CN109252963B - Gravity switching unit and aeroengine reverse-flying oil supply and ventilation device comprising same - Google Patents
Gravity switching unit and aeroengine reverse-flying oil supply and ventilation device comprising same Download PDFInfo
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- CN109252963B CN109252963B CN201811289385.2A CN201811289385A CN109252963B CN 109252963 B CN109252963 B CN 109252963B CN 201811289385 A CN201811289385 A CN 201811289385A CN 109252963 B CN109252963 B CN 109252963B
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- 230000005484 gravity Effects 0.000 title claims abstract description 159
- 238000009423 ventilation Methods 0.000 title claims abstract description 24
- 238000007789 sealing Methods 0.000 claims abstract description 21
- 239000000446 fuel Substances 0.000 claims 1
- 239000003921 oil Substances 0.000 abstract description 53
- 239000010687 lubricating oil Substances 0.000 abstract description 45
- 238000004891 communication Methods 0.000 description 5
- 230000000694 effects Effects 0.000 description 4
- 230000001050 lubricating effect Effects 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 230000002159 abnormal effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000000945 filler Substances 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 238000005461 lubrication Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000011089 mechanical engineering Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Classifications
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Multiple-Way Valves (AREA)
- Cooling, Air Intake And Gas Exhaust, And Fuel Tank Arrangements In Propulsion Units (AREA)
Abstract
The invention relates to a gravity switching unit and an aircraft engine back-flying oil supply ventilation device comprising the same, wherein the oil supply ventilation device comprises two gravity switching units and an oil tank, the gravity switching unit comprises a shell, a gravity switching cylinder body can be vertically matched in the shell in a sliding manner, a first through hole I and a second through hole I are formed in the wall of the shell, a first through hole II and a second through hole II are formed in the wall of the gravity switching cylinder body, sealing plates are connected to the upper surface and the lower surface of the shell, and a pipe connecting hole is formed in any sealing plate; the upper part and the lower part of the lubricating oil tank are respectively connected with the connecting pipe hole of the gravity switching unit, the through hole in a communicating state on the shell of the gravity switching unit connected with the lower part of the lubricating oil tank and the through hole in a staggered sealing state on the shell of the gravity switching unit connected with the upper part of the lubricating oil tank are connected with the booster pump through the lubricating oil guide pipe, and the other two through holes on the two shells are connected with the centrifugal ventilator through the air guide pipe. The invention can simultaneously ensure the oil supply and ventilation of the lubricating oil tank.
Description
Technical Field
The invention belongs to the technical field of engine lubrication in mechanical engineering, and particularly relates to a gravity switching unit and an aircraft engine reverse-flight oil supply ventilation device comprising the same.
Background
Aircraft, particularly military aircraft, have various flight attitude requirements, and the ability to sustain flight at different flight attitudes presents a significant challenge for stable operation of an aircraft gas turbine engine.
For a general aeroengine, when the engine flies down, the lubricating oil output of the lubricating oil tank and the ventilation of the lubricating oil tank are in abnormal working states, and due to the attitude reasons, an oil supply pipe at the bottom of the lubricating oil tank cannot convey lubricating oil to a booster pump and to a lubricating part through the booster pump, and at the moment, the lubricating oil supply of each lubricating part of the engine is interrupted, and the engine main bearing and each lubricating part are dry-ground due to long-time flying down, so that serious engine faults are generated. In addition, the breather pipe at the top of the lubricating oil tank can not normally convey the gas in the lubricating oil tank to the centrifugal ventilator so as to ensure the stability of the gas pressure in the lubricating oil tank, and long-time back flying can cause the overhigh gas pressure in the lubricating oil tank and can not normally work, so that the lubricating oil system of the engine is failed.
In order to solve the problems, at present, part of more advanced aeroengines adopt a hydraulic accumulator to supply oil in a reverse flight state, the oil for reverse flight is firstly stored in the hydraulic accumulator with a certain volume, and the hydraulic accumulator is extruded by high-pressure gas of a gas compressor to supply the oil during reverse flight. In this way, an engine with a low required amount of oil can be supplied, but in the case of a turbo engine, a large amount of oil is required as working fluid to be fed into the propeller control system, and if a hydraulic accumulator is used, the volume thereof needs to be several tens of liters to meet the requirements, resulting in a large volume and weight of the hydraulic accumulator. The gas communication in the lubricating oil tank adopts an independent valve to ensure the gas communication between the centrifugal ventilator and the lubricating oil tank during the back-off, but the device is arranged in the lubricating oil tank, has poor maintainability and is inconvenient to detach.
Disclosure of Invention
The invention aims to solve the technical problems of the prior art, namely providing a gravity switching unit and an aircraft engine reverse-flight oil supply ventilation device comprising the gravity switching unit, solving the problems of how to stably and continuously convey lubricating oil to an engine by a lubricating oil tank of an aircraft when the aircraft is in a reverse-flight attitude angle, ensuring continuous communication of air in the lubricating oil tank and a centrifugal ventilator and ensuring ventilation of the lubricating oil tank, and achieving the effects of small space occupation, small weight and convenience in maintenance.
In order to solve the technical problems, the invention adopts the following technical scheme:
the gravity switching unit comprises a shell, wherein the shell is a vertical hollow straight cylinder, a gravity switching cylinder body is vertically matched in the shell in a sliding manner, the gravity switching cylinder body is also a vertical hollow straight cylinder, and the outer wall of the gravity switching cylinder body corresponds to the inner wall of the shell; the wall of the shell is provided with a first through hole I and a second through hole I respectively, the wall of the gravity switching cylinder body is provided with a first through hole II and a second through hole II respectively, the first through hole I and the first through hole II are located on the same vertical plane, the distance from the first through hole I to the lower surface of the shell is equal to the distance from the first through hole II to the lower surface of the gravity switching cylinder body so as to enable the first through hole I to be communicated with the first through hole II when the gravity switching cylinder body is flush with the lower surface of the shell, the second through hole I and the second through hole II are located on the same vertical plane, and the distance from the second through hole I to the upper surface of the shell is equal to the distance from the second through hole II to the upper surface of the gravity switching cylinder body so as to enable the second through hole I to be communicated with the second through hole II when the gravity switching cylinder body is flush with the upper surface of the shell;
the height of the gravity switching cylinder is smaller than that of the shell, the height difference between the gravity switching cylinder and the shell is smaller than the minimum distance between the first through hole I and the lower surface of the shell and the minimum distance between the second through hole I and the upper surface of the shell, and the height difference between the gravity switching cylinder and the shell is larger than the sum of the radiuses of the first through hole I and the first through hole II and the sum of the radiuses of the second through hole I and the second through hole II so as to ensure that when any through hole on the gravity switching cylinder is communicated with the corresponding through hole on the shell, the other through hole is staggered and closed with the corresponding through hole on the shell;
the upper surface and the lower surface of the shell are respectively and hermetically connected with a sealing plate, and a pipe connecting hole is formed in any sealing plate.
The invention also relates to an aeroengine reverse-flying oil supply ventilation device, which comprises two gravity switching units and an oil tank, wherein the upper part and the lower part of the oil tank are respectively connected with the pipe holes of the gravity switching units one by one through pipes, the through holes in a communicating state on the shell of the gravity switching unit connected with the lower part of the oil tank and the through holes in a staggered closed state on the shell of the gravity switching unit connected with the upper part of the oil tank are connected with a booster pump through oil pipes, and the through holes in a staggered closed state on the shell of the gravity switching unit connected with the lower part of the oil tank and the through holes in a communicating state on the shell of the gravity switching unit connected with the upper part of the oil tank are connected with a centrifugal ventilator through air pipes.
The invention relates to an aeroengine reverse-flight oil supply ventilation device, which comprises two gravity switching units, wherein a conduit communicated with the upper part of an lubricating oil tank and a conduit communicated with the lower part of the lubricating oil tank are respectively connected with a pipe connecting hole of one gravity switching unit when in use, and under the action of gravity, in a vertical state, a shell in each gravity switching unit is correspondingly communicated with only one group of through holes of a gravity switching cylinder (namely, a first through hole I is communicated with a first through hole II or a second through hole I is communicated with a second through hole II), the current group of through holes of the gravity switching unit connected with the upper conduit of the lubricating oil tank are connected with a centrifugal ventilator, and the current group of through holes of the gravity switching unit connected with the lower conduit of the lubricating oil tank are connected with a booster pump, so that oil supply and ventilation of the lubricating oil tank in the vertical state are realized;
when the oil tank and the two gravity switching units are rotated 180 degrees and are inverted at 180 degrees in the other vertical state, the upper part and the lower part of the oil tank are switched in azimuth (because the oil is always output from the lower part due to gravity), the gravity switching cylinder of each gravity switching unit correspondingly switches through holes communicated with the shell under the action of gravity, at the moment, the shell in each gravity switching unit is communicated with the other group of through holes of the gravity switching cylinder, the current group of through holes of the gravity switching unit connected with the upper guide pipe of the oil tank are connected to the centrifugal ventilator, and the current group of through holes of the gravity switching unit connected with the lower guide pipe of the oil tank are connected to the booster pump; thus, the original oil-passing gravity switching unit passes through air in the vertical state, and the original gas-passing gravity switching unit passes through oil in the vertical state, so that oil supply and ventilation of the lubricating oil tank in the vertical state are realized.
Further optimizing the technical scheme, the two gravity switching units are inverted relatively.
Therefore, the two gravity switching units have the same structure, the manufacturing process is simplified, the first through holes I of the two gravity switching units are communicated through the external conduit and then correspondingly connected to the centrifugal ventilator or the booster pump during assembly, and the second through holes I of the two gravity switching units are communicated through the external conduit and then correspondingly connected to the booster pump or the centrifugal ventilator, so that the wrong assembly can be obviously avoided.
Further, one gravity switching unit is located right below the other gravity switching unit, and the two connecting pipe holes are respectively formed in the upper end of the upper gravity switching unit and the lower end of the lower gravity switching unit.
Therefore, the connecting pipe holes of the two gravity switching units are respectively arranged upwards and downwards in a back-to-back inverted mode during assembly, so that less space is occupied, and the connecting pipe is convenient to connect with the guide pipe of the lubricating oil tank.
Further, the two cases of the gravity switching units are of an integral structure and the two lower sealing plates are shared.
Thus, the two gravity switching units are manufactured into an integral structure, the integrity is better, and the intermediate connection or the auxiliary connection respectively fixed of the two gravity switching units is reduced.
Compared with the prior art, the invention has the following beneficial effects:
1. the reverse flight oil supply ventilation device of the aeroengine can realize stable and continuous lubricating oil delivery to the engine by the lubricating oil tank when in forward flight and reverse flight attitude angles, and simultaneously ensure that air in the lubricating oil tank is connected with a centrifugal ventilator, so that the normal operation of an engine lubricating oil system and an engine is ensured; the oil supply system and the engine can also normally operate when the aircraft is in various attitude angles converted between forward flight and reverse flight due to the fact that the oil supply and ventilation of the forward-flight and reverse-flight attitude angle lubricating oil tank are guaranteed.
2. Compared with the existing means, the gravity switching unit used by the reverse-flight oil supply and ventilation device of the aeroengine has the advantages of simple structure, small space occupation and small weight, is suitable for application on an aircraft, is independent of the lubricating oil tank, and is convenient to maintain.
Drawings
FIG. 1 is a schematic diagram of a gravity switching unit according to an embodiment;
fig. 2-3, partial enlarged views of part a;
FIG. 3 is a schematic structural view of an aircraft engine reverse-flight oil supply ventilation device according to an embodiment;
wherein, casing 1, first through-hole I11, second through-hole I12, go up shrouding 13, lower shrouding 14, take over hole 15, gravity switch barrel 2, first through-hole II 21, second through-hole II 22, filler neck 3, lubricating oil tank 4, air duct 5, centrifugal ventilator 6, lubricating oil duct 7, booster pump 8.
Detailed Description
The following describes the embodiments of the present invention in further detail with reference to the drawings.
Referring to fig. 1, in the gravity switching unit of the specific embodiment, a shell 1 is a vertical hollow straight cylinder, a gravity switching cylinder 2 is vertically slidably matched in the shell 1, and the gravity switching cylinder 2 is also a vertical hollow straight cylinder; the outer wall of the gravity switching cylinder 2 corresponds to the inner wall of the shell 1, and the height of the gravity switching cylinder 2 is smaller than that of the shell 1; the wall of the shell 1 is provided with a first through hole I11 and a second through hole I12 respectively, the wall of the gravity switching cylinder 2 is provided with a first through hole II 21 and a second through hole II 22 respectively, the first through hole I11 and the first through hole II 21 are located on the same vertical plane, the distance from the first through hole I11 to the lower surface of the shell 1 is equal to the distance from the first through hole II 21 to the lower surface of the gravity switching cylinder 2, so that the first through hole I11 and the first through hole II 21 are communicated when the gravity switching cylinder 2 is flush with the lower surface of the shell 1, the second through hole I12 and the second through hole II 22 are located on the same vertical plane, the distance from the second through hole I12 to the upper surface of the shell 1 is equal to the distance from the second through hole II 22 to the upper surface of the gravity switching cylinder 2, and the second through hole I12 and the second through hole II 22 are communicated when the gravity switching cylinder 2 is flush with the upper surface of the shell 1.
The above-mentioned limitation of the positions of all through holes is to use the central axis of the through hole as the reference for measurement or calibration. For the height difference between the gravity switching cylinder 2 and the housing 1, the height difference should be smaller than the minimum distance between the first through hole i 11 and the lower surface of the housing 1 and the minimum distance between the second through hole i 12 and the upper surface of the housing 1, and larger than the sum of the radii of the first through hole i 11 and the first through hole ii 21 and the sum of the radii of the second through hole i 12 and the second through hole ii 22, so as to ensure that the second through hole i 12 and the second through hole ii 22 are in a staggered closed state when the first through hole i 11 and the first through hole ii 21 are in a communicating state (when the gravity switching cylinder 2 is flush with the lower surface of the housing 1), or the first through hole i 11 and the first through hole ii 21 are in a staggered closed state when the second through hole i 12 and the second through hole ii 22 are in a communicating state (when the gravity switching cylinder 2 is flush with the upper surface of the housing 1); where the minimum distance is the distance from the edge of the through hole to the corresponding surface, rather than the central axis. Only by the requirement of the height difference, when the gravity switching cylinder 2 slides in the shell 1 to switch the communication relationship, one hole is ensured to be in a communication state, and the other hole is in a completely closed state, wherein the completely closed state means that two holes which are completely staggered with the corresponding holes on the shell and are staggered with each other are closed by the gravity switching cylinder 2 and the corresponding walls on the shell 1.
The upper surface and the lower surface of the shell 1 are respectively and hermetically connected with a horizontal upper sealing plate 13 and a horizontal lower sealing plate 14, a pipe connecting hole 15 is formed in the middle of the upper sealing plate 13, the pipe connecting hole 15 is communicated with the shell 1 and the inner cavity of the gravity switching cylinder 2, the upper sealing plate 13 and the lower sealing plate 14 enable the shell 1 to be of a sealed cavity structure, and meanwhile the upper sealing plate and the lower sealing plate are also used for limiting the stroke of the gravity switching cylinder 2 for sliding up and down.
Wherein, the outer wall of the shell 1 is provided with a connecting pipe nozzle 3 which is communicated with the corresponding positions of the connecting pipe hole 15, the first through hole I11 and the second through hole I12 so as to be convenient for externally connecting a conduit.
In practice, the horizontal cross-sectional shape of the housing 1 may be square, circular or other, and the present invention is not limited as long as it is a straight cylinder so that the gravity switching cylinder 2 can slide up and down along its inner wall. The outer wall of the gravity switching cylinder 2 corresponds to the inner wall of the shell 1, the airtight effect is achieved, when the lower surface of the gravity switching cylinder 2 is abutted to the lower sealing plate 14, the first through hole II 21 of the gravity switching cylinder is communicated with the first through hole I11 of the shell 1, the first through hole I11 of the shell 1 is communicated with the inner cavities of the shell 1 and the gravity switching cylinder 2, and the second through hole II 22 of the gravity switching cylinder 2 is naturally staggered with the second through hole I12 of the shell 1 because the height of the gravity switching cylinder 2 is smaller than the height of the shell 1 and the specific limit of the difference value of the heights of the two, and the outer wall of the gravity switching cylinder 2 corresponds to the inner wall of the shell 1, so that the second through hole I12 of the shell 1 is in an airtight state with the inner cavities of the shell 1 and the gravity switching cylinder 2. When the gravity switch cylinder 2 is inverted, the gravity switch cylinder 2 slides along the inner wall of the shell 1 due to gravity, when the upper surface of the gravity switch cylinder 2 is abutted against the upper sealing plate 13, the second through hole II 22 of the gravity switch cylinder is communicated with the second through hole I12 of the shell 1, the first through hole II 21 of the gravity switch cylinder is naturally staggered with the first through hole I11 of the shell 1, and the first through hole II 21 of the shell 1 is closed.
Of course, when the horizontal cross-sectional shape of the housing 1 is circular, an anti-rotation measure is required to prevent the gravity switching cylinder 2 from rotating relative to it within the housing 1.
Referring to fig. 2 and 3, the invention further provides an air supply and ventilation device for reverse flight of an aeroengine, which comprises two gravity switching units and an oil tank 4, wherein the two gravity switching units are in a relatively inverted position relationship, one gravity switching unit is positioned right below the other gravity switching unit, in the embodiment, a connecting pipe hole 15 of the gravity switching unit above is upward, a first through hole i 11 and a first through hole ii 21 are in a communicating state, a second through hole i 12 and a second through hole ii 22 are in a staggered and closed state, the connecting pipe hole 15 of the gravity switching unit below is downward due to the relatively inverted position relationship and the action of gravity, the second through hole i 12 and the second through hole ii 22 are in a communicating state, the first through hole i 11 and the first through hole ii 21 are in a staggered and closed state, a conduit communicated with the upper part of the oil tank 4 is connected with the connecting pipe hole 15 of the gravity switching unit above, and a conduit communicated with the lower part of the oil tank 4 is connected with the connecting pipe hole 15 of the gravity switching unit below; the first through holes I11 of the two gravity switching units are communicated through the air conduit 5 and then correspondingly connected to the centrifugal ventilator 6, the second through holes I12 of the two gravity switching units are communicated through the lubricating oil conduit 7 and then correspondingly connected to the booster pump 8, air in the lubricating oil tank 4 is communicated with the centrifugal ventilator 6 through the conduit at the upper part of the lubricating oil tank and the first through holes I11 of the upper gravity switching units, ventilation is guaranteed, lubricating oil in the lubricating oil tank 4 is connected with the booster pump 8 through the conduit at the lower part of the lubricating oil tank and the second through holes I12 of the lower gravity switching units, and lubricating oil is conveyed to a part to be lubricated through the booster pump 8.
When the oil tank 4 and the two gravity switching units are reversed at 180 degrees, the upper part and the lower part of the oil tank 4 are switched in azimuth, the oil is always output from the lower part of the oil tank 4 due to gravity, the gravity switching cylinders 2 of the two gravity switching units correspondingly switch through holes communicated with the shell 1 under the action of gravity, and the oil tank 4 is in the same structural form and working process as those of the oil tank when in forward flight, only because the oil and air from the oil tank 4 are exchanged by a guide pipe, the gravity switching unit passing through the oil when in forward flight is through the air, and the gravity switching unit passing through the oil when in forward flight is through the oil, thus ensuring the oil supply and ventilation of the oil tank 4 when in forward flight and in reverse flight attitude angle.
As can be seen from the connection manner of the embodiment and the use process described in the description, if the two gravity switching units are in a split structure, the connecting pipe holes 15 of the two gravity switching units can be formed in the upper sealing plate 13 or the lower sealing plate 14, and the process and effect of supplying oil and ventilating the oil tank 4 are not affected. In implementation, the two gravity switching units can be placed in an inverted relationship and/or an up-down relationship, or can be placed side by side in the same direction, so long as the gravity switching units are used vertically at the same time, and the use effect can be ensured if the corresponding catheters are connected correctly. In practice, if the two gravity switching units are in a vertically inverted position relationship as shown in fig. 2, the housing 1 of the two gravity switching units can be manufactured into an integral structure, so that the lower sealing plates 14 of the two gravity switching units can share one gravity switching unit, the integrity is better, the intermediate connection of the two gravity switching units can be reduced, and the auxiliary connection used for fixing the two gravity switching units on an airplane respectively can be reduced.
The invention is limited in that the shell 1 and the gravity switching cylinder 2 are hollow upright cylinder type, in order to ensure that the gravity switching cylinder 2 can vertically slide in the shell 1, and when the gravity switching cylinder is implemented, the outer wall of the shell 1 and/or the inner wall of the gravity switching cylinder 2 are replaced by a nonlinear structural form, and the gravity switching cylinder is also in the scope of the claims of the invention.
Finally, it is noted that the above embodiments are only for illustrating the technical solution of the present invention and not for limiting the same, and although the present invention has been described in detail with reference to the preferred embodiments, it should be understood by those skilled in the art that modifications and equivalents may be made thereto without departing from the spirit and scope of the technical solution of the present invention, which is intended to be covered by the scope of the claims of the present invention.
Claims (5)
1. Gravity switching unit, its characterized in that: the gravity switching device comprises a shell (1), wherein the shell (1) is of a vertical hollow straight cylinder type, a gravity switching cylinder body (2) capable of vertically sliding is matched in the shell (1), the gravity switching cylinder body (2) is also of a vertical hollow straight cylinder type, and the outer wall of the gravity switching cylinder body (2) corresponds to the inner wall of the shell (1); a first through hole I (11) and a second through hole I (12) are respectively formed in the wall of the shell (1), a first through hole II (21) and a second through hole II (22) are respectively formed in the wall of the gravity switching cylinder (2), the first through hole I (11) and the first through hole II (21) are located on the same vertical plane, the distance from the first through hole I (11) to the lower surface of the shell (1) is equal to the distance from the first through hole II (21) to the lower surface of the gravity switching cylinder (2) so as to enable the first through hole I (11) to be communicated with the first through hole II (21) when the gravity switching cylinder (2) is flush with the lower surface of the shell (1), the second through hole I (12) and the second through hole II (22) are located on the same vertical plane, and the distance from the second through hole I (12) to the upper surface of the shell (1) is equal to the distance from the second through hole II (22) to the upper surface of the gravity switching cylinder (2) so as to enable the second through hole I (12) to be flush with the second through hole II (22) when the gravity switching cylinder (2) is flush with the upper surface of the shell (1). The height of the gravity switching cylinder body (2) is smaller than that of the shell (1), the difference value of the height of the gravity switching cylinder body and the shell is smaller than the minimum distance between the first through hole I (11) and the lower surface of the shell (1) and the minimum distance between the second through hole I (12) and the upper surface of the shell (1), and the difference value of the height of the gravity switching cylinder body and the shell is larger than the sum of the radiuses of the first through hole I (11) and the first through hole II (21) and the sum of the radiuses of the second through hole I (12) and the second through hole II (22) so as to ensure that when any through hole on the gravity switching cylinder body (2) is communicated with the corresponding through hole on the shell (1), the other through hole is staggered and closed with the corresponding through hole on the shell (1); the upper surface and the lower surface of the shell (1) are respectively and hermetically connected with sealing plates, and a pipe connecting hole (15) is formed in any sealing plate;
the horizontal cross section shape of the shell (1) is circular, and the positions of the outer wall of the shell (1) corresponding to the connecting pipe hole (15), the first through hole I (11) and the second through hole I (12) are respectively provided with a connecting pipe nozzle (3) which is communicated with each other so as to be convenient for externally connecting a guide pipe.
2. The utility model provides an aeroengine flies back oil supply ventilation unit which characterized in that: the gravity switching unit comprises two gravity switching units as claimed in claim 1, and further comprises an oil tank (4), wherein the upper part and the lower part of the oil tank (4) are respectively connected with a connecting pipe hole (15) of the gravity switching unit one by one through a conduit, a through hole in a communicating state is formed in a shell (1) of the gravity switching unit connected with the lower part of the oil tank (4), a through hole in a staggered closed state is formed in the shell (1) of the gravity switching unit connected with the upper part of the oil tank (4), the through hole in a staggered closed state is connected with a booster pump (8) through an oil conduit (7), and the through hole in a communicating state is formed in the shell (1) of the gravity switching unit connected with the upper part of the oil tank (4).
3. The aircraft engine reverse-flight oil supply ventilation device according to claim 2, wherein: the two gravity switching units are inverted relatively.
4. A reverse flight fuel supply ventilation device for an aircraft engine according to claim 3, wherein: one gravity switching unit is positioned right below the other gravity switching unit, and the two pipe holes (15) are respectively formed at the upper end of the upper gravity switching unit and the lower end of the lower gravity switching unit.
5. The aircraft engine reverse-flight oil supply ventilation device according to claim 4, wherein: the shells (1) of the two gravity switching units are of an integrated structure, and the adjacent sealing plates share the same plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811289385.2A CN109252963B (en) | 2018-10-31 | 2018-10-31 | Gravity switching unit and aeroengine reverse-flying oil supply and ventilation device comprising same |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811289385.2A CN109252963B (en) | 2018-10-31 | 2018-10-31 | Gravity switching unit and aeroengine reverse-flying oil supply and ventilation device comprising same |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109252963A CN109252963A (en) | 2019-01-22 |
| CN109252963B true CN109252963B (en) | 2023-11-07 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201811289385.2A Active CN109252963B (en) | 2018-10-31 | 2018-10-31 | Gravity switching unit and aeroengine reverse-flying oil supply and ventilation device comprising same |
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| CN112625840B (en) * | 2020-12-30 | 2023-08-25 | 沈阳红梅食品有限公司 | Cooking wine fermenting installation with adjustable temperature |
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| CN2897456Y (en) * | 2006-01-17 | 2007-05-09 | 上海子锦电子科技有限公司 | Liquid-storage tank |
| DE102006057202A1 (en) * | 2006-12-05 | 2008-06-12 | Mtu Aero Engines Gmbh | Lubricating oil supply system for gas turbines of aircraft engine, has valve device which opens connection line upstream to main oil pump by ventilation line of oil tank to oil line |
| CN203783680U (en) * | 2014-04-18 | 2014-08-20 | 江西洪都航空工业集团有限责任公司 | Biaxial rotating type oil absorption ventilation device for aerobatics |
| CN104389684A (en) * | 2014-12-04 | 2015-03-04 | 江西洪都航空工业集团有限责任公司 | Rotatably flexible oil extractor |
| CN108413072A (en) * | 2018-05-23 | 2018-08-17 | 徐楠 | Gravity switching valve |
| CN208918704U (en) * | 2018-10-31 | 2019-05-31 | 重庆天骄航空动力有限公司 | Gravity switch unit and aero-engine inverted flight fuel feeding air-breather containing the unit |
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