CN110949676A - Liquid level jet flow sensor of aircraft fuel system - Google Patents
Liquid level jet flow sensor of aircraft fuel system Download PDFInfo
- Publication number
- CN110949676A CN110949676A CN201911312455.6A CN201911312455A CN110949676A CN 110949676 A CN110949676 A CN 110949676A CN 201911312455 A CN201911312455 A CN 201911312455A CN 110949676 A CN110949676 A CN 110949676A
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- Prior art keywords
- pipe joint
- hole
- mounting hole
- nozzle
- fuel system
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- 239000000446 fuel Substances 0.000 title claims abstract description 59
- 239000007788 liquid Substances 0.000 title claims abstract description 23
- 238000009434 installation Methods 0.000 claims description 16
- 238000007789 sealing Methods 0.000 claims description 15
- 239000002828 fuel tank Substances 0.000 abstract description 6
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000003139 buffering effect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D37/00—Arrangements in connection with fuel supply for power plant
- B64D37/34—Conditioning fuel, e.g. heating
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Measurement Of Levels Of Liquids Or Fluent Solid Materials (AREA)
Abstract
The application belongs to aircraft fuel system field, in particular to aircraft fuel system liquid level fluidic sensor includes: the device comprises a shell, a first fixing device and a second fixing device, wherein one end of the shell is provided with a first mounting hole, the other end of the shell is provided with a second mounting hole and a third mounting hole, and the middle of the shell is provided with a fourth mounting hole; the three pipe joints are respectively arranged in the first mounting hole, the third mounting hole and the fourth mounting hole; the screw plug is arranged in the second mounting hole; the first nozzle is arranged in the first mounting hole and connected with the first pipe joint; the second nozzle is arranged in the second mounting hole and connected with the screw plug; and the third nozzle is arranged in the fourth mounting hole and is connected with the third pipe joint. The liquid level jet flow sensor of the aircraft fuel system can output reliable flow and pressure, and outputs stable pressure for a fuel control pipeline according to the position change of the liquid level of the fuel tank, so that the correctness of the fuel supply and delivery logic sequence is guaranteed.
Description
Technical Field
The application belongs to the field of aircraft fuel systems, and particularly relates to a liquid level jet flow sensor of an aircraft fuel system.
Background
When the fuel of each fuel tank is transferred in an airplane fuel system, the fuel level is generally adopted for control, namely when the liquid level of one fuel tank reaches a certain position, the fuel transfer of the other fuel tank is started.
At present, the liquid level is controlled usually in an electric control mode, the electric control mode adopts a liquid level annunciator, when the liquid level reaches a set position, a magnetic floater is switched on to send an electric control signal, the electric control signal is used for controlling the opening of fuel accessories such as an electromagnetic valve and the like, and the situation that the signal cannot be sent due to the clamping stagnation of the magnetic floater or an unstable signal is sent due to the influence of the liquid level often occurs by adopting the mode, so that the oil transportation process is not controlled or is controlled disorderly.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
The object of the present application is to provide an aircraft fuel system level jet sensor to solve at least one problem of the prior art.
The technical scheme of the application is as follows:
an aircraft fuel system level jet sensor comprising:
the device comprises a shell, a first fixing hole and a second fixing hole, wherein the shell is arched, one end of the shell is provided with the first fixing hole, the other end of the shell is provided with the second fixing hole and the third fixing hole, through holes which are communicated with each other are formed between the second fixing hole and the third fixing hole, and the middle of the shell is provided with a fourth fixing hole, wherein the axis of the second fixing hole is superposed with the axis of the first fixing hole, and the axis of the fourth fixing hole is vertically crossed with the axis of the first fixing hole;
a pipe joint including a first pipe joint installed in the first mounting hole, a second pipe joint installed in the third mounting hole, and a third pipe joint installed in the fourth mounting hole;
a plug screw disposed in the second mounting hole;
and the nozzle comprises a first nozzle, a second nozzle and a third nozzle, the first nozzle is installed in the first installation hole and connected with the first pipe joint, the second nozzle is installed in the second installation hole and connected with the screw plug, and the third nozzle is installed in the fourth installation hole and connected with the third pipe joint.
Optionally, the first pipe joint is a screwed-in straight-through pipe joint, a through hole is formed in the center of the first pipe joint, one end of the first pipe joint is installed in the first installation hole of the shell through threaded connection, the other end of the first pipe joint is connected with the control pipeline through threaded connection, and a first sealing ring is arranged at the joint of the first pipe joint and the shell.
Optionally, a gasket is disposed between the first nozzle and the first pipe joint.
Optionally, the first nozzle is cylindrical, a through hole is formed in the center of the first nozzle, one side of the through hole, which is connected with the first pipe joint, is a tapered hole, the other side of the through hole is a straight hole, and the tapered hole is in a contracted shape from one side of the first pipe joint to one side of the straight hole.
Optionally, the cross section of the second nozzle is conical, a stepped through hole is formed in the center of the second nozzle, the radius of one side of the through hole, which is connected with the plug screw, is larger than that of the other side of the through hole, and the second nozzle is fixed in the second mounting hole through a conical end set screw.
Optionally, a stepped through hole is formed in the center of the second pipe joint, one end of the second pipe joint is installed in the third installation hole of the housing through threaded connection, the other end of the second pipe joint is connected with the control pipeline through threaded connection, and a second sealing ring is arranged at the joint of the second pipe joint and the housing.
Optionally, a through hole is formed in the center of the third pipe joint, one end of the third pipe joint is installed in the fourth installation hole of the housing through threaded connection, and the other end of the third pipe joint is in threaded connection with the control pipeline.
Optionally, a third sealing ring is arranged at a joint of the third pipe joint and the third nozzle, and a fourth sealing ring is arranged at a joint of the third pipe joint and the housing.
Optionally, the cross section of the third nozzle is stepped, a through hole is formed in the center of the third nozzle, the through hole is tapered, and the third nozzle is mounted in the fourth mounting hole through a nut.
Optionally, the fuse further comprises a first fuse, a second fuse and a third fuse, the first fuse is disposed between the first pipe joint and the third pipe joint, the second fuse is disposed between the screw plug and the second pipe joint, and the third fuse is disposed between the nut and the housing.
The invention has at least the following beneficial technical effects:
the liquid level jet flow sensor of the aircraft fuel system can output reliable flow and pressure, and outputs stable pressure for a fuel control pipeline according to the position change of the liquid level of the fuel tank, so that the correctness of the fuel supply and delivery logic sequence is guaranteed.
Drawings
FIG. 1 is a schematic overall view of an aircraft fuel system level jet sensor according to one embodiment of the present application;
FIG. 2 is a schematic illustration of a housing of an aircraft fuel system level jet sensor according to an embodiment of the present application;
FIG. 3 is a schematic view of a second pipe connection of an aircraft fuel system level jet sensor according to an embodiment of the present application;
FIG. 4 is a schematic view of a third adapter of an aircraft fuel system level jet sensor according to an embodiment of the present application;
FIG. 5 is a schematic view of a first nozzle of an aircraft fuel system level jet sensor according to one embodiment of the present application;
FIG. 6 is a schematic view of a second nozzle of an aircraft fuel system level jet sensor according to an embodiment of the present application;
FIG. 7 is a schematic view of a third nozzle of an aircraft fuel system level jet sensor according to an embodiment of the present application;
FIG. 8 is a schematic view of a nut of an aircraft fuel system level jet sensor according to an embodiment of the present application;
FIG. 9 is a gasket schematic of an aircraft fuel system level jet sensor according to one embodiment of the present application;
FIG. 10 is a plug screw schematic of an aircraft fuel system level jet sensor according to one embodiment of the present application;
FIG. 11 is a screw schematic view of an aircraft fuel system level jet sensor according to one embodiment of the present application;
FIG. 12 is a schematic view of a first pipe joint of an aircraft fuel system level jet sensor according to an embodiment of the present application;
FIG. 13 is a schematic view of a seal ring of an aircraft fuel system level jet sensor according to an embodiment of the present application.
Wherein:
1-a shell; 2-a second pipe joint; 3-a third pipe joint; 4-a first nozzle; 5-a second nozzle; 6-a third nozzle; 7-a nut; 8-a gasket; 9-a plug screw; 10-a screw; 11-a first pipe joint; 12-a fuse; 13-a second sealing ring; 14-a third sealing ring; 15-fourth seal ring.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. 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 application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.
In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.
The aircraft fuel system level jet sensor of the present application is described in further detail below with reference to fig. 1-13.
The application provides an aircraft fuel system liquid level fluidic sensor includes: a housing 1, a pipe joint, a screw plug 9 and a nozzle.
Specifically, as shown in fig. 1 and 2, the casing 1 is in an arc shape, a first mounting hole is formed in one end of the casing 1, a second mounting hole and a third mounting hole are formed in the other end of the casing 1, through holes communicated with each other are formed between the second mounting hole and the third mounting hole, and a fourth mounting hole is formed in the middle of the casing 1, wherein the axis of the second mounting hole coincides with the axis of the first mounting hole, and the axis of the fourth mounting hole perpendicularly intersects with the axis of the first mounting hole.
The pipe joints comprise a first pipe joint 11, a second pipe joint 2 and a third pipe joint 3; the first pipe joint 11 is mounted in the first mounting hole by a mounting nut, the second pipe joint 2 is mounted in the third mounting hole by a mounting nut, and the third pipe joint 3 is mounted in the fourth mounting hole by a mounting nut.
The screw plug 9 is arranged in the second mounting hole and is structured as shown in fig. 10, and is used for sealing the fuel flowing out of the inlet hole and simultaneously buffering the fuel entering into the inlet hole; further, the nozzles include a first nozzle 4 (as a jet nozzle), a second nozzle 5 (as a receiving nozzle), and a third nozzle 6 (as a cutoff nozzle); the first nozzle 4 is installed in the first installation hole and connected with the first pipe joint 11; and a gasket 8 (see fig. 9) is provided between the first nozzle 4 and the first pipe joint 11 for adjusting the distance between the nozzle and the pipe joint; the second nozzle 5 is arranged in the second mounting hole and is connected with the screw plug 9; the third nozzle 6 is installed in the fourth installation hole and connected to the third pipe joint 3.
Further, as shown in fig. 12, the first pipe joint 11 of the present application is a screw-in straight-through pipe joint, the center of which is provided with a through hole, one end of which is installed in the first installation hole of the housing 1 through a threaded connection, and the joint is provided with a first sealing ring 16, and the other end of which is connected with the control pipeline through a threaded connection.
Further, as shown in fig. 5, the first nozzle 4 of the present application is cylindrical, and a through hole is formed in the center, wherein the through hole is a tapered hole on one side connected to the first pipe joint 11, and the through hole is a straight hole on the other side, and the tapered hole is formed by contracting from one side of the first pipe joint 11 to one side of the straight hole.
Further, as shown in fig. 6, the cross section of the second nozzle 5 of the present application is tapered, a stepped through hole is formed in the center, the radius of one side of the through hole connected to the plug screw 9 is larger than the radius of the other side of the through hole, and the second nozzle 5 is fixed in the second mounting hole by a tapered end set screw 10.
Further, as shown in fig. 3, a stepped through hole is formed in the center of the second pipe joint 2, one end of the second pipe joint 2 is installed in the third installation hole of the housing 1 through threaded connection, the other end of the second pipe joint is connected with the control pipeline through threaded connection, and a second sealing ring 13 is arranged at the joint of the second pipe joint 2 and the housing 1.
Further, as shown in fig. 4, a through hole is opened at the center of the third pipe joint 3, one end of the third pipe joint 3 is installed in the fourth installation hole of the housing 1 through a threaded connection, and the other end is connected with a control pipeline through a threaded connection. In addition, a third sealing ring 14 is arranged at the joint of the third pipe joint 3 and the third nozzle 6, and a fourth sealing ring 15 is arranged at the joint of the third pipe joint 3 and the shell 1.
Further, as shown in fig. 4, a cross section of the third nozzle 6 of the present application is stepped, a through hole is formed in the center of the third nozzle, the through hole is tapered, and the third nozzle 6 is mounted in the fourth mounting hole through a nut 7 (see fig. 8).
Further, the aircraft fuel system liquid level jet flow sensor of the application can further comprise a fuse 12; the fuse 12 includes a first fuse, a second fuse, and a third fuse, the first fuse is disposed between the mounting nut of the first pipe joint 11 and the mounting nut of the third pipe joint 3, the second fuse is disposed between the screw plug 9 and the second pipe joint 2, and the third fuse is disposed between the nut 7 and the housing 1.
The liquid level jet flow sensor of the aircraft fuel system has the following use principle:
when the level of fuel in the tank submerges the level jet sensor, the pressure of the fuel supplied along the conduit to the level jet sensor jet nozzle (i.e. the first nozzle 4) cannot pass to the receiving nozzle (i.e. the second nozzle 5). When the fuel level in the fuel tank is lower than the level jet flow sensor, the fuel pressure supplied to the jet flow nozzle of the level jet flow sensor along the guide pipe is transmitted to the receiving nozzle, and the pressure is established with the control cavity of the fuel control valve at the rear part. After the oil tank sends out the oil-out signal, the fuel is controlled to be sprayed out from the cut-off nozzle of the liquid level jet flow sensor, the fuel jet flow which is led to the receiving nozzle from the jet flow nozzle is cut off, and the pressure of the fuel is cut off and controlled.
To sum up, the aircraft fuel system liquid level fluidic sensor of this application can export flow and pressure reliably, according to the position change of oil tank liquid level, for fuel control pipeline output stable pressure, and then guarantee the exactness of fuel feeding and delivery logic order.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (10)
1. An aircraft fuel system level fluidic sensor, comprising:
the mounting structure comprises an arched shell (1), wherein one end of the arched shell is provided with a first mounting hole, the other end of the arched shell is provided with a second mounting hole and a third mounting hole, through holes which are communicated with each other are formed between the second mounting hole and the third mounting hole, and the middle of the shell (1) is provided with a fourth mounting hole, wherein the axis of the second mounting hole is superposed with the axis of the first mounting hole, and the axis of the fourth mounting hole is perpendicularly intersected with the axis of the first mounting hole;
a first pipe joint (11), a second pipe joint (2), and a third pipe joint (3), the first pipe joint (11) being mounted in the first mounting hole, the second pipe joint (2) being mounted in the third mounting hole, the third pipe joint (3) being mounted in the fourth mounting hole;
a plug screw (9) disposed in the second mounting hole;
a first nozzle (4), a second nozzle (5) and a third nozzle (6), the first nozzle (4) is installed in the first installation hole and connected with the first pipe joint (11), the second nozzle (5) is installed in the second installation hole and connected with the screw plug (9), and the third nozzle (6) is installed in the fourth installation hole and connected with the third pipe joint (3).
2. Aircraft fuel system level jet sensor according to claim 1, characterised in that the first pipe connection (11) is a screw-in through pipe connection, which is mounted in a first mounting hole of the housing (1) by means of a screw connection at one end and is provided with a first sealing ring (16) at the connection and is screwed to a control line at the other end.
3. Aircraft fuel system level jet sensor according to claim 2, characterised in that a gasket (8) is provided between the first nozzle (4) and the first pipe connection (11).
4. The aircraft fuel system level jet sensor according to claim 3, characterized in that the first nozzle (4) is cylindrical and has a through hole in the center, the through hole is connected with the first pipe joint (11) and has a tapered hole on one side and a straight hole on the other side, and the tapered hole is contracted from one side of the first pipe joint (11) to one side of the straight hole.
5. The aircraft fuel system liquid level jet sensor as claimed in claim 1, wherein the second nozzle (5) is conical in cross section, a stepped through hole is formed in the center, the radius of one side of the through hole, which is connected with the screw plug (9), is larger than that of the other side of the through hole, and the second nozzle (5) is fixed in the second mounting hole through a conical end fastening screw (10).
6. The aircraft fuel system liquid level jet sensor according to claim 1, characterized in that a step-shaped through hole is formed in the center of the second pipe joint (2), one end of the second pipe joint (2) is installed in a third installation hole of the shell (1) through threaded connection, the other end of the second pipe joint is connected with a control pipeline through threaded connection, and a second sealing ring (13) is arranged at the joint of the second pipe joint (2) and the shell (1).
7. The aircraft fuel system liquid level jet sensor as claimed in claim 1, characterized in that a through hole is formed in the center of the third pipe joint (3), one end of the third pipe joint (3) is installed in a fourth installation hole of the shell (1) through threaded connection, and the other end of the third pipe joint is connected with a control pipeline through threaded connection.
8. Aircraft fuel system level jet sensor according to claim 7, characterized in that the junction of the third pipe connection (3) with the third nozzle (6) is provided with a third sealing ring (14) and the junction of the third pipe connection (3) with the housing (1) is provided with a fourth sealing ring (15).
9. The aircraft fuel system liquid level jet sensor as claimed in claim 8, wherein the third nozzle (6) is stepped in cross section and has a through hole in the center, the through hole is tapered, and the third nozzle (6) is mounted in the fourth mounting hole through a nut (7).
10. Aircraft fuel system level jet sensor according to claim 9, characterized by further comprising a fuse (12), the fuse (12) comprising a first fuse, a second fuse and a third fuse, the first fuse being arranged between the first pipe joint (11) and the third pipe joint (3), the second fuse being arranged between the screw plug (9) and the second pipe joint (2), the third fuse being arranged between the nut (7) and the housing (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911312455.6A CN110949676A (en) | 2019-12-18 | 2019-12-18 | Liquid level jet flow sensor of aircraft fuel system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911312455.6A CN110949676A (en) | 2019-12-18 | 2019-12-18 | Liquid level jet flow sensor of aircraft fuel system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110949676A true CN110949676A (en) | 2020-04-03 |
Family
ID=69982590
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911312455.6A Pending CN110949676A (en) | 2019-12-18 | 2019-12-18 | Liquid level jet flow sensor of aircraft fuel system |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110949676A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2008010037A2 (en) * | 2006-07-12 | 2008-01-24 | Toyota Jidosha Kabushiki Kaisha | Fuel injection device |
| CN203116799U (en) * | 2012-12-27 | 2013-08-07 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Controllable fluidic sensor |
| CN103292834A (en) * | 2013-03-04 | 2013-09-11 | 中国人民解放军海军航空工程学院青岛校区 | Aircraft fuel liquid level fluidic sensor test system |
| CN206246266U (en) * | 2016-12-05 | 2017-06-13 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of jet oil transfer pump |
| CN108426616A (en) * | 2018-02-01 | 2018-08-21 | 新奥泛能网络科技股份有限公司 | Fluidic sensor |
-
2019
- 2019-12-18 CN CN201911312455.6A patent/CN110949676A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2008010037A2 (en) * | 2006-07-12 | 2008-01-24 | Toyota Jidosha Kabushiki Kaisha | Fuel injection device |
| CN203116799U (en) * | 2012-12-27 | 2013-08-07 | 中国航空工业集团公司金城南京机电液压工程研究中心 | Controllable fluidic sensor |
| CN103292834A (en) * | 2013-03-04 | 2013-09-11 | 中国人民解放军海军航空工程学院青岛校区 | Aircraft fuel liquid level fluidic sensor test system |
| CN206246266U (en) * | 2016-12-05 | 2017-06-13 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of jet oil transfer pump |
| CN108426616A (en) * | 2018-02-01 | 2018-08-21 | 新奥泛能网络科技股份有限公司 | Fluidic sensor |
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Application publication date: 20200403 |
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