CN212027933U - Oil filter inlet pipe for aircraft engine - Google Patents
Oil filter inlet pipe for aircraft engine Download PDFInfo
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- CN212027933U CN212027933U CN202020907206.3U CN202020907206U CN212027933U CN 212027933 U CN212027933 U CN 212027933U CN 202020907206 U CN202020907206 U CN 202020907206U CN 212027933 U CN212027933 U CN 212027933U
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- pipe
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Abstract
The utility model discloses an aircraft engine oil filtering oil inlet pipe, which comprises an oil inlet pipeline, wherein the outer side of the oil inlet pipeline is sleeved with a rubber pipe sleeve, the outer side of the rubber pipe sleeve is connected with a mounting seat for fixing the position of the oil inlet pipeline, one end of the oil inlet pipeline is provided with an oil inlet interface for connecting an oil supply system, one end of the oil inlet pipeline, which is far away from the oil inlet interface, is provided with an oil outlet interface for connecting a fuel filter, one side of the oil inlet interface, which is close to the oil inlet pipeline, is connected with a metal pipeline, the outer side of the oil inlet pipeline is in threaded connection with a fixing sleeve for fixing the metal pipeline and the oil inlet pipeline, a back suction prevention component for preventing the back suction of fuel oil is arranged in the metal pipeline, the back suction prevention component comprises a limiting seat, one side of the limiting seat, which, has the advantages of protective function, good sealing performance and convenient maintenance.
Description
Technical Field
The utility model relates to an aviation accessory technical field specifically is an aeroengine oil filters into oil pipe.
Background
An aircraft engine is a highly complex and precise thermal machine, and is an engine for providing power required by flying of an aircraft. The heart of the airplane is known as 'industrial flower', which directly affects the performance, reliability and economy of the airplane and is an important embodiment of national science and technology, industry and national defense strength.
The oil inlet pipe is used for connecting an oil supply system and an aircraft engine, oil in the oil tank is fed into the fuel filter through the oil delivery pump through the oil inlet pipe and is supplied to the engine for working, the aircraft engine can vibrate during working, the oil inlet pipe connected with the aircraft engine can be vibrated to generate noise, the service life of driving experience and other components is influenced, the oil inlet pipe of the aircraft engine has good sealing performance and prevents fuel backflow, meanwhile, the aircraft engine is convenient to overhaul, and the safety of aviation driving is guaranteed.
Aiming at the problems, the oil filtering and feeding pipe for the aircraft engine, which has good sealing performance and a protection effect, is provided.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide an aeroengine oil filters into oil pipe to solve the problem that proposes in the above-mentioned background art.
In order to achieve the above object, the utility model provides a following technical scheme:
the utility model provides an aeroengine oil filters into oil pipe, includes into oil pipe, the rubber pipe box has been cup jointed in the oil pipe outside, the rubber pipe box outside is connected with the mount pad that is used for fixed oil pipe position, it is equipped with the oil feed interface that is used for connecting oil feeding system to advance oil pipe one end, the one end that oil pipe kept away from the oil feed interface is equipped with the interface that produces oil that is used for connecting fuel filter into oil pipe, the oil feed interface is close to one side connection metal pipeline of oil pipe, be equipped with in the metal pipeline and be used for preventing the subassembly of preventing suck-back of fuel.
Preferably, the mount pad includes the mounting panel, the mounting panel is equipped with two sets ofly, and is two sets of the mounting panel passes through set screw and connects, be equipped with on the mounting panel and be used for the fixed mounting hole of advancing oil pipe way, one side that the mounting panel is close to the rubber pipe box is equipped with buffer spring.
Preferably, one side that the oil inlet pipeline is close to the oil outlet interface is equipped with the flange with fire oil filter interface connection, be equipped with sealed the pad on the flange, sealed one side that is close to the oil filter interface of firing is equipped with the arch, fire oil filter interface be equipped with protruding matched with sealed pad recess, one side that the oil inlet pipeline is close to sealed pad is equipped with the oil feed interior conduit, the external diameter of oil feed interior conduit is less than the internal diameter of firing the oil filter interface, the oil feed pipeline outside is equipped with the lock nut who is used for screwing the oil outlet interface.
Preferably, one side that advances oil pipe way and be close to metal pipeline is equipped with the hickey, the metal pipeline inner wall is equipped with the screw thread with hickey matched with, the hickey is close to screw thread one side and is equipped with two sets of sealing washers, advance oil pipe way outside threaded connection have the fixed cover that is used for fixed metal pipeline and advances oil pipe way.
Preferably, the anti-suck-back component comprises a limiting seat, a valve ball is arranged on one side, away from the oil inlet pipeline, of the limiting seat, a baffle is arranged on one side, away from the limiting seat, of the valve ball, and a conical sealing surface matched with the surface of the valve ball is arranged on one side, close to the valve ball, of the baffle.
Preferably, the diameter of the valve ball is smaller than the inner diameter of the metal pipeline, the inner diameter of the limiting seat is smaller than the diameter of the valve ball, and the inner diameter of the baffle is smaller than the diameter of the valve ball.
Preferably, spacing seat includes the fixed block, fixed block fixed connection metal pipeline inner wall, one side fixed connection limiting plate that the fixed block is close to the valve ball, the limiting plate array sets up on the fixed block, be equipped with the oil feed passageway that is used for the fuel to pass through between the limiting plate.
Compared with the prior art, the beneficial effects of the utility model are that:
the utility model discloses a set up the rubber pipe box, play the guard action to advancing oil pipe, prevent that other part damages to advance oil pipe and lead to the oil leak, guarantee aeroengine safety work.
Through setting up the mount pad, can be fixed with oil inlet pipe, the buffer spring of inner wall can cushion the vibrations that oil inlet pipe produced simultaneously, and noise abatement's production is favorable to oil inlet pipe's use.
Through setting up the anti-suck-back subassembly, can effectually prevent that the fuel in the aeroengine from suck the oil tank backward and cause the damage, guarantee aeroengine's safe in utilization, simple structure, the function is practical, the convenient maintenance of changing.
Through setting up sealing washer and sealed the pad in each junction of advancing oil pipe, the leakproofness is good, prevents the oil leak, and convenient the dismantlement simultaneously conveniently maintains the clearance, reduces the time of maintaining the engine, convenient to use.
Drawings
FIG. 1 is a schematic structural diagram of an oil filter inlet pipe of an aircraft engine.
FIG. 2 is a schematic structural diagram of an anti-suck-back assembly in an oil filter inlet pipe of an aircraft engine.
FIG. 3 is a schematic structural view of a limiting seat in an oil filter inlet pipe of an aircraft engine.
FIG. 4 is a schematic cross-sectional view of a mounting seat in an oil filter inlet pipe of an aircraft engine.
FIG. 5 is a schematic structural diagram of an oil outlet port in an oil filter and inlet pipe of an aircraft engine.
FIG. 6 is a schematic diagram of an external structure of an oil filter inlet pipe of an aircraft engine.
In the figure: 1-an oil inlet pipeline, 2-a rubber pipe sleeve, 3-an installation seat, 301-an installation plate, 302-a fixing screw, 303-an installation hole, 4-a fixing sleeve, 5-an oil inlet interface, 6-an oil outlet interface, 601-a sealing gasket, 602-an oil inlet inner pipeline, 603-a locking nut, 7-an anti-suck-back component, 8-a sealing ring, 9-a limiting seat, 901-a fixing block, 902-a limiting plate, 903-an oil inlet channel, 10-a metal pipeline, 11-a valve ball and 12-a baffle plate.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
Referring to fig. 1-6, in the embodiment of the present invention, an oil filter inlet pipe for an aircraft engine, includes oil inlet pipe 1, rubber pipe sleeve 2 has been cup jointed in the oil inlet pipe 1 outside, rubber pipe sleeve 2 plays the guard action to oil inlet pipe 1, prevents that other parts from damaging oil inlet pipe 1 and leading to the oil leak, guarantees aircraft engine safety work.
The rubber pipe box 2 outside is connected with mount pad 3 that is used for fixed oil inlet pipe 1 position, mount pad 3 includes mounting panel 301, mounting panel 301 is equipped with two sets ofly, and is two sets of mounting panel 301 passes through set screw 302 and connects, be equipped with on mounting panel 301 and be used for the mounting hole 303 that will advance oil pipe 1 fixed, one side that mounting panel 301 is close to rubber pipe box 2 is equipped with buffer spring, during the use, passes through set screw 302 with two sets of mounting panel 301 and fixes, advance oil pipe 1 and connect behind the engine, with fixed with mount pad 3 with mounting hole 303 complex screw, through setting up mount pad 3, can be fixed with oil pipe 1, the buffer spring of inner wall can cushion the vibrations that oil pipe 1 produced simultaneously, noise abatement's production is favorable to advancing oil pipe 1's use.
The fuel inlet pipe 1 one end is equipped with oil feed interface 5 that is used for connecting oil feeding system, the one end that oil feed interface 5 was kept away from to oil feed pipeline 1 is equipped with the interface 6 that produces oil that is used for connecting fuel filter, metal pipeline 10 is connected to one side that oil feed interface 5 is close to oil feed pipeline 1, be equipped with in the metal pipeline 10 and be used for preventing the subassembly 7 that prevents suck-back that prevents that the fuel from suck-back.
A flange connected with a fuel filter interface of an aircraft engine is arranged on one side of the fuel outlet interface 6 close to the fuel inlet pipeline 1, a sealing gasket 601 is arranged on the flange, a protrusion is arranged on one side of the sealing gasket 601 close to the fuel filter interface, a sealing gasket groove matched with the protrusion is arranged on the fuel filter interface, an oil inlet inner pipeline 602 is arranged on one side of the fuel inlet pipeline 1 close to the sealing gasket 601, the outer diameter of the oil inlet inner pipeline 602 is smaller than the inner diameter of the fuel filter interface, a locking nut 603 used for screwing the fuel outlet interface 6 is arranged on the outer side of the fuel inlet pipeline 1, the sealing performance of the fuel outlet interface 6 can be enhanced by the protrusion on the sealing gasket 601, and the oil inlet inner pipeline 602 is communicated with;
when the oil outlet port 6 is installed, the oil inlet inner pipeline 602 is installed in the fuel filter port, when fuel flows out from the oil inlet pipeline 1, the fuel can be reduced to pass through the sealing gasket 601, the sealing performance of the oil outlet port 6 is further enhanced, the oil outlet port 6 is locked by the locking nut 603 after being connected with the fuel filter port, the oil inlet pipeline 1 is fixed, the oil outlet port 6 is sealed, the oil inlet port 5 is communicated with an oil supply system, fuel oil normally flows and enters the aircraft engine after being filtered by the fuel filter, the oil inlet port 5 and the oil outlet port 6 are convenient to disassemble and repair, meanwhile, the sealing performance is good, oil leakage when the oil inlet pipeline 1 is used is prevented, meanwhile, the oil inlet pipeline 1 is convenient to maintain and clean, and the use is convenient.
Advance one side that oil pipe way 1 is close to metal pipeline 10 and be equipped with hickey, metal pipeline 10 inner wall be equipped with hickey matched with screw thread, hickey is close to screw thread one side and is equipped with two sets of sealing washers 8, the leakproofness between oil pipe way 1 and the metal pipeline 10 can be strengthened to sealing washer 8, 1 outside threaded connection of oil pipe way has fixed cover 4 that is used for fixed metal pipeline 10 and oil pipe way 1, will advance oil pipe way 1's hickey connection metal pipeline 10 during the use, later will fix cover 4 and screw, fixes metal pipeline 10 and advance oil pipe way 1's position, further seals metal pipeline 10 and the junction that advances oil pipe way 1, prevents the oil leak, conveniently dismantles simultaneously and overhauls.
The anti-suck-back component 7 comprises a limiting seat 9, the limiting seat 9 comprises a fixing block 901, the fixing block 901 is fixedly connected with the inner wall of the metal pipeline 10, one side of the fixing block 901, which is close to the valve ball 11, is fixedly connected with a limiting plate 902, the limiting plates 902 are arranged on the fixing block 901 in an array manner, and an oil inlet passage 903 for fuel oil to pass through is arranged between the limiting plates 902;
one side of the limiting seat 9, which is far away from the oil inlet pipeline 1, is provided with a valve ball 11, one side of the valve ball 11, which is far away from the limiting seat 9, is provided with a baffle plate 12, one side of the baffle plate 12, which is close to the valve ball 11, is provided with a conical sealing surface matched with the surface of the valve ball 11, the diameter of the valve ball 11 is smaller than the inner diameter of the metal pipeline 10, the inner diameter of the limiting seat 9 is smaller than the diameter of the valve ball 11, the inner diameter of the baffle plate 12 is smaller than the diameter of the valve ball 11, when the oil inlet pipeline 1 normally feeds oil, fuel enters from the oil inlet interface 5, the valve ball 11 moves to one side close to the limiting plate 902 under the force of fuel oil flow, the fuel enters the inner cavity of the limiting seat 9 through the oil inlet channel 903 and flows into the oil inlet pipeline 1, when the oil supply system stops supplying oil into the oil inlet pipeline 1, the reverse suction occurs, the valve ball 11 moves to, the aircraft engine fuel oil supply system can effectively prevent the aircraft engine fuel oil from being sucked back to cause damage, the aircraft engine is safe to use, the structure is simple, the function is practical, and replacement and maintenance are convenient.
The utility model discloses a theory of operation is: when the aircraft engine oil filter oil inlet pipe is used, the oil inlet pipeline 1 is connected with the metal pipeline 10, the fixing sleeve 4 is screwed, the oil inlet interface 5 is installed at the oil outlet end of an oil pump of an oil supply system, the oil outlet interface 5 is installed at the oil inlet end of a fuel filter of an aircraft engine, the locking nut 603 is screwed, the mounting plate 301 is fixed outside the rubber pipe sleeve 2 through the fixing screw 302, the mounting seat 3 is fixed through the screw matched with the mounting hole 303, during normal oil inlet, the valve ball 11 moves to one side close to the limiting plate 902, fuel enters the oil inlet pipeline 1 through the oil inlet channel 903, and when reverse suction occurs, the valve ball 11 moves to one side close to the baffle 12 to block the inner cavity of the metal pipeline 10 to prevent reverse suction.
It is obvious to a person skilled in the art that the invention is not restricted to details of the above-described exemplary embodiments, but that it can be implemented in other specific forms without departing from the spirit or essential characteristics of the invention. The present embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. Any reference sign in a claim should not be construed as limiting the claim concerned.
Furthermore, it should be understood that although the present description refers to embodiments, not every embodiment may contain only a single embodiment, and such description is for clarity only, and those skilled in the art should integrate the description, and the embodiments may be combined as appropriate to form other embodiments understood by those skilled in the art.
Claims (7)
1. The utility model provides an aeroengine oil filter advances oil pipe, includes into oil pipe way (1), its characterized in that: the utility model discloses a fuel oil filter, including oil inlet pipeline (1), rubber pipe box (2) has been cup jointed in the oil inlet pipeline (1) outside, rubber pipe box (2) outside is connected with mount pad (3) that are used for fixed oil inlet pipeline (1) position, oil inlet pipeline (1) one end is equipped with oil feed interface (5) that are used for connecting oil feeding system, the one end that oil feed interface (5) were kept away from in oil inlet pipeline (1) is equipped with oil outlet interface (6) that are used for connecting fuel oil filter, metal pipeline (10) are connected to one side that oil feed interface (5) are close to oil inlet pipeline (1), be equipped with in metal pipeline (10) and be used for preventing.
2. The aircraft engine oil filter inlet pipe of claim 1, characterized in that: mounting base (3) include mounting panel (301), mounting panel (301) are equipped with two sets ofly, and are two sets of mounting panel (301) are connected through set screw (302), be equipped with on mounting panel (301) and be used for advancing oil pipe way (1) fixed mounting hole (303), one side that mounting panel (301) are close to rubber pipe box (2) is equipped with buffer spring.
3. The aircraft engine oil filter inlet pipe of claim 1, characterized in that: one side that produces oil interface (6) is close to oil feed pipeline (1) is equipped with the flange with fire oil filter interface connection, be equipped with sealed pad (601) on the flange, sealed pad (601) are close to the one side of firing oil filter interface and are equipped with the arch, fire oil filter interface and be equipped with protruding matched with sealed pad recess, one side that oil feed pipeline (1) is close to sealed pad (601) is equipped with oil feed inner tube way (602), the external diameter of oil feed inner tube way (602) is less than the internal diameter of firing oil filter interface, oil feed pipeline (1) outside is equipped with lock nut (603) that are used for screwing out oil interface (6).
4. The aircraft engine oil filter inlet pipe of claim 1, characterized in that: advance oil pipe way (1) and be close to one side of metal pipeline (10) and be equipped with hickey, metal pipeline (10) inner wall be equipped with hickey matched with screw thread, hickey is close to screw thread one side and is equipped with two sets of sealing washers (8), advance oil pipe way (1) outside threaded connection have be used for fixed metal pipeline (10) and advance fixed cover (4) of oil pipe way (1).
5. The aircraft engine oil filter inlet pipe of claim 1, characterized in that: prevent suck-back subassembly (7) including spacing seat (9), one side that advances oil pipe way (1) is kept away from in spacing seat (9) is equipped with valve ball (11), one side that spacing seat (9) were kept away from in valve ball (11) is equipped with baffle (12), one side that baffle (12) are close to valve ball (11) is equipped with the toper sealing surface with valve ball (11) surface complex.
6. The aircraft engine oil filter inlet pipe of claim 5, characterized in that: the diameter of the valve ball (11) is smaller than the inner diameter of the metal pipeline (10), the inner diameter of the limiting seat (9) is smaller than the diameter of the valve ball (11), and the inner diameter of the baffle plate (12) is smaller than the diameter of the valve ball (11).
7. The aircraft engine oil filter inlet pipe of claim 5, characterized in that: the limiting seat (9) comprises a fixing block (901), the fixing block (901) is fixedly connected with the inner wall of the metal pipeline (10), one side of the fixing block (901) close to the valve ball (11) is fixedly connected with a limiting plate (902), the limiting plate (902) is arranged on the fixing block (901) in an array mode, and an oil inlet channel (903) for fuel oil to pass through is arranged between the limiting plates (902).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020907206.3U CN212027933U (en) | 2020-05-26 | 2020-05-26 | Oil filter inlet pipe for aircraft engine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020907206.3U CN212027933U (en) | 2020-05-26 | 2020-05-26 | Oil filter inlet pipe for aircraft engine |
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| Publication Number | Publication Date |
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| CN212027933U true CN212027933U (en) | 2020-11-27 |
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| CN202020907206.3U Active CN212027933U (en) | 2020-05-26 | 2020-05-26 | Oil filter inlet pipe for aircraft engine |
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| CN (1) | CN212027933U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112881216A (en) * | 2021-02-09 | 2021-06-01 | 马丽娟 | Pressure vessel pulse fatigue equipment testing device |
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2020
- 2020-05-26 CN CN202020907206.3U patent/CN212027933U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112881216A (en) * | 2021-02-09 | 2021-06-01 | 马丽娟 | Pressure vessel pulse fatigue equipment testing device |
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