CN112576850A - Sealing element for aviation pipeline - Google Patents

Sealing element for aviation pipeline Download PDF

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Publication number
CN112576850A
CN112576850A CN202110016915.1A CN202110016915A CN112576850A CN 112576850 A CN112576850 A CN 112576850A CN 202110016915 A CN202110016915 A CN 202110016915A CN 112576850 A CN112576850 A CN 112576850A
Authority
CN
China
Prior art keywords
pipe
pipeline
rubber
connecting piece
oil
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.)
Withdrawn
Application number
CN202110016915.1A
Other languages
Chinese (zh)
Inventor
王建彬
徐慧敏
江本赤
李庆安
疏达
赵长红
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Anhui Polytechnic University
Original Assignee
Anhui Polytechnic University
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Anhui Polytechnic University filed Critical Anhui Polytechnic University
Priority to CN202110016915.1A priority Critical patent/CN112576850A/en
Publication of CN112576850A publication Critical patent/CN112576850A/en
Withdrawn legal-status Critical Current

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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
    • F16L—PIPES; JOINTS OR FITTINGS FOR PIPES; SUPPORTS FOR PIPES, CABLES OR PROTECTIVE TUBING; MEANS FOR THERMAL INSULATION IN GENERAL
    • F16L53/00—Heating of pipes or pipe systems; Cooling of pipes or pipe systems
    • F16L53/30—Heating of pipes or pipe systems
    • F16L53/32—Heating of pipes or pipe systems using hot fluids
    • 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
    • F16L23/00—Flanged joints
    • F16L23/02—Flanged joints the flanges being connected by members tensioned axially
    • 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
    • F16L39/00—Joints or fittings for double-walled or multi-channel pipes or pipe assemblies
    • F16L39/005—Joints or fittings for double-walled or multi-channel pipes or pipe assemblies for concentric pipes
    • 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
    • F16L43/00—Bends; Siphons
    • 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
    • F16L55/00—Devices or appurtenances for use in, or in connection with, pipes or pipe systems
    • F16L55/16—Devices for covering leaks in pipes or hoses, e.g. hose-menders
    • F16L55/162—Devices for covering leaks in pipes or hoses, e.g. hose-menders from inside the pipe
    • F16L55/164—Devices for covering leaks in pipes or hoses, e.g. hose-menders from inside the pipe a sealing fluid being introduced in the pipe
    • 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
    • F16L59/00—Thermal insulation in general
    • F16L59/14—Arrangements for the insulation of pipes or pipe systems
    • F16L59/16—Arrangements specially adapted to local requirements at flanges, junctions, valves or the like
    • F16L59/18—Arrangements specially adapted to local requirements at flanges, junctions, valves or the like adapted for joints
    • 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
    • F16L9/00—Rigid pipes
    • F16L9/18—Double-walled pipes; Multi-channel pipes or pipe assemblies

Abstract

The invention discloses a sealing element for an aviation pipeline, which comprises a pipeline connecting piece, an oil inlet pipe and an oil outlet pipe, wherein the oil inlet pipe is fixedly clamped and mounted on one side of the outside of the pipeline connecting piece, the oil outlet pipe is fixedly clamped and mounted on the other side of the outside of the pipeline connecting piece, a heating mechanism is embedded and mounted in the pipeline connecting piece, the heating mechanism comprises a supporting pipe, a water inlet pipe, a return pipe, a curved circulating pipe, a heat-conducting silicone grease layer and an asbestos heat-insulating layer, liquid which is cooled and absorbed by an aircraft engine is guided into the curved circulating pipe through the water inlet pipe, the curved circulating pipe and the heat-conducting silicone grease layer heat a hollow inner container in the supporting pipe, the heat of the supporting pipe is preserved by matching with the asbestos heat-insulating layer, and heated liquid flows back through the return pipe, so that the heating and temperature rising function of, the problem of solidification of oil in the pipeline connecting piece is easily caused.

Description

Sealing element for aviation pipeline
Technical Field
The invention relates to the technical field of aviation pipe fittings, in particular to a sealing element for an aviation pipeline.
Background
The sealing element is a material or a part of a part for preventing fluid or solid particles from leaking from adjacent joint surfaces and preventing external impurities such as dust, moisture and the like from invading into the interior of machinery equipment, although the rubber and plastic sealing element is small, the rubber and plastic sealing element has the function of making the rubber and plastic sealing element become a basic part and a fitting in national economy main industries such as national defense, chemical industry, petroleum, coal, transportation, mechanical manufacturing and the like, and plays a very important role in the development of national economy.
However, when the existing sealing element for the aviation pipeline is used, the pipeline connecting piece is affected by the low temperature of the external environment, so that the solidification of oil liquid in the pipeline connecting piece is easily caused, the blockage of the aviation pipeline and the aging and damage of the pipeline after the connecting rubber tube is used for a long time are caused, and the problem of the leakage of liquid in the aviation pipeline is easily caused.
Disclosure of Invention
The invention aims to provide a sealing element for an aviation pipeline with heating anti-condensation and anti-leakage repairing functions, so as to solve the problems in the background technology.
In order to achieve the purpose, the invention provides the following technical scheme: a sealing element for an aviation pipeline comprises a pipeline connecting piece, an oil inlet pipe and an oil outlet pipe, wherein the oil inlet pipe is fixedly clamped and mounted on one side of the outer part of the pipeline connecting piece, the oil outlet pipe is fixedly clamped and installed at the other side of the outer part of the pipeline connecting piece, the heating mechanism is embedded and installed in the pipeline connecting piece, the oil inlet pipe and the oil outlet pipe are both embedded with a connecting rubber pipe, the outside of the connecting rubber pipe is sleeved with a sealing mechanism, the pipeline connecting piece and the inner wall of the oil outlet pipe are respectively provided with a fixing mechanism in a clamping way, the heating mechanism is used for heating the oil circuit in the pipeline connecting piece by liquid which is cooled and absorbs heat of the aircraft engine, the sealing mechanism is used for sealing the leakage position when the outer wall of the connecting rubber pipe is damaged, and the fixing mechanism is used for dismounting and mounting the connecting rubber pipe.
Furthermore, heating mechanism includes a supporting pipe, a water inlet pipe, a return pipe, curved circulation pipe, heat conduction silicone grease layer and asbestos heat preservation, the embedding of supporting pipe is installed pipeline connecting piece bottom middle part, the installation of water inlet pipe embedding is in pipeline connecting piece heat conduction silicone grease layer paste cover install curved circulation pipe inner wall, the installation is covered in the subsides of asbestos heat preservation curved circulation pipe outer wall.
Furthermore, the inside of the supporting pipe is provided with a hollow inner container, the top end of the water inlet pipe is communicated with one side of the bottom end of the curved circulating pipe, and the top end of the return pipe is communicated with the other side of the bottom end of the curved circulating pipe.
Further, sealing mechanism includes upper ring, lower ring, stores up gluey sacculus, cavity guide arm and outage, the upper ring cup joints to be installed connect the outside one side of rubber tube, the lower ring cup joints to be installed connect the outside opposite side of rubber tube, the cavity guide arm runs through to be installed the lower ring inside with upper ring top surface, it installs to store up gluey sacculus cup joint the cavity guide arm top, the outage evenly runs through to be seted up upper ring and store up gluey sacculus outer wall surface.
Further, the middle part of the interior of the rubber storage ball bag is wrapped with an air compression air bag, and the rubber storage ball bag is fixedly connected with the inner wall of the oil inlet pipe through a blocking cover.
Further, fixed establishment includes ring groove, rubber tube joint, slippage groove, compression spring and spacing fixture block, ring groove sets up advance an oil pipe inner wall tip, the rubber tube joint is installed connect the rubber tube top, the slippage groove is evenly set up ring groove bottom border position department, the compression spring embedding is installed ring groove bottom, spacing fixture block is evenly installed rubber tube joint outer wall border position department.
Furthermore, the outer diameter of the limiting clamping block is smaller than the inner diameter of the slipping groove, and a sealing rubber ring is attached to the inner portion of the annular clamping groove.
Further, fixed flanges are installed on two sides of the outside of the pipeline connecting piece, and a fixed lug is installed on one side of the top end of the outside of the pipeline connecting piece in a welded mode.
Compared with the prior art, the invention has the beneficial effects that:
according to the invention, the heating mechanism is arranged, the support pipe protects the outer parts of the water inlet pipe and the return pipe, liquid which is cooled and absorbs heat of the aircraft engine is guided to the curved circulating pipe through the water inlet pipe, the curved circulating pipe and the heat-conducting silicone layer heat the hollow inner container in the support pipe, the asbestos heat-insulating layer is matched to insulate the inner part of the support pipe, and the return pipe returns heated liquid, so that the heating and temperature-rising functions of the inner pipeline of the pipeline connecting piece are realized, and the problem that the pipeline connecting piece is influenced by low temperature of the external environment, so that oil in the pipeline connecting piece is easily solidified to block the aircraft pipeline is solved.
The sealing mechanism is arranged, when oil leakage is caused by damage of the outer wall of the connecting rubber pipe, due to reduction of oil pressure inside the oil inlet pipe, glue stored inside the rubber storage ball bag can be discharged into the hollow guide rod through the air compression air bag and is sequentially discharged into the upper ring and the lower ring through the hollow guide rod, the glue is coated on the inner wall of the oil inlet pipe through the liquid discharge hole, and glue joint plugging is performed between the leakage position of the outer wall of the connecting rubber pipe and the inner wall of the oil inlet pipe, so that the temporary plugging protection function of the connecting rubber pipe is realized, and the problem that liquid of an aviation pipeline is easy to leak due to aging and damage of the pipeline after the connecting rubber pipe is used for a long time.
Be provided with fixed establishment, will connect rubber tube top ring groove joint inside the oil feed pipe, the spacing fixture block screw in of rubber tube joint side is fixed to ring groove inside at the slippage groove to support the rubber tube joint bottom by compression spring, thereby realized connecting the rubber tube and advancing the quick assembly disassembly between the oil pipe, guaranteed the fastness of connecting the rubber tube installation and the convenience of later stage change.
Drawings
Fig. 1 is a schematic perspective view of a pipe connection according to an embodiment of the present invention.
Fig. 2 is a perspective view of the curved circulating pipe installation in the embodiment of fig. 1.
Fig. 3 is a schematic cross-sectional view of the interior of the pipe connection in the embodiment of fig. 1.
Fig. 4 is a schematic perspective view of the hollow guide rod of fig. 3.
FIG. 5 is a perspective view of the hose connector of the embodiment of FIG. 3.
Fig. 6 is a perspective view of the compression spring assembly in the embodiment of fig. 1.
Reference numerals: 1. a pipe connection; 2. an oil inlet pipe; 3. an oil outlet pipe; 4. a fixed flange; 5. a heating mechanism; 501. a support tube; 502. a water inlet pipe; 503. a return pipe; 504. a curved circulation tube; 505. a thermally conductive silicone layer; 506. an asbestos insulation layer; 6. fixing the ear; 7. connecting a rubber tube; 8. a sealing mechanism; 801. an upper ring; 802. a lower ring; 803. a glue storage balloon; 804. a hollow guide rod; 805. a drain hole; 9. a fixing mechanism; 901. an annular neck; 902. a hose joint; 903. a slipping groove; 904. a compression spring; 905. and a limiting clamping block.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
Referring to fig. 1-6 together, a sealing member for an aircraft pipeline comprises a pipeline connector 1, an oil inlet pipe 2 and an oil outlet pipe 3, the oil inlet pipe 2 is fixedly clamped and mounted on one side of the outside of the pipeline connector 1, the oil outlet pipe 3 is fixedly clamped and mounted on the other side of the outside of the pipeline connector 1, a heating mechanism 5 is embedded and mounted inside the pipeline connector 1, a connecting rubber pipe 7 is embedded and mounted inside the oil inlet pipe 2 and the oil outlet pipe 3, a sealing mechanism 8 is sleeved and mounted outside the connecting rubber pipe 7, a fixing mechanism 9 is clamped and mounted on the inner walls of the pipeline connector 1 and the oil outlet pipe 3, the heating mechanism 5 comprises a supporting pipe 501, an inlet pipe 502, a return pipe 503, a curved circulating pipe 504, a heat-conducting silicone grease layer 505 and an asbestos insulation layer 506, the supporting pipe 501 is embedded and mounted in the middle of, the return pipe 503 is embedded in the other side of the inside of the support pipe 501, the curved circulation pipe 504 is sleeved and installed inside the pipeline connecting piece 1, the heat-conducting silicone layer 505 is attached and installed on the inner wall of the curved circulation pipe 504, the asbestos heat preservation layer 506 is attached and installed on the outer wall of the curved circulation pipe 504, the hollow liner is installed inside the support pipe 501, the top end of the water inlet pipe 502 is communicated and connected with one side of the bottom end of the curved circulation pipe 504, the top end of the return pipe 503 is communicated and connected with the other side of the bottom end of the curved circulation pipe 504, the support pipe 501 protects the outside of the water inlet pipe 502 and the return pipe 503, the liquid which is cooled and absorbs heat of the aircraft engine is guided into the curved circulation pipe 504 through the water inlet pipe 502, the hollow liner inside the support pipe 501 is heated through the curved circulation pipe 504 and the heat-conducting silicone layer 505, the heat preservation is matched with the asbestos heat preservation layer, the problem of pipeline connecting piece 1 receive the microthermal influence of external environment, cause pipeline connecting piece 1 inside fluid to take place to solidify easily, cause the jam of aviation pipeline is solved.
The sealing mechanism 8 comprises an upper ring 801, a lower ring 802, a rubber storage balloon 803, a hollow guide rod 804 and a liquid discharge hole 805, the upper ring 801 is sleeved and installed at one side of the outer part of the connecting rubber tube 7, the lower ring 802 is sleeved and installed at the other side of the outer part of the connecting rubber tube 7, the hollow guide rod 804 is installed inside the lower ring 802 and on the top end surface of the upper ring 801 in a penetrating way, the rubber storage balloon 803 is sleeved and installed at the top end of the hollow guide rod 804, the liquid discharge hole 805 is uniformly arranged on the outer wall surfaces of the upper ring 801 and the rubber storage balloon 803 in a penetrating way, an air compression balloon is wrapped at the middle part inside the rubber storage balloon 803, the rubber storage balloon 803 is fixedly connected with the inner wall of the oil inlet tube 2 through a baffle cover, when oil is leaked due to breakage of the outer wall of the connecting rubber tube 7, the oil pressure inside the oil inlet tube 2 is reduced, the glue stored inside the rubber storage balloon 803 can be discharged into the hollow guide rod 804 through the air compression, glue is coated on the inner wall of the oil inlet pipe 2 through the liquid discharge hole 805, and the outer wall leakage position of the connecting rubber pipe 7 and the inner wall of the oil inlet pipe 2 are subjected to glue joint plugging, so that the temporary plugging protection function of the connecting rubber pipe 7 is realized, and the problem that the liquid of an aviation pipeline is easy to leak due to aging and damage of the pipeline after the connecting rubber pipe 7 is used for a long time is solved.
The fixing mechanism 9 comprises an annular clamping groove 901, a rubber pipe joint 902, a slipping groove 903, a compression spring 904 and a limiting clamping block 905, wherein the annular clamping groove 901 is arranged at one end part of the inner wall of the oil inlet pipe 2, the rubber pipe joint 902 is clamped and installed at the top end of the connecting rubber pipe 7, the slipping groove 903 is uniformly arranged at the edge position of the bottom end of the annular clamping groove 901, the compression spring 904 is embedded and installed at the bottom end of the annular clamping groove 901, the limiting clamping block 905 is uniformly installed at the edge position of the outer wall of the rubber pipe joint 902, the outer diameter of the limiting clamping block 905 is smaller than the inner diameter of the slipping groove 903, a sealing rubber ring is pasted and covered inside the annular clamping groove 901, the annular clamping groove 901 at the top end of the connecting rubber pipe 7 is clamped and installed inside the oil inlet pipe 2, the limiting clamping block 905 at the rubber pipe joint 902 side is screwed into the annular clamping groove 901, the firmness of the installation of the connecting rubber tube 7 and the convenience of later-stage replacement are ensured.
In order to guarantee the fastness of advancing oil pipe 2 and going out oil pipe 3 in the installation of 1 both sides of pipeline connecting piece, mounting flange 4 is all installed to 1 outside both sides of pipeline connecting piece, in order to be connected fixedly between pipeline connecting piece 1 and the external equipment, 1 outside top one side welded mounting of pipeline connecting piece has fixed ear 6.
In conclusion, when the sealing element for the aviation pipeline provided by the invention works, firstly, the annular clamping groove 901 at the top end of the connecting rubber pipe 7 is clamped inside the oil inlet pipe 2, the limiting clamping block 905 at the rubber pipe joint 902 side is screwed into the annular clamping groove 901 at the slipping groove 903 for fixing, and the bottom end of the rubber pipe joint 902 is supported by the compression spring 904, so that the quick installation between the connecting rubber pipe 7 and the oil inlet pipe 2 is realized;
next, the exterior of the water inlet pipe 502 and the return pipe 503 is protected by the support pipe 501, the liquid which is cooled and absorbs heat of the aircraft engine is guided to the interior of the curved circulating pipe 504 through the water inlet pipe 502, the hollow liner inside the support pipe 501 is heated by the curved circulating pipe 504 and the heat-conducting silicone layer 505, the interior of the support pipe 501 is insulated by matching with the asbestos insulation layer 506, and the heated liquid is returned by the return pipe 503.
Finally, when oil leaks due to the damage of the outer wall of the connecting rubber tube 7, due to the reduction of the oil pressure inside the oil inlet tube 2, the glue stored inside the glue storage balloon 803 can be discharged into the hollow guide rod 804 through the air compression balloon, and is sequentially discharged into the upper ring 801 and the lower ring 802 through the hollow guide rod 804, the glue is coated on the inner wall of the oil inlet tube 2 through the liquid discharge hole 805, and the glue is connected and blocked between the leakage position of the outer wall of the connecting rubber tube 7 and the inner wall of the oil inlet tube 2.
It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.

Claims (8)

1. The sealing element for the aviation pipeline comprises a pipeline connecting piece (1), an oil inlet pipe (2) and an oil outlet pipe (3), wherein the oil inlet pipe (2) is fixedly clamped and mounted on one side of the outer part of the pipeline connecting piece (1), and the oil outlet pipe (3) is fixedly clamped and mounted on the other side of the outer part of the pipeline connecting piece (1);
its characterized in that, heating mechanism (5) is installed in the inside embedding of pipeline connecting piece (1), advance oil pipe (2) with go out the inside equal embedding of oil pipe (3) and install connection rubber tube (7), it installs sealing mechanism (8) to connect rubber tube (7) outside cup joint, pipeline connecting piece (1) with go out the equal joint of oil pipe (3) inner wall and install fixed establishment (9), it is right that heating mechanism (5) are used for the liquid after the aeroengine cooling is endothermic pipeline connecting piece (1) inside oil circuit heats up, sealing mechanism (8) are used for glue when connecting rubber tube (7) outer wall and taking place the damage and seal to the seepage department, fixed establishment (9) are used for right it carries out the dismouting to connect rubber tube (7).
2. The aircraft pipeline sealing element according to claim 1, wherein the heating mechanism (5) comprises a supporting pipe (501), a water inlet pipe (502), a return pipe (503), a curved circulating pipe (504), a heat-conducting silicone layer (505) and an asbestos insulation layer (506), the supporting pipe (501) is embedded in the middle of the bottom end of the pipeline connecting piece (1), the water inlet pipe (502) is embedded in one side of the inside of the supporting pipe (501), the return pipe (503) is embedded in the other side of the inside of the supporting pipe (501), the curved circulating pipe (504) is sleeved and installed in the pipeline connecting piece (1), the heat-conducting silicone layer (505) is attached to the inner wall of the curved circulating pipe (504), and the asbestos insulation layer (506) is attached to the outer wall of the curved circulating pipe (504).
3. The aircraft pipeline sealing element as claimed in claim 2, wherein a hollow liner is installed inside the supporting pipe (501), the top end of the water inlet pipe (502) is connected with one side of the bottom end of the curved circulating pipe (504) in a penetrating manner, and the top end of the return pipe (503) is connected with the other side of the bottom end of the curved circulating pipe (504) in a penetrating manner.
4. The sealing element for the aviation pipeline according to claim 1, wherein the sealing mechanism (8) comprises an upper ring (801), a lower ring (802), a rubber storage balloon (803), a hollow guide rod (804) and a liquid discharge hole (805), the upper ring (801) is sleeved and mounted on one side of the outer portion of the connecting rubber pipe (7), the lower ring (802) is sleeved and mounted on the other side of the outer portion of the connecting rubber pipe (7), the hollow guide rod (804) is installed inside the lower ring (802) and on the top end surface of the upper ring (801) in a penetrating manner, the rubber storage balloon (803) is sleeved and mounted on the top end of the hollow guide rod (804), and the liquid discharge hole (805) is uniformly formed in the outer wall surfaces of the upper ring (801) and the rubber storage balloon (803) in a penetrating manner.
5. The sealing element for the aviation pipeline according to claim 4, wherein an air compression air bag is wrapped at the middle part of the interior of the rubber storage balloon (803), and the rubber storage balloon (803) is fixedly connected with the inner wall of the oil inlet pipe (2) through a baffle cover.
6. The aircraft pipeline sealing element according to claim 1, wherein the fixing mechanism (9) comprises an annular clamping groove (901), a rubber pipe joint (902), a slipping groove (903), a compression spring (904) and a limiting clamping block (905), the annular clamping groove (901) is formed in one end portion of the inner wall of the oil inlet pipe (2), the rubber pipe joint (902) is installed at the top end of the connecting rubber pipe (7) in a clamping mode, the slipping groove (903) is formed in the edge position of the bottom end of the annular clamping groove (901) uniformly, the compression spring (904) is installed at the bottom end of the annular clamping groove (901) in an embedding mode, and the limiting clamping block (905) is installed at the edge position of the outer wall of the rubber pipe joint (902) uniformly.
7. The sealing element for the aviation pipeline according to claim 6, wherein the outer diameter of the limiting clamping block (905) is smaller than the inner diameter of the slip-off groove (903), and a sealing rubber ring is attached to the inside of the annular clamping groove (901).
8. The aircraft pipeline sealing element according to claim 1, wherein fixing flanges (4) are installed on two outer sides of the pipeline connecting piece (1), and a fixing lug (6) is welded and installed on one side of the top end of the outer portion of the pipeline connecting piece (1).
CN202110016915.1A 2021-01-07 2021-01-07 Sealing element for aviation pipeline Withdrawn CN112576850A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202110016915.1A CN112576850A (en) 2021-01-07 2021-01-07 Sealing element for aviation pipeline

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202110016915.1A CN112576850A (en) 2021-01-07 2021-01-07 Sealing element for aviation pipeline

Publications (1)

Publication Number Publication Date
CN112576850A true CN112576850A (en) 2021-03-30

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CN202110016915.1A Withdrawn CN112576850A (en) 2021-01-07 2021-01-07 Sealing element for aviation pipeline

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Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN204717182U (en) * 2015-05-04 2015-10-21 中国南方航空工业(集团)有限公司 Gas-liquid sealing joint and motor
CN205842018U (en) * 2016-07-04 2016-12-28 临海市四通制管有限公司 A kind of electromotor with clamping sleeve blow-out patch seals oil pipe
CN108679211A (en) * 2018-06-04 2018-10-19 北京长城华冠汽车技术开发有限公司 Oil cooling system and automobile
CN209277872U (en) * 2019-01-10 2019-08-20 蒋玉林 A kind of sampling device for freezen protection at portal of petroleum attraction well
CN212178181U (en) * 2020-06-04 2020-12-18 杭州光旭绿色能源科技有限公司 Integrated high-pressure rubber hose joint capable of avoiding environmental pollution
CN214498992U (en) * 2020-11-17 2021-10-26 四川广旺能源发展（集团）有限责任公司代池坝煤矿 Gas extraction drilling hole sealing device

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN204717182U (en) * 2015-05-04 2015-10-21 中国南方航空工业(集团)有限公司 Gas-liquid sealing joint and motor
CN205842018U (en) * 2016-07-04 2016-12-28 临海市四通制管有限公司 A kind of electromotor with clamping sleeve blow-out patch seals oil pipe
CN108679211A (en) * 2018-06-04 2018-10-19 北京长城华冠汽车技术开发有限公司 Oil cooling system and automobile
CN209277872U (en) * 2019-01-10 2019-08-20 蒋玉林 A kind of sampling device for freezen protection at portal of petroleum attraction well
CN212178181U (en) * 2020-06-04 2020-12-18 杭州光旭绿色能源科技有限公司 Integrated high-pressure rubber hose joint capable of avoiding environmental pollution
CN214498992U (en) * 2020-11-17 2021-10-26 四川广旺能源发展（集团）有限责任公司代池坝煤矿 Gas extraction drilling hole sealing device

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Application publication date: 20210330