CN113236544A - Function detection device for fuel booster pump of airplane - Google Patents
Function detection device for fuel booster pump of airplane Download PDFInfo
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- CN113236544A CN113236544A CN202110447623.3A CN202110447623A CN113236544A CN 113236544 A CN113236544 A CN 113236544A CN 202110447623 A CN202110447623 A CN 202110447623A CN 113236544 A CN113236544 A CN 113236544A
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- oil
- booster pump
- fuel booster
- detection device
- conveying pipe
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04B—POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS
- F04B51/00—Testing machines, pumps, or pumping installations
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Measuring Volume Flow (AREA)
Abstract
The invention discloses a function detection device for an aircraft fuel booster pump, which comprises a fuel booster pump main body and static elimination protection plates, wherein the static elimination protection plates are arranged on two sides of the fuel booster pump main body, a base is fixed at the bottom end of the fuel booster pump main body, one end of the fuel booster pump main body is connected with an oil pumping valve, the other end of the oil pumping valve is connected with an oil conveying pipe, an oil return filter is arranged inside the oil conveying pipe, a temperature sensor is arranged on the right side of the oil return filter, a liquid level sensor is arranged on the right side of the temperature sensor, an electric control throttle valve is arranged on the right side of the liquid level sensor, a turbine flowmeter is connected on the right side of the electric control throttle valve, and a detection device box is connected above the turbine flowmeter. The function detection device for the aircraft fuel booster pump is provided with the oil return filter for filtering pollutants generated or invaded at the tail end of an oil circuit system, and the pollutants are prevented from causing pollution to an oil tank or the booster pump.
Description
Technical Field
The invention relates to the technical field of booster pump detection devices, in particular to a function detection device for an aircraft fuel booster pump.
Background
The test equipment for detecting various functions of the aircraft fuel booster pump judges whether the performance of the pump is qualified or not by testing whether various performance parameters of the pump meet the design specified range or not, and whether the performance of the pump meets the airworthiness safety standard or not for installation and use.
The airplane fuel booster pump function detection device in the market is generally installed at an oil outlet of a pump body of a fuel booster pump or an oil inlet of an oil tank in use, a fuel oil channel is easily blocked due to poor maintenance, oil transportation is not smooth, detection contents of part of detection devices are simple and are only used for testing, detection data cannot be transmitted to a control platform in real time, information reference cannot be provided for a detector or a pilot, and therefore the airplane fuel booster pump function detection device is provided.
Disclosure of Invention
The invention aims to provide a function detection device for an aircraft fuel booster pump, which aims to solve the problems that the function detection device for the aircraft fuel booster pump in the market, which is provided by the background technology, is generally arranged at an oil outlet of a pump body of the fuel booster pump or an oil inlet of an oil tank in use, the maintenance is not good, a fuel oil passage is easily blocked, the oil transportation is not smooth, the detection content of part of detection devices is simple, only test use is carried out, the detection data cannot be transmitted to an operation and control platform in real time, and information reference cannot be provided for a detector or a pilot.
In order to achieve the purpose, the invention provides the following technical scheme: the utility model provides an aircraft fuel booster pump function detection device, includes fuel booster pump main part and static-removing protection plate, the static-removing protection plate is installed to the both sides of fuel booster pump main part, and the bottom mounting of fuel booster pump main part has the base, the one end of fuel booster pump main part is connected with the pump fuel valve, and the other end of pump fuel valve is connected with defeated oil pipe, defeated oil pipe's inside is provided with the oil return and strains, and the right side that the oil return was strained is provided with temperature sensor, temperature sensor's right side is provided with level sensor, and level sensor's right side is provided with automatically controlled choke valve, the right side of automatically controlled choke valve is connected with turbine flowmeter, and turbine flowmeter's top is connected with the detection device box, the protection mask is installed on the top of detection device box, and the one end of detection device box is connected with the cable.
Preferably, the oil return filter penetrates through the inside of the oil conveying pipe, the end face structure of the oil return filter is a hollowed-out net structure, and a communication structure is formed between the oil conveying pipe and the oil return filter.
Preferably, the temperature sensor runs through the outer surface of the oil conveying pipe, the liquid level sensor runs through the inside of the oil conveying pipe, and the ground of the liquid level sensor is tightly attached to the inner bottom surface of the oil conveying pipe.
Preferably, constitute the connectivity structure between defeated oil pipe and the automatically controlled choke valve, and defeated oil pipe and automatically controlled choke valve are connected for dismantling.
Preferably, constitute the intercommunication structure between defeated oil pipe and the turbine flowmeter, and defeated oil pipe and turbine flowmeter mutually support.
Preferably, the protection mask penetrates through the upper surface of the detection device box, the detection device box is detachably connected with the protection mask, and a communication structure is formed between the detection device box and the cable.
Preferably, the detection device box is internally provided with a single chip microcomputer, and the single chip microcomputer is matched with the turbine flowmeter.
Compared with the prior art, the invention has the beneficial effects that: the function detection device for the aircraft fuel booster pump is provided with the oil return filter for filtering pollutants generated or invaded at the tail end of an oil circuit system, and the pollutants are prevented from causing pollution to an oil tank or the booster pump.
The temperature sensor and the liquid level sensor are used for monitoring the temperature and the liquid level height of fuel oil in the oil delivery pipe, so that the oil pressure can be conveniently adjusted according to the working pressure of the oil delivery pipe, and the oil delivery pipe is prevented from being damaged due to overhigh working strength; the arranged electric control throttle valve is used for controlling the flow rate of fuel in the fuel delivery pipe and adjusting the flow rate of the fuel according to different experimental requirements or flight conditions; the turbine flowmeter is used for monitoring the actual flow rate of the fuel in the oil delivery pipe, and workers can conveniently check whether the actual flow rate of the fuel is matched with the opening and closing degree of the oil pumping valve and the electric control throttle valve.
The protection mask is used for protecting electronic components in the detection device box from collision damage, so that scattering of internal components caused by collision is avoided, and the detachable structure is convenient for later maintenance and overhaul of the interior of the detection device box; the single chip microcomputer is used for collecting, analyzing and sorting data monitored by the sensors, and transmitting the data to the workbench through a cable, so that a worker can conveniently confirm whether the system works normally.
Drawings
FIG. 1 is a schematic perspective view of the present invention;
FIG. 2 is a schematic perspective view of the detecting device of the present invention;
FIG. 3 is a schematic cross-sectional view of an oil return filter according to the present invention;
FIG. 4 is a schematic sectional view of a cartridge of the detecting unit of the present invention.
In the figure: 1. a fuel booster pump main body; 2. a static-removing protection plate; 3. a base; 4. an oil pumping valve; 5. an oil delivery pipe; 6. a detection device cartridge; 7. protecting the mask; 8. a cable; 9. oil return filtration; 10. a temperature sensor; 11. a liquid level sensor; 12. an electrically controlled throttle valve; 13. a turbine flow meter; 14. and a single chip microcomputer.
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. 1-4, the present invention provides a technical solution: a function detection device for an aircraft fuel booster pump comprises a fuel booster pump main body 1 and static elimination protection plates 2, wherein the static elimination protection plates 2 are arranged on two sides of the fuel booster pump main body 1, and a base 3 is fixed at the bottom end of the fuel booster pump main body 1, one end of the fuel booster pump main body 1 is connected with an oil pumping valve 4, and the other end of the oil pumping valve 4 is connected with an oil delivery pipe 5, an oil return filter 9 is arranged inside the oil delivery pipe 5, and the right side of the oil return filter 9 is provided with a temperature sensor 10, the right side of the temperature sensor 10 is provided with a liquid level sensor 11, and the right side of the liquid level sensor 11 is provided with an electric control throttle valve 12, the right side of the electric control throttle valve 12 is connected with a turbine flowmeter 13, and a detection device box 6 is connected above the turbine flowmeter 13, a protective mask 7 is mounted on the top end of the detection device box 6, and a cable 8 is connected to one end of the detection device box 6.
In the invention: the oil return filter 9 penetrates through the oil conveying pipe 5, the end face structure of the oil return filter 9 is a hollow net structure, and a communication structure is formed between the oil conveying pipe 5 and the oil return filter 9; the oil return filter 9 is used for filtering pollutants generated or invaded at the tail end of the oil circuit system, and the oil tank or the booster pump is prevented from being polluted by the pollutants.
In the invention: the temperature sensor 10 penetrates through the outer surface of the oil conveying pipe 5, the liquid level sensor 11 penetrates through the inner part of the oil conveying pipe 5, and the ground of the liquid level sensor 11 is tightly attached to the inner bottom surface of the oil conveying pipe 5; the temperature sensor 10 and the level sensor 11 that set up are arranged in the temperature and the fuel liquid level height of monitoring fuel in defeated oil pipe 5, are convenient for adjust the oil pressure according to defeated oil pipe 5's operating pressure, avoid too high damage defeated oil pipe 5 of working strength.
In the invention: a communicating structure is formed between the oil delivery pipe 5 and the electric control throttle valve 12, and the oil delivery pipe 5 and the electric control throttle valve 12 are detachably connected; the arranged electric control throttle valve 12 is used for controlling the flow rate of the fuel in the oil delivery pipe 5 and adjusting the flow rate of the fuel according to different experimental requirements or flight conditions.
In the invention: a communicating structure is formed between the oil pipeline 5 and the turbine flowmeter 13, and the oil pipeline 5 and the turbine flowmeter 13 are matched with each other; the turbine flowmeter 13 is used for monitoring the actual flow rate of the fuel in the oil delivery pipe 5, and workers can conveniently check whether the actual flow rate of the fuel is matched with the opening and closing degrees of the oil pumping valve 4 and the electric control throttle valve 12.
In the invention: the protective mask 7 penetrates through the upper surface of the detection device box 6, the detection device box 6 is detachably connected with the protective mask 7, and a communication structure is formed between the detection device box 6 and the cable 8; the protection mask 7 that sets up is used for protecting the electronic components in the detection device box 6 not receive the collision damage, avoids leading to inside components and parts to scatter because of the collision, and detachable construction is convenient for the later stage and is safeguarded and overhauld the inside of detection device box 6.
In the invention: the single chip microcomputer 14 is installed in the detection device box 6, and the single chip microcomputer 14 is matched with the turbine flowmeter 13; the single chip microcomputer 14 is used for collecting, analyzing and sorting data monitored by the sensors, and transmitting the data to the workbench through the cable 8, so that a worker can conveniently confirm whether the system works normally.
The working principle is as follows: for the function detection device of the airplane fuel booster pump, firstly, under a test environment, a fuel booster pump main body 1 is installed on a fixed workbench through a base 3, airplane fuel is boosted through the fuel booster pump main body 1 and pumped into an oil delivery pipe 5 through an oil pumping valve 4, the oil pumping valve 4 can control oil discharge of the booster pump, a shell of the fuel booster pump main body 1 is static-free after being static-removed through a static-removing protection plate 2, the potential safety hazard of static fire is eliminated, then the pumped fuel passes through an oil return filter 9 in the oil delivery pipe 5 and is in contact with a temperature sensor 10 (model: platinum electric PT100) and a liquid level sensor 11 (model: jointly measured SIN-P260), the temperature sensor 10 is used for measuring temperature data of the fuel, the liquid level sensor 11 is used for detecting the liquid level height of the fuel in a pipeline, the fuel continuously flows through an electric control throttle valve 12 (model: DVG), and the electric control throttle valve 12 is used for controlling, and finally, when the flow passes through a turbine flowmeter 13 (model: Huahai DN25), the flow of the final flow is detected, all data detected finally are transmitted to a single chip microcomputer 14 arranged in a detection device box 6 through electric signals, the single chip microcomputer 14 is transmitted to a workbench through a cable 8 after being processed and analyzed, and is used for reference of workers or pilots, a protection mask 7 arranged on the detection device box 6 is used for protecting electric elements in the detection device box 6, and the design of easy disassembly is convenient for later-stage overhaul and maintenance.
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 (7)
1. The utility model provides an aircraft fuel booster pump function detection device, includes fuel booster pump main part (1) and static-removing protection board (2), its characterized in that: the static-removing protection plate (2) is installed on two sides of the fuel booster pump main body (1), the base (3) is fixed at the bottom end of the fuel booster pump main body (1), one end of the fuel booster pump main body (1) is connected with the oil pumping valve (4), the other end of the oil pumping valve (4) is connected with the oil conveying pipe (5), the oil returning and filtering pipe (9) is arranged inside the oil conveying pipe (5), the right side of the oil returning and filtering pipe (9) is provided with the temperature sensor (10), the right side of the temperature sensor (10) is provided with the liquid level sensor (11), the right side of the liquid level sensor (11) is provided with the electric control throttle valve (12), the right side of the electric control throttle valve (12) is connected with the turbine flowmeter (13), the upper part of the turbine flowmeter (13) is connected with the detection device box (6), and the, and one end of the detection device box (6) is connected with a cable (8).
2. An aircraft fuel booster pump function testing device as claimed in claim 1, wherein: the oil return filter (9) penetrates through the oil conveying pipe (5), the end face structure of the oil return filter (9) is a hollow net structure, and the oil conveying pipe (5) and the oil return filter (9) form a communicating structure.
3. An aircraft fuel booster pump function testing device as claimed in claim 1, wherein: the temperature sensor (10) penetrates through the outer surface of the oil conveying pipe (5), the liquid level sensor (11) penetrates through the inner part of the oil conveying pipe (5), and the ground of the liquid level sensor (11) is tightly attached to the inner bottom surface of the oil conveying pipe (5).
4. An aircraft fuel booster pump function testing device as claimed in claim 1, wherein: constitute the intercommunication structure between defeated oil pipe (5) and automatically controlled choke valve (12), and defeated oil pipe (5) and automatically controlled choke valve (12) are connected for dismantling.
5. An aircraft fuel booster pump function testing device as claimed in claim 1, wherein: the oil delivery pipe (5) and the turbine flowmeter (13) form a communicating structure, and the oil delivery pipe (5) and the turbine flowmeter (13) are matched with each other.
6. An aircraft fuel booster pump function testing device as claimed in claim 1, wherein: the protection mask (7) penetrates through the upper surface of the detection device box (6), the detection device box (6) and the protection mask (7) are detachably connected, and a communication structure is formed between the detection device box (6) and the cable (8).
7. An aircraft fuel booster pump function testing device as claimed in claim 1, wherein: the detection device box (6) is internally provided with a single chip microcomputer (14), and the single chip microcomputer (14) is matched with the turbine flowmeter (13).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110447623.3A CN113236544A (en) | 2021-04-25 | 2021-04-25 | Function detection device for fuel booster pump of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110447623.3A CN113236544A (en) | 2021-04-25 | 2021-04-25 | Function detection device for fuel booster pump of airplane |
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| Publication Number | Publication Date |
|---|---|
| CN113236544A true CN113236544A (en) | 2021-08-10 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110447623.3A Pending CN113236544A (en) | 2021-04-25 | 2021-04-25 | Function detection device for fuel booster pump of airplane |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102192065A (en) * | 2010-03-18 | 2011-09-21 | 上海航新航宇机械技术有限公司 | Device for detecting function of oil fuel booster pump of civil aircraft |
| CN109115473A (en) * | 2017-06-22 | 2019-01-01 | 中航贵州飞机有限责任公司 | A kind of aircraft fuel system oil pump testing device |
| CN109282861A (en) * | 2018-09-29 | 2019-01-29 | 山东科尔自动化仪表股份有限公司 | A kind of shaftless gas turbine meter and measurement method |
| CN208745739U (en) * | 2018-08-31 | 2019-04-16 | 泰州高盛机电制造有限公司 | A kind of novel anti-automotive oil tank for being emptied anti-oil return and splashing |
| CN208968627U (en) * | 2018-12-01 | 2019-06-11 | 漳州市泛联电子科技有限公司 | A kind of photoelectric level monitoring device |
-
2021
- 2021-04-25 CN CN202110447623.3A patent/CN113236544A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102192065A (en) * | 2010-03-18 | 2011-09-21 | 上海航新航宇机械技术有限公司 | Device for detecting function of oil fuel booster pump of civil aircraft |
| CN109115473A (en) * | 2017-06-22 | 2019-01-01 | 中航贵州飞机有限责任公司 | A kind of aircraft fuel system oil pump testing device |
| CN208745739U (en) * | 2018-08-31 | 2019-04-16 | 泰州高盛机电制造有限公司 | A kind of novel anti-automotive oil tank for being emptied anti-oil return and splashing |
| CN109282861A (en) * | 2018-09-29 | 2019-01-29 | 山东科尔自动化仪表股份有限公司 | A kind of shaftless gas turbine meter and measurement method |
| CN208968627U (en) * | 2018-12-01 | 2019-06-11 | 漳州市泛联电子科技有限公司 | A kind of photoelectric level monitoring device |
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Application publication date: 20210810 |