CN217206832U - Aviation fuel booster pump testing device - Google Patents
Aviation fuel booster pump testing device Download PDFInfo
- Publication number
- CN217206832U CN217206832U CN202123419257.5U CN202123419257U CN217206832U CN 217206832 U CN217206832 U CN 217206832U CN 202123419257 U CN202123419257 U CN 202123419257U CN 217206832 U CN217206832 U CN 217206832U
- Authority
- CN
- China
- Prior art keywords
- oil
- oil way
- auxiliary
- booster pump
- main
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Landscapes
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The utility model provides an aviation fuel booster pump testing arrangement, its technical essential is: the oil tank comprises a movable base (12), a support (13) fixed on the movable base (12), an oil tank (5) connected between the movable base (12) in a hinged mode, a booster pump (9) arranged at the bottom of the oil tank (5) through a flange sleeve (8), an oil distribution pipe (11) arranged on the front face of the oil tank (5) and communicated with the flange sleeve (8), a pressure gauge (10) communicated with the oil distribution pipe (11), a main oil way (1) and an auxiliary oil way (2) which are used for communicating the oil tank (5) with the oil distribution pipe (11) and are parallel to each other, a main flow meter (3) and an auxiliary flow meter (4) which are respectively communicated with the main oil way (1) and the auxiliary oil way (2), and a main oil way ball valve (6) and an auxiliary oil way ball valve (7) which are correspondingly arranged on the main oil way (1) and the auxiliary oil way (2). It has the advantages of simple and compact structure, convenient and fast use and the like.
Description
Technical Field
The utility model relates to an aviation field check out test set, an aviation fuel booster pump testing arrangement specifically says so, its performance test who is mainly applicable to aviation fuel booster pump.
Background
In a normal state, the aviation fuel booster pump test needs to be inverted, and the flow meters with different flow ranges are used for measurement according to different aviation fuel booster pumps. The performance test of the aviation fuel booster pump is very complicated.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing an aviation fuel booster pump capability test device, through standard operation, effectively protect the aviation fuel booster pump not receive the damage, and then improve work efficiency. It has the advantages of simple and compact structure, convenient and fast use and the like.
In order to achieve the above purpose, the utility model provides a following technical scheme: the aviation fuel booster pump testing device is technically characterized by comprising a movable base, a support fixed on the movable base, an oil tank connected between the movable base, a booster pump arranged at the bottom of the oil tank through a flange sleeve, an oil distributing pipe arranged on the front side of the oil tank and communicated with the flange sleeve, a pressure gauge communicated with the oil distributing pipe, a main oil way and an auxiliary oil way which are used for communicating the oil tank with the oil distributing pipe and are parallel to each other, a main flow meter and an auxiliary flow meter respectively communicated with the main oil way and the auxiliary oil way, and a main oil way ball valve and an auxiliary oil way ball valve correspondingly arranged on the main oil way and the auxiliary oil way, wherein the main oil way and the auxiliary oil way are communicated with the top of the oil tank around the bottom and the back of the oil tank.
The utility model has the advantages that: the aviation fuel booster pump integrates two oil paths, tests the large-flow aviation fuel booster pump and the small-flow aviation fuel booster pump respectively, and is structurally designed into a reversible structure, so that great convenience is provided for the performance test of the aviation fuel booster pump. Through the design of the reversible oil tank, the installation and the performance test of the aviation fuel booster pump are facilitated. Through two different flow oil circuit designs, can satisfy the performance test of the aviation fuel booster pump of different flow demands. To sum up, this aviation fuel booster pump testing arrangement has advantages such as test convenience, safe and reliable, the suitability is strong.
Drawings
Fig. 1 is a schematic isometric side view structure diagram I of the present invention.
Fig. 2 is an isometric side view schematic diagram II of the present invention.
Fig. 3 is a schematic view of the structure of the present invention.
Fig. 4 is a schematic rear view of the present invention.
Detailed Description
The following describes the specific contents of the present invention in detail through specific embodiments with reference to fig. 1 to 4. The aviation fuel booster pump testing device comprises a movable base 12, a support 13 fixed on the movable base 12, an oil tank 5 connected between the movable base 12 in a hinged mode, a booster pump 9 arranged at the bottom of the oil tank 5 through a flange sleeve 8, an oil distribution pipe 11 arranged on the front face of the oil tank 5 and communicated with the flange sleeve 8, a pressure gauge 10 communicated with the oil distribution pipe 11, a main oil way 1 and an auxiliary oil way 2 which are used for communicating the oil tank 5 with the oil distribution pipe 11 and are parallel to each other, a main flow meter 3 and an auxiliary flow meter 4 respectively communicated with the main oil way 1 and the auxiliary oil way 2, and a main oil way ball valve 6 and an auxiliary oil way ball valve 7 correspondingly arranged on the main oil way 1 and the auxiliary oil way 2, wherein the main oil way 1 and the auxiliary oil way 2 are communicated with the top of the oil tank 5 around the bottom and the back of the oil tank 5. The main oil way 1 and the auxiliary oil way 2 are respectively used for large-flow fuel oil and small-flow fuel oil.
During testing, the turnable oil tank 5 is adjusted, the flange sleeve 8 is placed on the turnable oil tank, and the aviation fuel booster pump 9 holding the test is correctly installed on the flange sleeve 8. The fuel tank 5 can be turned over, so that the aviation fuel booster pump 9 is arranged at the lower part of the device. And (3) correctly connecting the circuit of the aviation fuel booster pump 9, opening a ball valve of an oil way corresponding to the tested aviation fuel booster pump 9, and observing the display of the pressure gauge 10 and a flowmeter of the corresponding oil way. And after the test is finished, closing the ball valve, disconnecting the circuit, and detaching the tested aviation fuel oil booster pump after the reversible oil tank is turned over.
Description of reference numerals: the device comprises a main oil way 1, an auxiliary oil way 2, a main flow meter 3, an auxiliary flow meter 4, an oil tank 5, a main oil way ball valve 6, an auxiliary oil way ball valve 7, a flange sleeve 8, a booster pump 9, a pressure gauge 10, an oil distributing pipe 11, a movable base 12 and a support 13.
Claims (1)
1. The utility model provides an aviation fuel booster pump testing arrangement which characterized in that: comprises movable bases (12), a bracket (13) fixed on the movable bases (12), an oil tank (5) hinged between the movable bases (12), a booster pump (9) arranged at the bottom of the oil tank (5) through a flange sleeve (8), an oil distribution pipe (11) arranged at the front of the oil tank (5) and communicated with the flange sleeve (8), the oil distribution device comprises a pressure gauge (10) communicated with an oil distribution pipe (11), a main oil way (1) and an auxiliary oil way (2) which are used for communicating an oil tank (5) with the oil distribution pipe (11) and are parallel to each other, a main flow meter (3) and an auxiliary flow meter (4) which are respectively communicated with the main oil way (1) and the auxiliary oil way (2), and a main oil way ball valve (6) and an auxiliary oil way ball valve (7) which are correspondingly arranged on the main oil way (1) and the auxiliary oil way (2), wherein the main oil way (1) and the auxiliary oil way (2) are communicated with the top of the oil tank (5) by surrounding the bottom and the back of the oil tank (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202123419257.5U CN217206832U (en) | 2021-12-31 | 2021-12-31 | Aviation fuel booster pump testing device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202123419257.5U CN217206832U (en) | 2021-12-31 | 2021-12-31 | Aviation fuel booster pump testing device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217206832U true CN217206832U (en) | 2022-08-16 |
Family
ID=82787263
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202123419257.5U Active CN217206832U (en) | 2021-12-31 | 2021-12-31 | Aviation fuel booster pump testing device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN217206832U (en) |
-
2021
- 2021-12-31 CN CN202123419257.5U patent/CN217206832U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN201803832U (en) | Tester using acoustic emission signals to detect valve leakage | |
| CN201034765Y (en) | Single corrugated elastic oil tank pressure test device | |
| CN217206832U (en) | Aviation fuel booster pump testing device | |
| CN102323006B (en) | Portable pressure calibrator | |
| CN210509544U (en) | Diaphragm pump detecting system | |
| CN201897546U (en) | Mechanical load testing device for photovoltaic cell component | |
| CN210981683U (en) | Sealing performance measuring device of automatic instrument based on vibration environment | |
| CN209014251U (en) | A kind of jack for plane axletree pressure loading test device | |
| CN208420295U (en) | A kind of sealing shroud detecting tool | |
| CN211262625U (en) | Intelligent hanging type gas meter air tightness detection device | |
| CN220893537U (en) | Flowmeter check out test set | |
| CN210269071U (en) | Portable pipeline pressure testing device | |
| CN211553328U (en) | A test water testing arrangement for fire control is terminal | |
| CN218584282U (en) | Pressure and flow integrated test tool | |
| CN201488760U (en) | Integrated single-outlet comprehensive detection platform for series flow and leakage of valve | |
| CN202693235U (en) | Hydraulic part comprehensive performance test board | |
| CN201903429U (en) | Piezometric device of fuel gas micro pressure meter | |
| CN210686264U (en) | Water pump performance comprehensive test platform | |
| CN220101492U (en) | Hydraulic pump test bed | |
| CN220508425U (en) | Ultrahigh pressure generator testing device | |
| CN221706676U (en) | Novel pressure type water level gauge testboard | |
| CN219416341U (en) | Water consumption detection device for water balance test | |
| CN220230864U (en) | Simple pipeline element testing device | |
| CN205981387U (en) | Electromechanical synchronous detection system of water gauge | |
| CN217276761U (en) | Detection device for detecting internal leakage of hydraulic oil cylinder |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |