CN216894852U - Experimental device for general type measures aviation fuel pump flow resistance characteristic - Google Patents
Experimental device for general type measures aviation fuel pump flow resistance characteristic Download PDFInfo
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- CN216894852U CN216894852U CN202123337570.4U CN202123337570U CN216894852U CN 216894852 U CN216894852 U CN 216894852U CN 202123337570 U CN202123337570 U CN 202123337570U CN 216894852 U CN216894852 U CN 216894852U
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Abstract
The utility model designs a universal experimental device for measuring the flow resistance characteristic of an aviation fuel pump. The technical scheme of the utility model is as follows: the experimental device comprises experimental oil tank, booster pump, bypass governing valve, flowmeter, import manometer, export manometer, import switching section, export switching section, tested product, through setting up booster pump and attached test equipment, the flow resistance of the tested fuel pump is measured in initiative pressure boost, has thoroughly solved in the past that test equipment adopts the vacuum suction mode to measure the short measuring result inaccuracy of test time that the tested fuel pump exists, technical problem such as the big test result uniformity of flow fluctuation is poor. Meanwhile, the testing device can measure the flow resistance of the fuel pumps of different types through the switching tool, is good in universality and convenient to transform, greatly reduces the transformation workload of testing equipment, and saves enterprise funds.
Description
Technical Field
The utility model belongs to the field of mechanical design, and relates to a universal experimental device for measuring flow resistance characteristics of an aviation fuel pump.
Background
The test of the flow resistance characteristic of the aviation fuel pump is a new requirement in the test of the functional performance of the aviation fuel pump in recent years, and the fuel pump is required to flow fuel with certain flow through an inlet pipe and an outlet pipe of the fuel pump under the condition of no work, and the flow resistance characteristic of the fuel pump is obtained by measuring the pressure loss of an outlet of the fuel pump. The common test method is that the fuel pump is placed in a container filled with fuel, a vacuumizing device is connected with an outlet of the fuel pump, and the fuel flows through an inlet and an outlet of the fuel pump in a mode of sucking an outlet of the fuel pump to enable an inlet of the fuel pump to form negative pressure. The method has high implementation difficulty, and the measurement result is not very accurate due to poor measurement stability.
SUMMERY OF THE UTILITY MODEL
The purpose of the utility model is as follows: a general experimental device for measuring the flow resistance characteristic of an aviation fuel pump is designed.
The technical scheme of the utility model is as follows:
a universal experimental device for measuring the flow resistance characteristic of an aviation fuel pump comprises a test oil tank, a booster pump, an inlet pressure gauge, a tested product, an outlet pressure gauge, a bypass regulating valve and a flowmeter; the booster pump is installed in experimental oil tank bottom, and the export of booster pump is connected with inlet pressure gauge, and inlet pressure gauge connects the product being tested, is connected with outlet pressure gauge by the product being tested, and outlet pressure gauge connects the flowmeter, and the flowmeter connects experimental oil tank, is equipped with the bypass governing valve between product being tested and the experimental oil tank, realizes surveying the self-loopa of flow resistance.
Further, still include the import changeover portion, the import changeover portion is installed between import manometer and the product under test.
Further, still include export changeover portion, it installs between product and the export manometer to draw together export changeover portion.
Furthermore, the outlet end of the bypass regulating valve is connected to the test oil tank, and the connecting pipeline is lower than the outlet pipe of the booster pump.
The output flow range of the booster pump is 0-20000L/h.
The inlet pressure gauge and the outlet pressure gauge are respectively positioned at the horizontal positions, the drift diameter is DN50, the length is 80mm, and the inlet pressure gauge and the outlet pressure gauge are respectively positioned at the inlet and the outlet of a tested product by 40 mm.
The utility model has the beneficial effects that: the utility model designs a universal experimental device for measuring the flow resistance characteristic of an aviation fuel pump, which is used for actively measuring the flow resistance of a tested fuel pump in a pressurizing manner by arranging a pressurizing pump and an auxiliary test device, and thoroughly solves the technical problems of short test time, inaccurate measurement result, large flow fluctuation, poor test result consistency and the like existing in the conventional test device which adopts a vacuum suction manner to measure the tested fuel pump. Meanwhile, the testing device can measure the flow resistance of the fuel pumps of different types through the switching tool, is good in universality and convenient to transform, greatly reduces the transformation workload of testing equipment, and saves enterprise funds. The utility model can be popularized and applied to flow resistance characteristic tests of various aviation fuel pumps and aviation accessories.
Description of the drawings:
FIG. 1 is a schematic diagram of a general experimental device for measuring flow resistance characteristics of an aviation fuel pump according to the utility model.
Detailed Description
The present invention is described in further detail below.
A flow resistance characteristic experiment device for a universal aviation fuel pump comprises a test oil tank 1, a booster pump 2, an inlet pressure gauge 3, a tested product 5, an outlet pressure gauge 7, a bypass regulating valve 8 and a flowmeter 9; booster pump 2 is installed in 1 bottom of experimental oil tank, and booster pump 2's export is connected with import manometer 3, and import manometer 3 is connected by examination product 5, is connected by examination product 5 and export manometer 7, and flowmeter 9 is connected to export manometer 7, and flowmeter 9 connects experimental oil tank 1, is equipped with bypass control valve 8 between examination product 5 and the experimental oil tank 1, realizes surveying the self-loopa of flow resistance.
Further, the test device also comprises an inlet adapter section 4, wherein the inlet adapter section 4 is arranged between the inlet pressure gauge 3 and the tested product 5, and the inlet adapter section 4 is used for adapting to inlet interfaces of different types of tested products 5.
Further, the device also comprises an outlet adapter section 6, wherein the outlet adapter section 6 is arranged between the tested product 5 and an outlet pressure gauge 7, and the outlet adapter section 6 is used for adapting to outlet interfaces of different types of tested products 5.
Further, the outlet end of the bypass regulating valve 8 is connected to the test oil tank 1, and the connecting pipeline is lower than the outlet pipe of the booster pump 2. The fluctuation of the oil return liquid level is kept small, the liquid level tends to be more stable, and the possibility that the booster pump sucks air bubbles is reduced.
The output flow range of the booster pump 2 is 0-20000L/h. The flow resistance measurement requirements of different envelope lines can be met.
The inlet pressure gauge 3 and the outlet pressure gauge 7 are respectively positioned at horizontal positions, the drift diameter is DN50, the length is 80mm, and the inlet pressure gauge 3 and the outlet pressure gauge 7 are respectively positioned at the inlet and the outlet 40mm of the tested product 4. The pressure loss at the position of 40mm is smaller, and the measurement precision is higher. If the diameter is less than 40mm, the pressure fluctuation is large.
The working process of the device is as follows: selecting an inlet switching section 4 and an outlet switching section 6 which are matched with an inlet interface and an outlet interface of a tested product 5, and connecting the tested product 5 according to the graph 1; fuel oil at least submerging the booster pump 2 is added into the test oil tank 1, and the booster pump 2 is connected with a power supply; after the booster pump 2 works stably, the opening degree of the bypass adjusting valve 8 is adjusted, and the flow of the flowmeter 9 is monitored, so that the flow value meets the requirement of the inlet flow of the tested product 5; and respectively measuring pressure values of an inlet pressure gauge 3 and an outlet pressure gauge 7, and calculating the pressure difference between the inlet pressure gauge and the outlet pressure gauge to obtain the flow resistance characteristics of the fuel pump under different flows.
Claims (6)
1. A universal experimental device for measuring the flow resistance characteristic of an aviation fuel pump is characterized by comprising a test oil tank (1), a booster pump (2), an inlet pressure gauge (3), an inlet adapter section (4), a tested product (5), an outlet adapter section (6), an outlet pressure gauge (7), a bypass regulating valve (8) and a flowmeter (9); install in experimental oil tank (1) bottom booster pump (2), the export and the import manometer (3) of booster pump (2) are connected, imported manometer (3) are connected and are tried product (5), it is connected with export manometer (7) to be tried product (5), flowmeter (9) are connected in export manometer (7), flowmeter (9) connect experimental oil tank (1), be equipped with bypass control valve (8) between being tried product (5) and experimental oil tank (1), realize surveying the self-loopa of flow resistance.
2. The experimental device for measuring the flow resistance characteristic of the aviation fuel pump in the general type according to claim 1, further comprising an inlet adapter section (4), wherein the inlet adapter section (4) is installed between the inlet pressure gauge (3) and the tested product (5).
3. The experimental device for measuring the flow resistance characteristic of the aviation fuel pump in the general type according to claim 1, further comprising an outlet adapter section (6), wherein the outlet adapter section (6) is installed between the tested product (5) and an outlet pressure gauge (7).
4. The experimental device for measuring the flow resistance of the aviation fuel pump in the general type according to claim 1, wherein the outlet end of the bypass regulating valve (8) is connected to the test fuel tank (1), and the connecting pipeline is lower than the outlet pipe of the booster pump (2).
5. The experimental device for measuring the flow resistance characteristic of the aviation fuel pump in the general type according to claim 1, wherein the output flow rate of the booster pump (2) is in the range of 0-20000L/h.
6. The experimental device for measuring the flow resistance of the aviation fuel pump as claimed in claim 1, wherein the inlet pressure gauge (3) and the outlet pressure gauge (7) are respectively located at horizontal positions, have a through diameter of DN50 and a length of 80mm, and are respectively located at 40mm positions of an inlet and an outlet of the tested product (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202123337570.4U CN216894852U (en) | 2021-12-28 | 2021-12-28 | Experimental device for general type measures aviation fuel pump flow resistance characteristic |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202123337570.4U CN216894852U (en) | 2021-12-28 | 2021-12-28 | Experimental device for general type measures aviation fuel pump flow resistance characteristic |
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| CN216894852U true CN216894852U (en) | 2022-07-05 |
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| CN202123337570.4U Active CN216894852U (en) | 2021-12-28 | 2021-12-28 | Experimental device for general type measures aviation fuel pump flow resistance characteristic |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116447129A (en) * | 2023-06-19 | 2023-07-18 | 成都凯天电子股份有限公司 | Device for simulating high-altitude performance of missile fuel pump and testing method thereof |
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2021
- 2021-12-28 CN CN202123337570.4U patent/CN216894852U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116447129A (en) * | 2023-06-19 | 2023-07-18 | 成都凯天电子股份有限公司 | Device for simulating high-altitude performance of missile fuel pump and testing method thereof |
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