Atomization characteristic test device and method for aviation fuel and atomization environment at low temperature and low pressure

Abstract

The invention provides an atomization characteristic test device and method for aviation fuel and an atomization environment at low temperature and low pressure, and the device comprises a cooling assembly, the two sides of the cooling assembly are respectively provided with an oil tank and an atomization bin, the atomization bin is internally provided with a nozzle, and the outer side of the atomization bin is provided with a three-dimensional coordinate motion system; a pressure vacuum pump is further arranged on one side of the atomization bin. By adopting the device and the method for testing the atomization characteristics of the aviation fuel and the atomization environment under the low-temperature and low-pressure conditions, the atomization characteristics of the novel alternative fuel under the low-temperature and low-pressure conditions can be effectively tested. And important experimental basis is provided for optimization and application of fuel atomization through measurement and data analysis of the atomization particle size.

Description

Technical Field

[0001] The invention relates to the field of aviation fuel testing, and in particular to an atomization characteristic testing device and method for aviation fuel when both the aviation fuel and the atomization environment are at low temperature and low pressure. Background Art

[0002] The atomization characteristics of aviation fuel will change under low temperature and low pressure environment. Specifically, when the temperature decreases, the viscosity of the fuel increases and the surface tension increases, which may cause the atomization cone angle to become smaller and the oil droplet atomization particle size to increase. At the same time, the average velocity of the oil droplets may increase in low temperature environments, but the change in the average velocity of the oil droplets on the same measurement section will decrease. In addition, changes in pressure will also affect the atomization characteristics. For example, as the pressure increases, the difference in the atomization cone angle at different temperatures may decrease, and the increase in the oil droplet atomization particle size may also decrease.

[0003] Although there have been some studies on the atomization characteristics of aviation fuel, most of these studies focus on the analysis of atomization characteristics under normal temperature and pressure or specific working conditions. There are relatively few studies on atomization characteristics under low temperature and low pressure environments, and there is a lack of systematic experimental equipment and test methods. Therefore, the existing technology has certain limitations in simulating low temperature and low pressure environments, accurately controlling experimental conditions, and accurately measuring atomization characteristics. Summary of the invention

[0004] The purpose of the present invention is to provide an atomization characteristic test device and method for aviation fuel and atomization environment at low temperature and low pressure, which can effectively realize the atomization characteristic test of new alternative fuels under low temperature and low pressure conditions. Through the measurement and data analysis of the atomized particle size, it provides an important experimental basis for the optimization and application of fuel atomization.

[0005] To achieve the above-mentioned purpose, the present invention provides an atomization characteristic test device when both the aviation fuel and the atomization environment are at low temperature and low pressure, comprising a cooling component, a fuel tank and an atomization bin are respectively arranged on both sides of the cooling component, a nozzle is arranged in the atomization bin, and a three-dimensional coordinate motion system is arranged outside the atomization bin; A pressure vacuum pump is also provided on one side of the atomization bin.

[0006] Preferably, an oil pump, an oil filter, a first valve, a pressure gauge, a flow meter, a thermometer, and a second valve are sequentially arranged between the oil tank and the atomization bin.

[0007] Preferably, an overflow valve is further provided between the oil pump and the oil tank.

[0008] Preferably, the cooling component is also provided with a dry ice bin and a plate heat exchanger.

[0009] Preferably, a laser particle size analyzer is provided outside the atomization chamber.

[0010] A method for testing the atomization characteristics of aviation fuel and atomization environment at low temperature and low pressure, comprising the following steps: The oil in the oil tank is pressurized by the oil pump, filtered by the oil filter, and then enters the pipeline through the first valve. The pipeline is equipped with a pressure gauge, flow meter and thermometer in sequence to monitor the state of the oil in real time. The other end of the pipeline flows the excess oil back to the oil tank through the overflow valve; By controlling the second valve to open, the oil flows into the nozzle for atomization test. An atomization bin is provided below the nozzle. A cold air inlet is provided on the upper cover of the atomization bin. The cold air is cooled by dry ice through a plate heat exchanger and then injected into the atomization bin to achieve low temperature conditions. There is an exhaust port at the right end of the atomization chamber, and the atomization chamber is evacuated by a vacuum pump to make it close to a vacuum state, simulating low-pressure conditions; The atomization chamber is located in a three-dimensional coordinate motion system. The rotation of the motor is controlled by the control panel to achieve movement of the nozzle in the XYZ direction and axial rotation. PIV laser particle size analyzers are installed at the left and right ends of the atomization chamber to measure the size of the atomized particles. The test results are converted into binary graphics through post-processing software.

[0011] Therefore, the present invention adopts the above-mentioned atomization characteristic test device and method when both the aviation fuel and the atomization environment are at low temperature and low pressure, which can effectively realize the atomization characteristic test of the new alternative fuel under low temperature and low pressure conditions. Through the measurement and data analysis of the atomized particle size, it provides an important experimental basis for the optimization and application of fuel atomization. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] Figure 1 The present invention is a schematic diagram of an atomization characteristic test device for aviation fuel when both the atomization environment and the atomization environment are at low temperature and low pressure.

[0013] Reference numerals 1. Cooling component; 101. Dry ice bin; 102. Plate heat exchanger; 2. Oil tank; 3. Atomization bin; 4. Nozzle; 5. Three-dimensional coordinate motion system; 6. Pressure vacuum pump; 7. Oil pump; 8. Oil filter; 9. First valve; 10. Pressure gauge; 11. Flow meter; 12. Thermometer; 13. Overflow valve; 14. Laser particle size analyzer; 15. Second valve. DETAILED DESCRIPTION

[0014] The technical solution of the present invention is further described below through the accompanying drawings and embodiments.

[0015] Unless otherwise defined, technical or scientific terms used in the present invention shall have the common meanings understood by one having ordinary skills in the field to which the present invention belongs.

[0016] Embodiment 1 A device for testing the atomization characteristics of aviation fuel and atomization environment at low temperature and low pressure comprises a cooling component 1, on which a dry ice bin 101 and a plate heat exchanger 102 are also arranged.

[0017] Dry ice refrigeration: Place an appropriate amount of dry ice in the plate heat exchanger 102. The temperature of dry ice is about -78.5°C, and it has a very strong refrigeration capacity. When using dry ice, attention should be paid to handling safety and avoid direct contact with the skin.

[0018] Dry ice sublimates under normal pressure and is converted into gaseous carbon dioxide (CO2). In this process, dry ice absorbs heat from the air in the plate heat exchanger 102, causing the air temperature in the plate heat exchanger 102 to drop rapidly. By properly designing the structure of the heat exchanger (such as increasing the heat exchange surface area and flow channels), the cooling efficiency can be improved and the rapid low temperature of the air can be promoted.

[0019] COOL AIR INJECTION: The cooled air is delivered to the cold air inlet above the atomization chamber 3 through the pipe system. In this process, the pipe should minimize heat loss and be wrapped with good insulation materials.

[0020] Once the cold air enters the atomization chamber 3, strong convection will be formed in the atomization chamber 3, quickly and evenly reducing the temperature in the entire atomization chamber 3. In order to further enhance the circulation of air in the atomization chamber 3, a fan or other flow-increasing device can be installed. This will help ensure that the temperature in the atomization chamber 3 reaches the preset low temperature range and improve the repeatability and controllability of the experiment.

[0021] Temperature monitoring: High-precision temperature sensors, such as thermocouples or thermistors, are installed inside the atomization chamber 3 to monitor the temperature changes in the atomization chamber 3 in real time. These sensors should have fast response time and good stability to ensure the accuracy of temperature measurement.

[0022] The temperature monitoring system should be connected to the data acquisition system so that the operator can view the temperature information in the atomization chamber 3 in real time. At the same time, a temperature threshold alarm function is set so that timely measures can be taken when the temperature exceeds the standard to prevent the experimental data from being affected. Through continuous monitoring, it will ensure that the temperature in the atomization chamber 3 is always kept within the experimental requirements, creating ideal low temperature conditions for subsequent atomization tests.

[0023] The cooling component 1 is provided with an oil tank 2 and an atomizing chamber 3 on both sides, a nozzle 4 is provided in the atomizing chamber 3, and a three-dimensional coordinate motion system 5 is provided outside the atomizing chamber 3; a pressure vacuum pump 6 is also provided on one side of the atomizing chamber 3. An oil pump 7, an oil filter 8, a first valve 9, a pressure gauge 10, a flow meter 11, a thermometer 12, and a second valve 15 are provided between the oil tank 2 and the atomizing chamber 3 in sequence. An overflow valve 13 is also provided between the oil pump 7 and the oil tank. A PIV laser particle size analyzer 14 is provided outside the atomizing chamber 3.

[0024] Start the pressure vacuum pump 6: During the experimental preparation stage, ensure that the pressure vacuum pump 6 is in good condition and is tightly connected to the air extraction port of the atomization chamber 3. Start the pressure vacuum pump 6 installed at the right end of the atomization chamber 3. The pressure vacuum pump 6 should be of a type suitable for the experimental requirements, such as a diaphragm vacuum pump or a rotary vane vacuum pump, etc., with good air extraction capacity and stability.

[0025] After the pressure vacuum pump 6 is started, it will first gradually reduce the pressure in the atomization chamber 3. The operator needs to pay close attention to the reading of the pressure gauge 10 to optimize the vacuum extraction process and ensure that it reaches the target pressure.

[0026] Pressure monitoring: A pressure sensor is installed inside the atomization chamber 3 to monitor the pressure fluctuation inside the atomization chamber 3 in real time. A suitable pressure sensor needs to have high sensitivity and a wide range to adapt to a wide range of pressure changes.

[0027] By installing a pressure monitoring system, data can be centrally transmitted to the control panel, and operators can observe the pressure status in real time. When the pressure drops to the low pressure range set for the experiment, the system will issue a prompt to ensure that the experimental conditions meet the requirements.

[0028] Vacuum degree adjustment: The operator can adjust the vacuum pump 6's pumping speed and working time according to the real-time pressure data, so as to balance the pumping effect and the temperature change in the atomization chamber 3. It should be noted that as the pressure decreases, the temperature in the atomization chamber 3 may change, so measures need to be taken to coordinate.

[0029] The valve control system can be used to adjust the air extraction volume when necessary to ensure dual control of the fluidity of the gas in the atomization chamber 3 and the dissipation of heat. At the same time, the working state of the pressure vacuum pump 6 is regularly checked to ensure that the equipment operates at the best performance, and finally the atomization chamber 3 is in a near-vacuum state to simulate low-pressure conditions and ensure the accuracy and repeatability of the atomization experiment.

[0030] A method for testing the atomization characteristics of aviation fuel and atomization environment at low temperature and low pressure, characterized in that it comprises the following steps: The oil in the oil tank 2 is pressurized by the oil pump 7, filtered by the oil filter 8, and then enters the pipeline through the first valve 9. The pipeline is equipped with a pressure gauge 10, a flow meter 11 and a thermometer 12 in sequence to monitor the state of the oil in real time. The other end of the pipeline flows the excess oil back to the oil tank 2 through the overflow valve 13; By controlling the second valve 15 to open, the oil flows into the nozzle 4 for atomization test. An atomization bin 3 is provided below the nozzle 4. A cold air inlet is provided on the upper cover of the atomization bin 3. The cold air is cooled by dry ice through a plate heat exchanger and then injected into the atomization bin 3 to achieve low temperature conditions. An exhaust port is provided at the right end of the atomization chamber 3, and the atomization chamber 3 is evacuated by a pressure vacuum pump 6 to make it in a near-vacuum state, simulating low-pressure conditions; The atomizing chamber 3 is located in the three-dimensional coordinate motion system 5, and the rotation of the motor is controlled by the control panel to realize the movement of the nozzle 4 in the XYZ direction and the axial rotation; The left and right ends of the atomization chamber 3 are provided with laser particle size analyzers 14 for measuring the size of the atomized particles. The test results are converted into binary graphics through post-processing software.

[0031] Therefore, the present invention adopts the above-mentioned atomization characteristic test device and method when both the aviation fuel and the atomization environment are at low temperature and low pressure, which can effectively realize the atomization characteristic test of the new alternative fuel under low temperature and low pressure conditions. Through the measurement and data analysis of the atomized particle size, it provides an important experimental basis for the optimization and application of fuel atomization.

[0032] Finally, it should be noted that the above embodiments are only used to illustrate the technical solution of the present invention rather than to limit it. Although the present invention has been described in detail with reference to the preferred embodiments, those skilled in the art should understand that they can still modify or replace the technical solution of the present invention with equivalents, and these modifications or equivalent replacements cannot cause the modified technical solution to deviate from the spirit and scope of the technical solution of the present invention.

Claims

1. A test device for the atomization characteristics of aviation fuel and atomization environment at low temperature and low pressure, characterized in that: It includes a cooling component, wherein an oil tank and an atomization bin are respectively arranged on both sides of the cooling component, a nozzle is arranged in the atomization bin, and a three-dimensional coordinate motion system is arranged outside the atomization bin; A pressure vacuum pump is also provided on one side of the atomization bin.

2. The atomization characteristic test device of the aviation fuel and the atomization environment at low temperature and low pressure according to claim 1, characterized in that: An oil pump, an oil filter, a first valve, a pressure gauge, a flow meter, a thermometer and a second valve are sequentially arranged between the oil tank and the atomization bin.

3. The atomization characteristic test device of the aviation fuel and the atomization environment at low temperature and low pressure according to claim 2, characterized in that: An overflow valve is also arranged between the oil pump and the oil tank.

4. The atomization characteristic test device of the aviation fuel and the atomization environment at low temperature and low pressure according to claim 1, characterized in that: The cooling component is also provided with a dry ice bin and a plate heat exchanger.

5. The atomization characteristic test device of the aviation fuel and the atomization environment at low temperature and low pressure according to claim 1, characterized in that: A laser particle size analyzer is arranged outside the atomization chamber.

6. A method for testing the atomization characteristics of aviation fuel when both the atomization environment and the atomization environment are at low temperature and low pressure according to any one of claims 1 to 5, characterized in that: The following steps are involved: The oil in the oil tank is pressurized by the oil pump, filtered by the oil filter, and then enters the pipeline through the first valve. The pipeline is equipped with a pressure gauge, flow meter and thermometer in sequence to monitor the state of the oil in real time. The other end of the pipeline flows the excess oil back to the oil tank through the overflow valve; By controlling the second valve to open, the oil flows into the nozzle for atomization test. An atomization bin is provided below the nozzle. A cold air inlet is provided on the upper cover of the atomization bin. The cold air is cooled by dry ice through a plate heat exchanger and then injected into the atomization bin to achieve low temperature conditions. There is an exhaust port at the right end of the atomization chamber, and the atomization chamber is evacuated by a vacuum pump to make it close to a vacuum state, simulating low-pressure conditions; The atomization chamber is located in a three-dimensional coordinate motion system. The rotation of the motor is controlled by the control panel to achieve movement of the nozzle in the XYZ direction and axial rotation. Laser particle size analyzers are installed at the left and right ends of the atomization chamber to measure the size of the atomized particles. The test results are converted into binary graphics through post-processing software.

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