CN214085605U - A sealed packing box for aeroengine - Google Patents
A sealed packing box for aeroengine Download PDFInfo
- Publication number
- CN214085605U CN214085605U CN202023104422.3U CN202023104422U CN214085605U CN 214085605 U CN214085605 U CN 214085605U CN 202023104422 U CN202023104422 U CN 202023104422U CN 214085605 U CN214085605 U CN 214085605U
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- CN
- China
- Prior art keywords
- upper cover
- base
- guide post
- connecting end
- support
- 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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- 238000012856 packing Methods 0.000 title claims description 22
- 238000007789 sealing Methods 0.000 claims abstract description 20
- 239000011152 fibreglass Substances 0.000 claims abstract description 17
- 239000002184 metal Substances 0.000 claims abstract description 16
- 229920001971 elastomer Polymers 0.000 claims abstract description 10
- 238000004806 packaging method and process Methods 0.000 claims abstract description 8
- 230000000740 bleeding effect Effects 0.000 claims description 9
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 7
- 229910002804 graphite Inorganic materials 0.000 claims description 7
- 239000010439 graphite Substances 0.000 claims description 7
- 230000003014 reinforcing effect Effects 0.000 claims description 3
- 229920001973 fluoroelastomer Polymers 0.000 claims description 2
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 abstract description 5
- 229910001873 dinitrogen Inorganic materials 0.000 abstract description 3
- 230000007797 corrosion Effects 0.000 abstract description 2
- 238000005260 corrosion Methods 0.000 abstract description 2
- 230000003647 oxidation Effects 0.000 abstract description 2
- 238000007254 oxidation reaction Methods 0.000 abstract description 2
- 239000007789 gas Substances 0.000 description 9
- 238000000034 method Methods 0.000 description 3
- 238000013461 design Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 229920006337 unsaturated polyester resin Polymers 0.000 description 2
- YCKRFDGAMUMZLT-UHFFFAOYSA-N Fluorine atom Chemical compound [F] YCKRFDGAMUMZLT-UHFFFAOYSA-N 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000005536 corrosion prevention Methods 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 229910052731 fluorine Inorganic materials 0.000 description 1
- 239000011737 fluorine Substances 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- JEIPFZHSYJVQDO-UHFFFAOYSA-N iron(III) oxide Inorganic materials O=[Fe]O[Fe]=O JEIPFZHSYJVQDO-UHFFFAOYSA-N 0.000 description 1
- 238000005461 lubrication Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000000178 monomer Substances 0.000 description 1
- 229910052757 nitrogen Inorganic materials 0.000 description 1
- 230000002265 prevention Effects 0.000 description 1
- 150000003839 salts Chemical class 0.000 description 1
- 239000002023 wood Substances 0.000 description 1
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- Gasket Seals (AREA)
Abstract
The utility model relates to the technical field of packaging box sealing, and provides a sealing packaging box for an aircraft engine, which comprises an upper cover, a base and at least one circle of sealing rubber strip; an upper cover is arranged on the base in a matching way; sealing rubber strips are arranged on the contact surface of the base and the upper cover in the circumferential direction; the upper cover and the base both adopt metal shells; an outer layer of glass fiber reinforced plastic is arranged on the outer side of the metal shell; and the inner side of the metal shell is provided with a glass fiber reinforced plastic inner layer. The utility model discloses can fill into nitrogen gas and make the box inside completely isolated with external environment, avoid moist air to get into the incasement and produce the oxidation corrosion problem to the engine.
Description
Technical Field
The utility model relates to a packing box sealing technique field especially relates to a sealed packing box for aeroengine.
Background
The aircraft engine is a precise aircraft component, and the packaging link of the aircraft engine is important for the storage success and failure of the aircraft engine. The stability, the internal environment temperature, the humidity and the like of the engine need to be ensured in the transportation process. At present, the problems that metal or wood materials are used for an aviation engine packing box mostly, rust prevention and corrosion prevention of engine parts in a complex environment cannot be achieved, and the like are solved.
SUMMERY OF THE UTILITY MODEL
The utility model discloses mainly solve prior art's unable assurance engine part corruption, artifical technical problem such as drop into greatly, provide a sealed packing box for aeroengine, fill into nitrogen gas and make the box inside completely isolated with external environment, avoid moist air to get into the incasement and produce the oxidation corrosion problem to the engine.
The utility model provides a sealed packing box for an aeroengine, which comprises an upper cover 1, a base 2 and at least one circle of sealing rubber strip 5;
the base 2 is provided with an upper cover 1 in a matching way;
a sealing rubber strip 5 is arranged on the circumferential direction of the contact surface of the base 2 and the upper cover 1;
the upper cover 1 and the base 2 both adopt a metal shell 102; the outer side of the metal shell 102 is provided with a glass fiber reinforced plastic outer layer 101; an inner layer 103 of glass fiber reinforced plastic is arranged on the inner side of the metal shell 102.
Preferably, a sealing flange is arranged on one side of the upper cover 1;
the sealing flange includes: the flange comprises a flange body 8, an aviation adapter plug 12, a gas release plug 10, a gas release nozzle 13 and a self-locking quick gas charging connector 11;
the flange body 8 is used for being connected with the shell of the packing box; the flange body 8 is provided with a first through hole 801, a second through hole 802 and a first threaded hole 803;
the aviation adapter plug 12 is fixedly arranged on the first through hole 801;
the air bleeding nozzle 13 is welded on the flange body 8 through a second through hole 802;
the air release plug 10 is in threaded connection with an air release nozzle 13;
the self-locking quick inflation connector 11 is mounted on the first threaded hole 803.
Preferably, the flange body 8 is further provided with a second threaded hole 804; and a shock-proof pressure gauge 9 is arranged in the second threaded hole 804.
Preferably, the joints of the air bleeding nozzle 13 and the air bleeding plug 10 are both provided with fluororubber O-rings.
Preferably, the contacts of the aircraft patch plug 12 are replaceable.
Preferably, the upper cover 1 is provided with an upper support 3, and the base 2 is provided with a lower support 4; the upper support 3 comprises a connecting end; the lower end of the connecting end is open and the interior of the connecting end is hollow;
a guide post 6 is arranged on the lower support 4, and the guide post 6 corresponds to the lower end opening of the connecting end; when in alignment, the support is matched with the upper support 3 for use; when the upper holder 3 and the lower holder 4 are aligned, the guide post 6 is inserted into the lower end opening of the connection end.
Preferably, the connecting end is provided with a step surface, and the graphite self-lubricating sleeve 7 is fixedly arranged at the opening at the lower end of the connecting end.
Preferably, the front surface of the guide post 6 is provided with a scale, and the top end of the guide post 6 is conical;
the outer diameter of the guide post 6 is smaller than the inner diameter of the graphite self-lubricating sleeve 7.
Preferably, the upper end of the lower support 4 is provided with a groove; the lower end of the guide post 6 is provided with a bulge; said protrusions are intended to cooperate with the recesses of the lower holder 4.
Preferably, the upper support 3, the connecting end and the lower support 4 are respectively provided with a reinforcing rib.
The utility model provides a sealed packing box for aeroengine compares with prior art and has following advantage:
1. a sealed flange is set up on one side of the upper cover of a sealed packing box for aeroengine, can be for airtight space and can fill nitrogen gas pressurization, and set up and fill, gassing interface, manometer and aviation adapter plug integration integrated design, highly integrated, only need consider flange monomer mounted position during the main part design, convenient to use.
2. The shock-proof pressure gauge is arranged, and the environment in the sealed container can be monitored by matching with electronic equipment such as an electronic sensor. The air pressure in the box body is larger than the pressure outside the box body, so that external damp air can be prevented from entering the box body.
3. Set up upper portion support and lower part support on this packing box, use the guide effect and the upper portion support cooperation of guide pillar, realize automatic alignment, solved artifical alignment repeatedly, operating time is of a specified duration, the inaccurate problem in position.
Drawings
FIG. 1 is a schematic view of a sealed package for an aircraft engine according to the present invention;
FIG. 2 is a right side view of the sealed package cover for an aircraft engine provided by the present invention;
FIG. 3 is a schematic view of the uncapping condition of the sealed packing box for an aircraft engine provided by the present invention;
FIG. 4 is a schematic view of the upper cover assembly of the sealed package box for an aircraft engine provided by the present invention;
FIG. 5 is a schematic view of a sealing flange of a sealed package for an aircraft engine provided by the present invention;
fig. 6 is a schematic structural view of a flange body of the sealed packing box for an aircraft engine provided by the present invention;
FIG. 7 is a top plan view of a sealing flange for a sealed package for an aircraft engine;
FIG. 8 is a schematic view (front) of the upper and lower seats of a sealed package for an aircraft engine;
FIG. 9 is a schematic view (side) of the upper and lower support of the sealed package for an aircraft engine;
reference numerals: 1. an upper cover; 101. an outer layer of glass fiber reinforced plastic; 102. a metal housing; 103. a glass fiber reinforced plastic inner layer; 2. a base; 3. an upper support; 4. a lower support; 5. sealing rubber strips; 6. a guide post; 7. a graphite self-lubricating sleeve; 8. a flange body; 801. a first through hole; 802. a second through hole; 803. a first threaded hole; 804. a second threaded hole; 9. a shock-proof pressure gauge; 10. a gas release plug; 11. A self-locking quick inflation joint; 12. an aviation adapter plug; 13. and (4) discharging a gas nozzle.
Detailed Description
In order to make the technical problem solved by the present invention, the technical solution adopted by the present invention and the technical effect achieved by the present invention clearer, the present invention will be further described in detail with reference to the accompanying drawings and the embodiments. It is to be understood that the specific embodiments described herein are merely illustrative of the invention and are not limiting of the invention. It should be further noted that, for the convenience of description, only some but not all of the relevant portions of the present invention are shown in the drawings.
As shown in fig. 1 to 9, an embodiment of the present invention provides a sealed packing box for an aircraft engine, which includes an upper cover 1, a base 2, and at least one circle of sealing rubber strip 5; the base 2 is provided with an upper cover 1 in a matching way; a sealing rubber strip 5 is arranged on the circumferential direction of the contact surface of the base 2 and the upper cover 1;
the upper cover 1 and the base 2 both adopt a metal shell 102; the outer side of the metal shell 102 is provided with a glass fiber reinforced plastic outer layer 101; an inner layer 103 of glass fiber reinforced plastic is arranged on the inner side of the metal shell 102. The metal shell 102 is coated inside and outside by the glass fiber reinforced plastic inner layer 103 and the glass fiber reinforced plastic outer layer 101, unsaturated polyester resin is introduced into the fully-soaked glass fiber reinforced plastic by utilizing a vacuum negative pressure introduction process, and the glass fiber reinforced plastic outer layer, the metal shell and the glass fiber reinforced plastic inner layer form a whole after the unsaturated polyester resin is fully cured. The surface glass fiber reinforced plastic layer has good salt fog resistance, and the inside of the surface glass fiber reinforced plastic layer is made of metal materials, so that the requirement on the structural strength of air pressure during nitrogen charging can be met.
One side of the upper cover 1 of the utility model is provided with a sealing flange; the sealing flange includes: the flange comprises a flange body 8, an aviation adapter plug 12, a gas release plug 10, a gas release nozzle 13 and a self-locking quick gas charging connector 11;
the flange body 8 is used for being connected with the shell of the packing box; the flange body 8 is provided with a first through hole 801, a second through hole 802 and a first threaded hole 803; the aviation adapter plug 12 is fixedly arranged on the first through hole 801; the air bleeding nozzle 13 is welded on the flange body 8 through a second through hole 802; the air release plug 10 is in threaded connection with an air release nozzle 13; used for deflating the gas in the packing box; and fluorine rubber O-shaped rings are arranged at the joints of the air bleeding nozzle 13 and the air bleeding plug 10.
The self-locking quick inflation connector 11 is mounted on the first threaded hole 803.
The flange body 8 is also provided with a second threaded hole 804; the shock-proof pressure gauge 9 is arranged in the second threaded hole 804, so that information communication transmission of the internal and external electronic sensors can be realized, and information acquisition of electronic products is realized, if: internal pressure, humidity, temperature, etc.
The contacts of the aircraft patch plug 12 are replaceable. The electronic equipment is changed according to the specific requirement of the electronic equipment, is suitable for different electronic equipment, and is convenient to install and replace.
The utility model provides a sealed packing box for an aircraft engine, an upper cover 1 is provided with an upper support 3, and a lower support 4 is arranged on a base 2; the upper support 3 comprises a connecting end; the lower end of the connecting end is open and the interior of the connecting end is hollow; a guide post 6 is arranged on the lower support 4, and the guide post 6 corresponds to the lower end opening of the connecting end; when in alignment, the support is matched with the upper support 3 for use; when the upper holder 3 and the lower holder 4 are aligned, the guide post 6 is inserted into the lower end opening of the connection end.
The shape of the connecting end can be designed according to the shapes of the outer surfaces of the upper covers of different packing cases. The link sets up the step face, and the fixed graphite self-lubrication cover 7 that sets up of link lower extreme opening part.
The front surface of the guide post 6 is provided with a scale, and the top end of the guide post 6 is conical; the multi-position setting can detect whether the horizontal positions of the box cover are consistent or not, and the problem that the box closing positions are different every time is solved.
The outer diameter of the guide post 6 is smaller than the inner diameter of the graphite self-lubricating sleeve 7.
The upper end of the lower support 4 is provided with a groove; the lower end of the guide post 6 is provided with a bulge; said protrusions are intended to cooperate with the recesses of the lower holder 4.
And the upper support 3, the connecting end and the lower support 4 are respectively provided with a reinforcing rib so as to increase the strength of a joint surface and increase the stability.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; although the present invention has been described in detail with reference to the foregoing embodiments, it should be understood by those skilled in the art that: it is to be understood that modifications may be made to the technical solutions described in the foregoing embodiments, or some or all of the technical features may be equivalently replaced, without substantially departing from the scope of the technical solutions of the embodiments of the present invention.
Claims (9)
1. A sealed packing box for an aircraft engine is characterized by comprising an upper cover (1), a base (2) and at least one circle of sealing rubber strip (5);
an upper cover (1) is arranged on the base (2) in a matching way; a sealing flange is arranged on one side of the upper cover (1);
the sealing flange includes: the flange comprises a flange body (8), an aviation adapter plug (12), a gas release plug (10), a gas release nozzle (13) and a self-locking quick gas-filled connector (11);
the flange body (8) is used for being connected with the shell of the packing box; the flange body (8) is provided with a first through hole (801), a second through hole (802) and a first threaded hole (803);
the aviation adapter plug (12) is fixedly arranged on the first through hole (801);
the air bleeding nozzle (13) is welded on the flange body (8) through a second through hole (802);
the air release plug (10) is in threaded connection with the air release nozzle (13);
the self-locking quick inflation connector (11) is arranged on the first threaded hole (803);
sealing rubber strips (5) are arranged on the contact surfaces of the base (2) and the upper cover (1) in the circumferential direction;
the upper cover (1) and the base (2) both adopt metal shells (102); the outer side of the metal shell (102) is provided with a glass fiber reinforced plastic outer layer (101); and a glass fiber reinforced plastic inner layer (103) is arranged on the inner side of the metal shell (102).
2. The hermetic packaging box for aeroengines according to claim 1, characterized in that said flange body (8) is also provided with a second threaded hole (804); and a shock-proof pressure gauge (9) is arranged in the second threaded hole (804).
3. The sealed packaging box for aeroengines according to claim 1, characterized in that the joints of the air bleeding nozzle (13) and the air bleeding plug (10) are provided with fluororubber O-rings.
4. A sealed packaging for an aircraft engine according to claim 1, characterised in that the contacts of the aircraft adaptor plug (12) are replaceable.
5. A sealed packaging box for aeroengines, according to claim 1, characterized in that said upper cover (1) is provided with an upper seat (3) and said base (2) is provided with a lower seat (4); the upper support (3) comprises a connecting end; the lower end of the connecting end is open and the interior of the connecting end is hollow;
a guide post (6) is arranged on the lower support (4), and the guide post (6) corresponds to the lower end opening of the connecting end; when in alignment, the support is matched with the upper support (3); when the upper support (3) and the lower support (4) are aligned, the guide post (6) is inserted into the lower end opening of the connecting end.
6. The sealed packing box for aeroengines according to claim 5, characterized in that the connecting end is provided with a step surface, and a graphite self-lubricating sleeve (7) is fixedly arranged at the opening at the lower end of the connecting end.
7. The hermetic packaging box for aeroengines according to claim 5, characterized in that the guide post (6) has a graduated scale on the front face, the top end of the guide post (6) is conical;
the outer diameter of the guide post (6) is smaller than the inner diameter of the graphite self-lubricating sleeve (7).
8. A sealed packing box for aeroengines according to claim 5, characterized in that the lower support (4) is grooved at its upper end; the lower end of the guide post (6) is provided with a bulge; the protrusion is used for matching with the groove of the lower support (4).
9. A package according to claim 5, wherein the upper support (3), the connecting end and the lower support (4) are provided with respective reinforcing ribs.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202023104422.3U CN214085605U (en) | 2020-12-22 | 2020-12-22 | A sealed packing box for aeroengine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202023104422.3U CN214085605U (en) | 2020-12-22 | 2020-12-22 | A sealed packing box for aeroengine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN214085605U true CN214085605U (en) | 2021-08-31 |
Family
ID=77430989
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202023104422.3U Active CN214085605U (en) | 2020-12-22 | 2020-12-22 | A sealed packing box for aeroengine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN214085605U (en) |
-
2020
- 2020-12-22 CN CN202023104422.3U patent/CN214085605U/en active Active
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: A sealed packing box for Aeroengine Effective date of registration: 20220429 Granted publication date: 20210831 Pledgee: Dalian technology Financing Guarantee Co.,Ltd. Pledgor: Dalian Shunjin FRP Products Co.,Ltd. Registration number: Y2022980005057 |
|
| PE01 | Entry into force of the registration of the contract for pledge of patent right | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Date of cancellation: 20231018 Granted publication date: 20210831 Pledgee: Dalian technology Financing Guarantee Co.,Ltd. Pledgor: Dalian Shunjin FRP Products Co.,Ltd. Registration number: Y2022980005057 |
|
| PC01 | Cancellation of the registration of the contract for pledge of patent right |