hole; the locking cavity cover 2 is connected with the supporting disk 1 of the lubricating oil tank to form a locking cavity. The wedge-shaped locking blocks 3 are a pair of wedge-shaped structures which are centrosymmetric about the rotating shaft, and are inserted into a locking cavity formed by the lubricating oil tank supporting disk 1 and the locking cavity cover 2 through fan-shaped special-shaped holes in the locking cavity cover 2 to realize the fastening of parts.
The connecting shaft 4 is sequentially divided into a thread section, an optical axis section, a tail end disc and a hexagonal prism boss in the axial direction. The wedge-shaped locking block 3 and the connecting shaft 4 are matched and fixed through a hole shaft in the axial direction. The connecting shaft 4 sequentially penetrates through the shock absorber 5, a hanging ring at the top end of the mounting support 6, the other shock absorber 5 and the wedge-shaped locking block 3 to be connected through threads. The damper 5 is made of metal and rubber, the outer circle and the inner hole are both made of metal, and rubber is clamped between the outer circle and the inner hole.
The connecting part buckling cover 7 is of a semi-cavity structure, and a through hole is formed in the center of the top end of the connecting part buckling cover to enable a hexagonal prism boss of the connecting shaft 4 to penetrate through the through hole; 6 waist-shaped holes are uniformly distributed on the periphery of the through hole along the circumferential direction and are connected with 6 threaded holes in a disc at the tail end of the connecting shaft 4 through screws; 3 round holes are formed in the bottom of the joint buckling cover 7 and are connected with 3 threaded holes in the supporting plate 1 of the lubricating oil tank through screws.
The invention has the beneficial effects that:
1) compared with the traditional structure, the invention adopts a split structure and is assembled by a plurality of parts. In the actual installation process, the parts are easy to center, reliable fastening can be realized, and the installation process is simple, convenient and easy to realize; in the actual disassembly process, the separation of each part is convenient to realize, and the parts can be smoothly taken down. In conclusion, the invention can realize the rapid loading and unloading function.
2) Compared with the traditional structure, the invention realizes the fastening of the mounting structure part and the lubricating oil tank by utilizing the matching between the locking cavity and the wedge-shaped locking block, and the hollow structure of the locking cavity greatly lightens the quality of the whole device.
3) The vibration absorber adopted by the invention can play a role in absorbing vibration of a vibration system consisting of the lubricating oil tank, the mounting structure and the engine case in actual use, and particularly can avoid damaging each part of the mounting structure.
Drawings
FIG. 1 is a three-dimensional view of the present invention.
Fig. 2 is a view showing an installation process of the shock absorber of the present invention.
Fig. 3 is a schematic structural view of a lock chamber cover of the present invention, wherein (a) is a front view, (b) is a side view, and (c) is a top view.
Fig. 4 is a schematic structural view of the wedge-shaped locking block of the present invention, wherein (a) is a front view, (b) is a side view, and (c) is a top view.
Fig. 5 is a schematic structural view of the joint buckle cover of the present invention, wherein (a) is a front view, (b) is a side view, and (c) is a top view.
Fig. 6 is an assembly process diagram of the mounting structure of the present invention.
In the figure: 1, a lubricating oil tank supporting plate; 2 locking a cavity cover; 3, a wedge-shaped locking block; 4 connecting the shaft; 5, a vibration damper; 6, mounting a support; 7 the joint is buckled with a cover.
Detailed Description
The working principle of the quick mount/dismount mounting structure is further explained below through the process of mounting and dismounting the mounting structure component at a single connection point.
As shown in figure 1, the quick assembling and disassembling type mounting structure for the lubricating oil tank of the aircraft engine comprises a lubricating oil tank supporting plate 1, a locking cavity cover 2, a wedge-shaped locking block 3, a connecting shaft 4, a shock absorber 5, a mounting support 6 and a connecting part buckling cover 7.
The supporting plate 1 of the lubricating oil tank is welded and fixed at the mounting points at the left side and the right side of the box body of the lubricating oil tank, and can not be detached from the box body when in use; the surface of the supporting disk 1 of the lubricating oil tank is provided with a cylindrical boss structure, and a pair of inclined planes which are centrosymmetric about the circle center are arranged on the boss. The locking cavity cover 2 is a columnar cavity, and the surface of the locking cavity cover is provided with a fan-shaped special-shaped hole; the locking cavity cover 2 is connected with the supporting disk 1 of the lubricating oil tank to form a locking cavity. The wedge-shaped locking blocks 3 are a pair of wedge-shaped structures which are centrosymmetric about the rotating shaft, and are inserted into the locking cavity through the fan-shaped special-shaped holes on the locking cavity cover 2 to realize the fastening of parts.
The connecting shaft 4 is sequentially divided into a thread section, an optical axis section, a tail end disc and a hexagonal prism boss in the axial direction. The wedge-shaped locking block 3 is matched and fixed with the connecting shaft 4 in the axial direction through a hole shaft. The connecting shaft 4 sequentially penetrates through the shock absorber 5, a hanging ring at the top end of the mounting support 6, the other shock absorber 5 and the wedge-shaped locking block 3 to be connected through threads. The damper 5 is made of metal and rubber, the outer circle and the inner hole are both made of metal, and rubber is clamped between the outer circle and the inner hole.
The connecting part buckling cover 7 is of a semi-cavity structure, and a through hole is formed in the center of the top end of the connecting part buckling cover to enable a hexagonal prism boss of the connecting shaft 4 to penetrate through the through hole; 6 waist-shaped holes are uniformly distributed on the periphery of the through hole along the circumferential direction and are connected with 6 threaded holes in a disc at the tail end of the connecting shaft 4 through screws; 3 round holes are formed in the bottom of the joint buckling cover 7 and are connected with 3 threaded holes in the supporting plate 1 of the lubricating oil tank through screws.
During the course of the installation process,
the method comprises the following steps: the mount bracket 6 should be first mounted to the engine case at a correct position according to a predetermined mounting position so that the mount bracket 6 is in a fixed state.
Step two: the connecting shaft 4 penetrates through a shock absorber 5, the shock absorber 5 is an outer side shock absorber, the bottom surface of the outer side shock absorber is attached to the circular surface of a disc at the tail end of the connecting shaft 4, then the connecting shaft 4 penetrates through a hanging ring of the mounting support 6, and at the moment, the outer circular surface of the outer side shock absorber is attached to the inner wall of the hanging ring hole of the mounting support 6; then, another damper 5 is passed through the connecting shaft 4 from the opposite direction and is brought into contact with the mounting bracket 6 by means of a suspension ring.
Step three: at the tail end of the connecting shaft 4, the wedge-shaped locking block 3 is screwed in clockwise, so that the wedge-shaped locking block 3 is in a connecting state relative to the connecting shaft 4, but the wedge-shaped locking block 3 does not need to be completely screwed and fixed relative to the connecting shaft 4.
Step four: the direction of the wedge-shaped locking block 3 is adjusted by rotating the connecting shaft 4, so that the center line of the wedge-shaped locking block 3 is approximately in a vertical downward position, then the fan-shaped special-shaped hole of the locking cavity is aligned with the wedge-shaped locking block 3, the sliding oil tank is moved along the axis direction, so that the wedge-shaped locking block 3 can be smoothly inserted into the locking cavity, and the fan-shaped special-shaped hole is consistent with the shape of the wedge-shaped locking block 3 in shape but larger in size, so that the wedge-shaped locking block can be smoothly inserted under the condition of position deviation.
Step five: clockwise rotation connecting axle 4, connecting axle 4 drives wedge latch segment 3 and rotates together, and when rotation angle reached 90, wedge latch segment 3 will realize the fastening with the locking chamber, and at the same time in the in-process of screwing, because connecting axle 4 is the dextrorotation with wedge latch segment 3's screw thread, the screw thread here will also be screwed completely.
Step six: the screw at the joint buckle cover 7 and the supporting disk 1 of the lubricating oil tank is firstly screwed to enable the joint buckle cover to occupy the correct installation position, and then the screw at the joint buckle cover 7 and the disk at the tail end of the connecting shaft 4 is screwed.
In the course of the disassembly process,
the method comprises the following steps: firstly, screws at the positions of the joint buckle cover 7 and the connecting shaft 4 and the positions of the joint buckle cover 7 and the supporting plate 1 of the lubricating oil tank are screwed off, and the joint buckle cover 7 is detached.
Step two: by rotating the connecting shaft 4 in the counter-clockwise direction, two situations may occur: one is that the wedge-shaped locking block 3 is firstly screwed out from the locking cavity, and the other is that the connecting shaft 4 is firstly screwed out from the wedge-shaped locking block 3. To the condition of precedingly unscrewing of wedge latch segment 3, when clockwise rotation angle reached 90, owing to continue rotatory, wedge latch segment 3 can not be through the space of locking chamber axis opposite side, consequently wedge latch segment 3 can block in 90 positions, continues rotatory connecting axle 4 this moment, alright unscrew connecting axle 4 from wedge latch segment 3's screw hole, then can take off all the other parts in proper order after extracting connecting axle 4. When connecting axle 4 was twisted out from wedge-shaped latch segment 3 earlier, the two lost connection this moment, and other parts can be taken off after extracting connecting axle 4, but the wedge can be blocked in the locking intracavity, and through 3 cylinder tops ear-shaped archs of wedge-shaped latch segment, can continue to rotate wedge-shaped latch segment 3, make it deviate from the locking chamber.
Claims (5)
1. A quick assembling and disassembling type mounting structure for an aircraft engine lubricating oil tank is characterized by comprising a lubricating oil tank supporting plate (1), a locking cavity cover (2), a wedge-shaped locking block (3), a connecting shaft (4), a shock absorber (5), a mounting support (6) and a connecting part buckle cover (7);
the lubricating oil tank supporting plate (1) is connected with the lubricating oil tank body; the locking cavity cover (2) is a columnar cavity and is connected with the sliding oil tank supporting disk (1) to form a locking cavity; the wedge-shaped locking block (3) is embedded into the locking cavity through a fan-blade-shaped special-shaped hole in the locking cavity cover (2) to realize the fastening of parts;
the connecting shaft (4) sequentially penetrates through the shock absorber (5), a hanging ring at the top end of the mounting support (6) and the other shock absorber (5) to be connected with the wedge-shaped locking block (3);
the top and the bottom of the joint buckle cover (7) are respectively connected with the connecting shaft (4) and the lubricating oil tank supporting disc (1).
2. A quick-release mounting arrangement for aircraft engine fuel tanks, according to claim 1, characterised in that the wedge-shaped locking blocks (3) are a pair of wedge-shaped structures which are centred with respect to the axis of rotation.
3. The quick assembling and disassembling type mounting structure for the aircraft engine lubricating oil tank according to claim 1 or 2, characterized in that the joint buckle cover (7) is of a half-cavity structure, and a through hole is formed in the center of the top end of the joint buckle cover so that a hexagonal prism boss on the top of the connecting shaft (4) can penetrate through the through hole.
4. A quick-release mounting structure for an aircraft engine fuel tank according to claim 1 or 2, wherein the damper (5) is made of metal and rubber, and the outer circle and the inner hole are both metal and rubber is sandwiched therebetween.
5. A quick-release mounting structure for an aircraft engine lubricating oil tank according to claim 3, characterized in that the damper (5) is made of metal and rubber, the outer circle and the inner hole are both made of metal, and rubber is sandwiched between the outer circle and the inner hole.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111457071.0A CN114198378B (en) | 2021-12-02 | 2021-12-02 | Rapid assembling and disassembling type mounting structure for aero-engine lubricating oil tank |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111457071.0A CN114198378B (en) | 2021-12-02 | 2021-12-02 | Rapid assembling and disassembling type mounting structure for aero-engine lubricating oil tank |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114198378A CN114198378A (en) | 2022-03-18 |
| CN114198378B true CN114198378B (en) | 2022-09-23 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202111457071.0A Active CN114198378B (en) | 2021-12-02 | 2021-12-02 | Rapid assembling and disassembling type mounting structure for aero-engine lubricating oil tank |
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102015351A (en) * | 2008-05-06 | 2011-04-13 | 雷诺股份公司 | Device for securing a fuel filler flap assembly |
| DE102017011872A1 (en) * | 2017-12-21 | 2018-05-30 | Daimler Ag | Flap assembly for a trough of a body of a motor vehicle |
Family Cites Families (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5273330A (en) * | 1992-11-23 | 1993-12-28 | General Motors Corporation | Twist-lock mounting assembly and method for a bumper energy absorber |
| FR2966208B1 (en) * | 2010-10-13 | 2012-12-28 | Snecma | CONNECTING HOUSING BETWEEN A MOTOR BLOWER DRIVE SHAFT AND A BEARING BEARING |
| FR2973588B1 (en) * | 2011-03-31 | 2013-03-29 | Renault Sa | ELECTRIC LOADING TRAPPER DEVICE FOR ELECTRIC VEHICLE COMPATIBLE WITH PITCH SHOCK |
| KR101284372B1 (en) * | 2012-02-06 | 2013-07-09 | 주식회사 니프코코리아 | A bolt clip |
| CN205207366U (en) * | 2015-12-18 | 2016-05-04 | 吕勇刚 | Locking screens mechanism is dismantled fast to quick cramping head |
| CN207297531U (en) * | 2017-10-23 | 2018-05-01 | 深圳市洲明科技股份有限公司 | Locking device |
| CN208734692U (en) * | 2018-08-27 | 2019-04-12 | 深圳市合一新材料研发有限公司 | A kind of Quick fastening solid lock for LED display |
| CN211032169U (en) * | 2019-08-05 | 2020-07-17 | 湖北航宇精工科技有限公司 | Mistake proofing type fuel tank cap |
| CN113251038A (en) * | 2020-02-12 | 2021-08-13 | 蓝硕文化科技(上海)有限公司 | Module pressing lock structure |
-
2021
- 2021-12-02 CN CN202111457071.0A patent/CN114198378B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102015351A (en) * | 2008-05-06 | 2011-04-13 | 雷诺股份公司 | Device for securing a fuel filler flap assembly |
| DE102017011872A1 (en) * | 2017-12-21 | 2018-05-30 | Daimler Ag | Flap assembly for a trough of a body of a motor vehicle |
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| Publication number | Publication date |
|---|---|
| CN114198378A (en) | 2022-03-18 |
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